Sentences Generator
And
Your saved sentences

No sentences have been saved yet

634 Sentences With "rocket motor"

How to use rocket motor in a sentence? Find typical usage patterns (collocations)/phrases/context for "rocket motor" and check conjugation/comparative form for "rocket motor". Mastering all the usages of "rocket motor" from sentence examples published by news publications.

type: All Declarative Interrogative Exclamative

structure: All Simple Compound Complex Compound-Complex

length: All <=10 words 10-20 words 20-30 words 30-50 words

"Range limitations are based on the rocket motor," Harrold explained.
Sometimes the thrust is provided by a fuel-burning rocket motor.
These include technical exploration of rocket motor upgrades and additional seeker technology.
The space plane then engages its onboard rocket motor to blast itself upward.
To help save the crew, a rocket motor is located underneath the capsule.
I felt like I was in space the minute we lit the rocket motor.
First, a tiny flicker of flame was visible on the right solid rocket motor.
There, the Pegasus is released and ignites its main rocket motor about five seconds later.
So if you need some cheap, reliable thrust, a solid rocket motor will do the trick.
You can't simulate the high G forces that we will feel during the rocket motor burn.
However, some payloads may need a supplemental rocket motor to get into space, according to TechCrunch.
Smoke and fire will soon fill the Utah desert as NASA tests the most powerful rocket motor ever built.
At this point, SpaceShipTwo separates from WhiteKnightTwo and ignites its rocket motor to complete the rest of the voyage.
The carrier aircraft then released the spacecraft from under its wing and then Unity's rocket motor roared the life.
Eve released Unity from under its wing and, with a two-member crew, Unity's rocket motor roared to life.
As expected, about 45 seconds after liftoff, the escape system kicked in, igniting the rocket motor underneath the crew capsule.
The two craft will climb together to about 50,000 feet before SpaceShipTwo is released and its rocket motor kicks on.
Rocket motor ignitors, M-5000 explosives and batteries were found in a search of Barnett's home, according to the complaint.
On Tuesday, engineers fired up a rocket motor that will be part of the most powerful rocket ever launched to space.
Unity reached Mach 3 — three times the speed of sound — before the rocket motor was switched off shortly before 9 a.m.
On February 28th, MAVEN performed a rocket motor burn in order to increase its velocity by less than a mile an hour.
About 45 seconds later, the capsule separated from the rocket while a solid-rocket motor at the base of the capsule ignited.
"The rocket motor is performing terrific; we're actually getting some extra thrust," Virgin Galactic CEO George Whitesides told CNBC after the test.
A rocket motor then accelerated Unity to Mach 1.87 during a 30-second rocket burn before the ship's two pilots shut it down.
You know, so we have a soft rocket motor, we use a reentry technique that is patented, and obviously it's an air launch system.
This will ignite a small rocket motor underneath the capsule, pushing it away from the booster, before touching down under parachute in the Texas desert.
It's not much of an exaggeration to say that any rocket that uses solid propellants and works means that the rocket motor was built flawlessly.
Eve released Unity from under its wing and, with a two-member crew of Mark Stucky and Dave Mackay, Unity's rocket motor roared to life.
Instead of needing two liquids to mix inside a chamber, the propellants of a solid rocket motor are already mixed together in a big, solid chunk.
U.S. defense contractor Northrop Grumman won U.S. antitrust approval to buy solid rocket motor supplier Orbital ATK with conditions, the Federal Trade Commission said on Tuesday.
Within the next few days, the European Space Agency plans to fire up the current largest solid rocket motor built in one segment for the first time.
The spaceship is dropped from a jet-powered aircraft and fires a rocket motor, reaching over three times the speed of sound as it climbs through Earth's atmosphere.
And then also with marginal equipment-based things like our rocket motor cartridge — we're already integrating innovations that enable us to build them cheaper, but still maintain quality.
The spaceship is dropped from a jet-powered aircraft and fires a rocket motor, reaching over three times the speed of sound as it climbs though Earth's atmosphere.
This particular test was a cold motor test used to provide data on how the rocket motor operates at the colder end of its accepted propellant temperature range.
A rocket motor is located underneath the capsule Blue Origin has already tested out this system on the ground, but it hasn't tried it out during flight yet.
WASHINGTON, June 5 (Reuters) - Northrop Grumman won U.S. antitrust approval to buy solid rocket motor supplier Orbital ATK, Inc, with conditions, the Federal Trade Commission said on Tuesday.
After taking off from a runway attached to the WhiteKnightTwo "mothership," Unity then detached at some 45,000 feet before its rocket motor ignited and the craft blasted into space.
If for some reason that booster explodes — either on the ground or during ascent — a rocket motor on the bottom of the capsule will ignite for about two seconds.
The spaceship is dropped from a jet-powered aircraft and fires a rocket motor, reaching over three times the speed of sound as it climbs though the Earth's atmosphere.
You can see more comparison that Wisbith makes, like the largest radio telescope on The Strip in Las Vegas and a NASA M1 rocket motor compared to a car, here.
Once it drops from the carrier ship, the space plane's rocket motor is designed to kick on, bringing it to a top altitude of about 100 kilometers, 62 miles, eventually.
Even if the North Koreans were able to master solid propulsion tomorrow, it's practically impossible to swap out a liquid propellant engine for a solid rocket motor because, well, rocket science.
On a Thursday afternoon in June, a 17-foot-tall rocket motor—looking like something a dedicated amateur might fire off—stood fire-side-up on the salty desert of Promontory, Utah.
Flown by two pilots, spaceship is dropped from a jet-powered aircraft and fires a rocket motor, reaching over three times the speed of sound as it climbs though the Earth's atmosphere.
A rocket motor on the back of the vehicle ignites, pushing it up to an altitude of around 55 miles — a height that many consider to be beyond the boundary to space.
The space plane will be released from WhiteKnightTwo at about 50,000 feet and then SpaceShipTwo's rocket motor will kick on, hurtling it up to about 100 kilometers (62 miles) above the Earth.
"The XM1113 uses a large high-performance rocket motor that delivers nearly three times the amount of thrust when compared to the legacy M549A1 RAP," Ductri Nguyen, XM1113 Integrated Product Team Lead.
Allan McDonald, director of the Space Shuttle Solid Rocket Motor Project for the engineering contractor Morton Thiokol, refused to sign a launch recommendation for the Challenger the night before over safety concerns.
In a subsequent search of Barnett's residence, law enforcement officers recovered rocket motor ignitors, M-5000 explosives, and battery sources consistent with the type used in the explosive devices, according to the criminal complaint.
Human rocket scientists have toyed with something similar, in order to overcome one of the biggest problems of spaceship design: that a craft propelled by a rocket motor must carry its fuel with it.
The Atlas V used for this launch was configured with a payload fairing 13 feet in diameter to accommodate the Orbiter, and used a single solid rocket motor to provide the necessary propulsive power.
Blue Origin initiated the escape system about 45 seconds after takeoff today, causing a rocket motor to ignite underneath the New Shepard's crew capsule — the portion of the vehicle that's meant to carry people.
The spaceship is dropped from a jet-powered aircraft at about 40,000 feet before firing its rocket motor, reaching over three times of the speed of sound as it climbs though the Earth's atmosphere.
In the 1941 model, the rocket motor was at the front of the spin-stabilized projectile, ensuring that a high-explosive warhead would normally be above ground on detonation, thus giving maximum fragmentation spread.
As it neared the ground, the booster's rocket motor fired, its landing legs deployed and it touched down, 2 miles (3.2 km) from the launch site, as it has done on its four previous flights.
Behind Stucky and Mackay was a seventeen-hundred-gallon tank of liquid nitrous oxide, and, farther back, a twenty-seven-hundred-pound rocket motor, which was packed with ignition squibs and one ton of solid fuel.
They also gave it a rocket motor to accelerate it to a speed fast enough for that edge to create a cavity consisting of a single, giant bubble which envelopes the entire torpedo except for the steering fins.
Analysis by the London-based International Institute for Strategic Studies of video footage of the latest two launches suggests Pyongyang now has a working rocket motor based on Soviet rocket engines not used by Russia since the 1990s.
At first, South Korean officials monitoring the launch said the missile was either a modified version of the Nodong, first deployed more than a decade ago, or the 3,000km-range Musadan, possibly equipped with a solid-fuel rocket motor.
Consisting of a rocket motor, seeker, warhead and fuze, APKWS rockets can track and attack targets such as small groups of enemy fighters, thin-skinned vehicles and other targets for which a Hellfire might be too large or unnecessary.
"We will now push on with the remaining portion of our flight test program, which will see the rocket motor burn for longer and VSS Unity fly still faster and higher," Branson said in a statement after the landing.
The satellite was put into a Geosynchronous Transfer Orbit (GTO), an elliptical orbit that places satellites in a position to get into Geosynchronous Earth Orbit using another smaller rocket motor once the main launcher (in this case, Falcon 9) is expended.
But on March 210th pictures appeared in the North Korean media of what appeared to be a nose-cone from a KN-238 placed on an engine test stand one and a half metres beneath an ignited Scud rocket motor.
In the mid-2000s, Iranian-backed Hezbollah groups in Iraq partially disassembled rockets like these, affixing large homemade explosive warheads to the rocket motor to create a weapon that coalition intelligence officers call the IRAM, or improvised rocket-assisted munition.
After a 35-minute flight delay, New Shepard launched from its West Texas launch facility at around 11:35 am ET. About 45 seconds into the launch, a solid rocket motor fired for two seconds pushing the crew capsule away from the booster.
North Korea is merrily chugging along in its quest to develop rocket engines for long-range missiles that could one day send a nuclear weapon across the world, according to recent reports indicating that Kim Jong-un's regime had successfully tested a solid-fuel rocket motor.
In addition, an examination of North Korea's recent test of a large liquid rocket motor revealed the types of propulsion units used and the revelation that with this technology a North Korean intercontinental ballistic missile would have greater range than expected, enabling it to even reach the U.S. east coast.
"We will now push on with the remaining portion of our flight test program, which will see the rocket motor burn for longer and VSS Unity fly still faster and higher towards giving thousands of private astronauts an experience which provides a new, planetary perspective to our relationship with the Earth and the cosmos," said Branson.
"A guidance kit we have developed goes in between the warhead and the rocket motor, making it into a precise, accurate and low collateral damage weapon," Dave Harrold, Director of Business Development for Survivability, Targeting and Sensing at BAE Systems BAE has designed its APKWS rockets with a particular "mid-body" design engineered for additional targeting and guidance.
At times, he seemed to carry the entire burden of the disaster on his shoulders, although it was he, on the afternoon before the launch, who made a critical phone call to Allan J. McDonald, the Thiokol engineer in charge of the solid rocket motor project at the Kennedy Space Center, alerting him to concerns about the O-rings.
Other recent tests include a large solid-fuelled rocket motor of the kind needed to launch a mobile medium-range missile at very short notice (liquid-fuelled rockets, like those on the KN-08, take much longer to prepare for flight and are harder to move around) and the launch of a ballistic missile apparently from a submerged submarine in late April.
VSS Unity made the trip attached to the carrier aircraft that will bring it up to its launch altitude, where it'll detach from the plane (named 'VMS Eve') and climb to the edge of space, providing the customers on board with "several minutes" of weightlessness in near zero-G when the spacecraft's rocket motor disengages at the peak of its journey.
19 seconds after firing the rocket motor was ignited and the projectile was accelerated through the stratosphere. When the rocket burnt out the center section containing the rocket motor fell away and the projectile continued on its course. The maximum range for this projectile was but due to the weight of the rocket motor the projectile carried less explosives.
A1: On the last check flight before live firing the parent aircraft descended into a storm at 22,000 ft. When smooth conditions were regained at about 8,000 ft altitude the test vehicle A1 carrying all the prototype examples of instruments and equipment was found to have parted from the aircraft and disappeared beneath the waters of the Bristol Channel. List of Test Vehicles in Chronological Order Ref. Type Details A1 Complete Lost in cloud during early flight trials—30/05/47 A2 Complete First release—rocket motor failed to ignite—08/10/47 A9 Fuselage Rocket motor starting tests. Released from 35,000 ft 29/02/48 fired A8 Fuselage Rocket motor starting tests• Release from 35,000 if—29/02/48 non firing A12 Fuselage Rocket motor starting tests. Release from 25,000 ft—ignition fired 05/03/48 All Fuselage Rocket motor starting tests. Release from 25,000 ft—ignition fired 07/06/48 A10 Fuselage Rocket motor starting tests. Release from 35,000 if—explosion in tail 09/06/48 A3 Complete Rocket motor starting tests.
The rocket motor, developed by Thiokol, was capable of producing up to thrust.
The "3 inch" designation referred to the diameter of the rocket motor tube.
There were five first-stage rocket motor tests planned to be carried out by Alliant Techsystems (ATK) in Promontory, Utah. The second test firing of a KEI first stage rocket motor was conducted on 14 June 2007. The static firing included a full duration burn and a demonstration of the thrust vector control nozzle. The fourth test firing of the first-stage rocket motor was completed on November 13, 2008.
A pulsed rocket motor is typically defined as a multiple pulse solid-fuel rocket motor. This design overcomes the limitation of solid propellant motors that they cannot be easily shut down and reignited. The pulse rocket motor allows the motor to be burned in segments (or pulses) that burn until completion of that segment. The next segment (or pulse) can be ignited on command by either an onboard algorithm or in pre-planned phase.
She flew the rocket she designed and built, named Lucky 7 on an M1500 Rocket Motor.
The largest vendor of model rocket motors in the world is Estes Industries. The largest vendors of high-power rocket motors in the world are Cesaroni Technology Inc. and RCS Rocket Motor Components, Inc. The very first model rocket motor certified was by Model Missiles Inc.
The PAC-2 missile is long, weighs about , and is propelled by a solid-fueled rocket motor.
ONERA, based in France, and Volvo Flygmotor, based in Sweden, developed sounding rockets using hybrid rocket motor technology. The ONERA group focused on a hypergolic rocket motor, using nitric acid and an amine fuel. The company flew eight rockets: Once in April 1964, three times in June 1965, and four times in 1967.
A rocket cap is threaded into the base. The cap is removed prior to firing to allow ignition of the rocket motor for extended range. The rocket motor body contains seven pounds of solid rocket propellant arranged in two segmented grains. Each of the three segments of the forward grain contains an ignition pellet.
The free rocket used by the WS-1 and WS-1B consists of the warhead and fuse, an FG-42/43 rocket motor and the tail section. The FG-42/43 rocket motor is a single chamber, solid rocket motor with an advanced hydroxy-terminated polybutadine (HTPB) composition rocket propellant. The rocket of the WS-2 system features four control surfaces in the middle section of the rocket for terminal guidance. The rocket can be fitted with various types of warheads including anti-armour/personnel submunition, blasting, fuel air explosive (FAE), and high-explosive (HE).
The missile has a diameter of 0.56 m and is 6 m in length. It uses a single-stage solid propellant rocket motor. The Hatf IA and Hatf IB are upgraded versions with improved range and accuracy. The Hatf IA increased maximum range to 100 km by using an improved rocket motor and lighter materials in the missile's construction.
In applications which stay relatively in the atmosphere and require longer durations of lower thrust over a specific speed range the air turborocket can have a weight advantage over the standard solid fuel rocket motor. In terms of volumetric requirements, the rocket motor has the advantage due to the lack of inlet ducts and other air management devices.
The sole Su-7 was completed in 1944. Test flights demonstrated a top speed of 510 km/h (275 kn, 315 mph) at 12,000 m (39,370 ft) without the rocket motor, and 705 km/h (380 kn, 440 mph) with the rocket. In 1945, the rocket motor exploded during flight testing, killing the pilot and destroying the aircraft.
Developed for use with the Sea Oryx system, the Sea TC-1 variant has an improved seeker, data- link, and rocket motor.
The rockets utilized a standard rocket motor, fitted with a larger-diameter warhead; a longer-ranged version utilizing a motor was also produced.
By 1963, maintenance issues with the solid rocket motor were proving acute, and the rocket was removed from the inventory during that year.
A pair of prototype aircraft were constructed; on 20 April 1956, the first performed its maiden flight at Istres, initially flying only using jet power, the rocket motor was not installed at all. On 30 March 1957, the second Durandal conducted its first flight, joining the test programme shortly thereafter. It was the second prototype that first made use of the rocket motor during April 1957. During flight testing, a maximum speed of was attained at an altitude of, even without using the extra power of the rocket motor; this rose to 1667 km/h at 11,800 m while the rocket was active.
The small "Thunderbird" rocket of 1947 produced an acceleration of 100 G with a polysulfide composite propellant, star-grained cross-section solid rocket motor.
The motor nozzle is recessed in the center of the boat-tail rocket motor base of the projectile, and thrust is along the longitudinal axis.
According to NASA: "An investigation board concluded that the most likely cause of the mishap was structural failure of the spacecraft due to plume heating during the solid-rocket motor burn. Alternate possible but less likely causes determined were catastrophic failure of the solid rocket motor, collision with space debris, and loss of dynamic control of the spacecraft."CONTOUR at NASA.gov. Retrieved 2012-01-19.
The second design is a simplified version, intended to reduce cost by eliminating the rocket motor, depending on its natural buoyancy to propel the mine upward. There is yet a third mine derived from the second one with further simplification to reduce cost by further eliminating the control fins, thus lacking the directional capability, and this mine had to be released much earlier from its anchorage like the one with directional capability but without the rocket motor. The area control of both type, of course, is much less than the one with rocket motor, but still larger than the Specialized-1, which could only travel in straight line.
Redesigned Clamp-Type 2C1.5-4 Rocket Motor used for remote testing Cockrell's career took his family across the United States, including Alabama, Utah, Texas, and Virginia.
4, no. 19, p. 8.National Electric aims high (for the highest quality in the production of rocket motor bodies), Missiles and Rockets, November 29, 1965, v.
Parsch 2006 A modified, larger version of the Beach Barrage Rocket, using the Mk 9 rocket motor, was also produced, being introduced into service in late 1944.
A tandem-charge warhead is used to defeat any reactive armour present. In addition, thrust from the rocket motor provides kinetic energy to help destroy the target.
The AGM-69A was retired in 1993 over growing concerns about the safety of its warhead and rocket motor. There were serious concerns about the solid rocket motor, when several motors suffered cracking of the propellant, thought to occur due to the hot/cold cycling year after year. Cracks in the propellant could cause catastrophic failure once ignited. The SRAM was effectively replaced by the AGM-86 cruise missile.
On February 22, 2015 Raytheon announced an Extended Range upgrade to NASAMS- launched AMRAAM, calling it AMRAAM-ER. This combines the AMRAAM seeker with the ESSM rocket motor.
28 June 2012. Retrieved 19 May 2013. On 20 June 2012, the first hot-fire test under the control of SpaceShipTwo's proprietary Rocket Motor Controller (RMC) was successfully conducted.
The lower section was connected to a stage containing a rocket motor. It had a shiny metallic ring added to the bottom, with brightness magnitude from +5 to +8.
Low stratus clouds lay over the Ocksenkopf. The Walter liquid-fueled rocket motor built up to full thrust and Sieber pushed the button to ignite the four solid boosters.
The HTPB hybrid rocket motor and its oxidizer valve system were produced in SNC's manufacturing facility in Poway, California in conjunction with Scaled Composites. In 2013, the Poway facility was reported to be "currently producing motors for both SpaceShipTwo and SNC’s own Dream Chaser orbital crew vehicle". SNC closed the Poway facility in late 2014. The polyamide hybrid rocket motor is a modified version of the polybutadiene version, with different oxidizer valve arrangement.
The Sparrow has four major sections: guidance section, warhead, control, and rocket motor (currently the Hercules MK-58 solid-propellant rocket motor). It has a cylindrical body with four wings at mid-body and four tail fins. Although the external dimensions of the Sparrow remained relatively unchanged from model to model, the internal components of newer missiles represent major improvements, with vastly increased capabilities. The warhead is of the continuous-rod type.
All of the segments are contained in a single rocket motor case as opposed to staged rocket motors.Jensen, G.E, & Netzer D.W. Tactical Missile Propulsion, AIAAProgress in Astronautics and Aeronautics Volume 170 1996 The pulsed rocket motor is made by pouring each segment of propellant separately. Between each segment is a barrier that prevents the other segments from burning until ignited. At ignition of a second pulse the burning of the propellant generally destroys the barrier.
The first work on hybrid rockets was performed in the late 1930s at IG Farben in Germany and concurrently at the California Rocket Society in the United States. Leonid Andrussow, working in Germany, first theorized hybrid propellant rockets. O. Lutz, W. Noeggerath, and Andrussow tested a hybrid rocket motor using coal and gaseous N2O as the propellants. Oberth also worked on a hybrid rocket motor using LOX as the oxidizer and graphite as the fuel.
The extreme vibration and acoustic environment inside a rocket motor commonly result in peak stresses well above mean values, especially in the presence of organ pipe-like resonances and gas turbulence.
The very first APCP propellant model rocket motor made was by Rocket Development Corporation (Irv Wait). Circa 1970. The largest vendor of professional solid rockets in the world is Orbital ATK.
This model for the rocket motor was developed by Probert, WilliamsWilliams, F. A. "Introduction to Analytical Models of High Frequency Combustion Instability,”." Eighth Symposium (International) on Combustion. Williams and Wilkins. 1962. and Tanasawa.
1950s–1960s: Electrical Division National Electric Defense Products Facilities manufactured rocket motor bodies for Nike family of guided missiles. 1969: The company acquired a saw manufacturer Shurly & Dietrich, which continued operations until 1973.
This ignites a pyro. booster charge, which is retained in the safe and arm device behind a perforated plate. The booster charge ignites the propellant in the igniter initiator; and combustion products of this propellant ignite the solid rocket motor initiator, which fires down the entire vertical length of the solid rocket motor igniting the solid rocket motor propellant along its entire surface area instantaneously. At T−0, the two SRBs are ignited, under command of the four onboard computers; separation of the four explosive bolts on each SRB is initiated; the two T-0 umbilicals (one on each side of the spacecraft) are retracted; the onboard master timing unit, event timer and mission event timers are started; the three SSMEs are at 100%; and the ground launch sequence is terminated.
P80 is a solid-fuel first-stage rocket motor used on the European Space Agency Vega rocket (in the P80FW version). It is the world's largest and most powerful one-piece solid-fuel rocket engine.
The IA variant was created to address deficiencies with the radar radio frequency altimeter, cooling system, and the rocket motor of the missile. The redesigned missile was designated HF-1A and entered production in 1981.
Previously, he served as manager of the Shuttle Projects Office. There he managed the Shuttle's propulsion elements, including the Space Shuttle Main Engine, External Tank, Redesigned Solid Rocket Motor, Solid Rocket Booster, Advanced Solid Rocket Motor, and related systems and activities, including the Michoud Assembly Facility. Bridwell was born in Linton, Indiana, on October 4, 1935 and graduated from State High School in Terre Haute, Indiana, in 1953. He earned a bachelor of science degree in aeronautical engineering in 1958 from Purdue University, West Lafayette, Indiana.
In June 2012, Scaled Composites received an FAA permit to conduct rocket-powered supersonic test flights. SpaceShipTwo flight tests resumed in June 2012. In September 2012, Virgin Galactic announced that the unpowered subsonic glide flight test program was essentially complete. The company thereafter stated its intention to fit the hybrid rocket motor and control system to the vehicle, before resuming the glide flight test program with the rocket motor installed, in order to recharacterize the spacecraft's glide performance with slightly different weight distribution and aerodynamics.
In a standard hybrid rocket motor, the solid material is the fuel. In a reverse hybrid rocket motor, the oxidizer is solid. William Avery of the Applied Physics Laboratory used jet fuel and ammonium nitrate, selected for their low cost. His O/F ratio was 0.035, which was 200 times smaller than the ratio used by Moore and Berman. In 1953 Pacific Rocket Society (est. 1943) was developing the XDF-23, a × hybrid rocket, designed by Jim Nuding, using LOX and rubber polymer called "Thiokol".
The Block IIA is being jointly developed by Raytheon and Mitsubishi Heavy Industries; the latter manages "the third-stage rocket motor and nose cone". The U.S. budgeted cost to date is $1.51 billion for the Block IIA.
On 25 June 1954, the first prototype of the MD.550 Delta, without afterburning engines or rocket motor and with an unusually large vertical stabilizer, conducted its maiden flight.Jackson World Air Power Journal Volume 14, p. 120. In this configuration, it was able to attain a maximum speed of Mach 1.15. Following initial flights, it received a redesign that involved the vertical stabilizer being reduced in size along with the installation of afterburners and a rocket motor; it was at this point that the aircraft was renamed as the Mirage I.Brindley 1971, pp.
Scaled Composites performed a series of subscale rocket hot-firings between June 2005 and April 2009, before choosing a full-scale rocket motor design. News reports in early 2009 reported that the hot fire tests had been "completed" and that Spacedev (later acquired by Sierra Nevada Corporation) had been contracted by Scaled Composites to assist Scaled in developing SS2. By December 2011, 21 full-scale hot-fire ground tests had been carried out on RocketMotorTwo. "Virgin Galactic successfully completes SpaceShipTwo glide flight test and rocket motor firing on same day". SpaceRef.com.
The HVAR was designed by engineers at Caltech during World War II as an improvement on the 5-Inch Forward Firing Aircraft Rocket (FFAR), which had a diameter warhead but an underpowered diameter rocket motor. The desire for improved accuracy from the flatter trajectory of a faster rocket spurred the rapid development. HVAR had a constant diameter for both warhead and rocket motor, increasing propellant from of Ballistite. U.S. Ballistite propellant had a sea level specific impulse of over , compared with about for the British Cordite, German WASAG and Soviet PTP propellants.
Before loading, the lifting plug is replaced by a fuze, and the protector cap over the rocket-motor nozzle is removed; the 155 mm M549/M549A1 HERA is not intended to be fired in the 'rocket-off' mode. On-target effects are enhanced by the shell's HF-1 steel body. The 155 mm M549 HERA forward shell body is filled with a nominal 7.26 kg of Composition B. The M549A1 HERA filler is 6.8 kg of cast TNT. At the instant of firing, the propellant gases ignite a pyrotechnic delay train in the rocket motor.
The benefit of this setup is increased specific impulse over that of a rocket. For the same carried mass of propellant as a rocket motor, the overall output of the air turborocket is much higher. In addition, it provides thrust throughout a much wider speed range than a ramjet, yet is much cheaper and easier to control than a gas turbine engine. The air turborocket fills a niche (in terms of cost, reliability, ruggedness, and duration of thrust) between the solid- fuel rocket motor and gas turbine engine for missile applications.
Hydra 70s have also been fired from UH-60 and AH-6 series aircraft in US Army service. The AH-1G Cobra and the UH-1B "Huey" used a variety of launchers including the M158 seven-tube and M200 19-tube rocket launchers designed for the Mk 40 rocket motor; however, these models have been replaced by upgraded variants in the U.S. Marine Corps because they were not compatible with the Mk 66 rocket motor. The Hydra 70 rocket system is also used by the U.S. Navy, and the U.S. Air Force.
In 1998 SpaceDev acquired all of the intellectual property, designs, and test results generated by over 200 hybrid rocket motor firings by the American Rocket Company over its eight-year life. SpaceShipOne, the first private manned spacecraft, was powered by SpaceDev's hybrid rocket motor burning HTPB with nitrous oxide. However, nitrous oxide was the prime substance responsible for the explosion that killed three in the development of the successor of SpaceShipOne at Scaled Composites in 2007. The Virgin Galactic SpaceShipTwo follow-on commercial suborbital spaceplane uses a scaled-up hybrid motor.
The RIM-66B introduced changes that resulted in higher reliability. A new faster reacting autopilot, a more powerful dual thrust rocket motor, and a new warhead were added. Many RIM-66A missiles were re-manufactured into RIM-66B.
The OS-M series of rockets are larger than the OS-X series and aim to provide low cost flights to LEO and SSO.M series first-stage main rocket motor has been tested successfully on 4th of July.
A redesign was implemented to add reinforcement brackets and fittings in the aft ring of the skirt. These two modifications added approximately to the weight of each SRB. The result is called a Redesigned Solid Rocket Motor (RSRM).
While at periscope depth andbeing tracked by USS King's SQS-23B sonar, King fired an ASROC. The MK-44 torpedo separated from the rocket motor hit the Volador's sail after entering the water, leaving ahole in its sail.
"Bigger Stage." Flight International, 8 November 2005. In September 2005, the successful completion of key tests on the Vega's solid rocket motor igniters, a key milestone, was reported.Bentley, Ross. "Key tests for Vega igniters" Flight International, 21 September 2005.
The Space Shuttle used two Space Shuttle SRBs, which were the largest solid propellant motors ever built and the first designed for recovery and reuse. The propellant for each solid rocket motor on the Space Shuttle weighed approximately 500,000 kilograms..
It would create a 1 psi overpressure to 4782 feet and a 0.5 psi overpressure to 7970 feet. PFS also evaluated the risk of a rocket motor escaping the test stand, which was considered improbable given the design of the facility.
The service module was intended to provide rocket thrusters to control spacecraft attitude and provide orbital maneuvering capability to rendezvous with the International Space Station and then reenter the Earth's atmosphere. It included some structure, propellant tanks, and rocket motor systems.
A proximity fuze is laser-active timer with fuze and impact. The rocket motor has a burn time of 2.1 seconds, a maximum thrust of 27,000 newtons and can accelerate the Piranha missile up to Mach 2. The motor uses a smokeless propellant.
Its two solar panels generate upwards of 11 kilowatts of power. The spacecraft is equipped with X and Ka- band transponders. An R-4D bipropellant rocket motor and four XIPS-25 ion engines provide propulsion. USA-243 was launched by United Launch Alliance.
The rocket motor was capable of burning for approximately 87 s, having been upgraded since the previous flight. It was planned to shut off the motor at an altitude of 345,000 feet (105 km), presumably to avoid pushing the envelope too far.
Mitsubishi Type 73 jeep with two Type 64 anti-tank missile pods. The missile is cruciform in cross- section with four large wings. It is powered by a dual thrust rocket motor, which accelerates the missile to its cruising speed in 0.8 seconds.
Applications for infrared FPAs include missile or related weapons guidance sensors, infrared astronomy, manufacturing inspection, thermal imaging for firefighting, medical imaging, and infrared phenomenology (such as observing combustion, weapon impact, rocket motor ignition and other events that are interesting in the infrared spectrum).
The test demonstrated a successful operation of the first-stage rocket motor in its final flight configuration that was to be used during a Summer 2009 flight test. Due to the cancellation of KEI in May 2009, this test did not occur.
RocketMotorTwo is a hybrid rocket engine utilizing solid hydroxyl-terminated polybutadiene (HTPB) fuel and liquid nitrous oxide oxidizer – sometimes referred to as an N2O/HTPB motor – providing of thrust. The design makes use of lessons learned during the development of the SpaceShipOne hybrid rocket motor.
TC-2C is an advanced air-to- air version first tested in 2017 and intended to replace the standard TC-2. It features a number of incremental improvements including an improved rocket motor which allows an engagement range of 100km.speed amounted to Mach 6.
The MX-334 In 1942, John K. (Jack) Northrop conceived the XP-79 as a high-speed rocket-powered flying-wing fighter aircraft. In January 1943, a contract for two prototypes (s/n 43-52437 & 43-52438) with designation XP-79 was issued by the United States Army Air Forces (USAAF). Originally, it was planned to use a thrust XCALR-2000A-1 "rotojet" rocket motor from Aerojet that used mono-ethylaniline fuel and red fuming nitric acid (RFNA) oxidiser. However, the rocket motor configuration using canted rockets to drive the turbo-pumps was unsatisfactory and the aircraft was subsequently fitted with two Westinghouse 19B (J30) turbojets and re-designated XP-79B.
As with Polaris, starting a rocket motor when the missile was still in the submarine was considered very dangerous. Therefore, the missile was ejected from its launch tube using high pressure steam produced by a solid- fueled boiler. The main rocket motor ignited automatically when the missile had risen approximately above the submarine. The first test launch took place on 16 August 1968, the first successful at-sea launch was from a surface ship, the (from July 1 to December 16, 1969), earning the ship the Meritorious Unit Commendation, and the first test launch from a submarine took place on the on 3 August 1970.
Fenglei-7 (风雷7号) missile is first Chinese anti-radar missile (ARM), with Fenglei (or Feng Lei) meaning Wind (and) Storm. The abbreviated form of Fenglei-7 is FL-7, which should not be confused with the Chinese supersonic anti-ship missile FL-7, abbreviation for Feilong (Fei Long, 飞龙) meaning Flying Dragon. Fenglei-7 is an anti-radiation missile (ARM) derivative of PL-4 missile, sharing the same rocket motor, just like the way AGM-45 Shrike sharing the same rocket motor with AIM-7 Sparrow. In fact, PL-4 was mostly based on AIM-7 while Fenglei was mostly based on AGM-45.
Hybrid rocket motor detail of SpaceShipOne A hybrid-propellant rocket is a rocket with a rocket motor that uses rocket propellants in two different phases: one solid and the other either gas or liquid. The hybrid rocket concept can be traced back to at least the 1930s. Hybrid rockets avoid some of the disadvantages of solid rockets like the dangers of propellant handling, while also avoiding some disadvantages of liquid rockets like their mechanical complexity. Because it is difficult for the fuel and oxidizer to be mixed intimately (being different states of matter), hybrid rockets tend to fail more benignly than liquids or solids.
Typical firing range was about 1500 yards.E.W. Price, C.L. Horine, and C.W. Snyder (July 1998). "EATON CANYON, A History of Rocket Motor Research and Development in the Caltech-NDRC-Navy Rocket Program, 1941-1946,". 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cleveland, Ohio. AIAA.
Even though Virgin Galactic has run a number of ground tests on the new engine by May 2014, it was stated then that four additional ground tests of the polyamide-fueled engine were anticipated before the SpaceShipTwo flight tests could resume with the new-fuel rocket motor.
The missile is stored in a sealed canister which also acts as the launcher. Total weight of the missile and canister is 150 kg. It has five main sections: seeker, guidance and control, warhead, solid propellant rocket motor and servo. It is roll-stabilised in flight.
The solid rocket motor on both stages had a steerable nozzle for thrust vectoring. The 2nd stage had hydrazine reaction control jets for altitude control whilst coasting, and for separation from payload. Depending on mission, one, two or three 120 lb tanks of hydrazine could be fitted.
Internal components were replaced with miniaturized parts to take advantage of modern electronics technologies, yielding extra room within the missile for more fuel and a more powerful main rocket motor. The TK-2 possesses only modest capabilities against ballistic missiles but is highly effective against aircraft.
Solid- propellant rocket motors formed the first two stages of the interceptor missile. These rocket motor stages took the ASAT missile to the required height and velocity. After that, the nose tip heat shield was ejected and the IIR seeker of the Kill Vehicle locked onto the satellite.
The commander, instead, makes his own dramatic escape on his motorcycle after it deploys airfoils and a rocket motor and catches up with the cargo plane in midair. Although he has lost the battle, Gurerra shows admiration for Hunter's cunning, and he gives his old friend a thumbs up.
Tekoi Rocket Test Range, or Tekoi, is a former solid fuel rocket motor test and calibration site operated by Hercules Aerospace near the Utah Test and Training Range in Utah's West Desert, approximately west of Salt Lake City, Utah. It is located on the Goshute's Skull Valley Indian Reservation.
Demonstration and Shakedown Operation. Before the launch sequence is initiated, the on-board MARK 6 navigation system is activated. The specified mission trajectory is loaded onto the flight computer. Once the launch command is given, a steam generator system is activated, igniting a fixed solid-grain small rocket motor.
The missile is a single- stage, approximately 5.5 metre in length and 140 kg of weight with cruciform wing surface to increase high maneuverability and to give constant aerodynamic characteristics similar to Astra BVRAAM. It uses pre-fragmented warhead with optical proximity fuze and is powered by a dual-pulsed solid rocket motor made by Premier Explosives Limited (PEL) under technology transfer from DRDO. The dual-pulsed solid rocket motor produces variable thrust within a range of 0.6 to 2 Mach that reduces the overall reaction time while widening the targeting envelope as well as the engagement capability. DRDO ARM can target mobile integrated air-defence system as well as radar station that shutdown to avoid detection.
The missile is fitted with a multi-element IIR seeker capable of +/-90 degree off boresight angles. The missile seeker can be slaved to a helmet-mounted display (HMD), allowing the pilot to track a target beyond the aircraft's radar scan envelope using the missile's high off-boresight capability, achieved by the pilot turning his head towards the target to lock-on, better known as "look and shoot". Flight is controlled by a thrust-vector controlled solid rocket motor and free-moving type control wings on the missile's tail. The central portion of the missile has long, thin strakes, which help maintain missile maneuverability in the terminal homing stage after the rocket motor stops firing.
The Modular Midcourse Package (MMP), which is located in the forward portion of the warhead section, consists of the navigational electronics and a missile-borne computer that computes the guidance and autopilot algorithms and provides steering commands according to a resident computer program. The warhead section, just aft of the guidance section, contains the proximity fused warhead, safety-and-arming device, fuzing circuits and antennas, link antenna switching circuits, auxiliary electronics, inertial sensor assembly, and signal data converter. The propulsion section consists of the rocket motor, external heat shield, and two external conduits. The rocket motor includes the case, nozzle assembly, propellant, liner and insulation, pyrogen igniter, and propulsion arming and firing unit.
Nammo have been awarded a contract to evaluate engine performance requirements and 'find' the best engine design.Developing a high-performance rocket motor for the Heracles mission to the Moon May 2019 The engine may be fed by electrically driven pumps, from low pressure propellant tanks, which may enable in-space refueling.
In 2013 a Star 48GXV was tested for the Parker Solar Probe mission as the upper stage on an Atlas V 551 vehicle,ATK and NASA Successfully Demonstrate New Rocket Motor for Solar Probe Plus Mission but the development was cancelled, in favor of a Delta IV Heavy / Star 48BV combination.
By the late 1990s these were replaced with entirely Poland-designed elements. On January 1, 2013, Bumar Amunicja manufactured their 2,000th Grom missile set.2,000th Grom missile set - Armyrecognition.com, January 1, 2013 Grom was later improved into what became known as the Piorun, with a new seeker and rocket motor.
The BAT identifies high-value targets acoustically, using programs evolved from submarine warfare systems. The highest-value targets are selected and the Raytheon Optical system in the nose images the designated target. Each target's weakest point is selected. The retarder is dropped, the rocket motor fires, and is optically guided.
He was attached to supporting tethers. There were at least nine other people present, including a medical doctor.Great American Jet Pack, p. 39 On 17 February 1961, after nineteen tethered flights, Moore suffered his major setback when a tether could not support his weight after the rocket motor stopped firing.
In July 2007 at the Mojave spaceport three Scaled Composite employees were killed and three critically injured while testing components of the rocket motor for SpaceShipTwo. An explosion occurred during a cold fire test, which involved nitrous oxide flowing through fuel injectors. The procedure had been expected to be safe.
The projectile was developed to provide extended range for standard and developmental howitzers. The projectile has two distinctive preassembled components—the high explosive warhead and the rocket motor. The warhead is fabricated from high fragmentation steel for increased effectiveness and contains a bulk-filled explosive. Currently there are two models.
The PL-12 may use the radar and data link from the Russian R-77, or otherwise use systems benefiting from technology transfers from Russia. The missile uses a Chinese rocket motor and airframe. The PL-12 may have a passive homing mode for use against jammers and AEW aircraft.
Babcock 2008, p.328. The propulsion system was intended to be a liquid-fueled, dual-thrust rocket, using hypergolic, storable propellants.Babcock 2008, pp.387-390 The rocket motor planned for use in the Diamondback missile was based on that developed by NOTS for the Liquid Propellant Aircraft Rocket (LAR) project.
Propulsion was provided by a 223-newton rocket motor, mounted within the frame, which used the mono- propellant hydrazine. The nozzle, with 4-jet vane vector control, protruded from one wall of the octagonal structure. Power was supplied by 17,472 photovoltaic cells, covering an area of on the four solar panels.
The landing of each Penetrator would be identical. It began with the spinning up of the Penetrator for stability followed by separation from the orbiter. The Penetrator would fire a solid rocket motor which would begin to drop it from orbit. After 20–22 hours, the Penetrator would encounter the Martian atmosphere.
P120 is a solid-fuel first-stage rocket motor in development by Avio and ArianeGroup through the joint venture Europropulsion on behalf of European Space Agency for use on Vega C and Ariane 6. It will replace its predecessor P80 as the world's largest and most powerful one-piece solid-fuel rocket engine.
Following that flight the interior of the fairing was painted white, and some small stiffening ribs were added. The craft has a single unsteerable and unthrottleable hybrid rocket motor, a cold gas reaction control system, and aerodynamic control surfaces. All can be controlled manually. See the separate section below concerning the rocket engine.
Investigation quickly provided an anatomy of the failure. The right solid rocket motor ruptured starting at T+6 seconds and the resulting torque on the launch vehicle caused the left SRM to break away. This triggered its automatic destruct system, blowing the Stage 1 to pieces and rupturing the Stage 2's tank.
P.K. Nag (2002). Tata McGraw-Hill. p. 432. In the 13th century, the solid rocket motor was invented in China. Driven by gunpowder, this simplest form of internal combustion engine was unable to deliver sustained power, but was useful for propelling weaponry at high speeds towards enemies in battle and for fireworks.
However, because of some unknown issue in the first stage rocket motor, the scramjet payload could not be delivered to the correct altitude and speed in the flight test conducted on September 18, 2013. The unmanned spacecraft with the payload and the rocket plummeted in the North Sea off the cost of Norway.
The SM-3 evolved from the proven SM-2 Block IV design. The SM-3 uses the same solid rocket booster and dual thrust rocket motor as the Block IV missile for the first and second stages and the same steering control section and midcourse missile guidance for maneuvering in the atmosphere. To support the extended range of an exo-atmospheric intercept, additional missile thrust is provided in a new third stage for the SM-3 missile, containing a dual pulse rocket motor for the early exo-atmospheric phase of flight. Initial work was done to adapt SM-3 for land deployment ("Aegis ashore") to especially accommodate the Israelis, but they then chose to pursue their own system, the NATO code-name Arrow 3.
The main combustion chamber of the 509B engine used for the B V6 and V18 occupied the same location as the A-series' engine did, with the lower Marschofen cruise chamber housed within the retractable tailwheel's appropriately widened ventral tail fairing. On 6 July 1944, the Me 163B V18 (VA+SP), like the B V6 basically a standard production Me 163B airframe outfitted with the new, twin- chamber "cruiser" rocket motor with the aforementioned airframe modifications beneath the original rocket motor orifice to accept the extra combustion chamber, set a new unofficial world speed record of , piloted by Heini Dittmar, and landed with almost all of the vertical rudder surface broken away from flutter.de Bie, Rob. "Me 163B Komet - Me 163 Production - Me 163B: Werknummern list". robdebie.home.
The Ministry of Defence of the USSR. A small PG-15P powder charge is used to boost the projectile from the gun barrel at . Once the projectile has travelled , the rocket motor starts and accelerates it to . The OG-15V HE-Frag round weighs , it uses an OG-9 shell with a TNT bursting charge.
It is designed to increase the kill efficiency along with a higher range performance. Agni IV is equipped with state-of-the- art technologies, that includes indigenously developed ring laser gyro and composite rocket motor. It is a two-stage missile powered by solid propellant. Its length is 20 meters and launch weight 17 tonnes.
The missile used a kinetic energy penetrator to penetrate enemy armor. This effect was improved by a rocket motor that sped the munition up. It steered with impulse thrusters. MRM-KE used technology developed as part of the X-Rod and XM1007 Tank Extended Range Munition (TERM) programs, both of which have been cancelled.
There are large vertical tailbooms mounted on the end of each wing, with horizontal stabilizers protruding from the tailbooms. It has gear for horizontal landings. The overall mass of the fully fueled craft is , of which is taken by the fully loaded rocket motor. Empty mass of the spacecraft is , including the empty motor casing.
A monolithic, rocket motor was designed, which was too big to be transported by rail. A plan was devised where the rocket motors would be transported by barge to Cape Canaveral. To facilitate barges, a canal was dug (C-111) and a drawbridge installed for the U.S. Highway 1 crossing at mile marker 116 ().
An updated version of the missile entered service in 1967 designated the KSR-2M. It borrowed some features from the KSR-5 missile (NATO:AS-6 "Kingfisher") including a new Isayev S5.6.0000 rocket motor. This allowed the new missile to be launched from altitudes as low as 500 meters rather than the previous 1,500 meters.
Advanced Air Defence (AAD) Endo-atmospheric interceptor missile, being integrated at the Programme Air Defence ABM missile production facilities in Hyderabad. Note the Missile Jet Vanes at the end of the rocket motor. The system provides for very quick pitch over and roll control during launch. Development of the anti-ballistic missile system began in 1999.
The Block II missile was introduced in 1983 with a new rocket motor for longer range and a new warhead. The RIM-66G is for the Aegis combat system and the Mk26 missile launcher. The RIM-66H is for Aegis and the Mk41 vertical launcher. The RIM-66J is the version for the New Threat Upgrade.
An airbag ejects the forward five submunitions, then five in the aft bay. Following a preset timeline, the submunitions deploy parachutes so that they are spaced about apart. Then each submunition releases its chute, fires a rocket motor that stops its descent and spins it on its longitudinal axis, and releases Skeets 90 degrees apart, in pairs.
Upon rocket motor ignition, the missile tailcone was blown away by the exhaust plume. About 1,500 missiles were built at a cost of about $592,000 each by the time production ended in 1975. The Boeing Company sub-contracted with the Lockheed Propulsion Company for the propellants, which subsequently closed with the end of the SRAM program.
Subtypes are given one or more letter suffixes after the diameter number, or a trailing number (i.e., "-2") after the internal designation. The "T" prefix stands for Thiokol, and the following letter refers to the company division that developed the rocket motor. In this case, "E" refers to the Elkton, MD division and the "M" stands for motor.
The FJ-1 was the most important member of the FJ series ABM. The name FJ-1 was often used to replace HQ-81. The missile was long, weighed around , and was launched at 50-degree angle. Originally adopting two-stage liquid rocket motors, it was later improved to have one solid rocket motor and one liquid motor.
G. P. Sutton and Oscar Biblar, Rocket Propulsion Elements, (Eighth edition), pp. 595–599, John Wiley and Sons 2010. With N2O (nitrous oxide, or "laughing gas") as the oxidizer, it is used to power the SpaceShipTwo hybrid rocket motor developed by SpaceDev. It will also be oxidized by high-test peroxide in the land speed record attempt Bloodhound SSC.
The remaining unburned propellant shattered allowing more surface area of the rocket motor to burn, in turn increasing the pressure and rate of combustion to a speed that was no longer considered burning but was now a deflagration and destroyed the tower, and the pilot was disqualified because the judges refused to believe it was unarmed.
This weapon is reloadable and uses the 35-mm M73 training rocket. A subcaliber training device that uses a special tracer cartridge also exists for the M72. A training variant used by the Finnish armed forces fires 7.62-mm tracer rounds. The US Army tested other 66-mm rockets based on the M54 rocket motor used for the M72.
The test lasted 140 seconds with the motor delivering a maximum thrust of , simulating the complete burn time from liftoff and through the first phase of flight. No anomalies were seen and the performance met expectations. On 28 January 2019 a second test firing of 135 seconds at the Guiana Space Centre qualificated the P120C rocket motor for flight.
The complete FN-6 missile system weighs 16 kg. The missile is 1.495 m in length, and has a diameter of 0.072 m. The weight of the missile is unknown. It uses a single stage solid rocket motor, and can obtain a maximum speed of 360 m/s when flying head-on, and 300 m/s when tail chasing.
Sky Arrow is TV guided like LMD-002.Sky Arrow UAV employed missile The aerodynamic layout of Sky Arrow contains four pairs of control surfaces, with four parallelogram shaped ones in front, and four smaller trapezoid shaped ones in the tail, and the missile uses rocket motor instead of turbojet engine and thus does not have any intake.
The next year, the vehicle was put into mass production and by 1 May 1974 four of these vehicles had been delivered to the 3rd Artillery Regiment.de Mazarrasa (1990), p. 39 The missile itself weighs and is long. Using a simplified inertial guidance system and a solid propellant rocket motor, the Pluton has a maximum range of .
The FG-47 (a.k.a. SpaB-54) is a Chinese solid rocket motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation (also known as the 6th Academy of CASIC) for use in the Long March 2C SD/CTS/SMA third stage. It had its inaugural flight on the Iridium-MFS demonstration mission on September 1, 1997.
The thrust generated in the rocket of missile depends on this rate of flow. Thus Knowing quantitatively the burning rate of a propellant, and how it changes under various conditions, is of fundamental importance in the successful design of a solid rocket motor. The concept of Burning rate is also relevant in case of liquid propellants.
Spinning is used to make tubular (axis-symmetric) parts by fixing a piece of sheet stock to a rotating form (mandrel). Rollers or rigid tools press the stock against the form, stretching it until the stock takes the shape of the form. Spinning is used to make rocket motor casings, missile nose cones, satellite dishes and metal kitchen funnels.
In 2019 Nammo was awarded an ESA contract to initiate development of a reusable rocket engine for the ascent stage of the HERACLES lunar lander.Developing a high-performance rocket motor for the Heracles mission to the Moon May 2019 The engine may be fed by electrically driven pumps, from low pressure propellant tanks, which may enable in-space refueling.
The Shaheen-II is a longer ranged variant of the Shaheen-I missile. It was the most advanced ballistic missile in service until shaheen III with the Pakistan Armed Forces. It uses a two- stage solid-fuel rocket motor designed to carry conventional or nuclear payloads. It is transported and launched by a 6-axle transporter erector launcher (TEL).
About 24 hours after the maiden flight, the second Mesquito, 12.066, was launched from the same launch pad at the Wallops Flight Facility. The launch occurred early in the launch window, and was reported to have failed, due to a loss of control shortly after burnout of the solid rocket motor, and the loss of stabilisation fins during descent.
A wide variety of unique designs, homebuilts, and even a Mercury rocket motor share the display floor. The aircraft are supplemented by a collection of engines from World War I to the present day. It also houses a library, offices, a conference room and the museum's small gift shop. The hangar annex houses larger aircraft and engines.
Cajun Dart is the designation of an American sounding rocket. The Cajun Dart was used 87 times between 1964 and 1970. The Cajun rocket motor was developed from Deacon. Staged on top of a Nike rocket, it was part of the Nike-Cajun sounding rocket; it was also used as part of the Terasca three-stage rocket.
64-65 The rocket booster was similar to the smaller Type 10 and 3, in that the rocket booster consisted of an adapter plate, propellant chamber, butt plate, tail cone, braced tail fins, and a single venturi. However, with the Type 21/Type 22, the rocket motor is attached to the bomb with a different adapter plate for each type of bomb and the motor does not drop away when it burns out. An adapter sleeve fits into the tail of the warhead and the forward end of the rocket motor and was riveted around the circumference joining the two. In the center of the nose cap, there was a socket for a blasting cap that was electrically ignited by an umbilical cord that attached to the booster through a hole in the adapter sleeve.
When the time for weightlessness has arrived on a SS2 flight, the rocket motor will be turned off, ending the noise and vibration. Passengers will be able to see the curvature of the Earth. Numerous double-paned windows that encircle the cabin will offer views in nearly all directions. Cushioned seats will recline flat into the floor to maximize room for floating.
The 45 cm naval rocket was first discovered during the Battle of Luzon. It was a spin-stabilized rocket that was filled with 39 sticks of solid propellant weighing and the exhaust gasses were forced through six venturis that were angled at 18° to impart spin. The total weight of the rocket motor was .German and Japanese Solid-Fuel Rocket Weapons, pg.
It was released rearwards from rails on the wings of the aircraft. Thus, with the aircraft's forward motion cancelled-out by the rocket motor, the device fell directly onto the target. It possessed two advantages over the use of DCs; no pre-setting of depth was required, and the enemy was unaware of the attack if no hits were made.Hendrie 2006, p.56.
A suitable warhead of 10 kiloton began development at Atomic Weapons Establishment (AWRE). Codenamed ‘Tony’, this was a UK version of the US W44 Tsetse primary. The Propellant and Explosives Research and Manufacturing Establishment (PERME) developed the solid rocket motor based on the successful Cuckoo originally developed for the Black Knight experimental rocket. The engines were built by Bristol Siddeley Engines Ltd.
The OS-X1（aka "Chongqing Liangjiang Star"） is a suborbital high-altitude rocket, a sounding rocket, designed for research and testing. The solid rocket motor was successfully tested in December 2017. This 9-meter long rocket was launched at Jiuquan Satellite Launch Center on 7 September 2018 (04:10 UTC), reaching an altitude of 35 km and traveling 169 km.
The company provides vehicles to move rockets, boosters, and satellite payloads. The Solid Rocket Motor (SRM) transporter, for example, moved the Space Shuttle segments between refurbishment and storage facilities on the Cape Canaveral Air Force Station and the Vehicle Assembly Building. Payload Canister Transporters (PCT) moved payload canisters between space shuttle payload processing facilities, the vertical processing facility, and the launch pad.
It had a length of 13 m and a diameter of 1.4 m. Being a three-stage missile, it was fitted with two solid-propellant rocket motor stages and the Kill vehicle. The combined weight of the first and the second stages is 17.2 tons, with the third stage weighing 1.8 tons. The first two stages can carry 16.7 tons of fuel.
The glider design is based on a twin fuselage. NASA engineers plan to suspend the rocket stage below the center section of the glider wing. The glider will carry its own small rocket motor which will light for about 20 seconds after release from the tow plane to maintain velocity while climbing. The glider will then glide at a 70-degree angle.
The New Shepard Crew Capsule is a pressurized crew capsule that can carry six people, and supports a "full-envelope" launch escape system that can separate the capsule from the booster rocket anywhere during the ascent. Interior volume of the capsule is . The Crew Capsule Escape Solid Rocket Motor (CCE-SRM) is sourced from Aerojet Rocketdyne. After separation two or three parachutes deploy.
This canal became the southernmost freshwater canal in Southeast Florida and was dubbed the "Aerojet Canal". A concrete silo was constructed for the rocket motor, 180 feet deep into the Everglades. Aerojet needed a cylindrical chamber that would withstand the force and power a space- faring rocket would cause. Aerojet subcontracted the fabrication of 260-inch- diameter, 24m long chamber.
The FG-46 (a.k.a. EPKM and SpaB-170) is a Chinese spin stabilized solid rocket motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation (also known as the 6th Academy of CASIC) for use in the Long March 2E on GTO missions. It first flew as a prototype SPTS-M14 on July 16, 1990 on the Badr A mission.
Extended range shells are sometimes used. These special shell designs may be Rocket Assisted Projectiles (RAP) or base bleed to increase range. The first has a small rocket motor built into its base to provide additional thrust. The second has a pyrotechnic device in its base that bleeds gas to fill the partial vacuum created behind the shell and hence reduce base-drag.
To ensure sufficient performance, Vought made provisions for a Rocketdyne XLF-40 liquid-fueled rocket motor with 8,000 lbf (35.6 kN) of thrust in addition to the turbojet. Avionics included the AN/AWG-7 fire control computer, AN/APG-74 radar, and AN/ASQ-19 datalink. The system was expected to simultaneously track six and engage two targets.Gunston 1981, p. 244.
VYOM ('sky' in Sanskrit) is the Sounding Rocket designed by the BTech students of IIST. Vyom had its maiden flight on 11 May 2012 when it took to the sky from TERLS. and the mission was a total success. The objective of the launch was to flight-test the solid rocket motor and the accelerometer payload developed for the project.
The first NF-104A (USAF 56-0756) was accepted by the USAF on 1 October 1963. It quickly established a new unofficial altitude record of and surpassed this on 6 December 1963 by achieving an altitude of . The aircraft was damaged in flight June 1963 when a rocket oxidizer vessel exploded. It suffered an inflight rocket motor explosion in June 1971.
The Sea Skua failed to hit its target and failed to explode. The fault was believed to have been traced to a faulty connecting pin wire that ignites the rocket motor. The missile fell into the sea, and was not recovered. The Royal Malaysian Navy ordered Matra Bae Dynamics (MBDA) to take back the missiles to conduct system checks, and re- tested.
It has been developed by DRDO's laboratory Aeronautical Development Establishment (ADE). Ulka was earlier simply known as MT (Missile Target). It has been designed to be launched from subsonic or supersonic aircraft by means of an ejector release unit. It performed missions between 50 m to 13,000 m altitude at speeds ranging from 0.7 to 1.4 Mach with a rocket motor.
The casing must be designed to withstand the pressure and resulting stresses of the rocket motor, possibly at elevated temperature. For design, the casing is considered a pressure vessel. To protect the casing from corrosive hot gases, a sacrificial thermal liner on the inside of the casing is often implemented, which ablates to prolong the life of the motor casing.
Electric solid propellants (ESPs) are a family of high performance plastisol solid propellants that can be ignited and throttled by the application of electric current. Unlike conventional rocket motor propellants that are difficult to control and extinguish, ESPs can be ignited reliably at precise intervals and durations. It requires no moving parts and the propellant is insensitive to flames or electrical sparks.
All rocket concepts are limited by the rocket equation, which sets the characteristic velocity available as a function of exhaust velocity and mass ratio, of initial (M0, including fuel) to final (M1, fuel depleted) mass. The main consequence is that mission velocities of more than a few times the velocity of the rocket motor exhaust (with respect to the vehicle) rapidly become impractical.
The Komet had a HWK 109-509, a rocket motor which consumed methanol/hydrazine as fuel and high test peroxide as oxidizer. The hypergolic rocket motor had the advantage of fast climb and quick-hitting tactics at the cost of being very volatile and capable of exploding with any degree of inattention. Other proposed combat rocket fighters like the Heinkel Julia and reconnaissance aircraft like the DFS 228 were meant to use the Walter 509 series of rocket motors, but besides the Me 163, only the Bachem Ba 349 Natter vertical launch expendable fighter was ever flight-tested with the Walter rocket propulsion system as its primary sustaining thrust system for military-purpose aircraft. The earliest ballistic missiles, such as the Soviet R-7 that launched Sputnik 1 and the U.S. Atlas and Titan-1, used kerosene and liquid oxygen.
However, barely two month after the program begun, Cultural Revolution started and due to this political turmoil, PL-4 program was disrupted to a complete stop, and it would not be until more than a decade later, well after the end of Cultural Revolution, would the program restart again. The rocket motor of PL-4 is designated as FG101, and is shared by another anti-radar derivative named Fenglei-7 (风雷7号). The revival of PL-4 was partially due to the decision to develop the anti-radar derivative in January 1979. The designer of the rocket motor was Harbin Ship Engineering Academy (哈尔滨船舶工程学院), the predecessor of Harbin Engineering University, 349th Factory was tasked to manufacture the propellant, 845th Factory was tasked for ground test, and 331st Factory was tasked for final integration.
Built in 1941 under the authority of the Minister of Aircraft Production, the works was operated by the Bristol Aeroplane Company to build and repair Bristol Beaufort and Bristol Beaufighter torpedo fighter-bombers and Hawker Tempest fighters. After the war the company built pre-fab houses and schools there until the mid-fifties, and then rocket-motor manufacturing required by the Cold War took over.
The JL-2 is a naval variant of the land- based DF-31. Their common 2-metre diameter solid fuel rocket motor was successfully tested in late 1983, and research and development efforts were reorganized starting in 1985 to produce both missiles. The first JL-2 at-sea launch occurred in 2001 from a Type 031 submarine. The program was delayed after a failed test in 2004.
It was first used in flight on 20 November 1950, by Hawker's test pilot Trevor "Wimpy" Wade. Half a dozen flights were made using the rocket motor before a minor explosion damaged the aircraft. Although methanol was used in the P.1072, jet fuel could be used for the Snarler. It was decided that reheat was a more practical proposition for boosting jet thrust than rockets.
In March 1964, the Defense Meteorological Satellite Program (DMSP) office approved plans to develop a more powerful Thor Burner 2 launch vehicle. The Burner 2 was developed for the Air Force Space Systems Division in 1965. The Boeing Company served as prime contractor with major subcontractors: Thiokol Chemical Corporation (solid rocket motor); Honeywell Inc. (pre-programmed inertial guidance system); Walter Kidde Co. (reaction control system).
As integration contractor for the Air Force Space Experiment Support Program (SESP) Office, Boeing designed, built and tested the injection stage, or "payload dispenser," which carried the 2 satellites on top of a standard Burner II stage and placed them in precise orbits. The satellites were mounted on opposite sides of the injection stage, which housed a 640 kgf thrust, solid-propellant rocket motor, Star 37.
After modifications the first launch was carried out on 4 September 1943, towed behind a large truck. For more comprehensive testing, a Lockheed P-38 Lightning was used to tow the aircraft on its first proper flight on 2 October 1943. In early 1944 the no.2 aircraft was modified to take the Aerojet XCAL-200 rocket motor, reverting to the "secret" MX-324 designation.
The aircraft was also fitted with combined rudder and airbrakes outboard of the elevons. Testing with the rocket motor commenced on 22 June 1944, with the first aerotow launch for a powered flight on 5 July 1944, making it the first US-built rocket-powered aircraft to fly. Flight testing was concluded by 1 August 1944 and the two remaining aircraft were disposed of. The no.
In the end, it took Truly and NASA's "Return to Flight" program 31 months before the Space Shuttle Discovery successfully flew on September 29, 1988 with STS-26. In March 1986, Truly noted in a memo that there were several actions NASA needed to accomplish before launching another Shuttle flight. They included "Solid Rocket Motor joint redesign, Critical Items review, and Operations and Maintenance Instructions review".
They also produce high power rocket motor reloads, ranging from H to O impulse. High power reloads require proper certification from the National Association of Rocketry, or Tripoli Rocketry Association. Until 2017, all reloads required the use of Aerotech, Rouse-Tech, or Dr. Rocket reload casings. A recent cross-use certification agreement permits the use of 98mm Aerotech reloads in CTI (Cesaroni Technology Incorporated) hardware.
A despun dish antenna provided S and X band communication with Earth. A Star-24 solid rocket motor was integrated into the spacecraft to provide the thrust to enter orbit around Venus. From Venus orbit insertion to July 1980, periapsis was held between (at 17 degrees north latitude) to facilitate radar and ionospheric measurements. The spacecraft was in a 24-hour orbit with an apoapsis of .
DeYoung started his career with Hercules Aerospace in Salt Lake City, Utah, in 1985. He held numerous management positions at Hercules in its solid rocket motor and composite structures businesses. After ATK acquired Hercules in 1995, DeYoung continued to advance and held roles in finance, operations, composite structures, human resources, and munitions. DeYoung earned an undergraduate degree in business at Weber State University, in Ogden, Utah.
Tanasawa, Y. "On the Combustion Rate of a Group of Fuel Particles Injected Through a Swirl Nozzle." Technology Reports of Tohoku University 18 (1954): 195–208. It is reasonable to neglect Q_j, \ \Gamma_j, for distances not very close to the spray atomizer, where major portion of combustion occurs. Consider a one-dimensional liquid- propellent rocket motor situated at x=0, where fuel is sprayed.
Each solid rocket booster had four hold-down posts that fit into corresponding support posts on the mobile launcher platform. Hold-down bolts held the SRB and launcher platform posts together. Each bolt had a nut at each end, the top one being a frangible nut. The top nut contained two NASA standard detonators (NSDs), which were ignited at solid rocket motor ignition commands.
The solid rocket motor ignition commands were issued by the orbiter's computers through the master events controllers to the hold-down pyrotechnic initiator controllers (PICs) on the mobile launcher platform. They provided the ignition to the hold-down NSDs. The launch processing system monitored the SRB hold- down PICs for low voltage during the last 16 seconds before launch. PIC low voltage would initiate a launch hold.
The fifth stage was the NOTS-17 solid rocket motor, which had been developed by the Naval Ordnance Test Station. The Scout X-1A was launched on its only flight at 05:07 GMT on 1 March 1962. It flew from Launch Area 3 of the Wallops Flight Facility. The flight carried an atmospheric re-entry experiment to an apogee of , and was successful.
In October 2012, Scaled Composites installed key components of the rocket motor, and SpaceShipTwo performed its first glide flight with the engine installed in December 2012. The spacecraft's first powered test flight took place on 29 April 2013, briefly driving SpaceShipTwo to a supersonic velocity. Richard Branson said it "couldn't have gone more smoothly". On 5 September 2013, the second powered flight was made by the SpaceShipTwo.
A newly designed spin-up orbital insertion solid propellant rocket motor third stage was added to the two existing Nitric acid/UDMH liquid propellant stages. An attempt to use this vehicle to launch a Chinese satellite before Japan's first attempt ended in failure on November 16, 1969. The first DF-4 liquid-propellant with two-stage, single-warhead IRBM was tested with success on January 30, 1970.
It also features anti-laser filters to protect the operator from blinding battlefield lasers. When the trigger is pressed, the rocket motor is fired electronically. The rocket leaves the launcher at a speed of approximately 250 meters per second. It is accurate enough to be used against armoured vehicles at a range of 350 meters, and can engage larger stationary targets up to 600 meters away.
While the rocket motor is still burning, this will cause the flight path to curve into the wind. The TRADOC bulletin explains aiming difficulties for more distant moving targets in crosswinds at some length. Similar to a recoilless rifle the RPG-7 has no noticeable recoil, the only effect during firing being that of the sudden lightness of the launcher as the rocket leaves the tube.
The simplest version of an air- augmentation system is found in the shrouded rocket. This consists largely of a rocket motor or motors positioned in a duct. The rocket exhaust entrains the air, pulling it through the duct, while also mixing with it and heating it, causing the pressure to increase downstream of the rocket. The resulting hot gas is then further expanded through an expanding nozzle.
The Seacat is a small, subsonic missile powered by a two-stage solid fuel rocket motor. It is steered in flight by four cruciformly arranged swept wings and is stabilised by four small tail fins. It is guided by command line-of-sight (CLOS) via a radio-link; i.e., flight commands are transmitted to it from a remote operator with both the missile and target in sight.
At higher altitudes the air density decreases and the vehicle must travel faster to achieve a sufficient inlet mass capture. At even higher altitudes, the DASS engine will need to store onboard oxidizer to be used with a rocket motor in its flow path. The target is to achieve a major component of orbital velocity when operating in the airbreathing mode before switching to the rocket mode.
The Trident II is a three-stage rocket, each stage containing a solid-fuel rocket motor. The first motor is made by Northrop Grumman. This first stage incorporates a solid propellant motor, parts to ensure first-stage ignition, and a thrust vector control (TVC) system. The first-stage section, compared to the Trident C-4, is slightly larger, allowing increased range and a larger payload.
Rocket motor, casing removed The engine's fuel chemistry used 80% high test hydrogen peroxide or 'T-Stoff'. This was a 'cold cycle' engine; the peroxide acted as a monopropellant and was decomposed by a catalyst into superheated steam and oxygen. The catalyst used was a consumable liquid solution of calcium permanganate or 'Z-Stoff'. As this catalyst is consumed, the engine is regarded as a bipropellant engine.
A fixed amount of propellant is contained in the rocket motor. The steel-cased rocket is stabilized with spin imparted by six angled nozzles in its base. Type 63 rockets may be launched without the launcher; improvised firing can employ tubing, rails or even dirt berms. The Type 63 was distributed on the basis of six per infantry regiment, or 18 per infantry division.
The Astrocam 110 (or Astrocam) is a model rocket with a built-in camera for taking aerial photographs. The Astrocam was introduced in the 1979 Catalog by its manufacturer Estes and it can be flown with B6-4 and C6-7 model rocket motors (see Model rocket motor classification). The Astrocam was available as kit, or as ready-to-fly model. Both versions use the Estes Delta II launch body.
Attached to the rocket motor 250 mm L9 53 kg is a 228 m long hose packed with 1455 kg of pe6/al explosive. After the hose lands on the ground it detonates and destroys over 90% of mines along its entire length. The 10% that are not destroyed are simply pushed aside to safety. It can be used in tandem to defeat double impulse mines or mines of greater depth.
Rasta Launch Gilmour Space employs a proprietary hybrid rocket motor technology that it believes overcomes many of the traditional challenges of hybrid rockets. A hybrid-propellant rocket utilises a mixture of solid and liquid fuel. Advantages of hybrid rockets include acceptably high specific impulse values with relatively very low complexity and associated risks. In general, hybrid rocket engines are the safest of the three major rocket engines – e.g.
In the absence of an emergency, the LES was routinely jettisoned about 20 or 30 seconds after the launch vehicle's second-stage ignition, using a separate solid-fuel rocket motor manufactured by the Thiokol Chemical Company. Abort modes after this point would be accomplished without the LES. The LES was carried but never used on four uncrewed Apollo flights, and fifteen crewed Apollo, Skylab, and Apollo-Soyuz Test Project flights.
The engineering and development work of the second- generation engine was done in-house, by Virgin Galactic. The work began on the new formulation for the hybrid engine in 2013, and by May 2014—when SNC's involvement with SS2 propulsion using the first-generation rocket motor was ended—the new engine formulation had already completed full-duration burns of over 60 seconds in ground tests on an engine test stand.
In 1944, Sergei Korolev and Glushko designed the RD-1KhZ auxiliary rocket motor tested in a fast-climb Lavochkin La-7R for protection of the capital from high-altitude Luftwaffe attacks."Last of the Wartime Lavochkins", AIR International, Bromley, Kent, U.K., November 1976, Volume 11, Number 5, pages 245-246. At the end of World War II, Glushko was sent to Germany and Eastern Europe to study the German rocket program.
The FJ-3, the last member of FJ series missile used in HQ-81 ABMS begun development in May 1974. It was a three-stage rocket motor powered ABM launched from a silo, but it was cancelled in 1977. However, subsystems of FJ-3 were developed and used on other Chinese missile programs, such as the S-7 vehicle mounted computer, which was later used on the DF-5 ballistic missile.
The operator would launch a missile and guide it along a line of site to an approaching enemy aircraft by a joystick, issuing a radio command. The Hilda missile was small and subsonic, powered by a two-stage rocket motor and steered by four swept wings and stabilised by four tail fins. Hilda missile system File:Sea Cat missile.png A Hilda missile, similar to that operated by 121 Squadron.
The Bell company was awarded a contract to develop, flight test, and demonstrate a practical SRLD. A rocket motor with a thrust of 280 pounds-force (1.25 kN or 127 kgf) was chosen. The pack with its fuel weighed 125 lb (57 kg). The pack had a fiberglass frame contoured to fit the operator's body, secured with straps, and cylinders of fuel and nitrogen were attached to the frame.
Very few believed the contrary, but one of them was Ernst Heinkel. Following his offer of unhesitating support, Heinkel placed at the disposal of von Braun an He 112 fuselage shell less wings for the standing tests. In 1936 von Braun had advanced far enough to begin trials. A great tongue of flame from the rocket motor roared through the fuselage tail to set up the back thrust.
Kamag Transporttechnik was founded in 1969 and is headquartered in Ulm, Baden- Württemberg, Germany. Its primary goal was to shift heavy transports to the road. Today, Kamag develops and produces specialized transporters and other modular vehicles for a wide range of applications. Space Shuttle Endeavour on Kamag transport modules Solid Rocket Motor transporter vehicle manufactured by Kamag NASA has been a customer of Kamag Transporttechnik since the year 1979.
Not surprisingly, the "T" prefix stands for Thiokol, and the following letter refers to the company division that developed the rocket motor. In this case, "E" refers to the Elkton, MD division and the "M" stands for motor. The most common use of the Star 48 was as the final stage of the Delta II launch vehicles. Other launchers have also incorporated the motor, but with lower frequency.
The AJ-260-2 rocket motor remains in the silo to this day. In 2013, the massive shed structure covering the silo was dismantled and the silo covered with several 33 ton concrete beams. The facility was the subject of documentaries Space-Miami and Aerojet Dade: An Unfinished Journey. An urban exploration visit to the site in 2007 was also featured in the documentary Urban Explorers: Into the Darkness.
Successful completion of the Patriot system (PAC-3) flight test in New Mexico, United States , Ministry of Defense, September 17, 2008 PAC-3 units are deployed in 6 bases near metropolises, including Tokyo, Osaka, Nagoya, Sapporo, Misawa and Okinawa. Japan participates in the co-research and development of four Aegis components with the US: the nose cone, the infrared seeker, the kinetic warhead, and the second-stage rocket motor.
83 mm HEAT round sectioned to show (wooden replica) booster and main charges, copper cone and rocket motor The RL-83 Blindicide is primarily an antitank rocket launcher, but other rockets can be fired. It was produced by Mecar SA of Belgium and was an improved derivative of the M20A1 Bazooka. Its name translates to "armor killer", derived from the French "blindé" (armoured vehicle) and the suffix -cide meaning to kill.
Low-scoring players in the multiplayer version of the game Perfect Dark and GoldenEye 007 are awarded with the designation "mostly harmless". In the 2008 edition of the board game Cosmic Encounter, the human race is given the attribute "Mostly Harmless". In the game Kerbal Space Program, there is an atomic rocket motor with the description "mostly harmless". Another reference is in the book title Mostly Harmless Econometrics.
In aircraft, an ejection seat is a system designed to rescue the pilot or other crew of an aircraft (usually military) in an emergency. In most designs, the seat is propelled out of the aircraft by an explosive charge or rocket motor, carrying the pilot with it. The concept of an ejectable escape capsule has also been tried. Once clear of the aircraft, the ejection seat deploys a parachute.
However, exterior ballistics analysis also deals with the trajectories of rocket-assisted gun-launched projectiles and gun-launched rockets; and rockets that acquire all their trajectory velocity from the interior ballistics of their on-board propulsion system, either a rocket motor or air-breathing engine, both during their boost phase and after motor burnout. External ballistics is also concerned with the free- flight of other projectiles, such as balls, arrows etc.
Spaceport Camden is a proposed spaceport in Camden County, Georgia, near the city of Woodbine. The proposed site tested the largest solid rocket motor ever fired as part of the Apollo Program and Camden County, Georgia was originally considered as a NASA launch site in the 1960s. Spaceport Camden began limited development as a rocket launch facility in early 2014, with its first launch taking place in August 2017, reaching .
They were used by the United States Navy and United States Marine Corps near the end of the war during the battle of Okinawa, and during the Korean War. A problem with the sheer power of the rocket motor causing damage to the firing aircraft was resolved by having the Tiny Tim drop like a bomb, and a lanyard attached to the rocket would snap, causing the rocket to ignite.
This is a sectioned Messerschmidt 163 Rocket Motor Inselberg was born in 1936 in Athens, Greece. Later he attended Whittingehame College in Brighton England. He attended the University of Illinois at Urbana-Champaign (UIUC) receiving a B.Sc. in Aeronautical Engineering. Together with Gary van Sant, and two other students under the guidance of Paul Torda, they founded the University of Illinois Rocket Society in 1953; four years prior to Sputnik.
The missile is stored in a cylindrical transport container. On launch the missile is ejected from the tube by a solid rocket motor. After traveling a safe distance from the operator, the Daicel flight motor ignites and takes the missile to its cruising speed of approximately 200 meters per second. The missile is a thin cylinder with two sets of four pop-up fins positioned along the body of the missile.
Despite the simple looking solution, the solution is verified to be accurate experimentallyDunlap, R., Willouchby, P. G., & Hermsen, R. W. (1974). Flowfield in the combustion chamber of a solid propellant rocket motor. AIAA journal, 12(10), 1440–1442.. The solution is wrong for distances of order z\sim a since boundary layer separation at z=0 is inevitable, i.e., Taylor–Culick profile is correct for z\gg 1.
Employed by the Heylandt Company from 27 February 1928, in December 1929, Riedel was assigned responsibility for the development of rocket motors using liquid propellants, initially in collaboration with Max Valier who had joined the company at that date. Riedel took over full responsibility for the rocket motor development in 1930, after Valier’s untimely death following a rocket motor explosion during a test using paraffin oil (kerosene) as fuel instead of ethyl alcohol. In 1934, research and development of the Heylandt Company was taken over by the Army and amalgamated with the Wernher von Braun Group at the Army Proving Grounds at Kummersdorf, near Berlin, in order to carry out research and development of long-range rocket missiles. In March 1936, von Braun and Walter Riedel began consideration of much larger rockets than the A3 (under development at that time), which was merely a test vehicle and could not carry any payload.
Following a successful mate with two five-segment stacks of solid rocket motor segments, the pathfinder vehicle was moved out to Complex 41 on Saturday, 21 May. The first Titan IV vehicle supported a classified mission. Its launch had been scheduled for 7 June 1989, but the lift-off was pushed to 14 June due to a range timing generator problem and a computer malfunction. The countdown was picked up at 0254Z on 14 June.
These stations have internally mounted launchers (LAU-116/A) that use ejection for launching. The rapidly expanding gases, created by impulse cartridges, actuate ejector pistons and release the missile from the launcher.Patent US 8353237 The missile is propelled to a safe distance before it ignites its rocket motor. Stealth aircraft such as the F-22 use extensible launchers that are pneumatically actuated and are either rail (LAU-141/A) or ejector (LAU-142/A) types.
173, 175. In late 1954, the prototype attained a recorded speed of Mach 1.3 in level flight without rocket assistance, as well as reaching Mach 1.6 when using the rocket motor. According to aviation author John F. Brindley, testing of the Mirage I and prototypes of the rival Trident and Durandal designs had demonstrated the limitations of the light fighter concept, namely limitations on both endurance and equipment/payload capacity.Brindley 1971, p. 175.
Star 48 is a type of solid rocket motor used by many space propulsion and launch vehicle stages. It is used almost exclusively as an upper stage. It was developed primarily by Thiokol Propulsion, and is now manufactured by Orbital ATK, which purchased Thiokol in 2001. A Star 48B stage is also one of the few man-made items sent on escape trajectories out of the Solar System, although it is derelict since its use.
The Graphite-Epoxy Motor (GEM) is a solid rocket motor produced by ATK using epoxy composite casing. GEMs are used as boosters for the Delta II, Delta III, and Delta IV launch vehicles. The use of composite materials allows for booster casings several times lighter than the steel casings of the Castor 4 solid rocket motors they replaced. The first flight of a GEM occurred in 1990 on a Delta II 7925.
Constructed by British Aerospace, it was designed to be operated for seven years and carried 12 Ku band transponders, two of which were set aside as spares. The satellite contained a Mage-2 solid rocket motor to perform orbit circularisation at apogee. ECS-1 was launched by Arianespace, using an Ariane 1 carrier rocket, flight number L06. The launch took place at 11:59:03 UTC on 16 June 1983, from ELA-1 at Kourou.
The propellant particle size distribution has a profound impact on APCP rocket motor performance. Smaller AP and Al particles lead to higher combustion efficiency but also lead to increased linear burn rate. The burn rate is heavily dependent on mean AP particle size as the AP absorbs heat to decompose into a gas before it can oxidize the fuel components. This process may be a rate-limiting step in the overall combustion rate of APCP.
The system comprises three large components: a tow plane, a glider, and a rocket. The tow plane, a conventional small aircraft, carries the glider up to about before releasing the towline and flying back. The glider, carrying its own hybrid or solid rocket motor, will ignite its engine to glide higher that the tow plane's maximum altitude. Following burnout of its rocket, the glider will jettison the third (exclusively rocket powered) stage of the system.
A Delta II solid rocket motor GPS IIR-1 was launched on a Delta II 7925-9.5 rocket, serial number D241, from Launch Complex 17A at the Cape Canaveral Air Force Station. The launch occurred at 16:28:01 GMT (11:28 local time), on January 17, 1997. Thirteen seconds later, the rocket's flight termination system was activated by its onboard computer. This detonated explosive charges aboard the rocket, causing it to explode.
The solution is stored in two cylindrical aluminium tanks strapped to the core solid rocket motor and pressurised with nitrogen. Underneath these two SITVC tanks, Roll Control Thruster (RCT) modules with small bi-propellant (MMH/MON) liquid engine are also attached. On the PSLV-G and PSLV-XL, first stage thrust is augmented by six strap-on solid boosters. Four boosters are ground-lit and the remaining two ignite 25 seconds after launch.
The TE-307-2 Apache rocket motor was developed by Thiokol as an improvement of its Cajun series of rockets; the Apache was similar in appearance to Cajun, but had an improved propellant that allowed for better performance. Combined with a M5 Nike rocket booster for its first stage by Aerolab,Parsch 2004 the Nike-Apache sounding rocket was capable of lifting of instruments to an apogee of .Corliss 1971, p.82.
The FG-02 was a Chinese solid rocket motor burning Polysulfide. It was developed by China Hexi Chemical and Machinery Corporation (also known as the 6th Academy of CASIC) for use in the Long March 1 third stage. It has a total nominal mass of , of which is propellant load. It has an average thrust of with a specific impulse of 254 seconds burning for 38 seconds, with a total impulse of .
Operation Pushover determined how much damage would result from a V-2 toppling or exploding on a carrier deck, using a simulated deck built at White Sands. In late 1949, a fully fueled V-2 was set on a pedestal with four legs, two of which were rigged with explosives to be "blown away just after ignition of the rocket motor." Pushover No. 2 repeated the test with the deck raised several feet.
The National Guard Association of the United States has sent a letter asking for the U.S. Senate to stop the Army's plan to drop the SLAMRAAM program because without it there would be no path to modernize the Guard's AN/TWQ-1 Avenger Battalions. On 22 February 2015, Raytheon announced an Extended Range upgrade to NASAMS-launched AMRAAM, calling it AMRAAM-ER. This combines the AMRAAM seeker with the ESSM rocket motor.
DARE is also actively involved in providing the launch service for the Dutch CanSat project. In particular, DARE develops, produces, tests, and launches the CanSat launchers (CSL). Over the years these launcher have undergone several development iterations, balancing reliability, producibility, and payload capacity. The current CSL Version 7 consists of an all-Aluminium frame and, propelled by a solid rocket motor, can lift about five to six CanSats to an altitude of one kilometer.
He was more impressed with a 1933 regeneratively cooled engine developed by Harry Bull, of Syracuse, NY, and work by Eugene Saenger in Austria. With help from a couple professors, he began his own designs, calculations and experiments at Princeton.Winter, Frank H., "James H. Wyld (1912-1953)", History of Rocketry and Astronautics, AAS, Vol. 39, 2008 In 1936 he developed the concept of a regeneratively cooled liquid rocket motor, which he named M-15.
Israel Aerospace Industries announced in June 2009, that the Arrow 3 patented. exoatmospheric interception method includes a two-stage interceptor, like the Arrow 2, but purely based on hit- to-kill technology. Unlike most kill vehicles, which use liquid or gas propulsion, the new Israeli kill vehicle will be propelled by an ordinary rocket motor equipped with a thrust-vectoring nozzle. It will also be fitted with a gimbaled seeker for hemispheric coverage.
VP401 was later converted into a further prototype, the Hawker P.1072, the principal addition being in the form of an auxiliary rocket engine; configured as such, it became the first British rocket-powered aircraft."Rocket Motor Doubles Power of Jet Aircraft." Popular Mechanics, February 1952, p. 116. After a few flights were made in 1950, the rocket engine blew up during a test and although repaired, the airframe was scrapped soon after.
These projectiles consist of two major components, a warhead filled with 16 pounds of Composition B high explosive (M549) or 15 pounds of TNT high explosive (M549A1), and a solid propellant rocket motor. These components are threaded together so that the outer steel shells of both form a streamlined ogive. A supplementary charge is installed in the deep cavity of the nose. A rotating band encircles the assembled projectile near the base.
Improving the Corporal E involved drastic changes in the rocket motor, airframe, guide vanes and control system. The design was changed to a more easily produced, assembled, and accessible structure. The means of launching was changed from the rocket sitting upon its fins to being held by four arms holding it above the fins which would retract to release it. The first of the redesigned Corporal E missiles was available in May 1949.
The engines used a 3D-printed engine injector, designed with help from NASA's Science, Technology and Mission Directorate (STMD) Flight Opportunities program. This allows the injector to be produced as a single piece of hardware, instead of as individual components. The vehicle was also planned to include an optional third stage powered by a solid rocket motor. This would have allowed the upper stage to boost micro satellites into a higher orbit.
Here the problem is one of a bang-bang control at maximum possible thrust until the singular arc is reached. Then the solution to the singular control provides a lower variable thrust until burnout. At that point bang-bang control provides that the control or thrust go to its minimum value of zero. This solution is the foundation of the boost-sustain rocket motor profile widely used today to maximize missile performance.
One round > impacted the Yankee Extraction System rocket mounted directly behind the > headrest, igniting the rocket. His aircraft was observed to burst into > flames in the center fuselage section, with flames engulfing the cockpit > area. He pulled the extraction handle, jettisoning the canopy. The influx of > fresh air made the fire burn with greater intensity for a few moments, but > since the rocket motor had already burned, the extraction system did not > pull Col.
The rocket motor fires immediately after release in boost mode, accelerating the missile to its cruise speed. Once the missile turns on an approach course to the target, the motor switches to cruise mode, shutting down one of its chambers. The missile's autopilot then flies a course using inertial guidance toward the target. In anti-shipping mode the missile engages its J-band active radar in the final approach to the target.
The components were carried on single-axle trailers apart from the diesel generators that were built on two-axle trailers. The entire system, including the launchers, was readily transportable to new locations with mobility claimed to be similar to that of a heavy anti-aircraft gun system. A parachute recoverable training round, the RSC-57, was developed which was powered by a reduced burn time rocket motor with the recovery parachute replacing the warhead.
Sample payloads for sounding rockets The basic elements of a sounding rocket are a solid-fuel rocket motor and a science payload. Larger, higher altitude rockets have two to three stages to increase efficiency and payload capability. The freefall part of the flight is an elliptic trajectory with vertical major axis allowing the payload to appear to hover near its apogee. The average flight time is less than 30 minutes; usually between five and 20 minutes.
The Star 48 is a type of solid rocket motor developed primarily by Thiokol Propulsion, which was purchased by Orbital ATK in 2001. In 2018, Orbital ATK in turn was acquired by Northrop Grumman. The "48" designation refers to the approximate diameter of the fuel casing in inches; Thiokol had also manufactured other motors such as the Star 37 and Star 30. Internally, Thiokol's designation was TE-M-711 for early versions, and TE-M-799 for later ones.
"GAU-8 Avenger", GlobalSecurity.com The CRV7 had just been introduced into Royal Canadian Air Force service when it was entered as a part of a general competition in France. One part of the competition required the contestants to hit a tower with unarmed rockets. The Canadian pilot hit it on his first try, but aimed as if firing the much lower- powered Mk 40 and was therefore close enough that the rocket motor was still firing.
Waxwing apogee kick motor. An apogee kick motor (AKM) is a rocket motor that is regularly employed on artificial satellites to provide the final impulse to change the trajectory from the transfer orbit into its final (most commonly circular) orbit. For a satellite launched from the Earth, the rocket firing is done at the highest point of the transfer orbit, known as the apogee. An apogee kick motor is used, for example, for satellites launched into a geostationary orbit.
The Network Centric Airborne Defense Element (NCADE) is an anti-ballistic missile system being developed by Raytheon for the Missile Defense Agency. On Sept. 18, 2008 Raytheon announced it had been awarded a $10 million contract to continue NCADE research and development. The NCADE system is a boost phase interceptor based heavily on the AIM-120 AMRAAM, with the AMRAAM fragmentation warhead replaced by a hit-to-kill vehicle powered by a hydroxylammonium nitrate monopropellant rocket motor from Aerojet.
The Burner and Burner 2 rocket stages have been used as upper stages of launch vehicles such as the Thor-Burner and Delta since 1965. The currently available Burner 2 is powered by a Star 37 solid rocket motor. Thor Altair and Thor Burner were mainly used for US military meteorological programs (DMSP), although they also launched technological satellites. In addition to use on Delta family rockets, Burner 2 stages have been used on both Atlas and Titan rockets.
A rocket assisted projectile (RAP) is a cannon, howitzer, mortar, or recoilless rifle round incorporating a rocket motor for independent propulsion. This grants the projectile both greater speed and range than an ordinary shell, which is propelled only by the ballistic force of the gun's exploding charge. Some forms of rocket assisted projectiles can be outfitted with a laser-guide for greater accuracy. The German Sturmtiger (1944) used a 380 mm Rocket Propelled Round as its main projectile.
NASA plans to test the feasibility of releasing a small unpowered rocket from the one-third scale glider, followed by mounting a small rocket motor on the glider to test the feasibility of a rocket-assisted glider design. Further plans involve the construction of a full-scale platform. The project has obtained funding for NASA's 2015 financial year through the Game Changing Development program following the first successful test flight of the one-third scale glider.
Once all fuel had been exhausted, the rocket motor was intended to slip backwards from its attachment points and drop away from the aircraft. However, testing revealed that this would sometimes fail to detach or cause minor damage to the aircraft's underside when doing so.Moore 2008, pp. 73-74. Despite such difficulties being encountered, the F-100's ZELL system was considered to be feasible, but the idea of its deployment had become less attractive as time went on.
Various ejection seats In aircraft, an ejection seat or ejector seat is a system designed to rescue the pilot or other crew of an aircraft (usually military) in an emergency. In most designs, the seat is propelled out of the aircraft by an explosive charge or rocket motor, carrying the pilot with it. The concept of an ejectable escape crew capsule has also been tried. Once clear of the aircraft, the ejection seat deploys a parachute.
Tier One uses a hybrid rocket motor supplied by SpaceDev, with solid hydroxyl-terminated polybutadiene (HTPB, or rubber) fuel and liquid nitrous oxide oxidizer. It generates of thrust, and can burn for about . The physical layout of the engine is novel. The oxidizer tank is a primary structural component, and is the only part of the engine that is structurally connected to the spacecraft: the tank is in fact an integral part of the spacecraft fuselage.
The Mesquito is an American sounding rocket vehicle developed for the NASA Sounding Rocket Program on Wallops Island, Virginia. The Mesquito was developed to provide rocket-borne measurements of the mesospheric region of the upper atmosphere. An area of great science interest is in the 82–95 km region, where the conventional understanding of atmospherics physics is being challenged. The Mesquito is a two-stage sounding rocket using a solid propellant rocket motor as the first-stage propulsion device.
There are two MICA variants; MICA RF has an active radar homing seeker and MICA IR has an imaging infra-red homing seeker. Both seekers are designed to filter out counter-measures such as chaff and decoy flares. A thrust vector control unit fitted to the rocket motor increases the missile's agility. The missile is capable of lock-on after launch (LOAL) which means it is capable of engaging targets outside its seeker's at-launch acquisition range.
Once ejected from the launcher, the projectile coasts a safe distance and then the rocket motor is ignited, boosting it to its maximum speed, after which it coasts until impact. The gunner carries at least two rounds, while the assistant grenadier carries an additional three rounds. The ergonomic design of the controls, such as handles, launcher, barrel shape and optical sight, is a predefined standard. All controls are easy to handle in all shooting positions (lying, kneeling or standing).
Brown himself piloted RAE's Komet VF241 on a number of occasions, the rocket motor being replaced with test instrumentation. When interviewed for a 1990s television programme, Brown said he had flown five tailless aircraft (which did not include the pair of American Northrop X-4s) in his career (including the British de Havilland DH 108). Referring to the Komet, he said "this is the only one that had good flight characteristics"; he called the other four "killers".
When the projectile is fired, the propellant gases ignite the delay which burns for approximately 7 seconds and then sets off the rocket igniter to initiate the rocket motor, which burns for approximately three seconds. This additional thrust augments the velocity and consequently, the range of the projectile. If a PD or ET is used, the fuze detonates the supplementary charge and the supplementary charge detonates the warhead filler either on impact or the preset time.
This leaves little time for reaction and stimulated the design of close-in weapon systems (CIWS). Its rocket motor, which is fuelled by solid propellant, gives the Exocet a maximum range of . It was replaced on the Block 3 MM40 ship-launched version of the missile with a solid-propellant booster and a turbojet sustainer motor which extends the range of the missile to more than . The submarine-launched version places the missile inside a launch capsule.
This missile is one of a kind, proving many new technologies for the first time, and represents a significant leap in India's missile technology. The missile is lighter in weight and uses a two-stage rocket engine powered by solid propellant. The Composite Rocket Motor which has been used for the first time has given excellent performance. The missile system is equipped with modern and compact avionics with redundancy to provide a high level of reliability.
The formal goal was development of a sounding rocket. Malina and five associates (including Jack Parsons and Hsue-Shen Tsien) became known at Caltech as the "Suicide Squad" because of their dangerous experiments (and failures) when testing rocket motor designs. Malina's group was forced to move their operations away from the main Caltech campus into the more remote Arroyo Seco. This site and the research Malina was conducting would later become the Jet Propulsion Laboratory (JPL).
While the ordinary GTR-18A has a simple, model rocket type motor, an improved 'Dual Thrust Smokey Sam' tested in the early 2000s featured a modified rocket motor, providing a 1.5 second boost period, followed by a lower-thrust sustainer burn with burnout occurring at 7.1 seconds after launch.Taylor 2006 Receiving the altered designation DGTR-18A in the early 1990s, the Smokey Sam remains in production and operational service, being extensively used by the U.S. military.
The Hornet was planned as a battlefield missile for use against armored vehicles which would mount an electro-optical guidance system. The first test firing of the prototype XAGM-64A occurred in December 1964. It was powered by a fast-burning solid rocket motor. The electro-optical guidance system provided a live TV image to the cockpit; the operator would lock the missile onto the desired target before launch and the missile would home in on it automatically.
The Delta B, or Thor-Delta B was an American expendable launch system used for nine orbital launches between 1962 and 1964. A derivative of the Thor-Delta, it was a member of the Delta family of rockets. The first stage was a Thor missile in the DM-21 configuration, and the second stage was the Delta D, which was derived from the earlier Delta. An Altair solid rocket motor was used as a third stage.
The Delta A, or Thor-Delta A was an American expendable launch system used to launch two Explorer spacecraft in October 1962. A derivative of the Thor- Delta, it was a member of the Delta family of rockets. The first stage was a Thor missile in the DM-21 configuration, and the second stage was the Delta A, an uprated version of the original Delta. An Altair solid rocket motor was used as a third stage.
The high heat of sublimation of carbon prevented these rocket motors from operating efficiently, as it resulted in a negligible burning rate. AMROC test of thrust hybrid rocket motor in 1994 at Stennis Space Center. In the 1940s, the California Pacific Rocket Society used LOX in combination with several different fuel types, including wood, wax, and rubber. The most successful of these tests was with the rubber fuel, which is still the dominant fuel in use today.
Originally known as CMM (Common Modular Missile), the JCM (Joint Common Missile) was to be also a replacement for the BGM-71 TOW, but this requirement was later dropped. The program began in 2002 and a formal RFP (Request For Proposals) was issued to the industry in late 2003. Competitors included Boeing teamed with Northrop Grumman, Lockheed Martin and Raytheon. During late 2003 and early 2004, the competitors tested components (rocket motor, guidance, fuzing, system interface, etc.) of their JCM proposals.
The Teal could be launched at any altitude of up to ; speed at launch was between and . Following launch a dual-thrust solid fuel rocket motor ignited; thrust was for the first four seconds of powered flight, followed by for approximately 500 seconds propulsive time. Control was provided by a three-axis autopilot; radar reflectors and infrared flares provided an assist in tracking the drone, and at the end of nine minutes' flight time a self-destruct device would be activated.
A beyond-visual-range missile (BVR) is an air-to-air missile (BVRAAM) that is capable of engaging at ranges of or beyond. This range has been achieved using dual pulse rocket motors or booster rocket motor and ramjet sustainer motor. In addition to the range capability, the missile must also be capable of tracking its target at this range or of acquiring the target in flight. Systems in which a mid-course correction is transmitted to the missile have been used.
Mélanie is a French solid rocket motor, 16 cm in diameter. The first version was used as first stage of the Monica rocket.Les débuts de la recherche spatiale française IFHE,, Institut français d'histoire de l'espace - 2007 "Caractéristiques des fusées météo à propulsion solide et propulsion hybride.... Mélanie" It had a thrust increasing from 6.2 kN (Monica I) to 8.2 kN (Monica V) and a burn time of about five seconds. Melanie was later used in several ATEF and ONERA rockets.
With the end of the cold war in the 1990s the U.S. scaled back its development of new nuclear weapons. The Midgetman program was therefore cancelled in January 1992. The legacy of its lighter graphite-wound solid rocket motor technology lived on in the GEM side boosters used on the Delta rockets, and the Orion stages of the Pegasus air-launched rocket. The Soviet equivalent of this missile was the RSS-40 Kuryer which was tested but cancelled in October 1991.
Today the site comprises a Motor Assembly building, a Launch Control Center, a Meteorological Sounding System building, a Rocket Motor Storage hangar and a dormitory. The site has launched numerous solid-fuel rockets from the RX family (Roket Eksperimental), in particular the RX-250-LPN. Newer developments focus on building multi-stage rockets from individual RX elements, under the moniker RPS for Roket Pengorbit Satelit (literally "Satellite Orbiting Rocket"). The agency's goal is to reach orbit with indigenous rockets and satellites.
Rather than use rubber-based HTPB in the solid portion of the hybrid rocket motor—which had experienced serious engine stability issues on firings longer than approximately 20 seconds with the first-generation engine—the Virgin Galactic-developed SS2 hybrid rocket engine would now use thermoplastic polyamide (i.e., nylon) as the solid fuel component of the propellant. The plastic fuel was projected to have better performance (by several unspecified measures) and was expected to allow SpaceShipTwo to make flights to a higher altitude.
The original version of the missile, called Block 0, was based on the AIM-9 Sidewinder air-to-air missile, whose rocket motor, fuze, and warhead were used. Block 0 missiles were designed to initially home in on radiation emitted from a target (such as the active radar of an incoming antiship missile), switching to an infrared seeker derived from that of the FIM-92 Stinger missile for terminal guidance. In test firings, the Block 0 missiles achieved hit rates of over 95%.
Munitions used by the B-300 are propelled by a solid rocket motor, and can be equipped with one of two warhead variants. The first, high explosive anti-tank round, provides specialized support for anti-tank missions. The second, known as a high explosive follow- through round, is designed for use against fortified targets or enemy units behind cover. A primary charge punches a hole through the protective structure, allowing a secondary anti-personnel charge to pass through and detonate within the building.
In 2014 Quest Aerospace was purchased by RCS rocket motor components (Aerotech Consumer Aerospace) and was moved from Pagosa Springs, CO to Cedar City, Utah. Quest's products include model rockets powered by standard 18 mm motors as well as smaller rockets powered by Micro Maxx motors. The company produces both 18 mm motors and Micro Maxx motors for use in its model rocket kits. Powered by compressed black powder motors, some of these rockets can achieve altitudes of over 2000 feet.
Part of the Nike Ajax development program designed a new solid fuel rocket motor used for the missile's booster. This had originally been designed for the US Navy's missiles, and was enlarged for the Nike efforts. The rocket was so useful that it found numerous applications outside the military world as the Ajax missiles were decommissioned in the 1960s. Many sounding rockets used the booster as their first or second stage, and many of those used "Nike" in their name.
Today the Indian Space research programme is recognised as one of the most successful programmes in the world. Prakash was instrumental in taking a far-sighted decision to go for new generation Maraging Steel against 15 CDV-6 for construction of rocket motor casings for satellite launch vehicles. Indigenously produced Maraging steel 250 has been performing flawlessly and has emerged as a workhorse material for all Polar Satellite Launch Vehicle (PSLV) and Geosynchronous Satellite Launch Vehicle (GSLV) used thus far.
After the failure of the rocket motor, further development of the first two prototypes ended. To protect the pilot if the aircraft was damaged in combat the XP-79 was built using a welded magnesium alloy monocoque structure with a skin thickness at the trailing edge and a thickness at the leading edge. The pilot controlled the XP-79 through a tiller bar and rudders mounted below; intakes mounted at the wingtips supplied air for the unusual bellows-boosted split ailerons.
LAPAN manages a launch site called Stasiun Peluncuran Roket (literally "Rocket Launching Station"), located at Pameungpeuk Beach in the Garut Regency on West Java (). The facility was built from 1963 through cooperation between Indonesia and Japan, as the station was designed by Hideo Itokawa with the aim to support high atmospheric research using Kappa-8 rockets. This installation comprises a Motor Assembly building, a Launch Control Center, a Meteorological Sounding System building, a Rocket Motor Storage hangar and a dormitory.
In 1972, Space Data completed the development of the Viper IIIA solid propellant rocket motor. This motor followed the design of the Super Loki nearly identically and provided apogees of ~120 km for the ROBINSphere. This higher apogee allowed for measuring the wind and atmospheric vertical profiles through the 110–95 km region that were unobtainable from the Super Loki boosted ROBINSphere. The ROBINSphere is a calibrated weight inflatable 1 meter diameter radar reflecting balloon, weighing in at about 150 grams.
The prime contractor for the manufacture of the SRB motor segments was ATK Launch Systems (formerly Morton Thiokol Inc.) Wasatch Division based in Magna, Utah. United Space Boosters Inc. (USBI), a division of Pratt and Whitney, under United Technologies, was the original SRB prime contractor for SRB assembly, checkout and refurbishment for all non-solid- rocket-motor components and for SRB integration. They were the longest running prime contractor for the Space Shuttle that was part of the original launch team.
The Panzerschreck was larger and heavier than its American counterpart - the Panzerschreck had an 88 mm calibre, compared to the 60 mm calibre of the bazooka - which meant that it could penetrate thicker armor, but also produced more smoke when firing. Calibre 88 mm was selected as the existing RPzB. Gr. 4312 for 8.8 cm Raketenwerfer 43 was reused for Panzerschreck. Warhead and fuzing was carried over, but the rocket motor's housing needed lengthening from to to accommodate the longer rocket motor.
Soft launching is the method of launching a missile (such as an anti-tank guided missile) in such a way that the rocket motor ignites outside of the launch tube; the missile is ejected non-explosively. The objective is to minimize the risk of damage to the launcher by maintaining a safe distance. Contrast this with hard launching. A similar concept called cold launch was pioneered by the Soviet Union for application in vertical launch system clusters on board ships.
After the development of Astra Mark 1, three new variants are planned for future. Astra IR close combat missile with imaging infrared homing for shorter range up to . Astra Mark 2 with larger engagement envelope and a range of equivalent to AIM-120D while propulsion systems under consideration includes liquid-fuel ramjet, solid-fuel ramjet and dual pulse solid rocket motor. Astra Mark 3 will use newly developed solid fuel ducted ramjet (SFDR) technology with a maximum range of equivalent to Meteor missile.
The 100 mm round resembles a normal 100 mm anti-tank round, and is loaded and fired in the same fashion. The round uses a reduced explosive charge to launch the projectile out of the barrel of the gun at around 400 to 500 m/s. After leaving the gun barrel, a small cover falls away from the window on the rear of the missile. The rocket motor ignites 1.5 seconds after firing the missile, and it burns for 6 seconds.
This uses a double-hulled rocket nozzle that allows the rocket fuel to circulate as a coolant. A version of this rocket motor was tested by the American Rocket Society on December 10, 1938 at New Rochelle, New York. The design produced a thrust of 90 pounds force (400 N) that lasted for 13 seconds, and the steel chamber and nozzle were successfully protected by the design. This cooling design became the basis of all modern liquid-propellant rocket motors.
A third engine, a Jaguar supercharged V-8 is used as an auxiliary power unit to drive the oxidiser pump for the rocket, although this will be replaced by an electric motor. The cockpit exteriorInitially Bloodhound SSC was going to use a custom hybrid rocket motor being designed by Daniel Jubb. The rocket was successfully tested at Newquay Airport in 2012. However, constraints on cost, time and test facilities led to a decision to instead use a rocket designed by Norwegian company Nammo.
Up until this point the business had been run out of an old Nissen hut in a back corner of the Summerfield MOD solid fuel rocket motor factory with only 15 employees. Klark Teknik PLC was formed in 1985. In the following year Klark Teknik acquired the Hounslow-based studio mixing company DDA and subsequently moved the manufacturing to Kidderminster. The company further diversified by developing active studio monitors under the brand “Klark Acoustic”, winning a Queen's Award for export.
The Biosatellite 1 was the first series Biosatellite satellites. It was inserted in an initial orbit of 296 km perigee, 309 km apogee and 33.5 degrees of orbital inclination, with a period 90.5 minutes. The Biosatellite 1 was carrying several specimens for the study of the effects of the space environment on biological processes. When the capsule was returning to land, it separated from the vehicle properly, but its rocket motor did not work, leaving it stranded in a slowly decaying orbit.
Averaging 96,650 pounds thrust, the Algol 1D was the largest solid rocket motor flying in non-military space programs. Test hardware on May's successful Apollo test flight included: an unmanned instrumented command module, service module, launch escape system and the Little Joe II launch system. Algol engine used on Little Joe II Thrust: 465 kN each Length: 9.1 m Diameter: 1 m Weight full: 10,180 kg Weight empty: 1,900 kg Fuel: solid Burn time: 40 s Status: Retired 1966. Gross mass: .
Many establishments were formed, merged or changed their names over time to meet the needs of the UK Government at the time. These changes also involved the opening of new sites, operating across multiple sites, change of site location; and closing of sites. For example, the Explosives Research and Development Establishment (ERDE), merged with the Rocket Propulsion Establishment and became the Propellants, Explosives and Rocket Motor Establishment (PERME). PERME became part of the Royal Armament Research and Development Establishment (RARDE).
When the weapon is fired, the rotating band engages the barrel rifling to impart spin to the projectile for stability in flight. The obturator and rotating band form a seal to prevent leakage of gas pressure past the projectile. The burning propellant accelerates the projectile through the barrel at high velocity. Extended range is obtained through rocket assist; the rocket cap is removed prior to placing the projectile in the chamber, exposing the pyrotechnic delay assembly in the base of the rocket motor.
The production XM51 version had smaller rectangular fins, too small to stabilise the rocket, and was stabilised from launch by a unique "spin-on-straight-rail" system. The XM51 Little John was delivered to the field in November 1961 and remained in the regular Army's weapons inventory until August 1969. It was a spin-stabilized field artillery rocket that followed a ballistic trajectory to ground targets. The rocket XM51 consisted of a warhead, a rocket motor assembly, and an igniter assembly.
A GTR-18 is launched at the Crow Valley Range Complex, Philippines, 1984. The complete launch system, known as the Smokey Sam Simulator, includes single- and four-rail launching pads, an AN/VPQ-1 radar set, and the GTR-18A rockets themselves, making up the SMU-124/E system as a whole. When launched, the GTR-18's rocket motor produces a distinctive white plume, providing a realistic simulation of the launch of a surface-to- air missile.Kitfield 1995, p.166.
An anti-radar variant of the missile designated KSR-11 was also produced, being externally almost identical to the KSR-2. The KSR-11 was intended to home in on and destroy air-defence radar and ECM facilities. The missile used a 2PRG-11 passive radar seeker. A target drone version of the missile designated KRM-2 (MV-1) also entered service in 1966, with a different rocket motor, a range of 376 kilometers and a level flight endurance of 433 seconds.
Nitrous oxide may be used as an oxidizer in a rocket motor. This is advantageous over other oxidisers in that it is much less toxic, and due to its stability at room temperature is also easier to store and relatively safe to carry on a flight. As a secondary benefit, it may be decomposed readily to form breathing air. Its high density and low storage pressure (when maintained at low temperature) enable it to be highly competitive with stored high-pressure gas systems.
Hydra 70 rockets on an AH-1 Cobra helicopter The family of Hydra 70 (70 mm) 2.75 inch rockets perform a variety of functions. The war reserve unitary and cargo warheads are used for anti-materiel, anti-personnel, and suppression missions. The Hydra 70 family of folding-fin aerial rockets also includes smoke screening, illumination, and training warheads. Hydra 70 rockets are known mainly by either their warhead type or by the rocket motor designation, Mk 66 in US military service.
Engineering challenges include various types of combustion instabilities. Although the proposed motor was test fired in 2013, the Peregrine program eventually switched to a standard solid rocket for its 2016 debut. The University of Tennessee Knoxville has carried out hybrid rocket research since 1999, working in collaboration with NASA Marshall Space Flight Center and private industry. This work has included the integration of a water-cooled calorimeter nozzle, one of the first 3D-printed, hot section components successfully used in a rocket motor.
The entire space vehicle itself can be spun up to stabilize the orientation of a single vehicle axis. This method is widely used to stabilize the final stage of a launch vehicle. The entire spacecraft and an attached solid rocket motor are spun up about the rocket's thrust axis, on a "spin table" oriented by the attitude control system of the lower stage on which the spin table is mounted. When final orbit is achieved, the satellite may be de-spun by various means, or left spinning.
By modern standards the Seaslug is a huge missile with one sustainer rocket motor and 4 disposable boosters. The missile was a so-called 'beam rider'. It was launched from a huge rail launcher in the stern and boosted into the guidance beam from the fire direction radar which pointed at the target, a high altitude supersonic attack aircraft. Once in the beam the missile would fly at supersonic speed to the target where a proximity fuze would detect the target and detonate the continuous rod warhead.
In an emergency, the rocket engine could be jettisoned at low flight speeds. The rocket fuel (TG-02) was very hazardous and highly toxic, requiring special buildings for maintenance to be built in Buochs and Payerne and personnel involved in its handling to wear special protective suits; accordingly, the rocket motor was not used often. SEPR at the Flieger-Flab-Museum In 1967, the Mirage IIIS entered operational service with the Swiss Air Force; the Mirage IIIRS followed two years later.Brindley 1971, p. 190.
Following trials by the Royal Air Force of rocket-propelled, air-launched weapons for anti-submarine warfare during 1942, the United States Navy launched a high-priority project during the summer of 1943 for the development of an anti-submarine rocket of its own.Parsch 2004 The resulting rocket was a simple design with four tail fins for stabilization at the rear, powered by a rocket motor that had been under development by Caltech since 1943.von Braun and Ordway 1975, p.98. The warhead contained no explosive.
Rocket engines are sometimes used to boost gliders and sailplanes, the earliest being the 1950s model rocket motor called the Jetex engine. This uses solid fuel pellets, ignited by a wick fuse; the casing is reusable. These days, flyers can also mount single-use model rocket engines to provide a short (less than 10 second) burst of power. In some countries, government regulations and restrictions initially rendered rocket-propulsion unpopular, even for gliders; now, though, their use is expanding, particularly in scale model rocketry.
Antares offers three optional third stages: the Bi-Propellant Third Stage (BTS), a Star 48-based third stage and an Orion 38 motor. BTS is derived from Orbital Sciences' GEOStar spacecraft bus and uses nitrogen tetroxide and hydrazine for propellant; it is intended to precisely place payloads into their final orbits. The Star 48-based stage uses a Star 48BV solid rocket motor and would be used for higher energy orbits. The Orion 38 is used on the Minotaur and Pegasus rockets as an upper stage.
Advanced Precision Kill Weapon System II (APKWS II) Goes to War - Defensemedianetwork.com, 9 July 2012 Maximum range is constrained by use of the existing Hydra 70 motor, but since the seeker can see as far as , a more powerful motor could extend range while retaining accuracy;BAE Conducts First APKWS Flight Test on Aussie Helo; U.S. Army Contract Expected Soon - News.USNI.org, 27 April 2015 Nammo is working on a modified rocket motor that can extend range to .New rocket launcher for combat vehicles makes Middle East debut.
The drag is reduced by a gas generator located on the base of the projectile. Once ignited, the gas generator bleeds hot gas into the projectiles wake which causes the flow of air at the base to be less turbulent. The decrease in turbulence, reduces base drag, which typically accounts for 50 percent of total drag. The amount of thrust produced by the base burner unit is negligible and does not serve the same function as the rocket motor on a rocket assisted projectile (RAP).
The project was founded in the summer of 2006, with the specific goal of launching a rocket into space for less than GBP£1000.CU Spaceflight Home page As of November, 2007, CU Spaceflight has launched five uncrewed high-altitude balloons, of which two were not successful:CU Spaceflight News page Nova 2 was blown into the North Sea and Nova 5 failed to ignite the Martlet 1 solid rocket motor, but landed in a reusable state. CU Spaceflight is a participant of the UK High Altitude Society.
Having completed the programme of experiments, von Braun was interested in evaluating an aircraft with a rocket motor propulsion system. For this he needed an aircraft and support team. Initially the highest levels at the Army High Command and the Reich Air Ministry (RLM) were opposed to such "fantasies", as they called them. Many people, technicians and academic experts in positions of influence in aeronautics, maintained that an aircraft driven by a tail thrust would experience a change in the centre of gravity and flip over.
Thiokol was the sole manufacturer of the reusable Solid Rocket Motor used to launch the NASA Space Shuttle, which is being adapted for NASA's Space Launch System. Also in 2001, ATK entered the sporting and law enforcement ammunition market with the acquisition of the ammunition businesses of Blount International. This acquisition made ATK the nation's largest manufacturer of ammunition. In 2009, ATK acquired Eagle Industries and in 2010 ATK acquired Blackhawk Industries Products Group Unlimited, LLC, diversifying into the security and law enforcement market.
Category: micro-satellites orbital launch vehicle, similar to Lambda from Japan, but with lighter modern materials and modern avionics. Launch unguided at a 70-degree angle of inclination with a four-stage solid rocket motor launcher. Retrieved at March 29, 2011 Diameter: 420 mm Length: 6200 mm Lift-off mass: 1000 kg. Propellant: solid composite, firing time 13 seconds Thrust: 9.6 tons Flight duration: 205 seconds Maximum velocity: mach 4.5 Range: 101 km, 53000 m altitude Payload: diagnostic, GPS, altimeter, gyro, 3-axis accelerometer, processor and battery.
The rocket engine nozzles were slightly offset to rotate the missile - this increased accuracy by evening out the effect of any slight asymmetry in thrust. This configuration drastically limited both range and flight duration, but was used because of fears that ionised particles in the hot, rocket motor exhaust stream would interfere with the guidance radar signals; further development showed the fears were unfounded. Steering was accomplished by four rudders in a cruciform configuration. These were moved by four pairs of pneumatic servos, operated by solenoid valves.
Its centrebody houses the combustion chamber (much like the Astrium design mentioned below) allowing for a reduction in length, beyond that of the improved contouring. Wickman Spacecraft & Propulsion Company have developed and static-tested a solid motor in conjunction with an E-D. The University of Bristol, UK, has recently successfully tested gaseous hydrogen/air propellants as part of the STERN project. They are also involved in developing knowledge of the in-flight behaviour of the E-D nozzle using a hybrid rocket motor.
The rockets were developed for the interception of small, aggressively maneuvering targets. Weighing , the 9M330 missile is long, carries a warhead and has a peak speed of around Mach 2.8. Using command guidance and radar controlled proximity fuzes, the missiles can maneuver at up to 30 g and engage targets flying at up to Mach 2. Cold launched, the missiles are propelled out of the vehicle before the solid fuel rocket motor fires and the gas-dynamic maneuvering system turns them toward their target.
Two ships were eventually selected and were reactivated by VSE Corporation and transferred to Taiwan on 9 March 2017. These ships would replace aging Chiyang class (US ex-Knox-class frigate) vessels that joined the ROC Navy more than 20 years ago. After the US stopped supporting the SM-1 and their associated launch system support was taken up by NCSIST which also implemented an upgrade program for the missiles. Upgrades to the SM-1 include a better rocket motor and an active seeker.
This means they can be manhandled safely and maintained with the rocket motor installed. However, the lower specific impulse of these engines, combined with the requirement for longer range, demanded a much larger fuselage to store the required fuel. Hercules, still known officially as Nike B at this point,It is not clear in existing sources why the design was named "Nike B" and not "Nike IB", given that the Nike Zeus was known as "Nike II". grew to become a much larger design.
The first stage was a General Electric X-405 liquid- fueled engine (designated XLR50-GE-2 by the Navy), derived from the engine of the RTV-N-12a Viking. The second stage was the Aerojet General AJ10-37 (XLR52-AJ-2) liquid-fueled engine, a variant of the engine in the RTV-N-10 Aerobee. Finally, the third stage was a solid-propellant rocket motor. All three-stage Vanguard flights except the last one used a motor built by the Grand Central Rocket Company.
The projectile is launched from the gun by a small charge, which gives it an initial velocity of between 250 and 400 metres per second. The launch charge also imparts spin to the projectile by a series of offset holes. Once the projectile has traveled approximately 20 meters (65.6 feet) from the launcher, a rocket motor in its base ignites. For the PG-9 projectile, this takes it to a velocity of 700 metres per second (2,297 feet per second) before the motor burns out.
In a MIRV, the main rocket motor (or booster) pushes a "bus" (see illustration) into a free-flight suborbital ballistic flight path. After the boost phase the bus maneuvers using small on-board rocket motors and a computerised inertial guidance system. It takes up a ballistic trajectory that will deliver a reentry vehicle containing a warhead to a target, and then releases a warhead on that trajectory. It then maneuvers to a different trajectory, releasing another warhead, and repeats the process for all warheads.
Brimstone 2 was further updated with an insensitive munition compliant rocket motor and warhead in July 2016. It has successfully integrated onto the Tornado GR4 and has trialed on the Eurofighter Typhoon and AH-64E Apache. Nevertheless, this is only an Initial Operating Capability (IOC) for Brimstone 2 on the Tornado GR4 and it is still some 43 months beyond the originally projected October 2012 in- service date. In July 2016, MBDA further proposed a new variant of Brimstone 2 for the AH-64E Apache.
Spike was designed by the U.S. Navy, with assistance from DRS Technologies, and is proclaimed to be "the world's smallest guided missile." Initially made to be carried by U.S. Marines, with three missiles and the launcher able to fit in a standard backpack, it weighs , is long, and in diameter. The warhead weighs about 1 lb (450 gr) and employs the Explosively Formed Projectile (EFP) effect, made to penetrate before detonating. It is powered by a small rocket motor that gives it a range exceeding .
The missile would use an inertial guidance system with terminal guidance provided by active radar homing - a mode of flight that would later be employed in the AIM-120 AMRAAM. An infrared terminal homing seeker was also planned, which would allow the missile to engage without any emissions which would alert the target. The GD/Westinghouse design was even smaller, with a multiple-pulse pure solid rocket motor. It also had an inertial guidance system, but midcourse updating was provided via a dual-band semi-active radar.
Towards the end of the coast period, the third stage was spun up to a rate of 3 hertz (180 rpm) by means of six Imp rockets. Five seconds later, the third stage separated, and following ten more seconds of coasting, it ignited. The third stage was a Waxwing solid rocket motor, which burned for 55 seconds. Just over a minute after the third stage had burned out, the payload was released, and gas generators were used to push the spacecraft and spent upper stage apart.
K-15 was to consist of an "interceptor 250" (later designated La-250) carrying "Type 275" guided missiles. La-250 had to be able to intercept targets flying at , Mach 1.18) at up to from the airbase. Initial guidance was to be from Vozdukh-1 ground control with terminal onboard radar guidance for the last and automatic missile firing by the fire control system when in range. Missile "275" was projected to weigh and, powered by a liquid fuel rocket motor, its top speed was to exceed .
Some materials fail after repeated bending, even at low loads, but careful material selection and bearing design can make flexure bearing life indefinite. ;Short-life bearings Although long bearing life is often desirable, it is sometimes not necessary. describes a bearing for a rocket motor oxygen pump that gave several hours life, far in excess of the several tens of minutes life needed. Composite bearings Depending on the customized specifications (backing material and PTFE compounds), composite bearings can operate up to 30 years without maintenance.
Korolev teamed up with propulsion engineer Valentin Glushko, and together they excelled in the rocket industry, pushing the Soviet Union ahead of the United States in the space race. Instead of pursuing the RP-218, in 1935, Korolev and RN II began developing the SK-9, a simple wooden two-seat glider which was to be used for testing rocket engines.van Pelt, p. 121 The rear seat was replaced with tanks holding kerosene and nitric acid, and the OR-2 rocket motor was installed in the fuselage.
The fairly large missiles have an effective range of 4–24 km (2.5–15 miles) and an effective altitude of 50–14,000 m (164–45,931 ft). The missile weighs 599 kg (1,321 lb) and the warhead weighs 56 kg (123 lb). Top missile speed is approx. Mach 2.8. The combined propulsion system 9D16K included solid fuel rocket motor which, when burned out, forms the combustion chamber for a ramjet in a pioneering design putting this missile far ahead of its contemporaries in terms of propulsion.
StarTram is a proposal to launch vehicles directly to space by accelerating them with a mass driver. Vehicles would float by maglev repulsion between superconductive magnets on the vehicle and the aluminum tunnel walls while they were accelerated by AC magnetic drive from aluminum coils. The power required would probably be provided by superconductive energy storage units distributed along the tunnel. Vehicles could coast up to low or even geosynchronous orbital height; then a small rocket motor burn would be required to circularize the orbit.
An Altair solid rocket motor was used as a third stage. The basic design of the original Vanguard upper stages, featuring a pressure-fed nitric acid/UDMH, regeneratively cooled engine, was kept in place, but with an improved AJ10-118 engine. More significantly, the Delta stage featured cold gas attitude control jets allowing it to be stabilized in orbit for restart and more precise burns. The Thor-Delta was the first rocket to use the combination of a Thor missile and a Delta upper stage.
The tank is then pressurized with helium or nitrogen, which pushes the fuel out to the motors. A pipe leads from the tank to a poppet valve, and then to the decomposition chamber of the rocket motor. Typically, a satellite will have not just one motor, but two to twelve, each with its own valve. The attitude control rocket motors for satellites and space probes are often very small, or so in diameter, and mounted in groups that point in four directions (within a plane).
Following a series of rocket engine tests, Virgin announced in October 2015 that they would be changing the rocket motor back to hydroxyl-terminated polybutadiene (HTPB), with a similar formulation as they used earlier in the development program before switching to a nylon- based fuel grain. They will use HTPB to power the SpaceShipTwo when it resumes flight following the loss of the initial SS2 test vehicle in October 2014. Full qualification tests remain to be completed.SpaceShipTwo Bounces Back to Rubber Fuel, SpaceNews, 14 October 2015, accessed 26 November 2015.
According to Aviation Week, the shuttle initially entered a x orbit at an inclination of 28.45° to the equator. It then executed three OMS (orbital maneuvering system) burns, the last on orbit #4. The first of these circularized the orbit at . The first classified payload was code-named USA-67,NASA Space Data Center: NSSDC ID: 1990-097B USA-67 ELINT Program which was deployed from Atlantis' cargo bay on the 7th orbit and ignited its rocket motor at the ascending node of the 8th orbit to place it in a geo-synchronous transfer orbit.
The primary fire control sensor for the naval Barak-8/LRSAM will be the ELTA MF-STAR Naval AESA radar which Israel claims to be superior to many existing systems worldwide. The dual pulse rocket motor for the SAM was developed by DRDO, and the prototypes were supplied to IAI for integration with IAI systems to develop the complete missile. The other variant of the LRSAM will be fielded by the Indian Air Force. Along with the Akash SAM, the LRSAM fills a longer range requirement and both types will complement each other.
The G-load is more indicative of the strength of the cell as the missile does not have a narrow turning radius. To achieve a turning radius that would create a 50-G load would require a sophisticated digital autopilot and would only be possible when the rocket motor is burning. The acquisition target may be in standalone mode or with the missile "appointed" by the radar, HUD or crosshairs on the helmet (which means some off-boresight capacity). Radar acquisition of the target is particularly useful in night time or low visibility conditions.
A mockup of the SpaceShipTwo interior On June 21, 2004, Mike Melvill reached space funded entirely by private means. The vehicle, SpaceShipOne, was developed by Scaled Composites as an experimental precursor to a privately operated fleet of spaceplanes for suborbital space tourism. The operational spaceplane model, SpaceShipTwo (SS2), will be carried to an altitude of about 15 kilometers by a B-29 Superfortress-sized carrier aircraft, WhiteKnightTwo. From there SS2 will detach and fire its rocket motor to bring the craft to its apogee of approximately 110 kilometers.
Black Arrow satellite deployment, with Waxwing upper stage. Waxwing seen without its engine nozzle Waxwing was a British solid rocket motor used for apogee kick as the 3rd (upper) stage of the Black Arrow satellite launch vehicles. Waxwing was used to successfully place the Prospero X-3 satellite into low Earth orbit on 28 October 1971, Britain's only satellite launch on an indigenously-developed launch vehicle. Another use of Waxwing was to increase the velocity of test re-entry vehicles on Black Knight during tests for the Blue Streak missile.
The architectural design of KSEVT was created by four architect bureaus: Bevk-Perović, Dekleva-Gregorič, OFIS and Sadar+Vuga. The design derives from the plans for a habitable wheel, one of the three parts of a geostationary space station which is described in Potočnik's book Das Problem der Befahrung des Weltraums - der Raketen-Motor (The Problem of Space Travel - The Rocket Motor). The building is a concrete monolith object that consists of two low cylinders. In the dynamical relation of these two, an impression of levitation and rotation is created.
As a last resort, ground controllers decided that if they could not get Pioneer 1 to the Moon, they would place it in a high Earth orbit by firing the attached solid rocket motor. The inaccurate launch trajectory, however, had placed the probe on an orbital track that resulted in thermal heating and cooling beyond what the primitive temperature control system could handle. The probe's internals fell to near-freezing temperatures, rendering the solid motor igniter inoperable. Pioneer 1 reached a total distance of before beginning its descent back to Earth.
On 2 March 1953, the first prototype Trident I conducted the type's maiden flight; flown by test pilot Jacques Guignard, the aircraft used the entire length of the runway to get airborne, being powered only by its turbojet engines. It was initially flown without any rocket engine installed, relying solely upon its turbojet engines instead.Pelt 2012, pp. 160–161. According to aviation author Bill Gunston, the early test flights of the SO.9000 were 'hairy' prior to the installation of the rocket motor, which first occurred during September 1954.
The missile uses a single-stage liquid propellant rocket motor. The Ghauri-II design improves accuracy by an employing mechanisms that spin the single booster stage and warhead combination approximately 10 seconds before the termination of the powered flight phase at 110 seconds.Federation of American Scientists At this point, the warhead is then separated from the booster stage to fly on a re-entry trajectory that remains stable to its target, greatly enhancing the missile's accuracy. With the addition of GPS targeting the warhead accuracy is further enhanced.
At Minot, the wing flew the B-52H, which brought added vigor to its strategic deterrence mission. It also supported the post- attack command and control system (PACCS), July 1968 – December 1969. In the summer of 1975, the wing gained the Boeing AGM-69A short range attack missile (SRAM), which enhanced the ability of the B-52H to penetrate and survive in this hostile environment. Armed with a nuclear warhead and equipped with a simple inertial guidance system, the AGM-69A was propelled to its range of 20 to by a solid-propellant rocket motor.
The inner surface of the double-wall engine is niobium alloy and the outer surface is nimonic alloy. Due to technology denial of material for the scramjet engine, a new program was initiated and the materials were developed in-house. This led to self-sufficiency in the area and the scramjet engine was ground tested successfully for 20s instead of the initial 3s. In the 12 June 2019 test, the cruise vehicle was mounted on an Agni-I solid rocket motor to take it to the required altitude.
The P120C rocket motor is derived from the first stage of the Vega rocket P80. Like its predecessor, the structural casing is made of carbon fibre, which is built from pre-impregnated epoxy sheets through filament winding and automatic fabric deposition. It will contain 143.6 tons of HTPB 1912 solid propellant composed by 19% of aluminum powder, 69% of ammonium perchlorate with 12% of hydroxyl terminated polybutadiene binder. It takes of carbon fibre, wound over 33 days in climate controlled room held at 21 °C to make the engine's thick walls.
In addition, ESSM takes advantage of the latest missile guidance technology, with different versions for Aegis/AN/SPY-1, Sewaco/Active Phased Array Radar (APAR), and traditional target illumination all-the-way. In the 2000s the NATO Seasparrow Project Office began planning an upgraded Block 2 version of the ESSM. In 2014 Canada pledged 200M CAD to underwrite their share of the Block 2's development cost. ESSM Block 2 leverages the existing Block 1 rocket motor and features a dual-mode X band seeker, increased maneuverability, and other enhancements.
The first FFARs were developed by the U.S. Navy and introduced in June 1943. They had a 3.5-inch diameter and a non- explosive warhead, since they were used as an aircraft-launched ASW (Anti- Submarine Warfare) rocket and worked by puncturing the hull. It was accurate enough for use against surface ships and land targets, but these missions required an explosive warhead.Parsch 2004 A 5-inch anti-aircraft shell was attached to the 3.5-inch rocket motor, creating the 5-Inch FFAR, which entered service in December 1943.
Other launches: Apart from Indian payload, sounding rockets from many other countries (including United States, Russia, Japan, France, Germany) were also launched from Thumba, as part of mutual international collaboration. TERLS developed infrastructure for all aspects of rocketry, ranging from rocket design, rocket propellant, rocket motor casting, integration, payload-assembly, testing, evaluation besides building subsystems like payload housing and jettisonable nose cone. Fibre-reinforced plastic composite materials for nose cone were used in early programs at TERLS. The rocket launch from TERLS came to a stand-still in 2000.
In contrast to Blue Vesta, Red Top significantly rationalised the original Blue Jay design. The fuselage was straightened, removing the boat-tail design of the Firestreak and allowing the new "Linnet" rocket motor to more completely fill the increased volume. With the engine isolated at the rear of the missile, the warhead was moved forward from its former location wrapped around the engine at the rear. The former location required the control fin actuators to be placed in the nose, operating the fins using long pushrods running the length of the fuselage.
The A-5 played a vital role in testing the aerodynamics and technology of the A-4. Its rocket motor was identical to the A-3, but with a new control system provided by Siemens. The A-5 length was almost the same as the A-3, but was 4 inches larger in diameter (24.2 feet long and 2.5 feet in diameter). The A-5 was fitted with a Brennschluss receiving set, a parachute recovery system, could stay afloat for up to two hours, and was painted yellow and red, aiding recovery.
One late version of the engine added a small rocket motor (the BMW 109-718) at the rear and usually just above the exhaust of the engine, which added some thrust each for three to five minutes, for take off and short dashes.Christopher, p.124. In this configuration, it was known as the BMW 003R and was tested, albeit with some serious reliability problems, on single prototypes for advanced models of the Me 262 (the Me 262C-2b Heimatschützer II [Home Defender II]),Christopher, p.125. and He 162 (He 162E).
To fire the rocket, the firer moves a charge lever forward with his firing hand thumb. The rocket motor burns out before it leaves the launch tube, the resulting blast being directed rearwards from the launch tube. The rocket then coasts to the target, arming itself after it has passed a certain arming distance. The warhead is a HEAT shaped charge and could penetrate of rolled homogeneous armour at 90 degrees, as was taught to soldiers trained on the weapon system in the British Army, Royal Navy (Royal Marines) and RAF Regiment.
The PL-15 () is an active radar-guided very long range air-to-air missile developed by the People's Republic of China. The PL-15 entered military service in 2016 and is carried by the Chengdu J-10C, Shenyang J-16 and the Chengdu J-20, aircraft. The missile features an active electronically scanned array radar, and has a range exceeding 200 km – comparable to that of the Russian R-37 missile. It is 4 meters long and incorporates a dual-thrust rocket motor, capable of a speed of Mach 4.
The missile is considered to be very accurate, with an accuracy believed to match that of the company's other anti-tank missile, the Ingwe, at around 300 mm CEP at maximum range. It also has a long range for an anti-tank missile; at 10 km (6.2 mi) it is greater than the published range of most current competitors, including the Hellfire. The range is achieved due to an advanced solid-fuel composite rocket motor (developed by Somchem), which has a relatively slow burning rate compared to similar motors, as well as being essentially smokeless.
The characteristic aspects of the city, which at that time was military and industrial and chemical center of defense production, defined in many ways the Vladimir´s later choice of profession. In 1977 V. Zakhmatov graduated from the Samara (Kuibyshev) Polytechnic Institute with a degree in Chemistry and Technology of High-Molecular Compounds (0815 - Powder and solid rocket motor fuel). As a student, he started conducting research on explosives sensibility characteristics. After graduation, he worked as a test-engineer of ballistic test of ammunition (calibre size from 23 to 152mm, incl.
The momentum imparted to the spacecraft by the Bolo is not free. In the same way that the Bolo changes the spacecraft's momentum and direction of travel, the Bolo's orbital momentum and rotational momentum is also changed, and this costs energy that must be replaced. The idea is that the replacement energy would come from a more efficient and lower cost source than a chemical rocket motor. Two possible lower cost sources for this replacement energy are an ion propulsion system, or an electrodynamic tether propulsion system that would be part of the Bolo.
The Private program was begun in 1944 as an outgrowth of work by the California Institute of Technology's Guggenheim Aeronautical Laboratory that had produced the first practical jet- assisted take-off (JATO) rockets. The ORDCIT (Ordinance Department California Institute of Technology) project was the Private A whcih initiated on May 24, 1944. The Guggenheim Aeronautical Laboratory, California Institute of Technology (GALCIT) was reorganized as the Jet Propulsion Laboratory. The objective was to progressivly the size and range of missiles A GALCIT JATO rocket motor was used for research into the development of ballistic missiles.
The track of the main wheels was increased and because they were closer to the center of gravity, there was less weight on the nosewheel. Wing folding was limited to the outer wing panels. An FJ-4B with six rocket pods FJ-4F prototype with an additional rocket motor The FJ-4 was intended as an all- weather interceptor, a role that required considerable range on internal fuel. The FJ-4 had 50% more fuel capacity than the FJ-3 and was lightened by omitting armor and reducing ammunition capacity.
SRB ignition can occur only when a manual lock pin from each SRB safe and arm device has been removed. The ground crew removes the pin during prelaunch activities. At T−5:00, the SRB safe and arm device is rotated to the arm position. The solid rocket motor ignition commands are issued when the three Space Shuttle Main Engines (SSMEs) are at or above 90% of rated thrust, no SSME fail and/or SRB ignition Pyrotechnic Initiator Controller (PIC) low voltage is indicated and there are no holds from the Launch Processing System (LPS).
The solid rocket motor ignition commands are sent by the orbiter computers through the Master Events Controllers (MECs) to the safe and arm device NASA standard detonators (NSDs) in each SRB. A PIC single-channel capacitor discharge device controls the firing of each pyrotechnic device. Three signals must be present simultaneously for the PIC to generate the pyro firing output. These signals, arm, fire 1 and fire 2, originate in the orbiter general-purpose computers (GPCs) and are transmitted to the MECs. The MECs reformat them to 28 volt DC signals for the PICs.
The CTS is an upper stage developed by the China Academy of Launch Vehicle Technology (CALT) to improve the performance of the Long March 2C to high (>400 km of altitude) LEO missions like SSO. The two stage LM-2 delivers the payload and stage to an elliptical orbit with the desired apogee and the CTS points the stack in the direction of the correct vector and activates the solid rocket motor (SRM) main engine to circularize it. It then dispenses the spacecraft and does a passivisation procedure.
The recovery of the reentry vehicles on the succeeding two attempts were not successful. Three mice, one on each vehicle, died in these tests. The Able stage from the Atlas reentry vehicle tests was upgraded to become the Able I with a third stage consisting of an unguided Altair X-248 solid-fuel rocket motor. A Thor Able I was used in an attempt to place the 84 lb (38 kg) Pioneer 0 spacecraft into lunar orbit where it would take pictures of the lunar surface with a TV camera.
The Goshute tribe had planned on allowing the Private Fuel Storage consortium to store 44,000 tons of high- level nuclear waste from over 100 nuclear reactors on the site in above-ground storage. The license from the Nuclear Regulatory Commission, submitted in 1997, was approved in 2006. The tribe had received widespread opposition to the efforts, which were finally canceled in 2012. A 1999 report from Private Fuel Storage calculated the impact of an explosion from the largest solid-fuel rocket motor tested at Tekoi, being "1.2 million pounds of Class 1.1 explosive".
The Titan III family consisted of an enhanced Titan II core with or without solid rocket strap-on boosters and an assortment of upper stages. All Solid Rocket Motor (SRM)-equipped Titans (IIIC, IIID, IIIE, 34D, and IV) launched with only the SRMs firing at liftoff, the core stage not activating until T+105 seconds, shortly before SRM jettison. The Titan IIIA (an early test variant flown in 1964-65) and IIIB (flown from 1966-87 with an Agena D upper stage in both standard and extended tank variants) had no SRMs.
In 1988-89, The R. M. Parsons Company designed and built a full-scale steel tower and deflector facility, which was used to test the Titan IV Solid Rocket Motor Upgrade (SRMU). The launch and the effect of the SRMU thrust force on the space shuttle vehicle were modeled. To evaluate the magnitude of the thrust force, the SRMU was connected to the steel tower through load measurement systems and launched in-place. It was the first full-scale test conducted to simulate the effects of the SRMU on the main space shuttle vehicle.
Attnang was founded by Bavarian settlers in the late 8th century. The town of Puchheim is documented the first time in 1135, Attnang about one hundred years later in 1242. In 1912 the community changed its name from Puchheim to Attnang-Puchheim to acknowledge this growing part of the town. In World War II, the trainstation served as connection to the Schlier V-2 rocket motor test area. The Attnang-Puchheim marshalling yard was bombed on April 21, 1945 at 10:57 by 179 bombers of the US 15th Air Force from Foggia, Italy.
In October they tested for the first time their gaseous oxygen - methyl alcohol rocket motor. They used an area of the Arroyo Seco on the western edge of Pasadena, "a stone’s throw from the present-day Jet Propulsion Laboratory." After a series of tests, they tested the motor in that location for the last time in January 1937; it ran for 44 seconds at a chamber pressure of 75 psi. In March, Weld Arnold, then an assistant in the Astrophysical Laboratory at Caltech, joined the group as a photographer.
The AGM-88 can detect, attack and destroy a radar antenna or transmitter with minimal aircrew input. The proportional guidance system that homes in on enemy radar emissions has a fixed antenna and seeker head in the missile's nose. A smokeless, solid-propellant, booster-sustainer rocket motor propels the missile at speeds over Mach 2.0. The HARM missile was a program led by the U.S. Navy, and it was first carried by the A-6E, A-7, and F/A-18A/B aircraft, and then it equipped the EA-6B aircraft.
Many nations also use a weapon derived from the Carl Gustav, the one-shot AT4, which was originally developed in 1984 to fulfil an urgent requirement for an effective replacement for the M72 LAW after the failure of the FGR-17 Viper program the previous year. The ubiquitous RPG-7 is also technically a recoilless gun, since its rocket-powered projectile is launched using an explosive booster charge (even more so when firing the OG-7V anti-personnel round, which has no rocket motor), though it is usually not classified as one.
Pelt 2012, p. 163. Formal development of what would be designated the SE.212 Durandal by SNCASE was started during December 1963. The design team produced a compact aircraft furnished with a 60° delta wing and powered by a single SNECMA Atar 101F turbojet engine, equipped with afterburning. It was intended for the Durandal to take off while being solely powered by this conventional engine; once it had attained a high altitude, the aircraft's speed could then be boosted by the ignition of its auxiliary engine, a single SEPR 75 rocket motor.
Diethylzinc is not limited to only being used in chemistry. Because of its high reactivity toward air, it was used in small quantities as a hypergolic or "self igniting" liquid rocket fuel—it ignites on contact with oxidizer, so the rocket motor need only contain a pump, without a spark source for ignition. Diethylzinc was also investigated by the United States Library of Congress as a potential means of mass deacidification of books printed on wood pulp paper. Diethylzinc vapour would, in theory, neutralize acid residues in the paper, leaving slightly alkaline zinc oxide residues.
The explosion and depth of damage indicated that this plane carried a bomb. The rockets that were loaded in the launchers topside began exploding in every direction as the fire spread from one broken rocket motor to another causing a great deal of shrapnel and fragments to be in the air at all times. These rockets were propelled only short distances with numerous hits about the deck causing fires. The plane or bomb had also penetrated the forward assembly room causing assembled rockets to be propelled throughout the ship and the area surrounding it.
De-spin is needed since some final stages are spin-stabilized, and require fairly rapid rotation (around 50 rpm. Some, such as Pioneer, rotated at over 600 rpm) to remain stable during firing. (See, for example, the Star 48, a solid fuel rocket motor.) After firing, the satellite cannot be simply released, since such a spin rate is beyond the capability of the satellite's attitude control. Therefore, after rocket firing but before satellite release, the yo-yo weights are used to reduce the spin rates to something the satellite can endure (often 2-5 RPM).
Three Brimstones are carried on a launcher that occupies a single weapon station, allowing a single aircraft to carry many missiles. After a protracted development programme, single-mode or "millimetric" Brimstone entered service with RAF Tornado aircraft in 2005, and the dual-mode variant in 2008. The latter has been extensively used in Afghanistan and Libya. An improved Brimstone 2 was expected to enter service in October 2012, but problems with the new warhead from TDW and the ROXEL rocket motor put back the planned date to November 2015.
The pilot would be ejected from the cockpit by his own inertia and as soon as he was clear of the fuselage, he would open his personal parachute and descend to the ground.Gooden 2006, pp. 101–102. A parachute was to eject the valuable Walter rocket motor from the rear, which would decelerate the aircraft and eject the pilot with inertia, but associated problems were still not fully resolved prior to the war's end. Professor Wilhelm Fuchs reportedly calculated the Natter's aerodynamics at the Technische Hochschule, Aachen using a large analog computer.
Because of the energy required to achieve a Jupiter trajectory boost with an payload, the spacecraft included a propulsion module made of a solid-rocket motor and eight hydrazine monopropellant rocket engines, four providing pitch and yaw attitude control, and four for roll control. The propulsion module was jettisoned shortly after the successful Jupiter burn. Sixteen hydrazine MR-103 thrusters on the mission module provide attitude control. Four are used to execute trajectory correction maneuvers; the others in two redundant six-thruster branches, to stabilize the spacecraft on its three axes.
The AGM-130 is a powered air-to-surface missile designed for strikes at long range against various targets. It is essentially a rocket-boosted version of the GBU-15 bomb, with the rocket motor increasing the launch range and so giving the launch aircraft protection from whatever defenses may protect the target. Two can be carried by the F-111 and F-15E. In 1991 the development of some significant upgrades began; these included a new CCD seeker and a GPS/INS (GPS-aided Inertial Navigation System) mid-course guidance.
The AGM-130 is highly accurate, and is intended for use against high- value targets which are either slow moving or of fixed location. The GBU-15 is a modular weapon, and the AGM-130 continues this concept. It consists of a CCD TV or focal plane array imaging infrared seeker head, a radar altimeter, wings, strakes, a Mark 84 or BLU-109 warhead, a control section, and a rocket motor and data link unit. The AGM-130 needs little support on the ground, and can be based in remote "bare base" sites.
Käsemann 1999, pp. 47, 128 Postwar experimental aircraft of the aerodynamic configuration that the Me 163 used, were found to have serious stability problems when entering transonic flight, like the similarly configured, and turbojet powered, Northrop X-4 Bantam and de Havilland DH 108, which made the V18's record with the Walter 509B "cruiser" rocket motor more remarkable. Waldemar Voigt of Messerschmitt's Oberammergau project and development offices started a redesign of the 163 to incorporate the new twin- chamber Walter rocket engine, as well as fix other problems.
The M549 is a High-Explosive Rocket Assisted (HERA) 155 mm howitzer round developed for use by the US Military in order to add additional range to standard howitzers, with a maximum range 30.1 km from a M198 howitzer. The projectile has two distinctive pre-assembled components—the high explosive warhead and the rocket motor, making it a form of rocket-assisted projectile. The warhead is fabricated from high fragmentation steel for increased effectiveness in terms of damage caused to target and contains a bulk-filled explosive (Either TNT or Composition B).
EST (16:39 UTC). The disintegration of the vehicle began after a joint in its right solid rocket booster (SRB) failed at liftoff. The failure was caused by the failure of O-ring seals used in the joint that were not designed to handle the unusually cold conditions that existed at this launch. The seals' failure caused a breach in the SRB joint, allowing pressurized burning gas from within the solid rocket motor to reach the outside and impinge upon the adjacent SRB aft field joint attachment hardware and external fuel tank.
Since there was no evidence of abnormal SSME behavior until 72 seconds (only about one second before the breakup of Challenger), the engines were ruled out as a contributing factor in the accident. Other recovered orbiter components showed no indication of pre-breakup malfunction. Recovered parts of the TDRSS satellite also did not disclose any abnormalities other than damage caused by vehicle breakup, impact, and immersion in salt water. The solid rocket motor boost stage for the payload had not ignited either and was quickly ruled out as a cause of the accident.
The missile was prepared for launch by the navigator; the degree of automation provided by the Roobin-1K eliminated the need for a separate radar operator. For propulsion it used a liquid-fueled twin-chamber rocket motor that delivered 1,200 kgp in boost mode and 700 kgp in cruise mode. The fuel consisted of the TG-02 (sometimes TT-S2) fuel and AK-20F oxidizer which were toxic and highly corrosive, which made ground handling of the missile difficult. Once the launching aircraft's radar has locked onto a target, the missile can be launched.
The Former Indian defence minister A. K. Antony, addressing the annual DRDO awards ceremony, asked defence scientists to demonstrate the missile's capability at the earliest opportunity. DRDO chief V. K. Saraswat told Times of India in mid-2011 that DRDO had tested the three solid-propellant composite rocket motor stages of Agni-V independently and all ground tests had been completed. In September 2011, Saraswat confirmed that the first test flight would be conducted in 2012 from Wheeler Island off the Orissa coast.Agni-5 demo in February 2012. Ibnlive.in.com.
Pengorbitan-1, or RPS/RX-420, will be a four-stage rocket with the ability to place satellites in LEO. Category: microsatellite orbital launch vehicle, similar to Lambda from Japan, but with lighter modern materials and modern avionics. Launch unguided at a 70-degree angle of inclination with a four-stage solid rocket motor launcher.Retrieved at March 29, 2011 Diameter: Length: Lift-off mass: Propellant: solid composite, firing time 13 seconds Thrust: Flight duration: 205 seconds Maximum velocity: mach 4.5 Range: , of altitude Payload: diagnostic, GPS, altimeter, gyro, 3-axis accelerometer, processor and battery.
There are a number of hybrid rocket motor systems available for amateur/hobbyist use in high-powered model rocketry. These include the popular HyperTek systems and a number of 'Urbanski-Colburn Valved' (U/C) systems such as RATTWorks, Contrail Rockets, and Propulsion Polymers. All of these systems use nitrous oxide as the oxidizer and a plastic fuel (such as Polyvinyl chloride (PVC), Polypropylene), or a polymer-based fuel such as HTPB. This reduces the cost per flight compared to solid rocket motors, although there is generally more ground support equipment required with hybrids.
Consequently, the missile launch method also needed to be changed. Rather than launching directly from the mounting pylon, the redesigned missile used drop- launch, with the missile being jettisoned from the pylon on launch, and its rocket motor igniting on a time-delay. One dummy, 5 programmed, and 8 trial missiles were built in 1972 for the new design. A small run of one dummy (for launch system testing), 5 'programmed' (guidance and propulsion only, no warhead) and 8 fully functional trial missiles were built to the new design before the end of 1972.
Thor-Able at the Air Force Space & Missile Museum The Thor-Able was an American expendable launch system and sounding rocket used for a series of re- entry vehicle tests and satellite launches between 1958 and 1960. It was a two-stage rocket, consisting of a Thor IRBM as a first stage and a Vanguard- derived Able second stage. On some flights, an Altair solid rocket motor was added as a third stage. It was a member of the Thor family and an early predecessor of the Delta.
Terne III: Development and construction of a shipborne ASW. A Terne III weapon system consists of a search & track sonar, a fire-control system and the rocket launchers, which can store six salvos of six rockets each. The rocket itself, is a depth charge with multiple fusing modes (preset time after water entry, proximity, or contact), which is propelled through the air by a solid-fueled rocket motor. When the sonar detects a target, the fire-control system can fire a rocket salvo to place a string of depth charges apart, perpendicular to the target's course.
The RGM-165 LASM, also given the designation SM-4, was intended as means to give long- range precision fires in support of the US Marine Corps. Intended as an adaptation of the RIM-66, it retained the original MK 125 warhead and MK 104 rocket motor, with the radar seeker replaced by GPS/INS guidance. While test fired in 1997 using three modified RIM-66K SM-2MR Block III missiles, with 800 missiles set for replacement and IOC expected for 2003/2004, it was cancelled in 2002 due to limited capabilities against mobile or hardened targets.
The Ballistic Trajectory Extended Range Munition (BTERM) was a failed program to develop a precision guided rocket-assisted 127 mm (5-inch) artillery shell for the U.S. Navy. The program was originally named the Autonomous Naval Support Round (ANSR) and was developed by Alliant Techsystems.Ballistic Trajectory Extended Range Munition (BTERM) - Global Security The concept was similar to Raytheon's Extended Range Guided Munition with several simplifications and a larger rocket motor. The warhead was based upon that in the AGM-88 HARM anti-radiation missile, and was guided through GPS; however, unlike the ERGM it was intended to fly a strictly ballistic trajectory.
In May 1958, the first Mirage IIIA conducted its first flight. In October of that year, this aircraft achieved a top speed of Mach 2.2 during one of its test flights, thus becoming the first European aircraft to exceed Mach 2 in level flight. In December 1959, the tenth and final Mirage IIIA was rolled out; the last six pre-production aircraft were largely representative of the subsequent initial production standard. The test regime involved a wide variety of tasks, including the evaluation of the newer SEPR 841 rocket motor, various underwing drop tanks, and other major systems.
Interest in this substance began as a possible fuel for high-speed jets. The propellant mix that would produce the greatest specific impulse for a rocket motor is sometimes given as oxygen difluoride and pentaborane. During the early years of the space race and the missile gap, American rocket engineers thought they could more cheaply produce a rocket that would compete with the Soviets by using an existing first stage and putting an upper stage with an engine that produces thrust at a very high specific impulse atop it. So projects were begun to investigate this fuel.
The Congreve rocket William Congreve (1772-1828), son of the Comptroller of the Royal Arsenal, Woolwich, London, became a major figure in the field. From 1801 Congreve researched the original design of Mysore rockets and started a vigorous development program at the Arsenal's laboratory. Congreve prepared a new propellant mixture, and developed a rocket motor with a strong iron tube with conical nose. This early Congreve rocket weighed about 32 pounds (14.5 kilograms). The Royal Arsenal's first demonstration of solid-fuel rockets took place in 1805. The rockets were effectively used during the Napoleonic Wars and the War of 1812.
The Delta M or Thor-Delta M was an American expendable launch system used for thirteen orbital launches between 1968 and 1971. It was a member of the Delta family of rockets. The Delta M had a three-stage configuration. The first stage was the Long Tank Thor, a stretched version of the Thor missile, previously flown on the Delta L. Three Castor-2 solid rocket boosters were attached to the first stage to increase thrust at lift-off. A Delta E was used as the second stage, and the third stage was a Star-37D solid rocket motor.
The first AS-30 was a development of the 1960s Nord AS-20, to allow both an increase in range and a much larger warhead, and is almost identical to the earlier AS-20 in design. The AS-30 has four large steeply swept back fins such as those on the AS-20, cruciform in cross-section around the midsection of its body. However, because of its larger size, the AS-30 in addition has four smaller fins at the rear of the missile body to increase stability in flight. The AS-30 has a two-stage solid-fuel rocket motor.
The type was displayed publicly in 1981 but production was cancelled in 1982 because of significant problems with the solid rocket motor and the guidance system. Overall the type resembled the American MGM-52 Lance. The follow on missile to, to be named Sky Horse, was also abandoned in 1981 under US pressure although interest in the type was revived in the 1990s after the Third Taiwan Strait Crisis. In the 1980s the Institute worked with Honeywell to design a distributed open architecture combat system to replace the obsolete MK 37 Gun Fire Control System aboard Taiwan's Gearing-class destroyers.
Temple 2004, p.111. The zoom climb tactic, combined with the thrust from the rocket motor of the missile itself, allowed the missile to achieve its maximum range, or, alternatively, to reach space. A twelve-flight test series of the Bold Orion vehicle was conducted; however, despite suffering only one outright failure, the initial flight tests of the single- stage rocket proved less successful than hoped. Authorisation was received to modify the Bold Orion to become a two-stage vehicle; in addition to the modifications improving the missile's reliability, they increased the range of Bold Orion to over .
Richard Nakka's Experimental Rocketry Web Site, "Solid Rocket Motor Theory -- Chamber Pressure" Rocket engines, particularly solid-fuel rocket engines, produce very consistent thrust curves, making this a useful metric for judging their performance. This information is vital when designing spacecraft, particularly multistage spacecraft, since it may be advantageous to separate the engine and its associated fuel tanks and machinery before the fuel has been fully exhausted. This is because even though the engine is still producing thrust during the tail off phase, it may be so little that the spacecraft would be more efficient without it.
The Merlin WVRAAM(With in visual range air to air missile) will use off-boresight capable IIR(Imaging infrared) seeker with All aspect engagement capability and counter-countermeasure capability. It will have High thrust reduced smoke solid propellant technology and an electronic rocket motor aiming and firing system. According to the manufacturer it will have advanced agility due to its thrust vectoring, a unique warhead for maximum probability of kill and a reliable fuze. It will be compatible to the MIL-STD-1553 and MIL-STD-1760 military standards and is designed for use with the LAU-129 guided missile launcher.
Contraves Italiana, an Italian subsidiary of the Swiss armaments company Oerlikon Contraves, began development of a short-ranged () ship-based anti-ship missile system, named Nettuno in 1963. Guidance of Nettuno was by beam riding for course control, with altitude controlled automatically by an onboard radar altimeter, allowing the missile to carry out sea-skimming attacks. Command guidance was an alternative guidance method if jamming made the beam-riding method unusable. In 1965, Contraves Italiana began work on an improved missile, Vulcano, which used the same guidance system, but included a two-stage (booster + sustainer) rocket motor to give a longer () range.
Developed during 1942 by the California Institute of Technology (Caltech), under the direction of Charles Christian Lauritsen,Fowler 1975, p.229. in response to a requirement by the United States Navy for a rocket capable of being launched from landing craft to provide fire support during amphibious landings, the 4.5-Inch BBR was an improved version of the Mousetrap anti-submarine rocket system, using the Mousetrap's Mk 3 rocket motor mated to a general purpose aerial bomb.Rottman 2009, p.19. An impact fuse was mounted in the nose of the rocket, with an annular fin assembly providing stability.
The Bullpup had a Manual Command Line Of Sight guidance system with roll-stabilization. In flight the pilot or weapons operator tracked the Bullpup by watching a flare on the back of the missile and used a control joystick to steer it toward the target using radio signals. It was initially powered by a solid fuel rocket motor, and carried a 250 lb (110 kg) warhead. After launching the Bullpup, best accuracy was maintained by continuing to fly the same track, so that the pilot could sight down the smoke trail and steer the missile from directly behind as much as possible.
At the time of explosion, the rocket was above the launch complex. It was the lowest-altitude launch failure at Cape Canaveral since Atlas-Centaur AC-5 in 1965 and only the third total loss of a Delta in the previous two decades. An investigation determined that the failure was caused by a crack in the casing of the number 2 GEM-40 solid rocket motor, which started to form at T+6 seconds and grew from there. At T+12 seconds, the SRB casing ruptured and debris struck the number 8 SRB next to it, causing that motor to fail as well.
On 5 June 1929, Oberth won the first (Robert Esnault-Pelterie - André-Louis Hirsch) Prix REP-Hirsch of the French Astronomical Society for the encouragement of astronautics in his book Wege zur Raumschiffahrt ("Ways to Spaceflight") that had expanded Die Rakete zu den Planetenräumen to a full-length book.L'Aerophile, 1–15 June 1929, p.176; L. Blosset, Smithsonian Annals of Flight, No. 10, p. 11 The book is dedicated to Fritz Lang and Thea von Harbou. In the autumn of 1929, Oberth conducted a static firing of his first liquid-fueled rocket motor, which he named the Kegeldüse.
Cagle, Mary T., History of the Sergeant Weapon System, p 32, U.S. Army Missile Command, Redstone Arsenal, Alabama, 1972 Sergeant missile development began January 1955.Cagle, Mary T., History of the Sergeant Weapon System, p 36, U.S. Army Missile Command, Redstone Arsenal, Alabama, 1972 There were three basic steps planned: feasibility demonstration in 1955-1957, experimental development in 1958 and 1959, followed by final engineering in 1960 and 1961.Cagle, Mary T., History of the Sergeant Weapon System, p 97, U.S. Army Missile Command, Redstone Arsenal, Alabama, 1972 The rocket motor was designed by JPL and built by Thiokol.
The SRBs are jettisoned from the space shuttle at high altitude, about . SRB separation is initiated when the three solid-rocket motor-chamber pressure transducers are processed in the redundancy-management middle-value select and the head-end chamber pressure of both SRBs is less than or equal to . A backup cue is the time elapsed from booster ignition. The separation sequence is initiated, commanding the thrust vector control actuators to the null position and putting the main propulsion system into a second-stage configuration (0.8 seconds from sequence initialization), which ensures the thrust of each SRB is less than .
The Space Shuttle Solid Rocket Booster (Space Shuttle SRB) was the first solid-propellant rocket to be used for primary propulsion on a vehicle used for human spaceflight and provided the majority of the Space Shuttle's thrust during the first two minutes of flight. After burnout, they were jettisoned and parachuted into the Atlantic Ocean where they were recovered, examined, refurbished, and reused. The Space Shuttle SRB was the most powerful solid rocket motor ever flown. Each provided a maximum thrust, roughly double the most powerful single-combustion chamber liquid-propellant rocket engine ever flown, the Rocketdyne F-1.
Thomas was selected by NASA in March 1992 and reported to the Johnson Space Center in August 1992. In August 1993, following one year of training, he was appointed a member of the NASA Astronaut Corps and was qualified for an assignment as a mission specialist on Space Shuttle flight crews. While awaiting space flight assignment, Thomas supported shuttle launch and landing operations as an Astronaut Support Person (ASP) at the Kennedy Space Center. He also provided technical support to the Space Shuttle Main Engine project, the Solid Rocket Motor project and the External Tank project at the Marshall Space Flight Center.
The basic concept is very similar to the one used by most anti-tank missiles, with the exception that those systems normally use small wires to send guidance information to the missile, rather than a radio link. The missile contains a small 1.4 kg warhead with a contact fuse and a single-stage solid-rocket motor that accelerates the missile to about 650 m/s (about Mach 2). Engagement time to the maximum effective range is about 13 seconds. Response time from the start of the target detection to missile launch is about 6 seconds, which has been repeatedly confirmed in live firing.
SpaceDev has been working with NASA Ames to design a modern version of the NASA HL-20 Personnel Launch System, called the SpaceDev Dream Chaser. However, on August 18, 2006 it was revealed that SpaceDev did not win the contract. On December 18, 2006, SpaceDev announced that it has been awarded a $330,000 Phase I study contract from Benson Space Company to further the SpaceDev Dream Chaser spaceship program. The study will contribute to the ongoing development of the spaceship and will result in space vehicle and rocket motor designs ready for Phase II vehicle fabrication and testing.
However, the Challenger accident in 1986 caused a renewed dependence on expendable launch systems, with the Titan IV program significantly expanded. At the time of its introduction, the Titan IV was the largest and most capable expendable launch vehicle used by the USAF. The post-Challenger program added Titan IV versions with the Inertial Upper Stage (IUS) or no upper stages, increased the number of flights, and converted LC-40 at the Cape for Titan IV launches. As of 1991, almost forty total Titan IV launches were scheduled and a new, improved SRM (solid rocket motor) casing using lightweight composite materials was introduced.
The Spaceship Company (TSC) is a British/American spacecraft manufacturing company that was founded by Burt Rutan and Richard Branson in mid-2005 and was jointly owned by Virgin Group (70%) and Scaled Composites (30%) until 2012 when Virgin Galactic became the sole owner. TSC was formed to own the technology created by Scaled for Virgin Galactic's Virgin SpaceShip program. This includes developments on the care-free reentrySee section headed "SPACESHIPONE" at the FAQ Page of Scaled Composites' website for more details. system and cantilevered-hybrid rocket motor, licensed from Paul Allen and Burt Rutan's Mojave Aerospace.
Under Benson's guidance, SpaceDev developed critical hybrid rocket motor technology and furnished all of the rocket motors for Paul Allen's SpaceShipOne, the craft that earned the $10 million Ansari X Prize in 2004. Benson Space had completed its first round of financing and submitted a request for proposal to SpaceDev for the design and development of its SpaceDev Dream Chaser spaceships. BSC expected to be one of SpaceDev's largest customers, purchasing multiple spaceships and safe hybrid rocket motors for use in personal spaceflight. However, Jim Benson's illness and death led to the dissolution of the company.
Since Swiss industry still had no experience with the aircraft and aerodynamics of jet aircraft, several wind tunnel models were produced. In addition, a 3/5th scale wooden glider, the EFW N-20.01 was built to allow testing of the novel wing shape; this flew on 17 April 1948. The aircraft was equipped with a JATO solid rocket motor, which was able to be started independently to reach the necessary altitude for tests. The nose gear came from a de Havilland Vampire and the main landing gear from a Messerschmitt Bf 109; both were electromechanical retractable.
The Maverick has a modular design, allowing for different combinations of the guidance package and warhead to be attached to the rocket motor to produce a different weapon. It has long-chord delta wings and a cylindrical body, reminiscent of the AIM-4 Falcon and the AIM-54 Phoenix. Different models of the AGM-65 have used electro-optical, laser, and imaging infrared guidance systems. The AGM-65 has two types of warhead: one has a contact fuze in the nose, the other has a heavyweight warhead fitted with a delayed-action fuze, which penetrates the target with its kinetic energy before detonating.
The latter is most effective against large, hard targets. The propulsion system for both types is a solid-fuel rocket motor behind the warhead. The Maverick missile is unable to lock onto targets on its own; it has to be given input by the pilot or weapon systems officer (WSO) after which it follows the path to the target autonomously. In an A-10 Thunderbolt II, for example, the video feed from the seeker head is relayed to a screen in the cockpit, where the pilot can check the locked target of the missile before launch.
ERAAM+ would retain the ERAAM dual-pulse motor but fitted to a front end incorporating all the features of Phase 3 of the U.S. Department of Defense's (DoD) AMRAAM Pre-Planned Product Improvement (P3I) programme, which was planned out to 2015. These included upgraded seeker hardware and software to provide improved performance against advanced threats and replacement of the longitudinally mounted electronics boards with a circular design which reduced the volume occupied by the electronics allowing space for a longer rocket motor. As equal partners the U.S. and UK would jointly specify and develop the new missile.
A development contract was signed with Armstrong Whitworth lead development, and the Project 502 industry group was organized in 1949 to produce it. The DRPC suggested downgrading Red Heathen to use a missile with performance roughly equal to Seaslug, but replacing its guidance with a semi- active radar homing system which was more suitable for development of a long- range system in the future. English Electric continued development of this "new" Red Heathen. Later, looking for a second approach to the requirement, using a ramjet instead of a rocket motor, the RAE approached de Havilland, but they declined due to workload.
In 1995 Lockheed Martin produced an Advanced Transportation System Studies (ATSS) report for the Marshall Space Flight Center. A section of the ATSS report describes several possible vehicles much like the Ares I design, with liquid rocket second stages stacked above segmented solid rocket booster (SRB) first stages. The variants that were considered included both the J-2S engines and Space Shuttle Main Engines (SSMEs) for the second stage. The variants also assumed use of the Advanced Solid Rocket Motor (ASRM) as a first stage, but the ASRM was cancelled in 1993 due to significant cost overruns.
Cannelures, which are recessed rings around the projectile used to crimp the projectile securely into the case, will cause an increase in drag. Analytical software was developed by the Ballistics Research Laboratory – later called the Army Research Laboratory – which reduced actual test range data to parametric relationships for projectile drag coefficient prediction.MC DRAG - A Computer Program for Estimating the Drag Coefficients of Projectiles, McCoy, US Army Ballistic Research Laboratory, 1981 Large caliber artillery also employ drag reduction mechanisms in addition to streamlining geometry. Rocket- assisted projectiles employ a small rocket motor that ignites upon muzzle exit providing additional thrust to overcome aerodynamic drag.
Blue Origin partnered with Aerojet Rocketdyne to develop a pusher launch escape system for the New Shepard suborbital Crew Capsule. Aerojet Rocketdyne provides the Crew Capsule Escape Solid Rocket Motor (CCE SRM) while the thrust vector control system that steers the capsule during an abort is designed and manufactured by Blue Origin. In late 2012, Blue Origin performed a pad abort test of the escape system on a full-scale suborbital capsule. Four years later in 2016, the escape system was successfully tested in-flight at the point of highest dynamic pressure as the vehicle reached transonic velocity.
CSULB students had developed their Prospector 2 (P-2) rocket using a 1,000 lbf (4.4 kN) LOX/ethanol aerospike engine. This work on aerospike engines continues; Prospector-10, a ten-chamber aerospike engine, was test- fired June 25, 2008. bell and aerospike nozzle Further progress came in March 2004 when two successful tests sponsored by the NASA Dryden Flight Research Centre using high-power rockets manufactured by Blacksky Corporation, based in Carlsbad, California. The aerospike nozzles and solid rocket motors were developed and built by the rocket motor division of Cesaroni Technology Incorporated, north of Toronto, Ontario.
The first launch of the missile was conducted in November 1962, revealing problems with the liquid- fueled sustainer rocket motor. Concurrently, with the R-25 testing in 1962 the SFRY acquired S-75 Dvina (Russian: С-75; NATO reporting name: SA-2 Guideline), missile systems from the Soviet Union. As such, by the end of 1964 the decision was made to abandon the Vukan project that produced a total of twelve missiles. The knowledge and experience gained during this project were later incorporated into other projects for production of other armaments for the Yugoslav People's Army (JNA).
In 1972, the Algol III was developed by the Chemical Systems Division of United Technologies. The Algol III was a new high- performance solid rocket motor developed for use as the first stage of the NASA SCOUT-D and -E launch vehicles. It was first flown on Scout D-1 in 1972. The motor diameter was increased , providing 104,500 lb thrust. This was a 30% improvement of lifting capacity versus the Algol II-B. The motor delivers a 30% gain in total impulse over its predecessor and provides a 35-45% gain in payload mass capability at a fractional increase in cost.
The AIM-68 was designed with a dual- thrust solid-propellant rocket and was capable of reaching speeds of Mach 4 over its range. The prototypes were fitted with infrared guidance systems from GAR-2A/B (AIM-4C/D) Falcon missiles; the rocket motor from the AGM-12 Bullpup was used for propulsion. The warhead was a W30 0.5 kiloton nuclear warhead, smaller than the 1.5 kiloton model used on the Genie. The guidance system allowed the missile to be used against maneuvering targets, including single bombers, rather than whole formations as was the case for the Genie.
Richard Branson unveiled the rocket plane on 7 December 2009, announcing that, after testing, the plane would carry fare-paying passengers ticketed for short duration journeys just above the atmosphere. Virgin Group would initially launch from a base in New Mexico before extending operations around the globe. Built from lightweight carbon-composite materials and powered by a hybrid rocket motor, SS2 is based on the Ansari X Prize-winning SpaceShipOne concept – a rocket plane that is lifted initially by a carrier aircraft before independent launch. SS1 became the world's first private spaceship with a series of high-altitude flights in 2004.
These rockets were fired from a streamlined pod rather than individual rails, which greatly reduced drag and dramatically increased the number of rockets that could be carried. While a Hunter might carry eight RP-3s, it typically carried two 18-rocket pods for a total of 36 SNEBs. The SNEB was also more accurate; the RP-3 had an average dispersion around 2.3 degrees, while the larger snap-out fins of the SNEB reduced this to just over 1 degree. However, the smaller rocket motor did result in slightly lower velocity and longer flight times, although the effective range was slightly longer.
In 1930, von Braun attended the Technische Hochschule Berlin, where he joined the Spaceflight Society (Verein für Raumschiffahrt or "VfR") and assisted Willy Ley in his liquid-fueled rocket motor tests in conjunction with Hermann Oberth.Various sources such as The Nazi Rocketeers ( pp 5–8) list the young Wernher von Braun as joining the VfR as an apprentice to Willy Ley, one of the three founders. Later when Ley fled Germany because he was a Jew, von Braun took over the leadership of the Verein and changed its activity to military development. In spring 1932, he graduated with a diploma in mechanical engineering.
Early Booster Missile Nike I (three fin model). The Nike stage or Nike booster, a solid fuel rocket motor, was created by Hercules Aerospace for the Nike Ajax (M5) Nike Hercules (M5E1) (and M88 late in Hercules career). It was developed for use as the first stage of the Nike Ajax and Nike Hercules missiles as part of Project Nike. It was subsequently employed in a variety of missiles and multi-stage sounding rockets, becoming one of the most popular and reliable rocket stages, not only in the United States, but also in several other countries around the world.
With the ballistic Crow I having proved the propulsion concept sound, follow- up work on a modification of the vehicle to provide guidance was undertaken. The missile was fitted with a simple autopilot, utilizing infrared horizon- scanning to maintain the missile's attitude in flight. Captive flight tests of Crow began in February 1963 aboard an F-4B Phantom II carrier aircraft; on May 29, the first test launch was attempted, with three further launches taking place through May 1965. None of first three attempted flights were successful, however; malfunctions in the rocket motor, autopilot, and controls plagued the program.
The Sea Griffin will use a dual-mode seeker with an imaging infrared seeker and semi-active laser guidance, and a data-link to track multiple threats simultaneously and give it a fire-and-forget capability. The new seeker and an extended-range rocket motor, which will add 9.1 kg, will increase the range of the Sea Griffin to 15 km. In tests, the Sea Griffin's new imaging infrared (IIR) seeker has streamed video back to operators through the data-link to provide verification before the missile strikes the target.SeaGriffin Completes Guided Flight Test with Dual-mode Seeker – Deagel.
In the U.S. Army, Hydra 70 rockets are fired from the AH-64A Apache and AH-64D Apache Longbow helicopters using M261 19-tube rocket launchers, and the OH-58D Kiowa Warrior using seven-tube M260 rocket launchers. In the U.S. Marine Corps, either the M260 or M261 launchers are employed on the AH-1W SuperCobra and AH-1Z Viper, depending upon the mission. The M260 and M261 are used with the Mk 66 series of rocket motor, which replaced the Mk 40 series. The Mk 66 has a reduced system weight and provides a remote fuze setting interface.
An October 26, 2005 episode of the Television show MythBusters entitled "Confederate Rocket" featured a hybrid rocket motor using liquid nitrous oxide and paraffin wax. The myth purported that during the American Civil War, the Confederate Army was able to construct a rocket of this type. The myth was revisited in a later episode entitled Salami Rocket, using hollowed out dry salami as the solid fuel. In the February 18, 2007, episode of Top Gear, a Reliant Robin was used by Richard Hammond and James May in an attempt to modify a normal K-reg Robin into a reusable space shuttle.
On February 1, 2019, Gilmour revealed "One Vision", the first Ariel-class rocket to be constructed. The original launch date was set for late February, however, this was pushed back to "sometime in March". The main purpose of One Vision is to test the G-70 hybrid rocket motor, before it is used for commercial launches in 2020. One Vision will be launched from a custom-made mobile launch facility, which is the first of its kind built in Australia and should Ariel- class rockets be launched from it, would have the largest commercial launch capacity in the world.
First Titan IV Launch from LC 41, 14 June 1989 As TITAN 34D launch operations continued, the first Titan IV liquid rocket engines were installed on the Titan IV "pathfinder" vehicle at the end of January 1988, shortly before the core vehicle was erected in the VIB. Four Titan IV solid rocket motor segments were received at the SMAB by the middle of February 1988, and two electrical functional tests were conducted in early March. As "bugs" were worked out of various systems, the core vehicle had its first successful CST on 11 May 1988. The vehicle was moved to the SMAB around the middle of May.
U.S. ASM-135 ASAT missile U.S. Vought ASM-135 ASAT missile launch on 13 September 1985, which destroyed P78-1. Soviet Terra-3 Ground-based-laser- ASAT In the late 1950s, the U.S. Air Force started a series of advanced strategic missile projects under the designation Weapon System WS-199A. One of the projects studied under the 199A umbrella was Martin's Bold Orion air-launched ballistic missile (ALBM) for the B-47 Stratojet, based on the rocket motor from the Sergeant missile. Twelve test launches were carried out between 26 May 1958 and 13 October 1959, but these were generally unsuccessful and further work as an ALBM ended.
P80FW is a single monolithic solid rocket motor propelled by hydroxyl-terminated polybutadiene which burns for 114 seconds and is jettisoned at an altitude of 53 km after achieving a relative speed of 1.7 km/s. The engine shares specifications with Ariane 5 solid rocket boosters - it has the same 3 meter diameter and similar height to the largest segments of the booster. This allows using the same facilities and equipment at the Guiana Propellant Plant for loading the propellant and transporting the engine to the launch site. The nozzle of the P80 is also a direct evolution of the one used in Ariane 5 boosters.
The insurers considered asking NASA to fly a Space Shuttle mission to attach a solid rocket motor to the satellite, which would have been used to correct its orbit. The Shuttle mission would have been similar to STS-49, which reboosted Intelsat 603 following the failure of its launch on a Commercial Titan III. Unlike with Intelsat 603, however, Orion 3 would have needed to perform a Lunar flyby to reduce inclination. NASA considered attaching cameras and a scientific payload to the satellite for the flyby, however reboosting the satellite was subsequently deemed to not be sufficiently cost-effective, and Orion 3 was abandoned.
When fitted with the reconnaissance pod, supersonic performance was severely diminished. The Mirage IIIS could be optionally fitted with a SEPR (Société d'Etudes pour la Propulsion par Réaction) 841 rocket engine with its nitric acid oxidiser tank. It was installed under the rear of the fuselage on a removable adaptor; it could be removed and a similar-shaped fuel tank installed instead. The SEPR rocket enabled the Mirage IIIS to reach an altitude of 24,000 m with its additional thrust of 1500 kp; the rocket motor could be switched off and restarted a maximum of three times during a flight, and had a maximum running time of 80 seconds.
66-68 The body of the motor, warhead and nose cone were all made from rolled steel and were welded together. The warhead contained of Trinitroanisole and in the center of the nose cone, there was a pocket that could house either a Navy nose fuze as used by the 20 cm naval rocket or Army mortar fuze. The launcher was a two-wheeled wooden cart with a metal baseplate that held the base of the rocket. The rocket was launched by pulling a lanyard which tripped a spring powered hammer at the bottom left of the launcher which set off a percussion cap which started the rocket motor.
Scientific objectives included imaging the nuclei at resolutions of up to , performing spectral mapping of the nuclei at resolutions of up to , and obtaining detailed compositional data on gas and dust in the near-nucleus environment, with the goal of improving knowledge of the characteristics of comet nuclei. After the solid rocket motor intended to inject the spacecraft into solar orbit was ignited on August 15, 2002, contact with the probe could not be re-established. Ground-based telescopes later found three objects along the course of the satellite, leading to the speculation that it had disintegrated. Attempts to contact the probe were ended on December 20, 2002.
Kinetic weapons have always been widespread in conventional warfare—bullets, arrows, swords, clubs, etc.—but the energy a projectile would gain while falling from orbit would make such a weapon rival all but the most powerful explosives. A direct hit would presumably destroy all but the most hardened targets without the need for nuclear weapons. Such a system would involve a 'spotter' satellite, which would identify targets from orbit with high-power sensors, and a nearby 'magazine' satellite to de-orbit a long, needle-like tungsten dart onto it with a small rocket motor or just dropping a very big rock from orbit (such as an asteroid).
Not fully understanding how to pilot the CARM, the Quinn and Carther warriors engage its main rocket motor, which accelerates the ship at several g, enough to prevent the crew from reaching the controls to turn the motor off. The CARM is propelled up into the thinnest part of the gas torus before running dangerously low on fuel. As a result, they become the first Smoke Ring inhabitants in centuries to see the naked stars. Unknown to any of the inhabitants of the Smoke Ring, Discipline, the ship in which their ancestors arrived, remains in orbit, and its AI autopilot, Kendy, has been attempting to watch their progress.
When extended, the inner tube telescopes outward toward the rear, guided by the channel assembly, which rides in an alignment slot in the outer tube's trigger housing assembly. This causes the detent lever to move under the trigger assembly in the outer tube, both locking the inner tube in the extended position and cocking the weapon. Once armed, the weapon is no longer watertight, even if the launcher is collapsed into its original configuration. When fired, the striker in the rear tube impacts a primer, which ignites a small amount of powder that "flashes" down a tube to the rear of the rocket and ignites the propellant in the rocket motor.
The idea was to combine the booster and ramjet into a single airframe, thereby reducing cost, size, and range safety requirements, as nothing would be jettisoned in flight. Marquardt took advantage of its advanced metal-forming talents to fill the void left by the end of Bomarc ramjet production. Products such as air inlets for the F-4 Phantom, cases for the submarine-launched Polaris missile, leading-edge slats for the Lockheed L-1011, and launch rocket motor cases for TOW missiles became main products of the firm."$4.9 Million Contract Goes to Marquardt", Los Angeles, California, The Los Angeles Times, May 6, 1964, p.
Zefiro is a family of solid-fuel rocket motor developed by Avio and used on the European Space Agency Vega rocket. The name Zefiro derives from the acronym ZEro FIrst stage ROcket, conceived when this motor was intended to be used as first and second stages of San Marco program of the Italian Space Agency (ASI). After its intended use as booster was shelved the acronym was dropped and only the reference to the Greek god of the west wind Zephyrus remained. two models, Zefiro 23 and Zefiro 9A, are in use with Vega and another model, Zefiro 40, is in development for Vega-C.
This left only the Sea Sparrow using the basic platform, and it no longer had to fit on aircraft. So instead of simply using the P and R models as they were, it was decided to dramatically upgrade the weapon. The ESSM emerged as a completely new weapon, common only in name with the original, although using all of the same support equipment allowing it to be fit to ships already mounting the older models. Compared to the Sea Sparrow, ESSM has a larger, more powerful rocket motor for increased range and agility, as well as upgraded aerodynamics using strakes and skid-to-turn.
In 2005, Sir Richard Branson of the Virgin Group announced the creation of Virgin Galactic and his plans for a 9-seat capacity SpaceShipTwo named VSS Enterprise. It has since been completed with eight seats (one pilot, one co-pilot and six passengers) and has taken part in captive-carry tests and with the first mother-ship WhiteKnightTwo, or VMS Eve. It has also completed solitary glides, with the movable tail sections in both fixed and "feathered" configurations. The hybrid rocket motor has been fired multiple times in ground-based test stands, and was fired in a powered flight for the second time on 5 September 2013.
As part of the final year Aerospace Project, students and staffs from the University of Hertfordshire designed, built and tested a full sized rocket powered car under the mentorship of Ray Wilkinson, a senior professor from Department of Aerospace and Mechanical Engineering.With support from BBC - Bang Goes the Theory and Host Dallas Campbell, the Vauxhall VX220 sports car, was fitted with a large hybrid rocket motor that is designed to produce over half a tonne of thrust was tested in the Duxford Aerodrome. The project got lot of attention for its unprecedented success story and was showcased in local places to build interest in STEM.
The first oddity for using the Dragon was the delay between snapping the trigger and the ignition of the launch motor. This was due to a chemical battery charging the initiator circuit (the operator could hear a rising whine similar to the whine made by early integrated flash cameras when charging the flash circuit). This usually led to the operator tensing up in anticipation of the sudden explosion from the launcher that he knew was coming. The missile was discharged from the launcher tube by a "launch motor", which was a rocket motor that completely expended itself within the tube so as not to injure the operator with exhaust gas.
Katyusha rocket launcher, one of the earliest modern rocket artillery weapons A rocket is a self-propelled, unguided weapon system powered by a rocket motor. Rockets are used primarily as medium and long-range artillery systems, although historically they have also seen considerable use as air-to-surface, some use as air-to-air weapons, and even a few examples of surface-to-air devices. Examples of modern surface-to-surface rocket systems include the BM-27 Uragan and M270 Multiple Launch Rocket System. In military parlance, a rocket differs from a missile primarily by lacking an active guidance system; early missiles were known as "guided rockets" or "guided missiles".
Gorbachev and U.S. President Reagan signing the INF Treaty on 8 December 1987 alt=rocket motor burning The Pershing systems were eliminated after the ratification of the Intermediate-Range Nuclear Forces Treaty on 27 May 1988. The missiles began to be withdrawn in October 1988 and the last of the missiles were destroyed by the static burn of their motors and subsequently crushed in May 1991 at the Longhorn Army Ammunition Plant near Caddo Lake, Texas. Although not covered by the treaty, West Germany agreed unilaterally to the removal of the Pershing 1a missiles from its inventory in 1991, and the missiles were destroyed in the United States.
The Skybike is the standard-issue flying vehicle for U.Z.Z. Agents, similar in appearance to a jet ski, with a single jet or rocket motor at the back for propulsion, and two smaller retro-boosters on the front. Although, in the episode "Monument Racers", Professor Professor invented giant high-speed engines installed on the back of the Skybike, used to catch up with flying monuments. Skybikes are capable of vertical take off and landing, as well as being able to hover and fly backwards and have retractable tripod- style undercarriage. Most U.Z.Z. skybikes are blue, but Anita Knight's is green, and Victor Volt's is purple.
ARMs are less likely to hit the radar if the radar is turned off shortly after the missile is launched, as the longer the radar is off (and assuming it never turns back on), the more error is introduced into the missile's course. The ALARM even has an added loiter mode, with a built-in parachute, enabling it to descend slowly until the radar activates, whereupon the rocket motor will re-ignite. Even a temporary shut down of the enemy's missile guidance radar can be of a great advantage to friendly aircraft during battle. The DRDO Anti-Radiation Missile has been developed and tested by India.
During the closing weeks of World War II, the German work at Peenemünde was investigated by Soviet intelligence, amongst whom was rocket motor constructor Alexey Isayev, who found a copy of Sänger and Bredt's report. A translation was soon circulating among Soviet rocket designers, and a condensed version made its way to Stalin himself. In November 1946 the NII-1 NKAP research institute was formed with mathematician Mstislav Vsevolodovich Keldysh as its head to investigate and develop the German Sänger–Bredt design. In 1947, studies indicated that the high fuel consumption of Sänger's rocket-based design rendered the concept impracticable in the short term.
Sections of the SRB filled with propellant being connected The rocket propellant mixture in each solid rocket motor consisted of ammonium perchlorate (oxidizer, 69.6% by weight), atomized aluminum powder (fuel, 16%), iron oxide (catalyst, 0.4%), PBAN (binder, also acts as fuel, 12.04%), and an epoxy curing agent (1.96%). This propellant is commonly referred to as ammonium perchlorate composite propellant (APCP). This mixture gave the solid rocket motors a specific impulse of at sea level or in a vacuum. The main fuel, aluminum, was used because it has a reasonable specific energy density of about 31.0 MJ/kg, but a high volumetric energy density, and is difficult to ignite accidentally.
The Blindicide was also produced in a 100 mm version (the RL-100). The 83mm version fired a 1.6 kilogram projectile with a 0.5 kg warhead, while the 100 mm version fired a 2.75 kg projectile. The rate of fire was six rounds per minute and the range 400 meters for both versions. This rate of fire was considerably in excess of the M20A1 Bazooka since Blindicide used a mechanical firing pin hitting a percussion cap in the tail of the rocket motor rather than a hand grip magneto system that required trailing wires from each rocket to be connected to terminal posts on the launcher as each round was loaded.
He managed the development of the third-stage rocket motor for the Minuteman III strategic missile system. He entered upgrade training in the AC-119K night flying gunship at Lockbourne Air Force Base, Ohio, in February 1969 and subsequently was assigned to Southeast Asia for combat duty in July 1969. Casey flew 130 combat missions, principally road interdiction, as a navigator in the side-firing gunship. In October 1970 he was assigned to Wright-Patterson Air Force Base, Ohio, where he served as director of configuration management for the B-1, B-1 System Program Office, and later as director of projects, A-10 System Program Office.
In 1929, the German Minister of National Defense undertook research into the use of rocket propulsion for military purposes, and responsibility for rocket development was assigned to the Ballistics Branch of the Army Weapons Department. Walter Dornberger joined that branch in 1930. They built a test stand for liquid-propellant rockets, Experimental Station West, at Kummersdorf in December 1932. Dornberger, Walter Riedel, and Wernher von Braun tested their first rocket motor on 21 December, using liquid oxygen and 75% ethyl alcohol. Arthur Rudolph joined the organization, and work started on the Aggregate 1 (A-1), which was to be a complete missile, but then development moved on to the A-2.
If the manoeuvre from GTO to GEO is to be performed with a single impulse, as with a single solid-rocket motor, apogee must occur at an equatorial crossing and at synchronous orbit altitude. This implies an argument of perigee of either 0° or 180°. Because the argument of perigee is slowly perturbed by the oblateness of the Earth, it is usually biased at launch so that it reaches the desired value at the appropriate time (for example, this is usually the sixth apogee on Ariane 5 launchesArianeSpace, Ariane 5 User's Manual Issue 5 Revision 1, 2011 July, p. 2-13, accessed 8 March 2016.).
The Navy's FY 2016 budget included funding for an extended range AARGM-ER that uses the existing guidance system and warhead of the AGM-88E with a solid integrated rocket-ramjet for double the range. Development funding will last to 2020. In September 2016, Orbital ATK unveiled its extended-range AARGM-ER, which incorporates a redesigned control section and -diameter rocket motor for twice the range and internal carriage on the Lockheed Martin F-35A and F-35C Lightning II. Internal carriage on the F-35B isn't possible due to internal space limitations. The U.S. Navy awarded Orbital ATK a contract for AARGM-ER development in January 2018.
The light cruiser HMS Uganda was also hit and put out of action for almost the entire war as a result. A more widely employed weapon was the Henschel Hs 293, which included wings and a rocket motor to allow the bomb to glide some distance away from the launch aircraft. This weapon was designed for use against thinly armored but highly defended targets such as convoy merchantmen or their escorting warships. When launched, a small liquid-fueled rocket fired to speed the weapon up and get it out in front of the releasing aircraft, which was flown to approach the target just off to one side.
A smaller, less powerful version of the M10, the M9, was then developed, which could be fired from a rifle. This resulted in the creation of a series of rifle grenade launchers, the M1 (Springfield M1903), the M2 (Enfield M1917), the M7 (M1 Garand), and the M8 (M1 Carbine). However, a truly capable anti- tank weapon had yet to be found, and following the lead of other countries at the time, the U.S. Army prepared to evaluate competing designs for a more effective man portable anti-tank weapon. The combination of rocket motor and shaped charge warhead would lead to Army development of light antitank weapons..
Common Tiny Tim delivery aircraft during World War II included the PBJ-1 Mitchell, F4U Corsair, F6F Hellcat, TBM Avenger, and the SB2C Helldiver. After World War II, the United States Navy's rocket laboratory at Inyokern, California developed an even larger version of the Tiny Tim, called "Richard", which was 14 inches in diameter and one of the largest air-to-surface unguided rocket ever developed for the US military. While tested, it was never placed in production. The United States Navy also experimented with a version of the Tiny Tim which was a two-stage rocket, with another Tiny Tim rocket motor mounted behind a complete Tiny Tim.
The entire facility occupies over six square kilometers, and consists of a launch site, a static rocket motor test stand, vehicle checkout and processing buildings, a launch control building, a large support area, a complex headquarters building and an entry control point. The site is five times larger than Tonghae Launch Site. There is much speculation about the functions of different parts of the site but the nuances of satellite photography based guesswork may not be communicated effectively in the mass media. Western sources identified a building as a "high bay processing facility" which turned out to be the launch control centre when the site was visited by journalists.
The oxygen to fuel mixture was 1.0:0.85 at 25 tons of thrust, but as ambient pressure decreased with flight altitude, thrust increased until it reached 29 tons. The turbopump assembly contained two centrifugal pumps, one for the alcohol, and one for the oxygen, both connected to a common shaft. Hydrogen peroxide converted to steam, using a sodium permanganate catalyst powered the pump, which delivered 120 pounds of alcohol and 150 pounds of liquid oxygen per second to a combustion chamber at 210 psi. Dr. Thiel's development of the 25 ton rocket motor relied on pump feeding, rather than on the earlier pressure feeding.
The forward HE-filled shell body is constructed from high-fragmentation steel (HF1) and is of a low-drag aerodynamic profile. The rocket-motor body makes up the rear of the shell, this constructed from 4340 steel. The motor body weighs 13.5 kg (approximately 3.175 kg of which is propellant), is 266.7 mm long and is encircled by a welded overlay copper driving band and obturator band, both protected during storage and transit by a polycarbonate composition grommet. At the front of the projectile, the fuze cavity is protected during transport by an energy-absorbing lifting plug, which protects the fuze area from damage during storage, transit and handling.
The fins fold around the rocket when it is stowed in its launch tube, springing back as soon as it leaves the launch tube. In flight, the very slightly angled fins exert a stabilizing spin to the rocket, turning at approximately 750 rpm. The solid rocket motor burns for just 1.1 seconds, during which time it covers about 300 meters (985 ft). The S-5 is carried in rocket pods, with 4–32 rockets. The first were ORO-57 launchers, made in variants with capacity of 4, 8 and 16 rockets. Most typical became ORO-57K for 8 rockets, used especially with MiG-19.
Following a specification developed during 1951,Babcock 2008, p.321-324 the development of the BOAR rocket was started in 1952 at the Naval Ordnance Test Station (NOTS), located at China Lake, California.Parsch 2003 The project was intended to provide a simple means of extending the stand-off range of nuclear weapons delivered using the toss bombing technique, as some slower aircraft still faced marginal escape conditions when delivering ordinary gravity bombs even with the use of this technique. The rocket that emerged from the development process used a single, solid-fueled rocket motor mated to the W7 nuclear weapon, which had a yield of .
As part of that program, a Non-Destructive Testing (NDT) X-Ray facility was constructed in the ITL Area for the purpose of inspecting Titan solid rockets for flaws in propellant, restrictors, insulation and podding compounds. Construction of the NDT facility began on 1 October 1986, and solid rocket motor testing was conducted there as part of the Titan 34D recovery effort from 23 December 1986 through 12 June 1987. The last Titan 34D launched from the Cape had an extensive processing history between the time it first arrived at the Cape (e.g., 19 August 1981) and the time it was erected for the final time on Transporter No. 3 in Cell No. 1 on 13 December 1988.
The IBEX satellite, initially launched into a highly-elliptical transfer orbit with a low perigee, used a solid fuel rocket motor as its final boost stage at apogee, in order to raise its perigee greatly and to achieve its desired high-altitude elliptical orbit. IBEX is in a highly-eccentric elliptical terrestrial orbit, which ranges from a perigee of about to an apogee of about . Its original orbit was about —that is, about 80% of the distance to the Moon—which has changed primarily due to an intentional adjustment to prolong the spacecraft's useful life (see Orbit adjusted below). This very high orbit allows the IBEX satellite to move out of the Earth's magnetosphere when making scientific observations.
The whole rocket was originally planned to be completely indigenous, but due to technological constraints largely spurred by political pressure from the United States that discouraged independent research and development of rocket technology by South Korea, KARI decided that the KSLV would be built on the basis of the universal rocket module (URM) designed for the Russian Angara family of rockets. The first stage of the vehicle uses the Russian RD-151 engine, which is essentially the RD-191 de-powered to 170 tonnes-force (1.7 MN; 370,000 lbf) from 190 tonnes. The second stage is a solid rocket motor developed and built by KARI. The launch vehicle weighs , stands tall and has a diameter of almost .
During the mid-1990s, French firms Aérospatiale and SEP, along with Italian firm Bombrini-Parodi-Delfino (BPD), commenced discussions on the development of a proposed Ariane Complementary Launcher (ACL). Around the same time, Italy began to champion the concept of a new solid-propellant satellite launcher. This proposed launcher, dubbed Vega, was promoted as functioning to expand the range of European launch capabilities; Vega would be capable of launching a 1000 kg payload into a 700 km polar orbit. From the onset, the first of three stages would be based on the solid booster of the existing Ariane 5 expendable launch system while the second and third stages would make use of the in-development Zefiro rocket motor.
Initial experiments typically mounted a mock-up of the ablative material to be analyzed within a hypersonic wind tunnel.Hogan, C. Michael, Parker, John and Winkler, Ernest, of NASA Ames Research Center, "An Analytical Method for Obtaining the Thermogravimetric Kinetics of Char-forming Ablative Materials from Thermogravimetric Measurements", AIAA/ASME Seventh Structures and Materials Conference, April, 1966 Testing of ablative materials occurs at the Ames Arc Jet Complex. Many spacecraft thermal protection systems have been tested in this facility, including the Apollo, space shuttle, and Orion heat shield materials. Mars Pathfinder during final assembly showing the aeroshell, cruise ring and solid rocket motor The thermal conductivity of a particular TPS material is usually proportional to the material's density.
Gibson 2007, p. 45 with the project code XJ.521. The contractors were Hawker Siddeley and Marconi Space & Defence Systems (the renamed GEC guided weapons division) at Stanmore.Gibson 2007, p. 46 Major changes from the Sparrow were the addition of a Marconi semi-active inverse monopulse radar seeker, improved electronics, adapted control surfaces and a Thorn EMI active radar fuze. The rocket motors used were the Bristol Aerojet Mk 52 mod 2 and the Rocketdyne Mk 38 mod 4 rocket motor; the latest is the Aerojet Hoopoe. Tests of the resulting missile showed it could function successfully in hostile electronic countermeasures (ECM) environments and could engage targets under a wide variety of conditions.
There is also a backup low-light optical tracking system for heavy ECM environments. The latest 9M33M3 missiles have an increased total weight of 170 kg (375 lb) in order to provide the extended range coverage and larger warhead. Propulsion is provided by a dual-thrust solid fuel rocket motor. Both versions feature a missile speed of around Mach 2.4 (peaking at around Mach 3) for a maximum target engagement speed of around Mach 1.4 for the original missile and Mach 1.6 for the M2\M3 missiles. The warhead for the initial and M2 versions weighs 19 kg (42 pounds), increased to 40 kg (88 lb) in the M3 version to improve performance against helicopters.
The rocket motor burns completely before leaving the mouth of the launcher, producing gases around . The rocket propels the 66-mm warhead forward without significant recoil. As the warhead emerges from the launcher, six fins spring out from the base of the rocket tube, stabilizing the warhead's flight.note: no matter what you see in the movies, training films show that there is no "Whoosh!" on launch, but rather more of a loud "BANG!!" or "BLOOP!" for the training versions – and there is no smoke trail behind the rocket as it heads towards the target The early LAW warhead, developed from the M31 HEAT rifle grenade warhead, uses a simple, but extremely safe and reliable, piezoelectric fuze system.
Estes model rockets are popular and used by a large number of hobbyists and educators. However, measurements reported by a group at the University of Central Arkansas found that Estes rocket motor models A3-4T, A8-3, B4-4, B6-4, C6-5, and D12-3 have a measured impulses from 15.4% to 22.8% below the claimed impulse.Penn, Kim and William V. Slaton, Measuring Model Rocket Engine Thrust Curves, The Physics Teacher -- December 2010 -- Volume 48, Issue 9, pp. 591. A study at the Australian Defence Force Academy found Estes D11-P motor to have an impulse 11.4% below Estes specifications and the C6-0 motor to be 4.45% below Estes' specifications.
For launch, the missile seeker was slaved to the launch aircraft's radar (Ferranti AIRPASS in the Lightning and GEC AI.18 in the Sea Vixen) until lock was achieved and the weapon was launched, leaving the interceptor free to acquire another target.Gibson 2007, p. 35 A downside was that the missile was highly toxic (due to either the Magpie rocket motor or the ammonia coolant) and RAF armourers had to wear some form of CRBN protection to safely mount the missile onto an aircraft. "Unlike modern [1990s] missiles, ... Firestreak could only be fired outside cloud, and in winter, skies were rarely clear over the UK."Black, Ian, The Last of the Lightnings, pub PSL, 1996, , p141.
Zhuque-1 (ZQ-1, Chinese：朱雀一号or朱雀·南太湖号), also called LandSpace-1 or LS-1 (the name LandSpace-1 or LS-1 was originally reserved for a different rocket that did not in the end materialize; after cancellation of the rocket, the name LandSpace-1 was affiliated to LandSpace's rocket-to-be-developed, the Zhuque-1), is a -tall, three-stage solid-propellant rocket. All stages have a diameter of 1.35 m. It is likely based on the DF-26 missile's rocket motor. Zhuque-1 has a takeoff mass of and a thrust of , and is able to carry of payload into a low Earth orbit.
The tripod-mounted optical tracking unit The Tan-SAM 1 missile is cruciform in cross section with four clipped delta wings attached to the mid body, and four small steerable clipped delta fins at the rear of the missile. The missile is propelled by a solid rocket motor, with giving it a burn-out velocity of about Mach 2.4. It is initially inertially guided to a likely intercept point, with an all-aspect infra-red seeker taking over to handle terminal guidance. The missile has a 9.2-kilogram fragmentation warhead triggered either by contact or a radar proximity fuze with a lethal radius of between 5 and 15 meters depending on the target type.
DF-15 The DF-15 (CSS-6, also M-9 for export) was developed by the China Aerospace Science and Technology Corporation (CASC, previously known as the 5th Aerospace Academy)'s Academy of Rocket Motor Technology (ARMT, also known as the 4th Academy). The missile is a single- stage, solid-fuel SRBM with a 600 km range and a 500 kg payload. During the 1995-1996 Taiwan strait crisis, the PLA launched six DF-15's near the island of Taiwan in an "exercise" to demonstrate the missile's capability. Although the DF-15 is marketed for export, its range would violate the Missile Technology Control Regime (MTCR) agreement, and thus no DF-15 has been exported to date.
To provide the needed power, the ASRAAM is built on a 16.51 cm (6½ inch) diameter rocket motor compared with Sidewinder's (AIM-9M and X) and IRIS-T's 12.7 cm (5-inch) motors (which trace their history to the 1950s unguided Zuni rocket). This gives the ASRAAM significantly more thrust and therefore increased speed and range up to 50 km. The main improvement is a new 128×128 resolution imaging infrared focal plane array (FPA) seeker manufactured by Hughes before they were acquired by Raytheon. This seeker has a long acquisition range, high countermeasures resistance, approximately 90-degree off-boresight lock-on capability, and the possibility to designate specific parts of the targeted aircraft (like cockpit, engines, etc.).
The fuel pumps for the rocket motor were driven by the jet engine, thus the latter had to be kept running for the former to be ignited or to continue to power the aircraft.Pelt 2012, p. 164. In comparison to other French mixed-power experimental aircraft, such as the competing SNCASO Trident prototype interceptor, it was a heavier aircraft, intended to fly primarily on its jet engine rather than its rocket motor.Pelt 2012, pp. 163-164. Its armament was to consist of a single AA.20 air-to-air missile, which was to be carried underneath the fuselage's centreline; an alternative armament configuration involved a pair of 30 mm DEFA cannon or 24 68mm SNEB rockets.
MOOSE, originally an acronym for Man Out Of Space Easiest but later changed to the more professional-sounding Manned Orbital Operations Safety Equipment, was a proposed emergency "bail-out" system capable of bringing a single astronaut safely down from Earth orbit to the planet's surface. The design was proposed by General Electric in the early 1960s. The system was quite compact, weighing and fitting inside a suitcase-sized container. It consisted of a small twin- nozzle rocket motor sufficient to deorbit the astronaut, a PET film bag long with a flexible ablative heat shield on the back, two pressurized canisters to fill it with polyurethane foam, a parachute, radio equipment and a survival kit.
Parsons (dark vest) and GALCIT colleagues in the Arroyo Seco, Halloween 1936. JPL marks this experiment as its foundation. In hopes of gaining access to the state-of-the-art resources of Caltech for their rocketry research, Parsons and Forman attended a lecture on the work of Austrian rocket engineer Eugen Sänger and hypothetical above-stratospheric aircraft by the institute's William Bollay—a PhD student specializing in rocket-powered aircraft—and approached him to express their interest in designing a liquid-fuel rocket motor. Bollay redirected them to another PhD student, Frank Malina, a mathematician and mechanical engineer writing a thesis on rocket propulsion who shared their interests and soon befriended them.
The AJ-60A rocket motor was developed between 1999 and 2003 for use on the Atlas V. On January 19, 2006 the New Horizons spacecraft to Pluto was launched directly into a solar-escape trajectory at from Cape Canaveral using an Atlas V version with 5 of these SRBs and Star 48B third stage. New Horizons passed the Moon's orbit in just nine hours. In 2015, ULA announced that the Atlas V will switch to new GEM 63 boosters produced by Northrop Grumman Innovation Systems. (GEM 63XL, a stretched version of the GEM 63 booster will be used on the upcoming Vulcan rocket.) The first Atlas V launch with GEM 63 boosters is expected in 2020.
Walter had also been commissioned by the RLM to build a rocket engine for the He 112, so there were two different new rocket motor designs at Neuhardenberg: whereas the von Braun's engines were powered by alcohol and liquid oxygen, Walter engines had hydrogen peroxide and calcium permanganate as a catalyst. Von Braun's engine used direct combustion and created fire, the Walter devices hot vapours from a chemical reaction, but both created thrust and provided high speed. The subsequent flights with the He 112 used the Walter-rocket instead of von Braun's; it was more reliable, simpler to operate and the dangers to pilot and machine were less. All those test flights at Neuhardenberg were made by Erich Warsitz.
Artemis, named for the Greek goddess of the chase and death, was an early air- to-air missile project carried out by the Royal Aircraft Establishment (RAE) beginning in late 1943. The missile was intended for radar-equipped night fighters like the Bristol Beaufighter, which would track the target on their AI Mk. IV radar and then fire at a set range, with the missile homing on the signal of the AI radar being reflected off the target. The concept for Artemis led from an earlier project, Spaniel, a surface-to-air missile based on the RP-3 rocket motor. During development, a variation known as Air Spaniel was considered which would use radio control for guidance.
The trajectory requires high launch energy, so the probe was launched on a Delta IV Heavy class launch vehicle and an upper stage based on the Star 48BV solid rocket motor. Interplanetary gravity assists will provide further deceleration relative to its heliocentric orbit, which will result in a heliocentric speed record at perihelion. As the probe passes around the Sun, it will achieve a velocity of up to , which will temporarily make it the fastest human-made object, almost three times as fast as the previous record holder, Helios-2. Like every object in an orbit, due to gravity the spacecraft will accelerate as it nears perihelion, then slow down again afterward until it reaches its aphelion.
A preserved HWK 109-509B "cruiser" twin- chamber rocket motor (National Museum of the United States Air Force) Model of the Me 163C Model of the unbuilt Me 163D, erroneously marked with the Me 163B V18's markings for this airframe design The biggest concern about the design was the short flight time, which never met the projections made by Walter. With only seven and a half minutes of powered flight, the fighter truly was a dedicated point defense interceptor. To improve this, the Walter firm began developing two more advanced versions of the 509A rocket engine, the 509B and C, each with two separate combustion chambers of differing sizes, one above the other, for greater efficiency.Wiedmer, Erwin.
The AS-20 had four steeply swept-back fins, cruciform in cross-section around the midsection of its body. It used a dual-thrust solid rocket motor, which exhausted through two large nozzles during the boost stage, and a single center line nozzle during the sustain stage. The AS-20 uses a simple MCLOS guidance with the pilot aligning the flares on the missile's rear with the target and controlling the missile in flight after launch with a small joystick sending steering commands to the missile via a radio link. The steering commands steer the missile back to the line-of-sight by thrust vectoring by the movement of one of four metal vanes around the center sustainer nozzle.
Packing crates are used to demonstrate the danger of the M72 LAW back blast Backblast area for FGM-148 Javelin The backblast area is a cone-shaped area behind a rocket launcher, rocket-assisted takeoff unit or recoilless rifle, where hot gases are expelled when the rocket or rifle is discharged. The backblast area is dangerous to ground personnel, who may be burned by the gases or exposed to overpressure caused by the explosion. In confined spaces, common in urban warfare, even the operators themselves may be at risk due to deflection of backblast by walls or sturdier civilian vehicles behind them. Soft launch methods diminish backblast by ejecting the projectile some distance before its main rocket motor ignites.
Wilmore reads an instruction manual for using an IMAX camera inside Node 1 of the ISS. Wilmore was selected as a pilot by NASA in July 2000 and reported for training that August 2000. Following the completion of two years of training and evaluation, Wilmore was assigned technical duties representing the Astronaut Office on all propulsion systems issues including the Space Shuttle Main Engines, solid rocket motor, external tank, and also served on the astronaut support team that traveled to the Kennedy Space Center, Florida, in support of launch and landing operations. He flew to the International Space Station in September 2014 on Soyuz TMA-14M as a member of Expedition 41/42.
Targeting was by search radar and beam transmitter with targets tracked by a search radar until a beam riding transmitter locked on, at which point the missile could be fired, riding the beam until impact, proximity fuze or radio signal detonation. Launchers, slaved to the beam transmitter could launch missiles at any angle form 10° to 90° at a sustained rate of fire of up to two launches per minute. Control of the missiles was by vectoring rocket motor combustion chamber at launch and controllable rear fins at higher speeds. The complete system included a battery command post, target tracking radar, guidance beam transmitter and six twin railed trainable launchers and four diesel generator units.
A six-round clip capable of fitting the internal rocket bays of the F4D Skyray interceptor was also developed. Following a flyoff against the T-214 rocket, which indicated the necessity to modify the rocket motor to reduce the Gimlet's visual signature,Babcock 2008, pp.386–387. the Navy directed the development of a modified, 'hybrid' rocket, using the T-214's tail; this became known as "T-Gimlet". The modified rocket was considered to be suitable for the Navy's purposes; both the original Gimlet and the T-Gimlet were ordered for production, a 5 million dollar USD contract being allotted to start production at the Shumaker Naval Ammunition Depot in Arkansas.
V2 launched from Test Stand VII in the summer of 1943 HNLMS De Zeven Provinciën (F802) firing a Harpoon In modern language, a missile, also known as a guided missile, is a guided airborne ranged weapon capable of self- propelled flight usually by a jet engine or rocket motor. Missiles have four system components: targeting/guidance system, flight system, engine and warhead. Missiles come in types adapted for different purposes: surface-to- surface and air-to-surface missiles (ballistic, cruise, anti-ship, anti-tank, etc.), surface-to-air missiles (and anti-ballistic), air-to-air missiles, and anti-satellite weapons. Airborne explosive devices without propulsion are referred to as shells if fired by an artillery piece and bombs if dropped by an aircraft.
State and federal law require all rocket motors to be independently tested before they may be sold in the United States. The NAR Standards and Testing Committee (“S&T;”) performs this quality assurance for every individual rocket motor type and classification available to general consumers at its East Coast testing facilities at the Massachusetts Institute of Technology and its West Coast testing facilities in Hillsboro, Oregon. S&T; also re-tests each approved motor type every five years to ensure repeatability and help identify creeping degradation in manufacturing or distribution practices. In addition, S&T; collects and reduces data from motor malfunction reports sent in by consumers, using this data to trigger special testing of questionable motors and production lots.
Discussions with Aerojet of California USA took place aimed at exploiting the varied rocket-making skills of the two companies, and in 1959 the Banwell works became Bristol Aerojet (BAJ), with a board chaired by Sir Reginald Verdon-Smith of Bristol Aeroplane Company, with Dan Kimball leading the Aerojet representation. Co-operation began with the Blue Water lorry-launched battlefield nuclear missile, but the Blue Water project was cancelled in 1962, and so the MoS had no application for the polyurethane propellant which was promoted by Aerojet. BAJ Banwell concentrated on development of improved rocket motor cases and their materials, and here Aerojet assistance was valuable. A contract was executed for 5,500 motor cases for the Martin 'Bullpup' missile for Nato.
In engineering, Theodore von Kármán made many key advances in aerodynamics, notably his work on supersonic and hypersonic airflow characterization. A repeating pattern of swirling vortices is named after him, the von Kármán vortex street. Participants in von Kármán's GALCIT project included Frank Malina, who helped develop the WAC Corporal, which was the first U.S. rocket to reach the edge of space, Jack Parsons, a pioneer in the development of liquid and solid rocket fuels who designed the first castable composite-based rocket motor, and Qian Xuesen, who was dubbed the "Father of Chinese Rocketry". More recently, Michael Brown, a professor of planetary astronomy, discovered many trans-Neptunian objects, most notably the dwarf planet Eris, which prompted the International Astronomical Union to redefine the term "planet".
Zylon is an advanced fiber material, similar to Kevlar, that is sewn in a webbing pattern (like shoelace material) to make it stronger. The Zylon bridle provides space for airbag deployment, distance from the solid rocket motor exhaust stream, and increased stability. The bridle incorporates an electrical harness that allows the firing of the solid rockets from the backshell as well as provides data from the backshell inertial measurement unit (which measures rate and tilt of the spacecraft) to the flight computer in the rover. Rocket assisted descent (RAD) motors: Because the atmospheric density of Mars is less than 1% of Earth's, the parachute alone could not slow down the Mars Exploration Rover enough to ensure a safe, low landing speed.
The missile also had an unusual safety mechanism in case of a miss; rather than a self-destruct fuze, if the optical fuze didn't detect a target within 13–16 seconds, the warhead safety mechanism would be engaged to prevent its detonation upon impact. Propulsion is by a single-stage Solid- fuel rocket motor, which is ignited at a distance of few meters from the launch tube: as the throw-out charge ejects the missile from its canister, it is trailing a wire from its rear. The main rocket ignites when missile reaches the wire's end at a few metres distance, and is cut off from it. The seeker head is an unusual construction, using uncooled lead sulphide (PbS) detector elements, but with an unusual tracking mechanism.
Map showing missile assembly building at the left, and the launch pad at the right. The launch pad at the left, the rocket motor test stand at the right, marked with a red X. The facilities at Musudan-ri are modest, consisting of a launch pad at . The launch pad consists of a 30-meter umbilical tower with a top-mounted gantry crane, a flame blast bucket, a launch blockhouse with a connecting access tunnel, two semi-buried liquid fuel storage buildings, a concrete apron/pad and multiple small support buildings."Musudan Test Facility", FAS An engine test stand at , a missile assembly/checkout building at , a missile control building at and a Ground Tracking Facility (coordinates obtained from Google Earth in June, 2006.).
The Peregrine BVRAAM(Beyond visual range air to air missile) has solid state active RF(radio frequency) smart seeker with Fire and forget capability and Electronic counter-countermeasures and will be using All aspect engagement capable home on jam techniques with Data link update capable data link using lock on after launch techniques. In the words of the manufacturer it will have high thrust with reduced smoke solid propellant technology and completely electronic safe and reliable rocket motor arming and firing system. It too will have a design to maximise probability of kill and its fuze too will be reliable. It will be compatible to the MIL-STD-1553 and MIL-STD-1760 military standards and is designed for use with the LAU-129 guided missile launcher.
Testing proved that the F-100 was capable of a ZELL launch even while carrying both an external fuel tank and a single nuclear weapon mounted on its hard points. The conceived mission profile would have been for the pilot to have launched a retaliatory nuclear strike against the attacker before attempting to return to any available friendly airbase, or having to eject from the aircraft if a safe landing site could not be reached. Despite the extremely high thrust generated by the rocket motor, the F-100 reportedly subjected its pilot to a maximum of 4g of acceleration forces during the takeoff phase of flight, reaching a speed of roughly 300 mph prior to the rocket motor's depletion.Moore 2008, pp. 72-73.
Medaris has developed a new rocket motor which will make it possible to take Columbia into lunar orbit. With the help of High Eagle, he is able to attach the smuggled engine, and boost the shuttle to the Moon. He has also smuggled a bare-bones LEM, of his own design, aboard the shuttle, which will allow him to make a one-man EVA to the Apollo 17 landing site. Back on Earth, a mysterious consortium is using a private security company to try to sabotage Medaris' mission by any means possible, including hiring a group of computer hackers to take control of a set of hunter-killer satellites parked behind the Moon, and persuading Roscosmos to intervene and take over the shuttle in LEO.
The right SRB had come down largely intact onto a concrete structure near the pad, which had nobody inside it at the time of launch (the casing rupture had damaged the Inadvertent Separation Destruct System [ISDS] lanyards and prevented proper destruction of the SRM). The disaster drew comparisons to the shuttle accident three months earlier, which was also the victim of a solid rocket motor malfunction. However, the Titan incident was found to have a rather different cause as it had not suffered an O-ring burn-through, but instead the culprit was a small air pocket between the SRM propellant and its metal motor casing. This allowed hot exhaust gases to burn through the casing and eventually rupture the SRM.
After providing the US with the guarantee correspondence, South Korea started to produce a limited number of Hyunmoo missiles and was under the inspection of the United States until the production ended. The Hyunmoo system [the name roughly translates as "guardian angel of the northern skies"], has been indigenously developed in the Agency for Defense Development and now it is in service by the South Korean army. The missile is launched from the mobile launcher and fire-controlled by the battery control van. The Hyunmoo-1 missile, which is propelled by two-stage solid rocket motor and features inertial guidance and control system, can reach the heart of its intended targets under any weather conditions without any commands from the ground after fire.
All measurements are first stated in the U.S. customary units in which they were originally reported, with conversions to SI units also given. The flight was planned to take off from Mojave Spaceport in the early morning, when wind conditions are most favourable. Takeoff was scheduled for 06:47, but was delayed because of winds gusting to 50 mph (20 m/s), which subsided after sunrise. White Knight, carrying SpaceShipOne, taxied to the runway at 07:00, and took off at 07:11. After takeoff, White Knight and SpaceShipOne ascended to the launch altitude, planned to be around 14 km. At 08:09 SpaceShipOne was released, glided for 6 s, then went into nose-up attitude and the rocket motor was ignited.
Along with a further upgrade of the proximity fuse, the new missile incorporated (then) state-of-art technologies including: Von Karman supersonic aerodynamic profile; composite propellant, with a two-stage shaped burn and laminated body solid rocket motor; ceramic substrate surface mount PCBs; completely new electronic systems and software; both analogue and digital proprietary ASICs; highly ECM resistant front end and command link with redundant encoding; fully Digital Autopilot incorporating Kalman state filtering; inertial navigation comprising ring-laser roll and rate gyroscope; Kapton ribbon cabling. The missile warhead is available in two versions, the Mk. 2A for the normal anti-aircraft role, and the Mk. 2B, which includes a shaped charge warhead and dual fuses, and which is useful against light armour as well.
Two candidates were evaluated for the US Army's BDM program. One candidate from McDonnell-Douglas (later Talley Defense Systems) which used the same warhead as the Marine Corps SMAW, but with a rocket motor with a shorter burn time, and another developed by Sweden's FFV for Alliant Techsystems (later Honeywell), which replaced the standard HEAT warhead of the AT4/M136 with the same dual purpose warhead as used by the USMC SMAW. FFV designated the bunker buster version of the AT4 as the FFV AT8. In 1996 the McDonnell-Douglas candidate was chosen. In a unique move, the US Army ordered one batch of 1,500 then a second batch of 4,500 which were placed in contingency storage for expedited issue to units in combat.
This approach played to perceived MoD budget limitations and a realisation that the main threat on which the SR(A)1239 requirement had been predicated, the advanced R-77 derivatives, did not look like entering development any time soon. An incremental approach would allow any technological advances to be incorporated into future upgrades. These could have included multi-pulse rocket motors, thrust vectoring, hybrid rockets, gel propellants, and ductless external combustion ramjets. The Meteor team had considered an interim design, also powered by a dual-pulse solid rocket motor, but decided to offer a fully compliant solution, believing that the staged approach was not cost-effective due to concerns that upgrading from one version to the next would be more complicated than Raytheon claimed.
Shaheen I is a short-range ballistic missile (SRBM) with an optimal range of 750 km and propelled by a two-stage solid-fuel rocket motor. The Shaheen I can deliver either a conventional or a nuclear payload much faster than liquid fuelled missiles such as the Ghauri because it does not need to be fuelled before launch, reducing deployment time significantly. The Shaheen I is believed to be very accurate; Pakistani military sources state a CEP of 25 to 50 m can be achieved, partly due to a "post-separation attitude correction system." This system would allow the missile to modify its trajectory, improving accuracy and, along with the stealthy warhead shaping, giving some capability to evade missile defence systems.
In 1995, Hughes and British Aerospace collaborated on the "P3I ASRAAM", a version of ASRAAM as a candidate for the AIM-9X program. The P3I would have been very much like the AIM-132, but with the addition of thrust vectoring to provide increased agility and to carry a larger warhead to meet the requirements expressed by the AIM-9X program. The ultimate winner was the Hughes submission using the same seeker but with the rocket motor, fuze and warhead of the AIM-9M. The latter was a US Air Force stipulation to ease the logistics burden and save money by reusing as much as possible of the existing AIM-9 Sidewinder, of which 20,000 remained in the US inventory.
When Kynette was convicted largely on Parsons' testimony, which included his forensic reconstruction of the car bomb and its explosion, his identity as an expert scientist in the public eye was established despite his lack of a university education. While working at Caltech, Parsons was admitted to evening courses in chemistry at the University of Southern California (USC), but distracted by his GALCIT workload he attended sporadically and received unexceptional grades. By early 1938 the Group had made their static rocket motor, which originally burned for three seconds, run for over a minute. In May that year, Parsons was invited by Forrest J Ackerman to lecture on his rocketry work at Chapter Number 4 of the Los Angeles Science Fiction League (LASFL).
In 1591 a Belgian, Jean Beavie, described and sketched the important idea of multistage rockets, or rockets consisting of multiple stages, each igniting after the one below was depleted and decoupled. While there were many small rockets produced after years of research and experimentation, the first modern model rocket, and, more importantly, the model rocket motor, was designed in 1954 by Orville Carlisle, a licensed pyrotechnics expert, and his brother Robert, a model airplane enthusiast. They originally designed the motor and rocket for Robert to use in lectures on the principles of rocket-powered flight. But then Orville read articles written in Popular Mechanics by G. Harry Stine about the safety problems associated with young people trying to make their own rocket engines.
In March 2010 Brimstone was selected as the basis for the RAF's requirement under the Selective Precision Effects At Range (SPEAR) Capability 2 Block 1 programme. The Demonstration and Manufacture (D&M;) contract will increase the missile's performance "significantly", and convert the warhead and rocket motor to use insensitive munitions. Brimstone 2 will have an improved seeker, a more modular design and improvements to airframe and software for "an overall increase in performance with improvements in range and engagement footprint", including a "more than 200% increase" in maximum range. A five-release test campaign in October 2013 culminated in a successful strike against a pickup truck travelling at in a cluttered road environment and Brimstone 2 is planned to enter service on the Tornado in November 2015.
The Lunar Landing Research Facility was an area at NASA's Langley Research Center in Hampton, Virginia that was used to simulate Apollo Moon landings with a mock Lunar Module powered by a small rocket motor suspended from a crane over a simulated lunar landscape. Completed in 1965 at a cost of $3.5 million, the facility was used by 24 astronauts, including Neil Armstrong and Buzz Aldrin, to practice solving piloting problems they would encounter in the last 150 feet of descent to the surface of the Moon.NASA Impact Dynamics Research Facility The structure was used to facilitate "flying" a full-scale Lunar Excursion Module Simulator (LEMS). The LEMS was suspended from a -tall, -long A-frame gantry by an overhead bridge crane.
Many military analysts and enthusiasts have also postulated that since the Russian LWT is larger and heavier, to maintain the same range of CY-5 armed with lighter and shorter torpedoes of western origin, the rocket motor of Yu-8 would have to be either larger or more powerful. The existence of Yu-8 designation was first revealed in March 2014, and confirmed more than a year later by CCTV-7 in August 2015, when it aired a footage of Chinese naval war game that contained the launch of rocket propelled ASW torpedo from VLS of a Chinese warship, with designation Yu-8 torpedo assigned. Yu-8 is designed by the 705th Research Institute in Kunming, with program begun in 2002 and completed in 2006.
Members of the crew were interviewed and testimony was given by Exocet specialists (the Royal Navy had 15 surface combat ships armed with Exocets in the Falklands War). There was no evidence of an explosion, although burning propellant from the rocket motor caused fires which could not be checked as firefighting equipment had been put out of action. ;SS Atlantic Conveyor Atlantic Conveyor was a 14,950 ton roll- on, roll-off container ship launched in 1969 that had been hastily converted to an aircraft transport and was carrying helicopters and supplies, including cluster bombs.The Atlantic Conveyor - Before She Was Famous Two Exocet missiles had been fired at a frigate, but had been confused by its defences and re-targeted the Atlantic Conveyor.
It may also be used for regenerative cooling of rocket engines. Peroxide was used very successfully as an oxidizer in World War II German rocket motors (e.g. T-Stoff, containing oxyquinoline stabilizer, for both the Walter HWK 109-500 Starthilfe RATO externally podded monopropellant booster system, and for the Walter HWK 109-509 rocket motor series used for the Me 163B), most often used with C-Stoff in a self-igniting hypergolic combination, and for the low-cost British Black Knight and Black Arrow launchers. In the 1940s and 1950s, the Hellmuth Walter KG-conceived turbine used hydrogen peroxide for use in submarines while submerged; it was found to be too noisy and require too much maintenance compared to diesel-electric power systems.
In June 1937 Erich Warsitz undertook the initial flight testing of the He 112 fitted with von Braun's rocket engine. Despite the wheels-up landing and having the fuselage on fire, it proved to official circles that an aircraft could be flown satisfactorily with a back- thrust system through the rear. Also the firm of Hellmuth Walter at Kiel had been commissioned by the RLM to build a rocket engine for the He 112, so there were two different new rocket motor designs at Neuhardenberg; whereas the von Braun's engines were powered by alcohol and liquid oxygen, Walter engines had hydrogen peroxide and calcium permanganate as a catalyst. Von Braun's engine used direct combustion and created fire, the Walter produced hot vapours from a chemical reaction, but both created thrust and provided high speed.
The S-13 rocket was developed in the 1970s to meet requirements for a penetrating weapon capable of cratering runways and penetrating hardened aircraft shelters, bunkers and pillboxes, to fill a gap between 80 mm and 240 mm rockets and fulfill a role similar to the 127 mm Zuni rocket. The S-13 is conventional in layout, with a solid rocket motor and folding tail fins that provide stability after launch. The first trials were in 1973, but it was introduced only in 1983. S-13 rockets are shot from 5-tube launchers B-13L, that can be carried by most of Soviet and Russian attack and new fighter aircraft, like Sukhoi Su-17/20/22, Sukhoi Su-24, Sukhoi Su-25, Sukhoi Su-27, MiG-23BN, MiG-27, MiG-29.
The separation failed due to recontact between the Atlas - which was still under thrust - and the satellite, which only separated when the solid-fuel rocket motor intended to place NOAA-B into a circular sun- synchronous orbit fired. Because the satellite had been unable to perform the pitch-down maneuver necessary to reach its intended orbit the spacecraft ended up in a highly elliptical orbit that was unsuitable for the intended mission. Following unsuccessful attempts to correct the orbit using the satellite's attitude control thrusters, NASA pronounced the mission a failure. Unlike the earlier Nimbus 1, which was also launched into an unplanned elliptical orbit following a launch vehicle malfunction, no attempt appears to have been made to operate the spacecraft instrumentation during its remaining lifetime in orbit.
The first and second payloads were dubbed surrogate payload vehicles and matched closely the scramjet flight article, but lacked the internal flowpath and fuel system. They were designed as test rounds to validate vehicle subsystems, such as booster stack combination performance, fin sets, payload deployment mechanism, telemetry and trackability, and inlet shroud, before flight testing the more complicated scramjet flowpath, which was to undergo proof-of-concept testing in a wind tunnel prior to flight testing. The first surrogate vehicle, SPV1, was launched aboard an unguided Terrier/Improved Orion two-stage solid rocket motor stack from Wallops Island on October 18, 2003, approximately 12 months after program initiation. This had the exact outer mold line of the eventual shrouded scramjet payload and contained full onboard instrumentation and telemetry suites.
State-of-the-art systems for Quality Control and Metrology support the above manufacturing facilities. KELTEC can also undertake design and development of aerospace components, development of special processes like vacuum brazing of aluminium components, design and realisation of tools and fixtures required for production. KELTEC manufactures a number of major systems for the Geosynchronous Satellite Launch Vehicle (GSLV), including Inertial Control Systems; Control System Components; High Pressure Titanium Gas Bottles; Fuel / Oxidizer Tankages & Feed Line Systems, Liquid Propulsion Engine, Convergent Divergent Nozzles; and Launch Vehicle Solid Rocket Motor Cases. The Vikas engine is a Liquid Propellant Rocket engine which is used in the second stage of the Polar Satellite Launch Vehicle (PSLV) and the second stage and strap-on stages of the Geosynchronous Satellite Launch Vehicle (GSLV).
This was the first stage in Raytheon's incremental approach to fielding the full capability FMRAAM. The MoD had offered both teams the opportunity to propose alternative acquisition strategies which would have involved reaching the full capability on an incremental basis by initially providing an interim capability which could later be upgraded.. Raytheon's staged approach to meeting the full SR(A)1239 requirement offered an interim weapon with a capability between the AIM-120B AMRAAM and the FMRAAM. The Extended Range Air- to-Air Missile (ERAAM) had the FMRAAM seeker and guidance section mated to a dual-pulse solid propellant rocket motor. Raytheon estimated that ERAAM could be ready by the then Eurofighter ISD of 2004 and provided 80% of the FMRAAM capability but at only half the price.
However, the seekers had a very limited field of view so if the target aircraft was flying at right angles to the launcher, it would fly out of the seeker's view even as it left the launch rail. The other is that the rocket motor often burned out long before the missile reached its target (which is common with missiles, a typical motor burn time being around 4 seconds, the missile maneuvering on its velocity energy after motor burnout). One attempt to improve matters was made starting in the late 1960s by the Hawker Siddeley "Taildog", initially a private project but later officially supported as SRAAM. SRAAM's basic premise is that if pilots wanted to fire when the target was anywhere in front, then the missile should work in those situations.
Simultaneous tripropellant systems often involve the use of a high energy density metal additive, like beryllium or lithium, with existing bipropellant systems. In these motors, the burning of the fuel with the oxidizer provides activation energy needed for a more energetic reaction between the oxidizer and the metal. While theoretical modeling of these systems suggests an advantage over bipropellant motors, several factors limit their practical implementation, including the difficulty of injecting solid metal into the thrust chamber; heat, mass, and momentum transport limitations across phases; and the difficulty of achieving and sustaining combustion of the metal. In the 1960s, Rocketdyne fired an engine using a mixture of liquid lithium, gaseous hydrogen, and liquid fluorine to produce a specific impulse of 542 seconds, likely the highest measured such value for a chemical rocket motor.
As with its American counterpart, China also decided to use the same rocket motor for both the AAM and ARM. Cultural Revolution delayed the program, and it was not until the general headquarter of the People's Liberation Army Air Force made requests to the Commission for Science, Technology and Industry for National Defense (COSTIND) twice, once in 1976 and again in 1977, did the program finally gather momentum. From June 27 to June 28, 1976, under the direction of the 8th Bureau of the Machinery Ministry of the Ministry of National Defense of the People's Republic of China, the National Defense Industry Bureau of Heilongjiang held a conference on the planning of Fenglei-7. Different tasks were assigned to various establishments and factories at this two-day conference.
Development of the Me 163 HWK 109-509A engine Position of the Walter HWK 109-509A-1 rocket motor Work on the design started around 1937 under the aegis of the Deutsche Forschungsanstalt für Segelflug (DFS)—the German Institute for the study of sailplane flight. Their first design was a conversion of the earlier Lippisch Delta IV known as the DFS 39 and used purely as a glider testbed of the airframe. A larger follow-on version with a small propeller engine started as the DFS 194. This version used wingtip-mounted rudders, which Lippisch felt would cause problems at high speed. Lippisch changed the system of vertical stabilization for the DFS 194's airframe from the earlier DFS 39's wingtip rudders, to a conventional vertical stabilizer at the rear of the aircraft.
Retrieved: 10 August 2013. ; Me 262 C-2b : Single prototype [made from Me 262A Werknummer 170 074] of rocket-boosted interceptor (Heimatschützer II) with two BMW 003R "combined" powerplants (BMW 003 turbojet, with a single thrust BMW 109-718 liquid-fuelled rocket engine mounted atop the rear of each jet exhaust) for boosted thrust, only flown once with combined jet/rocket power on 26 March 1945."Video of BMW 718 rocket engine test firing on this aircraft." German Jet Power, 1 August 2013. Retrieved: 10 August 2013. ;Me 262 C-3 : Heimatschützer III – proposed version with Jumo 004 turbojet engines replaced with Walter HWK RII-211 Liquid-fuelled rocket engines. ; Me 262 C-3a : Heimatschützer IV - a rocket- boosted interceptor with a Walter HWK 109-509S-2 rocket motor housed in a permanent belly pack.
The U.S. Army is developing the XM1113 RAP to replace the M549A1 shell. The XM1113 increases range from from a 39-caliber barrel using a large high-performance rocket motor delivering nearly three times more thrust, along with a streamlined exterior profile shape for lower drag. It also has better safety by replacing the traditional TNT explosive with an insensitive munitions warhead that is less likely to be accidentally set off. To achieve accuracy at the extended ranges, the Army will look at potentially using the M1156 Precision Guidance Kit, a smart fuse that screws into standard shells to give them near-precision accuracy or the next generation PGK-AJ which will be designed to reliably achieve accuracy at ranges out to 70km.. The XM1113 is planned for Limited Rate Initial Production in 2022.
Four years later the FVPE and FVDE merge to create the Fighting Vehicles Research and Development Establishment (FVRDE). FVRDE and the Military Experimental Engineering Establishment (MEXE) at Christchurch amalgamated in 1970 to form the Military Vehicles and Engineering Establishment (MVEE). In 1984-5 Chertsey became the Vehicles Department of the Royal Armament Research and Development Establishment (RARDE) as the MVEE and the Propellants, Explosives and Rocket Motor Establishment (PERME) based at Waltham Abbey and Westcott, merged with RARDE Fort Halstead. In the wake of the ending of the Cold War, RARDE merged with other research establishments in April 1991 to form the Defence Research Agency (DRA), an executive agency of the Ministry of Defence. In turn, DRA became a division of the Defence Evaluation and Research Agency (DERA) in 1995.
Previously, such information could only be transmitted verbally by operators because the older HQ-61 system could not be easily integrated into larger air defense network, and the communication subsystem of the C3I system of HQ-61 was only consisted of wired and wireless vocal communication equipment. Another improvement is the adaptation of new rocket motor which boosted the speed of the missile by a third, from the original Mach 3 of earlier versions of HQ-61 to Mach 4 of HQ-61C. The range is also increased but exactly how much is unknown. Some Chinese enthusiasts have claimed that because of the new rocket motors adopted, the size and the weight of the missile is also reduced slightly, but this has yet to be confirmed by other credible sources.
Brahmos missile Akash missile Integrated Guided Missile Development Program, during Prahlada's tenure as its chairman, is reported to have developed several key technologies for Indian space programme related to rocket propulsion, onboard avionics, missile systems, radar systems and hypersonic flight vehicles. He is also known to have contributed to the establishment of Compact Antenna Test Range, Structural Dynamic Test Centre, Supersonic Ramjet Engine Test facility, Subsonic Ramjet Engine Test facility, 6 Component Rocket Motor Test facility, Computer Integrated Tomography, Computational Fluid Dynamics Centre, Shock Tube facility, High Temperature Material Characterization Facility, High Temperature Structural Testing and Missile System Simulation Centre for Indian Space Research Organization. He has served as the project head for Akash, a surface to air missile system and as the chief designer of many other Indian missile systems viz. Prithvi, Agni and Nag.
The LGM-30 Minuteman is a U.S. land-based intercontinental ballistic missile (ICBM), in service with the Air Force Global Strike Command. , the LGM-30G Minuteman III version is the only land-based ICBM in service in the United States and represents the land leg of the U.S. nuclear triad, along with the Trident submarine-launched ballistic missile (SLBM) and nuclear weapons carried by long-range strategic bombers. Development of the Minuteman began in the mid-1950s when basic research indicated that a solid fuel rocket motor could stand ready to launch for long periods of time, in contrast to liquid- fueled rockets that required fueling before launch and so might be destroyed in a surprise attack. The missile was named for the Colonial Minutemen of the American Revolutionary War, who could be ready to fight on short notice.
They used a wind tunnel to determine stable flight configurations, starting from zero through to supersonic speeds. In December 1934, the first two A2s where successfully launched from the North Sea island of Borkum. The first casualties in rocket development occurred in March 1934, when Dr. Wahmke and 2 assistants were killed, and another assistant was injured. A propellant fuel tank exploded, while experimenting with mixing 90% hydrogen peroxide and alcohol, before combustion. In 1935, work commenced on using rocket motors to power aircraft. In 1936, a rocket motor was installed in tail of a Heinkel He 112, with 90 seconds worth of fuel. Flight tests (now also supported by the Luftwaffe) were carried out at Neuhardenberg (a large field about 70 kilometres east of Berlin, listed as a reserve airfield in the event of war).
Its rocket motor was produced by North American Aviation and its direction could be altered during flight by its fins. They worked in two ways: by directing the air around them, or by directing the thrust by their inner parts (or both at the same time). Both the Atlas-D and Redstone launch vehicles contained an automatic abort sensing system which allowed them to abort a launch by firing the launch escape system if something went wrong. The Jupiter rocket, also developed by Von Braun's team at the Redstone Arsenal in Huntsville, was considered as well for intermediate Mercury suborbital flights at a higher speed and altitude than Redstone, but this plan was dropped when it turned out that man-rating Jupiter for the Mercury program would actually cost more than flying an Atlas due to economics of scale.
At one point he pawned Helen's engagement ring, and he often asked her family for loans. Malina recounted that "Parsons and Forman were not too pleased with an austere program that did not include at least the launching of model rockets", but the Group reached the consensus of developing a working static rocket motor before embarking on more complex research. They contacted liquid-fuel rocket pioneer Robert H. Goddard and he invited Malina to his facility in Roswell, New Mexico, but he was not interested in cooperating—reticent about sharing his research and having been subjected to widespread derision for his work in rocketry. They were instead joined by Caltech graduate students Apollo M. O. "Amo" Smith, Carlos C. Wood, Mark Muir Mills, Fred S. Miller, William C. Rockefeller, and Rudolph Schott; Schott's pickup truck transported their equipment.
The testing of this fuel resulted in another calamity, when the testing rocket motor exploded; the fire, containing iron shed fragments and shrapnel, inexplicably left the experimenters unscathed. Malina solved the problem by replacing the gasoline with aniline, resulting in a successful test launch of a JATO-equipped A-20A plane at the Muroc Auxiliary Air Field in the Mojave Desert. It provided five times more thrust than GALCIT-27, and again reduced takeoff distance by 30%; Malina wrote to his parents that "We now have something that really works and we should be able to help give the Fascists hell!" Take-off on August 12, 1941 of America's first "rocket-assisted" fixed- wing aircraft, an ERCO Ercoupe fitted with a GALCIT developed solid propellant JATO booster GALCIT Project Number 1 during the JATO experiments (date as above).
Erich Bachem's BP-20 ("Natter") was a development from a design he had worked on at Fieseler, the Fi 166 concept, but considerably more radical than the other submissions.Green 1970, p. 65. It was built using glued and nailed wooden parts with an armour- plated bulkhead and bulletproof glass windshield at the front of the cockpit. The initial plan was to power the machine with a Walter HWK 109-509A-2 rocket motor; however, only the 109-509A-1, as used in the Me 163, was available.Gooden 2006, pp. 124–127. It had a sea level thrust variable between at "idle" to at full power, with the Natter's intended quartet of rear flank- mount Schmidding SG34 solid fuel rocket boosters used in its vertical launch to provide an additional thrust for 10 seconds before they burned out and were jettisoned.
At the same time, Hellmuth Walter's experiments into hydrogen peroxide based rockets were leading towards light and simple rockets that appeared well-suited for aircraft installation. Also the firm of Hellmuth Walter at Kiel had been commissioned by the RLM to build a rocket engine for the He 112, so there were two different new rocket motor designs at Neuhardenberg: whereas von Braun's engines were powered by alcohol and liquid oxygen, Walter engines had hydrogen peroxide and calcium permanganate as a catalyst. Von Braun's engines used direct combustion and created fire, the Walter devices used hot vapors from a chemical reaction, but both created thrust and provided high speed. The subsequent flights with the He-112 used the Walter-rocket instead of von Braun's; it was more reliable, simpler to operate, and safer for the test pilot, Warsitz.
Constructed in 1976 and 1977, Mass Driver 1 was an early demonstration of the concept of the mass driver, a form of electromagnetic launcher, which in principle could also be configured as a rocket motor, using asteroidal materials for reaction mass and energized by solar or other electric power. As originally envisioned, the mass driver was intended to launch payloads from a lunar base to L5, the fifth Lagrange point in which a stable orbit can be maintained. This is where Gerard K. O'Neill proposed building a space colony (of the five Lagrange points, only L4 and L5 are truly stable, both for the real physical Earth/Moon system as well as for the ideal restricted 3-body case). The model consisted of a series of some 20 drive coils through which a small armature (called the bucket) traveled, pushed by the pulsed magnetic fields of the drive coils.
Both SARH and IR variants were heavier at and featured a larger warhead with a lethal radius of . The warhead also had a more reliable radar fuse, which greatly reduced the minimum range to for a rear-quarter engagement and for a head-on attack. Both could also be launched by and against fighter-sized targets maneuvering at 7g. The SARH R-24R featured a RGS-24 seeker head with superior ECM resistance and lock-on- after-launch capability, which avoided interference from the launching aircraft's own radar as the missile passed by its nose. This feature, along with a larger rocket motor and a lengthening of the missile's inertial phase of flight, gave it a 30% longer range than its predecessor: 17 km and 4 km against a forward or rear-facing target at low altitudes, and 35 km and 20 km respectively at high altitudes.
Such a setup makes use of the R-107 portable radio transceiver. One of the more unique aspects of the 2S4 is their nuclear capability. Development of tactical nuclear munitions for the type was initiated relatively late in the service cycle of the vehicle, in 1967, and resulted in the 3BW4 round using a 3B4 nuclear projectile with a yield of approx. 2 kt. This was improved on three years later with the development of a rocket-assisted 3WB11 nuclear round (using a 3B11 projectile with an RD-14 warhead and propelled by a 3M15 rocket motor). Development of a nuclear warhead for the M-240 was technologically limited for a period of time by the small bore of the weapon; miniaturization had only recently allowed for the reduction of the diameter of a nuclear device to a sufficiently small size so as to be used in a field artillery system.
The lower cost and lighter weight of the LAW, combined with a scarcity of modern heavy armored targets and the need for an individual assault weapon versus an individual anti-armor weapon, made it ideal for the type of urban combat seen in Iraq and mountain warfare seen in Afghanistan. In addition, a soldier can carry two LAWs on a mission as opposed to a single AT4. M72A7 firing trainer, showing Picatinny rail The U.S. Marine Corps Systems Command at Quantico, Virginia placed a $15.5-million fixed contract order with Talley Defense for 7,750 M72A7s, with delivery to be completed in April 2011. The M72A7 LAW is an improvement on previous versions, including an improved rocket motor for a higher velocity to accurately engage targets past 200 meters, an insensitive munitions warhead to reduce the likelihood of an accidental explosion, and a Picatinny rail to mount laser pointers and night sights.
With Challenger, an O-ring that should not have eroded at all did erode on earlier shuttle launches. Yet managers felt that because it had previously eroded by no more than 30%, this was not a hazard as there was "a factor of three safety margin" (in reality, the part had failed, and there was no safety factor.) Morton-Thiokol designed and manufactured the SRBs, and during a pre-launch conference call with NASA, Roger Boisjoly, the Thiokol engineer most experienced with the O-rings, pleaded with management repeatedly to cancel or reschedule the launch. He raised concerns that the unusually low temperatures would stiffen the O-rings, preventing a complete seal during flexing of the rocket motor segments, which was exactly what happened on the fatal flight. However, Thiokol's senior managers, under pressure from NASA management, overruled him and allowed the launch to proceed.
The Redl-Zipf V-2 rocket facility (code name Schlier) in central Austria between Vöcklabruck and Vöcklamarkt was for V-2 rocket motor testing after Raxwerke test equipment had been moved from Friedrichshafen. The facility tested V-2 combustion chambers' compatibility with turbopumps since the rocket did not have a controller for reducing the turbopumping of propellant into the chamber if pressure became too high. The World War II facility used forced labor of the Schlier-Redl-Zipf subcamp of the Mauthausen-Gusen concentration camp and included a liquid oxygen generation plant in a nearby tunnel. After an August 1944 explosion at the liquid oxygen plant stopped Schlier production, the third V-2 liquid oxygen plant (5000 tons/month) was built at a slate quarry at Lehesten near the Mittelwerk (turbopump/chamber compatibility testing for Mittelwerk production was also performed at the Lehesten facility).
In 1988/9 NASA was planning on replacing the post-Challenger SRBs with a new Advanced Solid Rocket Motor (ASRM) to be built by AerojetLeary, Warren E., "NASA Picks Lockheed and Aerojet", New York Times, April 22, 1989 at a new facility, designed by subcontractor, RUST International, on the location of a cancelled Tennessee Valley Authority nuclear power plant, at Yellow Creek, Mississippi. The ASRM would be slightly wider (the booster's diameter would be increased from 146 inches to 150 inches) and have 200,000 pounds of extra propellant, and have produced additional thrust in order to increase shuttle payload by about 12,000lb, so that it could carry modules and construction components to the ISS. They were expected to be safer than the post-Challenger SRBs. The initial $1.2Bn contract was to be for 12 motors, with an option for another 88 at maybe another $1bn.
Thrusters, Star 48 booster and the internal components of the Forward Equipment Module The spacecraft's attitude control (orientation) was designed to be three-axis stabilized, including during the firing of the Star 48B solid rocket motor (SRM) used to place it into orbit around Venus. Prior to Magellan, all spacecraft SRM firings had involved spinning spacecraft, which made control of the SRM a much easier task. In a typical spin mode, any unwanted forces related to SRM or nozzle mis-alignments are cancelled out. In the case of Magellan, the spacecraft design did not lend itself to spinning, so the resulting propulsion system design had to accommodate the challenging control issues with the large Star 48B SRM. The Star 48B, containing 2,014 kg of solid propellant, developed a thrust of ~89,000 Newton (20,000 lbf) shortly after firing; therefore, even a 0.5% SRM alignment error could generate side forces of 445 N (100 lbf).
Grand Central signed a contract to produce the solid rocket motor for the Project Mercury escape tower. This motor was ultimately produced by Lockheed when the Redlands plant was sold to Lockheed Aircraft Corporation. Grand Central was acquired by Lockheed in February 1960 to become the Lockheed Propulsion Company as a research and production facility of solid fuel rockets and solid rocket propellant. On 8 September 1964, LPC President Robert F. Hurt launched a Zero Defects Program, aiming at a goal of defect-free performance in all phases of LPC operation. Representatives of Southern California firms supplying the company met at the Redlands headquarters on 16 September and were urged to pledge their support of the program. Copies of the Zero Defects Program were distributed to company representatives and were being sent to each of the company’s major suppliers across the country.Staff, “LPC Suppliers Support Zero Defects Plan,” The San Bernardino Daily Sun, San Bernardino, California, Thursday 17 September 1964, Volume LXXI, Number 15, page C-4.
The Hs 298 was designed specifically to attack Allied bomber aircraft and was the first missile designed specifically for air-to-air use. It was to be carried on special launch rails by Dornier Do 217s (five missiles) or Focke-Wulf Fw 190s (two missiles) and carried 48 kg (106 lb) of explosive, slightly more than the 40.8 kg warheads carried by unguided BR 21 heavy-calibre air-launched rockets in use from the spring of 1943 onwards. The Hs 298 was a mid-wing monoplane with tapered swept back wings and it had a single horizontal stabiliser with twin vertical fins. It was powered by a Henschel-designed rocket motor built by Schmidding as the 109–543; it had two stages, the first high velocity stage was designed to leave the launch aircraft at 938 km/h (585 mph), in the second stage the speed was brought back to 682 km/h (425 mph) to give a maximum range of about .
A concept model was displayed in 2015 as a TC-1 modified with an imaging infrared seeker, folding control surfaces, free-rolling tailfins, a more- powerful rocket motor, and a trainable launcher with either eight or sixteen all up rounds and a FLIR sensor on its left-hand side. The design was finalized in 2017, which sees the missile's aft section enlarged in diameter to accommodate more rocket fuel and its four rolling tailfins replaced with eight smaller, fixed ones. The launchers have also evolved into two more- distinct variants: one that is integrated into the ship's central combat management system (as well as being completely reliant on it for targeting information) and has a capacity of 24 missiles but no onboard sensors, and an "autonomous" version that houses only 12 missiles but has its own rotating search/tracking radar and FLIR/Electro-Optical sensor, along the same concept as the SeaRAM system.
Another factor that had influenced the cancellation was the hesitancy of the RAF to back either project, the service had apparently wanted to wait until after flight evaluations had been conducted before it was to make any determination on its preference. During late 1953, Saunders-Roe commenced work upon a derivative design, which was designated as the SR.177. Brennan considered the lack of an onboard radar on the SR.53 and the Avro 720 to have been a vital flaw despite it not being a requirement of the specification, leaving the pilot dependent on his own vision and direction being provided by ground-based radar control. Brennan had also been dissatisfied with the use of the turbojet engine; he believed that a larger jet engine should match the steady supersonic cruising speed of the aircraft, and that the rocket motor should be mainly used for high performance climbs, turns, and rapid acceleration instead.
The U.S. Navy's Naval Air Weapons Station China Lake organization was then brought into the project to provide expertise on existing rocket motor power. Lockheed proceeded with work to structurally reinforce the C-130 airframe to withstand rocket forces and to develop a passenger restraint system for 150 persons. Renner is an ASROC thrust vector control system expert. The resulting XFC-130H aircraft were modified by the installation of 30 rockets in multiple sets: eight forward-pointed ASROC rocket motors mounted around the forward fuselage to stop the aircraft, eight downward-pointed Shrike rockets fuselage-mounted above the wheel wells to brake its descent, eight rearward-pointed MK-56 rockets (from the RIM-66 Standard missile) mounted on the lower rear fuselage for takeoff assist, two Shrikes mounted in pairs on wing pylons to correct yaw during takeoff transition, and two ASROCs mounted at the rear of the tail to prevent it from striking the ground from over-rotation.
The AGM-88E was designed to improve the effectiveness of legacy HARM variants against fixed and relocatable radar and communications sites, particularly those that would shut down to throw off anti-radiation missiles, by attaching a new seeker to the existing Mach 2-capable rocket motor and warhead section, adding a passive anti-radiation homing receiver, satellite and inertial navigation system, a millimeter-wave radar for terminal guidance, and the ability to beam up images of the target via a satellite link just seconds before impact. This model of the HARM will be integrated onto the F/A-18C/D, F/A-18E/F, EA-18G, and Tornado ECR aircraft, and later on the F-35 (externally). In September 2015, the AGM-88E successfully hit a mobile ship target in a live-fire test, demonstrating the missile's ability to use antiradiation homing and millimeter-wave radar to detect, identify, locate, and engage moving targets. In December 2019, the German Air Force ordered the AARGM.
Seabourn Spirit in Rovinj, Croatia The motor of a rocket- propelled grenade (RPG), shown after striking the Seabourn Spirit On 5 November 2005 at 5:50 am, while Spirit was underway 115 km off the coast of Somalia with 115 passengers, the ship was attacked by two pirate speedboats launched by a mother ship.Bomb experts tackle missile, The Herald Sun, 8 November 2005 Machine guns were fired as well as rocket-propelled grenades at the cruise ship, and the remains of an RPG's rocket motor wedged itself in the wall of a roomRebuilding Africa tourism, Christian Science Monitor, 8 November 2005 and was disarmed by sailors from after the attack.Cruising into hell, The Daily Telegraph (Australia), 8 November 2005 It was reported that a second RPG bounced off the stern. No passengers were injured, but the ship's master-at- arms, Som Bahadur Gurung was hit by shrapnel whilst attempting to combat the raiders with a Long Range Acoustic Device (LRAD).
These rockets arrived too late to see service during the war, but were used post-war. The 2.36 inch (60 mm) Smoke Rocket M10 and its improved subvariants (M10A1, M10A2, M10A4) used the rocket motor and fin assembly of the M6A1, but replaced the anti-tank warhead with a white phosphorus (WP) smoke head. WP smoke not only acts as a visibility screen, but its burning particles can cause severe injuries to human skin. The M10 was therefore used to mark targets, to blind enemy gunners or vehicle drivers, or to drive troops out of bunkers and dugouts.. The 2.36-Inch Incendiary Rocket T31 was an M10 variant with an incendiary warhead designed to ignite fires in enemy-held structures and unarmored vehicles, or to destroy combustible supplies, ammunition, and materiel; it was not often utilized. The original M1 and M1A1 rocket launchers were equipped with simple fixed sights and used a launch tube without reinforcements. During the war, the M1A1 received a number of running modifications.
The XOV would then light its rocket motor (aerospike engines, similar to those used by the Lockheed Martin X-33), and could achieve both suborbital and orbital flight; one source quoted by Aviation Week estimates the XOV could reach an orbit of above the Earth, depending on payload and mission profile. The XOV would then reenter the atmosphere and glide back to any landing site where it would land horizontally on a conventional runway. This combination of jet- powered mothership and a smaller rocket-powered spaceplane resembles the civilian Tier One spaceplane system as well as NASA's X-15, but capable of much higher velocities and thus of attaining orbit. Readers are cautioned to examine the challenges involved in supersonic separation of vehicles as opposed to the more common subsonic separation of ordnance from aircraft, but this separation from the belly might be easier than from the top, which proved to be problematic on the Lockheed D-21/M-21.
In the early stages of World War II (1942), a complete prototype BI-1 (also known as The Devil's Broomstick), made its first several flights. The I-270 shared the BI-1's simple, tapered fuselage, bubble canopy, wing design, and dual-chambered bipropellant rocket motor. On the other hand, it was considerably larger than the BI-1 and featured short, reinforced wings (from the RP-218) and a raised T-tail which aircraft such as the Tupolev ANT-8 proved, offered better landing control than the BI-1's more traditional fighter layout. While there seems little doubt that the BI-1 influenced the design of the I-270, the latter appears far from a direct descendant of the former, and much closer to being a Soviet version of the Me 263, sharing very similar fuselage, canopy and landing gear layouts, while adding a conventional stabilizer surface atop the vertical tail, absent on the German design.
Harbin Ship Engineering Academy (HSEA, 哈尔滨船舶工程学院), the predecessor of Harbin Engineering University was tasked with the design of airframe, control surfaces and engine, and the 349th Factory was tasked with manufacturing these parts, as well as the development of propellant. HESA and Harbin Industrial University were tasked to design the fuse, seeker and flight control system while 254th Factory was tasked to manufacture these parts. On October 28, 1978, Central Military Commission of the People's Republic of China (CMC) formally gave its concurrence to develop Fenglei-7 ARM based on AGM-45, and additional assignment were given to the 349th factory and 254th Factory: the former was tasked to develop ground support equipment while the latter was tasked to develop the test equipment of the part it would manufacture. In March 1980, two prototypes with FG101 rocket motor successfully completed its test flight at the Base # 31 of People's Liberation Army, with results meeting the original requirements.
Von Braun's ideas rode a publicity wave that was created by science fiction movies and stories. Von Braun with President Dwight D. Eisenhower, 1960 In 1952, von Braun first published his concept of a crewed space station in a Collier's Weekly magazine series of articles titled "Man Will Conquer Space Soon!". These articles were illustrated by the space artist Chesley Bonestell and were influential in spreading his ideas. Frequently, von Braun worked with fellow German-born space advocate and science writer Willy Ley to publish his concepts, which, unsurprisingly, were heavy on the engineering side and anticipated many technical aspects of space flight that later became reality. The space station (to be constructed using rockets with recoverable and reusable ascent stages) would be a toroid structure, with a diameter of ; this built on the concept of a rotating wheel-shaped station introduced in 1929 by Herman Potočnik in his book The Problem of Space Travel – The Rocket Motor.
Avro Blue Steel nuclear missile (front) at the Midland Air Museum Avro Blue Steel missile (side view) at the Midland Air Museum behind the wing of an Avro Vulcan bomber Rear view of Blue Steel missile at RAF Cosford aerospace museum, showing the twin-chamber "Stentor" rocket motor Blue Steel was the result of a Ministry of Supply memorandum from 5 November 1954 that predicted that by 1960 Soviet air defences would make it impossible for V bombers to attack with nuclear gravity bombs. The answer was for a rocket-powered, supersonic missile capable of carrying a large nuclear (or projected thermonuclear) warhead with a range of at least . This would keep the bombers out of range of Soviet ground-based defences installed around the target area, allowing the missile to "dash" in at high speed. There would have to be a balance between the size of the warhead, the need for it to be carried by any of the three V-bomber types in use, and that it should be able to reach Mach 3.
The Sergeant was originated during 1948 at JPL Due to the large workload of the Corporal program rocket motor development for the Sergeant was transferred to the Redstone Division of the Thiokol Corporation.Cagle, Mary T., History of the Sergeant Weapon System, p 11, U.S. Army Missile Command, Redstone Arsenal, Alabama, 1972 Due to the failure of the Sergeant program to develop rapidly the early Sergeant was terminated in April 1951.Cagle, Mary T., History of the Sergeant Weapon System, p 15, U.S. Army Missile Command, Redstone Arsenal, Alabama, 1972 Another Army missile program, the Hermes program had developed the Hermes A2 another solid fueled missile.Cagle, Mary T., History of the Sergeant Weapon System, p 14, U.S. Army Missile Command, Redstone Arsenal, Alabama, 1972 The Hermes RV-A-10 (A2) was successful but not pursued with the motor serving as the inspiration for future solid rocket motors.Cagle, Mary T., History of the Sergeant Weapon System, p 15, U.S. Army Missile Command, Redstone Arsenal, Alabama, 1972 JPL, cautioned against making Sergeant a “crash” program as with Corporal.
Powered by rockets, certain designs were a blend of "aircraft and projectile" in the words of Nazi propaganda, with a vertical takeoff like a missile launch system attempted for the first time in a manned aircraft, such as the Bachem Ba 349 Natter —in which the test-pilot died in the first flight. The Natter and Julia designs were expected to climb to their ceiling at vertical or near vertical angles, while the Arado design was a parasite aircraft that needed to be carried by a "mother" plane, with the unpowered BV 40 needing an aerotow into action. These small interceptors had fuel for only a few minutes for combat action and landing was fraught with hazards, for after spending the rocket fuel the center of gravity would shift substantially making the aircraft difficult to handle at best and uncontrollable at worst. In the Natter or in the Fliegende Panzerfaust the pilot had to bail out at the end of a mission while the rear fuselage containing the rocket motor descended under its own parachute.
Following atmospheric re-entry, the traditional capsule-like spacecraft from the Mercury, Gemini, and Apollo series had very little control over where they landed. A steerable spacecraft with wings could significantly extend its landing envelope. However, the vehicle's wings would have to be designed to withstand the dynamic and thermal stresses of both re-entry and hypersonic flight. A proposed solution eliminated wings altogether: design the fuselage body itself to produce lift. NASA's refinements of the lifting body concept began in 1962 with R. Dale Reed of NASA's Armstrong Flight Research Center. The first full-size model to come out of Reed's program was the NASA M2-F1, an unpowered craft made of wood. Initial tests were performed by towing the M2-F1 along a dry lakebed at Edwards Air Force Base California, behind a modified Pontiac Catalina.Classical Pontiac and NASA Later the craft was towed behind a C-47 and released. Since the M2-F1 was a glider, a small rocket motor was added in order to extend the landing envelope.
His flight test of this rocket plane, the only one by an Allied pilot using the rocket motor, was accomplished unofficially: it was deemed to be more or less suicidal due to the notoriously dangerous C-Stoff fuel and T-Stoff oxidizer combination. Commenting to a newspaper in September 2015 he recalled, > To me it was the most exciting thing on the horizon, a totally new > experience. I remember watching the ground crew very carefully before take- > off, wondering if they thought they were waving goodbye to me forever or > whether they thought this thing was going to return. The noise it made was > absolutely thunderous and it was like being in charge of a runaway train; > everything changed so rapidly and I really had to have my wits about me. Brown flight-tested all three of the German jet designs to see front-line action in the war: the Messerschmitt Me 262 and the Arado Ar 234, each type powered by Junkers Jumo 004 engines, and the BMW 003-powered Heinkel He 162 turbojet combat aircraft.
Cape Canaveral on July 3, 2002. CONTOUR launched on a Delta 7425 (a Delta II Lite launch vehicle with four strap-on solid-rocket boosters and a Star 27 third stage) on July 3, 2002, at 6:47:41 UT (2:47:41 a.m. EDT) from Cape Canaveral Air Force Station. It was launched into a high-apogee Earth orbit with a period of 5.5 days. Following a series of phasing orbits, the Star 30 solid rocket motor was used to perform an injection maneuver on August 15, 2002, to put CONTOUR in the proper trajectory for an Earth flyby in August 15, 2003 followed by an encounter with comet Encke on November 12, 2003, at a distance of 100 to 160 km and a flyby speed of 28.2 km/s, 1.07 AU from the Sun and 0.27 AU from Earth. During the August 2002 injection maneuver, the probe was lost. Three more Earth flybys would have followed, in August 14, 2004, February 10, 2005, and February 10, 2006. On June 18, 2006, CONTOUR would have encountered comet Schwassmann-Wachmann-3 at 14 km/s, 0.95 AU from the Sun and 0.33 AU from Earth.
In the Tornado, however, Frazer-Nash hydraulic trapezes projected the missile out into the slipstream prior to motor ignition. This widened the missile's firing envelope by ensuring that the launch was not affected by turbulence from the fuselage. Skyflash was therefore converted to the 5000 TEMP series to incorporate the Frazer-Nash recesses in the body of the missile, Launch Attitude Control electronics in the autopilot section and improved wing surfaces. The Tornado-Skyflash combination became operational in 1987 with the formation of the first Tornado F.3 squadron.Flight 1 October 1988 From 1988 a further modification (6000 series) nicknamed "SuperTEMP" included the Hoopoe rocket motor to change the missile's flight profile from boost-and-glide (with a 4-second burn) to boost- sustain-glide (7-second burn), increasing its range and maneuverability. In RAF service the missiles were usually carried in conjunction with four short- range air-to-air missiles, either AIM-9 Sidewinders or ASRAAMs. A version with an active Thomson CSF-developed radar seeker and inertial mid-course update capability, Skyflash Mk 2 (called Active Skyflash), was proposed for both the RAF and Sweden.
During his career, Williams has conducted dozens of industrial and governmental consultations including (1) papermaking calender rolls, for which "he is considered, by virtue of his extensive work in the field, to be the nation's leading expert on stresses in rotary paper dryers"; (2) the first automated system for installing recessed highway lane delineation reflectors; (3) an earthquake analysis of the 500 KV bus system of the British Columbia (Canada) hydroelectric power generating station and the design of an isolation system to protect its electrical lines during seismic activity; (4) the design of composite rocket motor casings; (5) the residual-life prediction of composite aircraft structures; (6) the stress analysis of a high-speed optical pulsing system; (7) the stress analysis of pelvic implants and bone stints for the Orthopædic Unit of the Massachusetts General Hospital; (8) the effect of ultrasonic irradiation on the enhancement of composite fabrication; (9) the ultrasonic NDE delineation of strength and rupture modes in adhesively bonded joints; (10) the design of deepwater mooring composite systems for offshore oil platforms; (11) an NDE regimen for the structural acceptance of composite automotive leaf springs; among others.
At the DSEi conference in September 2007 it was announced the UK MoD was funding a study by MBDA to investigate a replacement for the Rapier and Sea Wolf missiles. The Common Anti-Air Modular Missile (CAMM) would share components with ASRAAM.. Common components include the very low signature rocket motor from Roxel, the warhead and proximity fuze from Thales. The Common Data Link (CDL) is the small "black box" that sits on top of the mast, especially clear in pictures of FLAADS(L) although it doesn't necessarily have to use the two-way data link to the launch vehicle, so, it could take mid-course corrections from any number of suitably equipped land or air platforms and then switch to active homing when it gets close enough. The original launch platform could have even moved by the time the missile hits. In 2014, India's defence ministry signed a £250m ($428m) contract with MBDA to equip its Sepecat/Hindustan Aeronautics Jaguar strike aircraft with the company's ASRAAM short range air-to-air missile. MBDA's offering overcame competition from competitors including Rafael's Python-5 missile, emerging as the winner in 2012.
Blohm & Voss designers began to consider airborne missiles late in 1938, even before the outbreak of war. First of these to be developed was the Bv 143, a glide bomb with rocket booster. Trials began in 1939.Hermann Pohlmann, Chronik Eines Flugzeugwerkes 1932-1945 (Story of an aircraft manufacturer, 1932-1945), Motor Buch, 2nd Impression, 1982, pp.194-196. By 1941, Allied merchant ships were slow and easy targets for German coastal bombers, but were proving increasingly well-equipped with anti-aircraft artillery, making short-range attacks prohibitively costly. Interest was raised in the development of a stand off weapon to engage unarmored merchant ships from beyond the range of the Bofors 40 mm gun. The BV 143 was one of several stand off bomb and missile designs researched by the Blohm & Voss Naval Engineering Works for this anti- shipping role.Sterrenburg, Frithjof A.S. The Oslo Report: Nazi secret weapons forfeited. wlhoward.com. Retrieved on June 6, 2009. The Bv 143 was designed to be air-dropped from beyond the range of antiaircraft guns, glide towards the target, engage its solid rocket motor below the line of fire of guns, and commence a short (30 second, maximum) high speed dash to the target, striking above the waterline.
The proliferation of surface-to-air missiles (SAMs) has made the Suppression of Enemy Air Defence a priority for any modern air force intending offensive action. Knocking out air search radars and fire control radars is an essential part of this mission. ARMs must have sufficient range that the launch platform is out of range of the SAMs, high speed to reduce the risk of being shot down and a seeker that can detect a range of radar types, but they do not need a particularly big warhead. The Soviet Union's first ARM was developed by the Raduga OKB engineering group responsible for the Soviet Union's missiles for heavy bombers. The Kh-22P was developed from the 6-tonne Kh-22 (AS-4 'Kitchen') missile. Experience gained with this led in 1973 to the Kh-28 (AS-9 'Kyle') carried by tactical aircraft such as the Su-7B, Su-17 and Su-24. It had Mach 3 capability and a range, greater than the contemporary AGM-78 Standard ARM. The Kh-28 was succeeded by the Kh-58 in 1978, which has similar speed and range but replaces the dual- fuel rocket motor with a much safer RDTT solid propellant.
The Ministry was enthusiastic on this concept; in May 1951, all interested companies were asked to examine this arrangement. The SR.53 was a sleek aircraft with a sharply- pointed nose, delta-like wing, and a T-tail. It was powered by a combination of a single Armstrong Siddeley Viper turbojet engine and de Havilland Spectre rocket engine, the exhausts of which were mounted one atop the other on the rear fuselage beneath the tail.Winchester 2005, p. 223.Wood 1975, pp. 55–56. Saunders-Roe had originally proposed to develop their own rocket motor to power the SR.53, having not been initially pleased with the performance of either the Spectre nor the Screamer; however, it was recognised that this would take substantial development work. By October 1952, the basic outline of the aircraft had been finalised, replacing the combined flap and ailerons of earlier proposed with slotted flaps, the Viper engine was relocated upwards and was to be fitted with a straight jet pipe rather than a bifurcated one, the tailplane was also moved to a higher position at the top of the fin. On 30 October 1952, the company received an Instruction to Proceed from the Ministry for the completion of three prototypes.
In February 1999 Raytheon added another interim level to their staged approach. The AIM-120B+ would feature the ERAAM/FMRAAM seeker and guidance section but attached to the AIM-120B solid rocket motor.. This would be ready for Eurofighter's 2004 ISD and could be updated to the ERAAM or FMRAAM configurations in 2005 and 2007 by swapping the propulsion system and updating the software. At the 1999 Paris Air Show the French Defence Minister expressed his country's interest in joining the Meteor project, putting further pressure on the UK to use BVRAAM as a focus for the consolidation of the European guided weapons industry.. The French offered to fund up to 20% of the development if Meteor won the UK contest. Inter-governmental letters of intent were exchanged between the UK and French defence ministers in advance of signing the official MoU prepared by Germany, Italy, Spain, Sweden, and the UK.. The French officially joined the programme in September 1999. In July 1999 the Swedish Air Force announced that it would not be funding development of Meteor due to a shortfall in the defence budget.. However, this decision was not expected to affect Sweden's participation in the programme, with funding being found from other sources.

No results under this filter, show 634 sentences.

Copyright © 2024 RandomSentenceGen.com All rights reserved.