Along the way, inertial guidance systems and GPS keep it on track, while external sensors, including lidar and cameras, watch for obstacles and potential landing sites should something go wrong.
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Helped by Concorde's two onboard inertial guidance systems, the crew guided the aircraft along the carefully-mapped trajectory and met the eclipse within 103 second accuracy of the planned rendezvous.
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Once it's inside a building, the drone uses an inertial guidance system and 2D laser scanner to find its way around, and a thermal imaging camera to seek out fires and humans.
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So for the time being North Korea has to program the coordinates into the missile's inertial guidance system, and trust that taking measurements like acceleration, speed, and angle of ascent, its internal computer can determine where the target is.
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Then it integrates the velocity to calculate the current position. Inertial guidance is difficult without computers. The desire to use inertial guidance in the Minuteman missile and Project Apollo drove early attempts to miniaturize computers. Inertial guidance systems are now usually combined with satellite navigation systems through a digital filtering system.
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The missile uses inertial guidance, resulting in a relatively poor CEP of 1,500 meters.
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The Sagnac effect is employed in current technology. One use is in inertial guidance systems. Ring laser gyroscopes are extremely sensitive to rotations, which need to be accounted for if an inertial guidance system is to return accurate results. The ring laser also can detect the sidereal day, which can also be termed "mode 1".
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The third flight test, the following June, utilized the inertial guidance system for the first time. It was a successful flight.
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For the Office of Naval Research, they worked on inertial guidance systems,Iberall, A.S. A new class of inertial guidance systems. Report to Office of Naval Research (ONR), Contract NONR 3778(00), 1962-63, 1965-66, 1968-69. hydrodynamics equations,Iberall, A.S. Contributions toward solution of the equations of hydrodynamics. Part A. The continuum limitations of fluid dynamics.
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In April 1959 she entered the Philadelphia Naval Shipyard, and received an inertial guidance system. Redfin became a laboratory and training ship for the testing of inertial guidance systems used in Polaris submarines. She preceded the first ballistic missile submarine as flagship of Submarine Squadron 14. After searching for the lost in April 1963, she was reclassified AGSS-272 on 28 June.
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Paul O. Larson. "Titan III Inertial Guidance System". AIAA Paper No. 65-306. AIAA Second Annual Meeting, 26–29 July 1965, San Francisco, CA.
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Astro-inertial guidance is a sensor fusion-information fusion of inertial guidance and celestial navigation. It is usually employed on submarine-launched ballistic missiles. Unlike silo-based intercontinental ballistic missiles, whose launch point does not move and thus can serve as a reference, SLBMs are launched from moving submarines, which complicates the necessary navigational calculations and increases circular error probable. This stellar-inertial guidance is used to correct small position and velocity errors that result from launch condition uncertainties due to errors in the submarine navigation system and errors that may have accumulated in the guidance system during the flight due to imperfect instrument calibration.
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The vehicle would enter a roll during its glide period to limit aerodynamic heating. Guidance was provided by a Honeywell inertial guidance unit.Brulle 2008, p. 94.
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One squadron of the 38th Wing, the 71st Tactical Missile Squadron, operated the B model of the Mace with an inertial guidance system and longer range, and remained active.
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R-29 Vysota Р-29 Высота (height, altitude) is a family of Soviet submarine- launched ballistic missiles, designed by Makeyev Rocket Design Bureau. All variants use astro-inertial guidance systems.
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At a predetermined altitude above the target, the terminal phase would begin. A velocity control maneuver (pull up, pull down) was executed under inertial guidance control to slow down the RV and achieve the proper impact velocity. The radar correlator system was activated and the radar scanned the target area. Radar return data was compared to pre-stored reference data and the resulting position fix information was used to update the inertial guidance system and generate RV steering commands.
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2004 Project Pigeon was American behaviorist B.F. Skinner's attempt to develop a pigeon- guided missile. The first U.S. ballistic missile with a highly accurate inertial guidance system was the short-range Redstone.
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In such a system, besides classic flight controls, many autopilots incorporate thrust control capabilities that can control throttles to optimize the airspeed. The autopilot in a modern large aircraft typically reads its position and the aircraft's attitude from an inertial guidance system. Inertial guidance systems accumulate errors over time. They will incorporate error reduction systems such as the carousel system that rotates once a minute so that any errors are dissipated in different directions and have an overall nulling effect.
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In the case of Gemini 10 the need for the maneuver was a result of misalignment of the inertial guidance platform, causing axial drift of the approach trajectory, prior to closing to docking distance.
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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.
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Advanced Inertial Reference Sphere The Advanced Inertial Reference Sphere (AIRS) is a highly accurate inertial guidance system designed for use in the LGM-118A Peacekeeper ICBM which was intended for precision nuclear strikes against Soviet missile silos.
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MISTRAM was used in the development and testing of inertial guidance system for the Minuteman ballistic missile, and subsequently was used for testing the Gemini spacecraft and the Saturn V launch system. With the decommissioning of the MISTRAM X-band interferometer at the Air Force Eastern Test Range in 1971, the flight-test community did not have a conventional ground-based range-instrumentation system better than, or comparable to, the inertial guidance systems whose performance was being assessed. This was true in the intervening years preceding GPS development and deployment.
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Ravenstein, p. 212. The SAC Missile Chronology gives 15 June as the operational date. SAC Missile Chrononology, p. 40. The Titan II was an improvement over the Titan I. It used storeable liquid propellant and all inertial guidance.
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OTR-21 Tochka ( ("point"); ) is a Soviet tactical ballistic missile. Its GRAU designation is 9K79; its NATO reporting name is SS-21 Scarab. It is transported in a 9P129 vehicle and raised prior to launch. It uses an inertial guidance system.
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Development of Mace "B" missiles began in 1954. The Mace "A" and Mace "B" were identical in all dimensions. The Mace "B" included a jam- proof inertial guidance system (designated TM-76B) and had a flight range exceeding 1,300 miles.
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The Atlas missiles A through D used radio guidance: the missile sent information from its inertial system to a ground station by radio, and received course correction information in return. The Atlas E and F had completely autonomous inertial guidance systems.
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Inertial navigation is significantly less accurate; the JDAM achieves a published Circular Error Probable (CEP) of under GPS guidance, but typically only under inertial guidance (with free fall times of 100 seconds or less).U.S. Air Force Factsheets: Joint Direct Attack Munition The Joint Direct Attack Munition (JDAM) is a guidance kit that converts unguided bombs, or "dumb bombs", into all-weather "smart" munitions. JDAM-equipped bombs are guided by an integrated inertial guidance system coupled to a Global Positioning System (GPS) receiver, giving them a published range of up to . JDAM-equipped bombs range from .
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Minutes after launch, the missile is outside the atmosphere and on a sub-orbital trajectory. The Guidance System for the missile was developed by the Charles Stark Draper Laboratory and is maintained by a joint Draper/General Dynamics Mission Systems facility. It is an Inertial Guidance System with an additional Star-Sighting system (this combination is known as astro-inertial guidance), which is used to correct small position and velocity errors that result from launch condition uncertainties due to errors in the submarine navigation system and errors that may have accumulated in the guidance system during the flight due to imperfect instrument calibration.
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This gives it sufficient range to strike targets as far away as Russia, India, and American bases in the Pacific. The missile uses an inertial guidance system, resulting in a large CEP of 1,500 meters. As of 2017, 10-15 launchers are deployed.
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The B611MR is a semi-ballistic surface-launched anti-radar missile first advertised in 2014. It uses GPS-inertial guidance and wideband passive radar. The missile is capable of flying flattened trajectory and performing pre-programmed maneuvers to reduce the chance of interception.
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Alacrán Missile, derived from the earlier Condor IAIII The Alacrán missile was a short range ballistic missile derived from the Condor Missile Program. Derived from the Condor IAIII prototype, the Alacrán missile had shorter stabilization fins, an inertial guidance system, and a 1000CAP1 cluster warhead.
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Another form of an AGV guidance is inertial navigation. With inertial guidance, a computer control system directs and assigns tasks to the vehicles. Transponders are embedded in the floor of the work place. The AGV uses these transponders to verify that the vehicle is on course.
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Target coordinates are fed into the missile before launch, and the initial flight phase is conducted under inertial guidance. At a distance of 10 km from the target the television guidance system is activated. An operator aboard the aircraft visually identifies the target and locks the missile onto it.
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This failure was attributed to a faulty inertial guidance system that had not been rigorously tested due to the rushed production schedule. Parts of the Polyus project's hardware were re-used in Kvant-2, Kristall, Spektr and Priroda Mir modules, as well as in the ISS module Zarya.
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Antiship cruise missile "Granit" Range estimates vary between 400 kmKuznetsov Class (Type 1143.5) Aircraft Carrier, Russia - Naval-Technology.com to 500 km to 550–625 km. The guidance system is mixed- mode, with inertial guidance, terminal active radar homing guidance and also anti-radar homing. Mid-course correction is probable.
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Gyroscopes can be used to construct gyrocompasses, which complement or replace magnetic compasses (in ships, aircraft and spacecraft, vehicles in general), to assist in stability (bicycles, motorcycles, and ships) or be used as part of an inertial guidance system. MEMS gyroscopes are popular in some consumer electronics, such as smartphones.
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The A-100 is a 300 mm, 10-tube multiple rocket launcher developed by Beijing- based China Academy of Launch Vehicle Technology (CALT, also known as 1st Space Academy) for the Chinese PLA ground forces. It is a derivative of Weishi Rockets WS-1 with simple cascade terminal inertial guidance.
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It was in between these two tests that the inertial guidance system was developed and implemented for testing. July 1, 1959: AX-11 at Cape Canaveral from a launch pad: this launch was successful, but pieces of the missile detached causing failure. It did show that the new guidance systems worked.
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The DF-15 uses a solid fuel, single-stage rocket. It is vertically launched from an eight-wheeled transporter erector launcher (TEL). The missile's trajectory is guided using small thrusters and an inertial guidance system on the warhead. The warhead is only a tenth of the size of the missile body.
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Unguided rocket artillery is notoriously inaccurate and slow to reload compared to artillery. A multiple rocket launcher helps compensate for this with its ability to launch multiple rockets simultaneously and a greater rate of fire. Modern rockets can use GPS or inertial guidance to combine the advantages of rockets with high accuracy.
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Guidance systems also vary greatly. Low-cost systems use a radar altimeter, barometric altimeter and clock to navigate a digital strip map. More advanced systems use inertial guidance, satellite guidance and terrain contour matching (TERCOM). Use of an automatic target recognition (ATR) algorithm/device in the guidance system increases accuracy of the missile.
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He served as a research associate in MIT's Instrumentation Laboratory from 1948 to 1952. The head of the instrumentation lab was Dr. C. Stark Draper, the father of inertial guidance and navigation. Under Draper, Atwood contributed numerous patents to the science and became an expert in navigation and guidance electronics and systems engineering.
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It is also much more difficult to predict where the warhead will land, since while the re-entry vehicle is on orbit, it is a very small object with few distinguishing marks and is hard to detect. Moreover, since the warhead can be commanded to land anywhere along the orbit's ground track, even detecting the warhead while it is in orbit does not allow accurate prediction of its intended target. Early R-36s used radio ground guidance on the reasoning that it would be more accurate than inertial guidance, however, the engineers eventually scrapped this when they decided that inertial guidance was good enough. The structure and design of the fractional orbit bombardment system were similar to a conventional R-36 ICBM system.
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The astro-inertial guidance uses star positioning to fine-tune the accuracy of the inertial guidance system after launch. As the accuracy of a missile is dependent upon the guidance system knowing the exact position of the missile at any given moment during its flight, the fact that stars are a fixed reference point from which to calculate that position makes this a potentially very effective means of improving accuracy. In the Trident system this was achieved by a single camera that was trained to spot just one star in its expected position. If it was not quite aligned to where it should be, it would indicate that the inertial system was not precisely on target and a correction would be made.
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Astra's older design resembled Matra Super 530D and Vympel R-77 in a few aspects. Astra is long with a diameter of and weighs . It uses an inertial guidance system driven by a fibre optic gyroscope with terminal guidance through active radar homing. It is capable of receiving course corrections through a secure data link.
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Minco's combination etched foil heater-platinum wire sensors were used on many NASA projects including the 1976 Viking Lander (heated soil samples) and Skylab (Inertial Guidance System). Of note, NASA investigated Minco due to the erratic gyros on Skylab causing spacewalks to replace the IGS. The heater-sensor was found not to be the problem.
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The Kh-32 missile is made in the Kh-22 case and their geometrical dimensions are completely identical. Due to the reduced warhead increased the volume of tanks. Installed another, more powerful engine. A new interference- free radar inertial guidance system with radio command correction and reference to the terrain (from altimeter) was installed.
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In 1968, the 2802nd Inertial Guidance and Calibration Group was inactivated and replaced by the Aerospace Guidance and Metrology Center (AGMC). The Calibration and Metrology Division was changed to the Directorate of Metrology on 8 November 1968. Newark Air Force Station was renamed Newark Air Force Base in June 1987. During the 1990s privatization took place at Newark AFB.
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The CM-602G is a land-attack version of the C-602. It is advertised as having a range of , a penetrating blast/fragmentation warhead, and an inertial guidance system using GPS data which may be augmented to provide man-in-the-loop control. The missile was revealed at the China International Aviation & Aerospace Exhibition in 2012.
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160–161 as the A model of the Mace was retired and the last missiles were shipped to Eglin Air Force Base. Florida to be used as targets.One squadron of the 38th Wing, the 71st Tactical Missile Squadron, operated the B model of the Mace with an inertial guidance system and longer range, and remained active.
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In 1943, production of the V-2 rocket began in Germany. It had an operational range of and carried a warhead, with an amatol explosive charge. It normally achieved an operational maximum altitude of around , but could achieve if launched vertically. The vehicle was similar to most modern rockets, with turbopumps, inertial guidance and many other features.
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Fifth, the V-2 program had provided vehicles for upper atmosphere and biological research. Additionally many components had to be manufactured due to shortages and deteriorated condition. Most notable was the inertial guidance system and mix computer. After the termination of V-2 flights by Hermes there were 5 final flights by V-2s from White Sands.
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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 .
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The inertial system provides short term data, while the satellite system corrects accumulated errors of the inertial system. An inertial guidance system that will operate near the surface of the earth must incorporate Schuler tuning so that its platform will continue pointing towards the center of the earth as a vehicle moves from place to place.
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Rochowicz, Robert (2018) (in Polish). Rakiety operacyjne i taktyczne w Siłach Zbrojnych PRL. „Poligon” No. 1/2018(62), p. 56-63, ISSN 1895-3344 Like the V-2, the R-11 relied on inertial guidance, and its flight was controlled by four graphite vanes in the engine exhaust, that were active only while the motor was burning.
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1\. 1963-1970, engineer for flight control analysis, Martin Marietta, Denver, Colo. 2\. 1970-1975, manager, Titan IIIC inertial guidance system, Martin Marietta, Denver, Colo. 3\. 1975-1980, Program Manager, Transtage Project, and Director of Space Systems, Martin Marietta, Denver, Colo. 4\. 1980-1982, Vice President of Business Development, Martin Marietta Denver Aerospace, Denver, Colo. 5\.
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Henry Earl Singleton (November 27, 1916 – August 31, 1999) was an American electrical engineer, business executive, and rancher/land owner. Singleton made significant contributions to aircraft inertial guidance and was elected to the National Academy of Engineering. He co-founded Teledyne, Inc., one of America's most successful conglomerates and was its chief executive officer for three decades.
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The missile was a two-stage rocket with inertial guidance, which could not be corrected after launch. The missile carried a nuclear depth bomb warhead of up to 10 kilotons in yield. The warhead could detonate at a depth of up to 200 m and had a lethal radius of 1.2 to 1.5 km against a submarine target.
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Many civilian aircraft use inertial guidance using a ring laser gyroscope, which is less accurate than the mechanical systems found in ICBMs, but which provide an inexpensive means of attaining a fairly accurate fix on location (when most airliners such as Boeing's 707 and 747 were designed, GPS was not the widely commercially available means of tracking that it is today). Today guided weapons can use a combination of INS, GPS and radar terrain mapping to achieve extremely high levels of accuracy such as that found in modern cruise missiles. Inertial guidance is most favored for the initial guidance and reentry vehicles of strategic missiles, because it has no external signal and cannot be jammed. Additionally, the relatively low precision of this guidance method is less of an issue for large nuclear warheads.
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Rocketdyne, Ramo-Wooldridge, AC Spark Plug, Bell Laboratories and General Electric were engaged as the subcontractors for the rocket engine, technical coordination, inertial guidance system, radio guidance system, and re-entry vehicle respectively. The first missile was delivered to Patrick Air Force Base on 26 October 1956. After four unsuccessful attempts, the first successful test flight took place on 20 September 1957.
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Signals from the accelerometers were then integrated to keep track of the spacecraft's velocity and position. The IMU was derived from the guidance system developed by Draper for the Polaris missile. Inertial guidance systems are not perfect and Apollo system drifted about one milliradian per hour. Thus it was necessary to realign the inertial platform periodically by sighting on stars.
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It is equipped with an inertial guidance system with terminal guidance. It can be equipped with a variable payload up to 500 kg, and can carry single HE explosive or cluster sub-munition warheads. It has a launch weight of 1,750 kg. It uses a single-stage solid propellant engine and has a length of 9.75m and a width of 0.56m.
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Autonetics D37D digital computer, part of the NS20 Navigation System. The Autonetics Division of Rockwell International produced all three generations of the Minuteman Missile Guidance Set (MGS). The MGS includes the Gyro Stabilized Platform (GSP), Digital Control Unit (DCU), Missile Guidance Set Control (MGSC) and the Amplifier Assembly. The MGS is an inertial guidance system which directs the flight of the missiles.
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The early integrated circuits were SSI. SSI circuits were crucial to early aerospace projects, and aerospace projects helped inspire development of the technology. Both the Minuteman missile and Apollo program needed lightweight digital computers for their inertial guidance systems. Although the Apollo guidance computer led and motivated integrated-circuit technology, it was the Minuteman missile that forced it into mass-production.
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Mindling & Bolton, p. 234 The squadron was equipped with the B model of the Mace, which was deployed so that a single crew was able to launch all missiles located at a single launch site directly from the underground bunkers in which they were stored. The 873rd was the first squadron equipped with the TM-76B, which used an inertial guidance system.Mindling & Bolton, p.
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Over longer distances the missile is controlled by an inertial guidance auto pilot with occasional encoded data link updates from the launch aircraft's radar on changes in spatial position or G of the target. As the missile comes within of its target, the missile switches to its active radar mode. The host radar system maintains computed target information in case the target breaks the missile's lock-on.
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The dimensions and the payload capacity remain the same. Hatf-IA is believed to have entered service in 1995. The Hatf IB represents the final evolution of the Hatf I missile system. It includes an inertial guidance system that considerably improves the accuracy of the missile and is otherwise identical to the Hatf IA, retaining the maximum range of 100 km and payload of 500 kg.
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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).
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Self-propelled howitzer with a 52 caliber barrel, 800 hp diesel engine & gross weight of 35 tonnes. It is deployed only with the People's Liberation Army. The PLZ-05 can fire the WS-35 shell, a guided munition with accuracy of and a max range reported to be . It is guided using Beidou Navigation Satellite System, the Chinese version of global positioning system, and inertial guidance.
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Other terms used to refer to inertial navigation systems or closely related devices include inertial guidance system, inertial instrument, inertial measurement unit (IMU) and many other variations. Older INS systems generally used an inertial platform as their mounting point to the vehicle and the terms are sometimes considered synonymous. Comparison of accuracy of various navigation systems. The radius of the circle indicates the accuracy.
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LSI leveraged its new expertise in controls, instruments and navigation systems into a steadily increasing share of government and general aviation contracts for research and development, as well as system delivery. Notable innovations since then include inertial guidance systems, "hands off" landing systems, the telemetry and navigational instrumentation for the Apollo Moon missions, and the flight controls for the Lockheed L-1011 commercial aircraft.
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Vanguard had no fins, and the first and second stages were steered by gimbaled engines. The second stage housed the vehicle's telemetry system, the inertial guidance system and the autopilot. The third stage was spin-stabilized, with the spin imparted by a turntable on the second stage before separation. The Vanguard's second stage served for decades as the Able and Delta second stage for satellite launch vehicles.
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Surveying instrumentation and techniques improved over the ensuing centuries. Models for the figure of the earth improved in step. In the mid- to late 20th century, research across the geosciences contributed to drastic improvements in the accuracy of the figure of the Earth. The primary utility of this improved accuracy was to provide geographical and gravitational data for the inertial guidance systems of ballistic missiles.
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In order to increase easy of use Košava 1 is launched from container thus enabling easy refiling of launcher. In order to increase accuracy it has inertial guidance with TV/IR homing head. After launching wings spread and missiles fly to attitude with rocket engine. After it has reached minimum range and appropriate attitude depending on target range continues flight towards target using lift generated by wings.
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In these cases, some other form of guidance is used to get the missile into the range where the signal is stronger. Examples would be radio control (command guidance) or inertial guidance systems, which fly the missile closer to the target. In this role, these are known as "midcourse guidance" systems. In practice, terminal guidance systems are often optical or active radar systems, in an effort to greatly increase accuracy.
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It had a thrust of 22,600 lb-force. By 1953–1954 six A-3Bs were test launched at White Sands, five successfully. One of the most important developments of the Hermes A-3 program was the first inertial guidance system tested on a ballistic missile. None of the Hermes missiles became operational, but did provide experience in the design, construction, and handling of large-scale missiles and rocket engines.
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The relied on inertial navigation while submerged and its UGM-27 Polaris missiles relied on inertial guidance to find their targets. Project areas that have surfaced in the news referred to Draper Laboratory's core expertise in inertial navigation, as recently as 2003. More recently, emphasis has shifted to research in innovative space navigation topics, intelligent systems that rely on sensors and computers to make autonomous decisions, and nano-scale medical devices.
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The SMKB (Smart-MK-Bomb) is a guidance kit that turns a standard Mk 82 (500 lbs) and Mk 83 (1.000 lbs) into a Precision-guided weapon, respectively called SMKB-82 and SMKB-83. The kit provides extended range up to and are guided by an integrated inertial guidance system coupled to three satellites networks, relying on wireless to handle the flow of data between the aircraft and the munition.
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All of these rockets used liquid propellant. The A4b used an inertial guidance system, while the A9 would have been controlled by a pilot. They started from a non-mobile launch pad. Following World War II von Braun and other lead Nazi scientists were secretly transferred to the United States to work directly for the U.S. Army through Operation Paperclip developing the V-2 into the weapon for the United States.
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The Titan II contained one W-53 nuclear warhead in a Mark 6 re-entry vehicle with a range of . The W-53 had a yield of 9 megatons. This warhead was guided to its target using an inertial guidance unit. The 54 deployed Titan IIs formed the backbone of America's strategic deterrent force until the LGM-30 Minuteman ICBM was deployed en masse during the early to mid-1960s.
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Work on the Redstone led to development of the first high-precision inertial guidance system on the Redstone rocket. As director of the Development Operations Division of the Army Ballistic Missile Agency, von Braun, with his team, then developed the Jupiter-C, a modified Redstone rocket. The Jupiter-C successfully launched the West's first satellite, Explorer 1, on January 31, 1958. This event signaled the birth of America's space program.
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Inertial motion capture technology is based on miniature inertial sensors, biomechanical models and sensor fusion algorithms. The motion data of the inertial sensors (inertial guidance system) is often transmitted wirelessly to a computer, where the motion is recorded or viewed. Most inertial systems use inertial measurement units (IMUs) containing a combination of gyroscope, magnetometer, and accelerometer, to measure rotational rates. These rotations are translated to a skeleton in the software.
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As mission range extended to thousands of miles, bombers started incorporating inertial guidance and star trackers to allow accurate navigation when far from land. These systems quickly improved in accuracy, and eventually became accurate enough to handle the bomb dropping without the need for a separate bombsight. This was the case for the 1,500 foot accuracy demanded of the B-70 Valkyrie, which lacked any sort of conventional bombsight.
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The RIM-66C was the first version of the Standard missile two. The missile became operational in 1978 with the Aegis combat system fitted to the . The RIM-66D was the SM-2 medium-range block I version for the New Threat Upgrade. The SM-2 incorporates a new autopilot giving it inertial guidance in all phases of flight except for the terminal intercept where semi-active radar homing is still used.
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The promise of lighter, higher-yield weapons was later confirmed during the Operation Castle nuclear test series, that began in March 1954. As a result, the stringent accuracy requirement for Atlas was reduced to between 2 and . This revision would also permit slashing the missile's weight and diameter. As a further benefit, the lower accuracy requirement eased the Atlas's guidance problem and prompted an investigation of an advanced, on board, all-inertial guidance system.
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The Valkyrie was designed to be a high-altitude Mach 3 bomber with six engines. Harrison Storms shaped the aircraftHeppenheimer 2006, pp. 96, 112, 116. with a canard surface and a delta wing, which was built largely of stainless steel, sandwiched honeycomb panels, and titanium. The XB-70 was designed to use supersonic technologies developed for the Mach 3 SM-64 Navaho, as well as a modified form of the Navaho's inertial guidance system.
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Chuck agrees, regretting not having any "me time" after the departure of Jill Roberts in the previous episode. As Chuck sits in the van, Casey and Sarah Walker infiltrate the GLA disguised as lab technicians. Suddenly, a masked villain rappels from the ceiling, knocks Casey over, and steals an inertial guidance system. Casey gives chase, tackling the agile man on the agency's front lawn and removing the man's mask to reveal Ty Bennett, who escapes.
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Shkval is supposed to have a rocket-type engine, but in the recent years has emerged publications from Russia and China about a "hydro ramjet" that use hydro reactive metal fuel (HRF) used for high speed torpedo. Available schemes of this type of engine shows also a dedicated steam circuit for the supercavitation generating head. Early designs may have relied solely on an inertial guidance system. The initial design was intended for nuclear warhead delivery.
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According to another source, one A3 reached a maximum downrange of and maximum altitude of . With each launch a failure, von Braun and Dornberger looked for the cause. At first there was some thought of an electrostatic charge that prematurely set off the parachute, but this was largely disproved. Ultimately, the failures were attributed to the inadequate design of the rocket's experimental inertial guidance system and minor instabilities in the body and fin design.
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The Mk 117 digital fire-control system provided targeting information to the missile prior to launch. After being fired, the capsule would float to the surface where the rocket would ignite and its fins would deploy. An inertial guidance system would direct the missile to the general location of the target. Initial plans were to have the surface-launched version operate in a similar manner: launched from the Mk 41 vertical launching system.
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The Redundant Strap Down Inertial Navigation System/Inertial Guidance System of GSLV housed in its equipment bay guides the vehicle from lift-off to spacecraft injection. The digital auto- pilot and closed loop guidance scheme ensure the required altitude maneuver and guide injection of the spacecraft to the specified orbit. The GSLV can place approximately into an easterly Low Earth orbit or (for the Mk. II version) into an 18° geostationary transfer orbit.
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It is unknown if it is a conversion of an existing dumb bomb, a field add-on kit for existing bombs, or a new and integrated weapon. It resembles a typical dumb with an added dorsal housing and a pair of fold-out wings. There is also an extended nose. The guidance system is unknown but has been described as both GPS-based, inertial guidance and possibly having some form of optical terminal guidance.
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The RSM-54 is a three-stage liquid-propellant ballistic missile with a range of . The warhead consists of four to ten multiple, independently targeted re-entry vehicles (MIRVs) each rated at . The missile uses stellar inertial guidance to provide a circular error probable (CEP) of . The CEP value is a measure of the accuracy of strike on the target and is the radius of the circle within which half the strikes will impact.
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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.
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This force creates a net torque on the ship, turning it so that it no longer points vertically. The pitchover angle varies with the launch vehicle and is included in the rocket's inertial guidance system. For some vehicles it is only a few degrees, while other vehicles use relatively large angles (a few tens of degrees). After the pitchover is complete, the engines are reset to point straight down the axis of the rocket again.
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AN/APG-63 radar A multimission avionics system includes a head-up display (HUD), advanced radar, AN/ASN-109 inertial guidance system, flight instruments, ultra high frequency communications, and tactical air navigation system and instrument landing system receivers. It also has an internally mounted, tactical electronic warfare system, Identification friend or foe system, an electronic countermeasures suite, and a central digital computer.Gunston 1986, p. 194. The HUD projects all essential flight information gathered by the integrated avionics system.
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The seeker uses a simple inertial guidance system through the midcourse, and homes during the terminal approach using a laser designator. Other versions offer anti-radiation seeking, or GPS guidance. The precision guided kit includes the addition of tail fins and an in-flight control system. Combining the laser seeker with the FAT warhead produces a capable long-range anti-tank missile that is faster and much less expensive than traditional platforms like the AGM-114 Hellfire.
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The High Virgo missile was a single-stage weapon, powered by a solid-fueled Thiokol TX-20 rocket, and was equipped with an advanced inertial guidance system derived from that of the AGM-28 Hound Dog cruise missile.McMurran 2008, p.266 Four tailfins in a cruciform arrangement provided directional control. The missile was developed by Lockheed, utilising components developed for several existing missiles to reduce the cost of the project, and also to reduce the development time required.
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Development of the A3 can be traced at least to February 1935 when Major Ernst Ritter von Horstig sent General Karl Becker a budget of almost half a million marks for the construction of two new test stands at Kummersdorf. Included were mobile test rigs, small locomotives, and office and storage space. The A3 plans called for a rocket with an inertial guidance system and a thrust engine.Neufeld, M.J. Von Braun: Dreamer of Space, Engineer of War.
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Viper was designed as a "self-guided standoff munition" for use in the Suppression of Enemy Air Defenses ("Iron Hand") role.Knacck 1978, p. 274 The Viper, based on the AGM-12C/E Bullpup missile, was fitted with an inertial guidance system,Parsch 2002 and had a radar altimeter-based fuse to ensure an airburst of the weapon's bomblet payload. It was developed in competition with the AGM-79 Blue Eye missile,Committee on Armed Services 1968, p. 125.
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Submarine-Launched Variant of China's YJ-18 Supersonic Anti-Ship Missile Emerges - Navyrecognition.com, 2 October 2017 The missile can be launched from vertical launching systems,United States Navy Office of Naval Intelligence: The PLA Navy, p.16 and possibly from submarine torpedo tubes. Chinese media claims the missile has an inertial guidance system using BeiDou Navigation Satellite System data, and carries a high-explosive warhead or an anti-radiation warhead to destroy electronics at short range.
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In 1966, the A model of the Mace was retired and the missiles were shipped to Eglin Air Force Base. Florida to be used as targets. However, the 71st Tactical was the only squadron of the wing that operated the B model of the Mace with an inertial guidance system and longer range, and it remained active when the rest of the wing was inactivated, transferring to the 36th Tactical Fighter Wing at Bitburg in October 1965.Ravenstein, pp.
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The Atlas guidance system was to be a combination of an on-board autonomous system and a ground-based tracking and command system. The self-contained system finally prevailed in ballistic missile applications for obvious reasons. In space exploration, a mixture of the two remains. In the summer of 1952, Dr. Richard Battin and Dr. J. Halcombe "Hal" Laning, Jr., researched computational based solutions to guidance and undertook the initial analytical work on the Atlas inertial guidance in 1954.
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Autonetics D-17 guidance computer from a Minuteman-I missile. Previous long-range missiles used liquid fuels that could only be loaded just prior to firing. The loading process took from 30 to 60 minutes in typical designs. Although lengthy, this was not considered to be a problem at the time, because it took about the same amount of time to spin up the inertial guidance system, set the initial position, and program in the target coordinates.
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Dials setting these values were used to zero out any visible drift, which resulted in accurate wind measurements, formerly a very difficult problem. Ball disk integrators were used in the analog guidance computers of ballistic missile weapon systems as late as the mid 1970s. The Pershing 1 missile system utilized the Bendix ST-120 inertial guidance platform, combined with a mechanical analog computer, to achieve accurate guidance. The ST-120 provided accelerometer information for all three axes.
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Astra (Sanskrit: "weapon") is an all weather beyond-visual-range air-to-air missile developed by the Defence Research and Development Organisation. It is the first air-to-air missile developed by India. It features mid-course inertial guidance with terminal active radar homing. Astra is designed to be capable of engaging targets at varying range and altitudes allowing for engagement of both short-range targets at a distance of and long-range targets up to a distance of .
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At this time China was under U.S. pressure not to supply the M Dongfeng series of missiles to Pakistan. It is believed by experts that possibly with Chinese connivance and facilitation, the latter was forced to approach North Korea for missile transfers. Reports indicate that North Korea was willing to supply missile sub-systems including rocket motors, inertial guidance systems, control and testing equipment for US$50 million. It is not clear what North Korea got in return.
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Kormoran 1 on a German Navy F-104G in 1984 A German Tornado IDS launching a Kormoran The AS.34 Kormoran (cormorant) is a German-produced anti-ship missile. The Kormoran uses an inertial guidance system for the midcourse phase, switching to active radar homing during the terminal attack phase. It carries a 165 kg (363 lb) delay-fused warhead, designed for 90mm of penetration prior to detonation. The maximum range is 23 km (~14 miles).
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Fırat University has been trying to develop computers, ballistics search, inertial guidance in connection with defense research during the last twenty years. In the past 20 years, Fırat University's educational programs have expanded beyond the physical sciences and engineering into social sciences like economics, linguistics, political science, medical science, dental surgery, architecture and management. Fırat University is characterised by its unique study and research opportunities. Social issues can be studied in the real- life-lab setting of East Anatolia.
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This report was referred to the FBI for the "unauthorized disclosure of information classified 'Secret'". An investigation into the disclosure was dropped when the US Air Force told the FBI that the disclosed information could not be declassified for purposes of prosecution.FBI files on Philip J. Klass published online by The Computer UFO Network on the World Wide Web (CUFON). Klass wrote some of the first articles on inertial guidance systems, infrared missile guidance, and microelectronics.
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With radios, Delco Electronics was losing market share rapidly to a foreign invasion of radios into GM dealerships. Also the anticipated technology transfer to commercial grade inertial guidance systems was not making much progress. Atwood was determined to change all this. Atwood initiated programs in Kokomo to turn back the foreign invasion of radios with improved products with new features and functions that made the radio more integrated with the vehicle controls (such as integration with steering wheel controls).
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The earliest integrated circuits were a happy accident. They were constructed not to save money, but to save weight, and permit the Apollo Guidance Computer to control an inertial guidance system for a spacecraft. The first integrated circuit logic gates cost nearly $50 (in 1960 dollars, when an engineer earned $10,000/year). Much to the surprise of many involved, by the time the circuits were mass-produced, they had become the least-expensive method of constructing digital logic.
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While deemed to be useful in astronavigation, but this time inertial guidance systems were becoming increasingly available; these devices would eventually displace the use of astronavigation and thus aircraft would increasingly be built without astrodomes or other accommodations for this means of navigation. Early jet-powered bombers, such as the English Electric Canberra and the V bombers, while furnished with internal navigation systems, would often still be navigable by astronavigation. During the early 1960s, astrodomes were still being employed in the USMC Lockheed Hercules GV-1 (later designated as C-130); the navigator was able to employ a bubble sextant hung from a hook in the middle of the dome. The USMC operated its Aerial Navigation School at MCAS Cherry Point, NC with graduates receiving their designation and wings as an Aerial Navigator. The Lockheed SR-71 Blackbird, a high speed aerial reconnaissance aircraft, was furnished with a complex array of navigation systems, which included an astro- inertial guidance system (ANS) to correct deviations produced by the inertial navigation system via a series of celestial observations.
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Ever since, more and more armed forces adopted weapons that are guided by electronics, human assistance or inertial guidance for wide range of purposes, including UCAVs. The first weapon confirmed to reach outer space were the German V-2 rockets in 1944, which were also among the first long-range ballistic missiles. V-2 rockets also led to the Space Race and eventually the Apollo 11 moon landing. The first atomic bombs were tested and used in warfare in 1945.
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The inertial guidance system allows the missile to be used as an artillery rocket against enemy military encampments or storage depots etc. The missile system is designed to be used like an artillery system, with 5–6 missiles fired simultaneously at the target area. Being a ballistic missile the Hatf-IB would reach its target much quicker than an ordinary artillery shell giving the target little warning to take evasive action. Hatf-IB was first flight tested in February 2000.
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A particular practical benefit of the design was the quiet submerged launch system, which used the missile's own buoyancy to lift it to the surface. The missile entered service in March 1980, but was never installed in any other submarine other than the K-140, and was out of service by 1991. Apparently this missile was also capable of performing the duties of SLCMs, as the targeting distance could be varied drastically. It was the first Soviet ballistic missile using astro-inertial guidance.
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It is carried on an AKU-58-1 launch pylon. The Kh-59ME has an external turbofan engine below the body just forward of the rear wings, but retains the powder-fuel accelerator. It also has a dual guidance system consisting of an inertial guidance system to guide it into the target area and a television system to guide it to the target itself. The 36MT turbofan engine developed for the Kh-59M class of missiles is manufactured by NPO Saturn of Russia.
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9M317ME missiles can be fired at 2-second intervals, while its reaction (readiness) time is up to 10 s. The missile was designed to be single-staged, inertial guidance, radio control mid-course update and terminal semi-active radar homing. The tail surfaces have a span of 0.82 m when deployed after the missile leaves the launch container by a spring mechanism. Four gas-control vanes operating in the motor efflux turn the missile towards the required direction of flight.
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Honeywell's ring laser gyroscope (RLG) system was at the heart of a patent lawsuit regarding the special optical coatings applied to mirrors inside the inertial guidance system. In 1990 Litton Industries, who Honeywell had just won a $400,000 settlement from, sued Honeywell for $2 billion. The lawsuit was both for patent claims and alleged unfair business practices that led to Honeywell's monopolization of the RLG market. Later Litton increased the claim to $6 billion on the basis patent infringement was willful.
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The JDAM is not a stand-alone weapon; rather it is a "bolt-on" guidance package that converts unguided gravity bombs into precision-guided munitions (PGMs). The key components of the system consist of a tail section with aerodynamic control surfaces, a (body) strake kit, and a combined inertial guidance system and GPS guidance control unit. The JDAM was meant to improve upon laser-guided bomb and imaging infrared technology, which can be hindered by bad ground and weather conditions.
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Modern SARH systems use continuous-wave radar (CW radar) for guidance. Even though most modern fighter radars are pulse Doppler sets, most have a CW function to guide radar missiles. A few Soviet aircraft, such as some versions of the MiG-23 and MiG-27, used an auxiliary guidance pod or aerial to provide a CW signal. The Vympel R-33 AA missile for MiG-31 interceptor uses SARH as the main type of guidance (with supplement of inertial guidance on initial stage).
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The Predator was a fire- and-forget weapon utilizing a system called predicted line of sight (PLOS). In this system the operator tracks the target for a short time (at least 2 seconds and no more than 12) prior to launch. This data is then combined with known missile flight performance to predict a flightpath that will intercept the target's course, and program the missile's autopilot system. An inertial guidance unit was incorporated into the autopilot to compensate for crosswind and other factors encountered in flight.
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The Hatf–I is an unguided ballistic missile mounted on a TEL vehicle with a range of ; it has capability of both carrying the conventional and nuclear payloads of . The programme initially led by the SRC after developing the Hatf–IA, an improved version with same payload."Pakistan derives its first 'Hatf' missiles from foreign space rockets," The Risk Report, October 1995, p. 5 Its final evolution led to the development of the Hatf–IB which includes a proper computer inertial guidance system with an extended range.
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An SM-2ER on the rail inside . There was a plan to build a nuclear armed standard missile mounting a W81 nuclear warhead as a replacement for the earlier Nuclear Terrier missile (RIM-2D). The USN rescinded the requirement for the nuclear armed missile in the 1980s, and the project was canceled.Raytheon RIM-67 Standard ER The Standard can also be used against ships, either at line-of-sight range using its semi-active homing mode, or over the horizon using inertial guidance and terminal infrared homing.
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On 1 February 1959, it was redesignated the Heath Maintenance Annex of the Dayton Air Force Depot. Authorization to begin construction was given by public law on 9 June 1960. The Dayton Air Force Depot personnel associated with the Air Force calibration program began their moves to the Heath Maintenance Annex in April 1962, and by June, most had been relocated to Heath, Ohio. In June, the name was also changed to the 2802nd Inertial Guidance and Calibration Group under HQ Air Force Logisitics Command.
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Von Steubens ballistic missile system was upgraded a second time in the early 1980s to use Trident I (C4) ballistic missiles. These missiles were also retrofitted to 11 other SSBNs of the James Madison and Benjamin Franklin classes, replacing their Poseidon missiles, and also were the first missiles carried by the early s. Trident missiles were three-stage missiles that provided for increased range along with advances in inertial guidance systems. Von Steuben continued making strategic deterrent patrols into the early 1990s with the Trident I missile.
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Four test flights of the High Virgo missile were conducted. Due to development problems, the first two did not include the inertial guidance system, instead they were fitted with a simple autopilot guiding the weapon on a pre-programmed course. Launched from its B-58 carrier aircraft at high altitude and supersonic speed, the initial flight, conducted on September 5, 1958, was a failure when the missile's controls malfunctioned. The second test, three months later, proved more successful, with the missile flying over a range of nearly .
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Saphir had a launch mass of , a diameter of and a length of . Saphir was launched 15 times, from July 5, 1965 to January 27, 1967. The Diamant rocket, which carried the first French satellite, Asterix-1, into orbit, was developed from the Saphir with the addition of a third stage. After the successful launch of Diamant, Saphir rockets were used to test technologies for France's burgeoning intercontinental ballistic missile development—namely radio and inertial guidance, warhead separation, and ablative heat shielding of a re-entry vehicle.
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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.
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Since the 1970s modern ballistic weapons have seen the development of far more accurate targeting technologies, particularly due to improvements in inertial guidance systems. This set the stage for smaller warheads in the hundreds-of-kilotons-range yield, and consequently for ICBMs having multiple independently targetable reentry vehicles (MIRV). Advances in technology have enabled a single missile to launch a payload containing several warheads. The number of independent warheads capable of deployment from ballistic missiles depends on the weapons platform the missile is launched from.
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The University of Gaziantep has been developing computers, ballistics search, inertial guidance in connection with defense research. The University of Gaziantep's educational programs have expanded beyond the physical sciences and engineering into social sciences like economics, linguistics, political science, medical science, dental surgery, architecture and management. Social issues can be studied in the real-life lab setting of Southeast Anatolia. Main research areas are the environment, energy (especially in solar and nuclear energy), material, construction, and information/communication technology, ballistics search and social sciences.
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To allow these ranges, the Matador was powered by a small turbojet engine in place of the V-1's much less efficient pulsejet. Matador was armed with the W5 nuclear warhead, essentially an improved version of the Fat Man design that was lighter and had a smaller cross section. A single U.S. Air Force group, 1st Pilotless Bomber Squadron, was armed with the weapon, keeping them on alert with a six-minute launch time. It could be easily retargeted, unlike weapons using inertial guidance systems.
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Since FY1991, the has started developing the range-extended version of ASROC to exploit the greater direct-path range of new low-frequency sonar (OQS-XX: later OQS-2x series). After that, following the end of the Cold War, it became a complete performance improvement version including not only simple range extension but also improvement in responsiveness. The missile is fired from Mk 41 vertical launching system and the maximum speed reaches supersonic. It is controlled by inertial guidance system which uses a thrust vector control.
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It is also planned to be equipped with the new "Izdeliye 305" or LMUR (Light Multi-role Unified Missile) multi purpose missile, designed for use against air and ground targets, and fitted with inertial guidance in initial flight, with mid-course updates by an operator before the target is acquired by the missile's own seeker, giving a range of . The Mi-28NM made its maiden flight in October 2016. ;Mi-28D: Simplified daylight operation version. Similar to Mi-28N, but without top-mounted radar and FLIR.
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Missile guidance is by GPS or Inertial guidance system for pinpoint accuracy at ranges of up to . An optional laser guidance enhancement will enable the weapon to hit at even higher precision, enable limited 'man in the loop' capability and address moving targets. Each missile is 1800 mm long, has a 150 mm diameter and a weight of 63 kg. The missile system could receive the location of enemy positions from unmanned air systems in the battlespace; and according to the received data, the JUMPER would launch a number of missiles.
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Astronautics Corporation of America (ACA) is a US supplier, designer, and manufacturer of avionics equipment to airlines, governments, commercial and defense aircraft manufacturers, and other avionics systems integrators, established in 1959. Products are used for air, sea, ground, missile and space applications. Over 150,000 aircraft have been equipped with Astronautics equipment. Astronautics products electronic flight instrument systems, electronic flight bags, engine indicating and crew alerting systems, network server systems, multifunction displays, mission and display processors and systems, flight directors, flight control systems, inertial guidance systems, air data computers, and autopilots.
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TechJect told investors that The Dragonfly would have the ability to be equipped with up to twenty environmental sensors (including GPS and cameras), dependent on electronics package. At minimum, the unit was to be equipped with a 3-axis accelerometer and a 3-axis gyroscope as is required for controlled flight through inertial guidance. At most, the unit was envisioned to equip approximately 20 sensors, including 3-axis accelerometers, 3-axis gyroscopes, 3-axis magnetometers, an ambient light sensor, an ambient humidity sensor, and a differential/absolute pressure sensor.
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Some highly advanced robots such as ASIMO and Meinü robot have particularly good robot navigation hardware and software. Also, self-controlled cars, Ernst Dickmanns' driverless car, and the entries in the DARPA Grand Challenge, are capable of sensing the environment well and subsequently making navigational decisions based on this information, including by a swarm of autonomous robots. Most of these robots employ a GPS navigation device with waypoints, along with radar, sometimes combined with other sensory data such as lidar, video cameras, and inertial guidance systems for better navigation between waypoints.
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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.
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The ultimate objective is to develop a missile that has an objective range of over , using a technologically advanced Taiwanese power plant with superior fuel efficiency and mission endurance, and possibly a more advanced and lighter miniaturized warhead. The HF-2E Block I missile uses inertial guidance with Global Positioning System (GPS) and TERCOM updates. For terminal guidance, it uses infrared homing (Imaging infrared) with an autonomous digital target recognition system. The IIR terminal seeker is used for target acquisition and to positively identify an optimal aim point.
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From 1953 to 1955, he served in the US Navy, completing two tours of duty in the Far East as an aerial navigator and electronics warfare operator with the VC-35. Later, he retired from the U.S. Naval Reserves as a Judge Advocate General Corps commander. Returning to civilian life, Rapp went to work as an aerospace engineer, specializing in inertial guidance and navigation systems. Some of his projects included Mercury, Gemini, Apollo, and SkyLab for the U.S. space program and Bomarc, the first operational surface-to-air missile for the Department of Defense.
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In 2016, Armenia, a Russian ally and a member of the Collective Security Treaty Organization (CSTO) became the first foreign country to operate the system. Iskander-E has a maximum range up to 280 km, to comply with Missile Technology Control Regime restrictions for export, and is fitted with a simplified inertial guidance system. It flies on a flattened trajectory under 50 km altitude, allowing aerodynamic steering using tail fins, permitting a less predictable flight path and accurate delivery. The system can also use missiles carrying warheads with cluster munitions.
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Other key figures at Convair were Charlie Bossart, the Chief Engineer, and Walter Schweidetzky, head of the guidance group. Schweidetzky had worked with von Braun at Peenemünde during World War II. The initial Delta guidance system assessed the difference in position from a reference trajectory. A velocity to be gained (VGO) calculation is made to correct the current trajectory with the objective of driving VGO to zero. The mathematics of this approach were fundamentally valid, but dropped because of the challenges in accurate inertial guidance and analog computing power.
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The new NS-50 missile guidance computer (MGC) is built around a 16-bit high-speed microprocessor chip set. They are both designed to solve real-time positional error problems under the adverse conditions encountered in airborne weapon systems. They accept and process data and generate steering signals with sufficient accuracy and speed to meet the requirements of the inertial guidance and flight control systems of the Minuteman ICBMs. Computer operation is controlled by an internally stored program which is loaded from a magnetic tape cartridge at the launch facility (LF).
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These applications include non-sparking tools that are used near flammable gases (beryllium nickel), in springs and membranes (beryllium nickel and beryllium iron) used in surgical instruments and high temperature devices. As little as 50 parts per million of beryllium alloyed with liquid magnesium leads to a significant increase in oxidation resistance and decrease in flammability. Beryllium copper adjustable wrench The high elastic stiffness of beryllium has led to its extensive use in precision instrumentation, e.g. in inertial guidance systems and in the support mechanisms for optical systems.
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The land based version of the TC-2N features the missile packaged in a sealed container-launcher. NCSIST has exhibited a truck mounted version with four missile pods. The TC-2 air-defense system was exhibited at International Defence Exhibition in Abu Dhabi with a reported canister length of 4m and an all up weight (combined canister and round) of 350kg. It reportedly has midcourse inertial guidance with data link and terminal active radar guidance and electronic counter-countermeasure (EECM) and protection, but a reported effective range of only 15km.
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The SMKB (Smart-MK-Bomb) is a Brazilian guidance kit that turns a standard Mk 82 or Mk 83 into a precision-guided weapon, respectively called SMKB-82 and SMKB-83. The kit provides extended range up to and are guided by an integrated inertial guidance system coupled to three satellites networks, relying on wireless to handle the flow of data between the aircraft and the munition. FT PGB is a family of Chinese satellite and Inertial, guided munitions. LS PGB is a family of Chinese GPS+INS or laser guided munitions.
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The Shtil-1 SAM system with a 3S-90 missile launcher is fitted forward of the bridge and is armed with the 9M317 (SA-N-12 "Grizzly", navalised SA-17) missile. 24 missiles are carried in a magazine located below deck. Guidance and target illumination for these missiles is provided by four MR-90 Orekh (NATO: Front Dome) radars, which are connected to a command and control post. The SA-N-12 missile uses a combination of inertial guidance and semi-active radar homing to its maximum range of .
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Most Atlas D launches were sub-orbital missile tests; however several were used for other missions, including orbital launches of crewed Mercury, and uncrewed OV1 spacecraft. Two were also used as sounding rockets as part of Project FIRE. A number were also used with upper stages, such as the RM-81 Agena, to launch satellites. The Atlas D was deployed in limited numbers as an ICBM due to its radio guidance while the fully operational E and F-series missiles had inertial guidance packages and a different ignition system that allowed faster engine starts.
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Like the Titan and Atlas lines of launch vehicles, the Delta II line was built on major components supplied by several different contractors. McDonnell-Douglas built the basic core vehicle and supplied fairing materials at its plant in Huntington Beach, California, but it shipped them to another plant in Pueblo, Colorado for further assembly and/or match ups with other contractors' components. Rocketdyne provided the Delta's main engine, and Aerojet supplied the vehicle's second stage engine. Delco supplied the inertial guidance system, and Morton Thiokol built the strap-on solid rocket motors used for the basic Model 6925 Delta II vehicle.
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They are now most commonly launched from the Mk 41 VLS, which is a modular design concept with different versions that vary in size and weight. There are three lengths for this VLS: for the self-defense version, for the tactical version, and for the strike version. The empty weight for an 8-cell module is for the self-defense version, for the tactical version, and for the strike version. The Standard can also be used against ships, either at line-of-sight range using its semi-active homing mode, or over the horizon using inertial guidance and terminal infrared homing.
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YJ-62A on a TA580/TAS5380 In a September 2014 article published in Joint Forces Quarterly, the YJ-62 is credited with a warhead, a speed of , and a sea-skimming terminal attack height of 7–10 metres. The missile has an inertial guidance system using GPS and BeiDou data, and an active terminal sensor. YJ-62A is credited with a range of up to . In lieu of official data, the United States Navy's Office of Naval Intelligence believes it is likely the YJ-62 has a longer range than the of the C-602 export version, at least 400 km.
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Nortronics had developed and produced Astro-inertial guidance/navigation systems for the SM-62 Snark. The system developed for the GAM-87 Skybolt was later adapted for use in the Lockheed SR-71 Blackbird and mostly referred to as NAS-14 and/or NAS-21. The UGM-27 Polaris missile was equipped with a MIT- developed inertial system, which later evolved to the Delco produced IMU of the Apollo PGNCS. The Saturn V was equipped with a MSFC-developed ST-124-M3 inertial platform which was a further development of the PGM-19 Jupiter's ST-90.
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Diagram of Saturn V instrument unit The Saturn V instrument unit is a ring- shaped structure fitted to the top of the Saturn V rocket's third stage (S-IVB) and the Saturn IB's second stage (also an S-IVB). It was immediately below the SLA (Spacecraft/Lunar Module Adapter) panels that contained the Lunar Module. The instrument unit contains the guidance system for the Saturn V rocket. Some of the electronics contained within the instrument unit are a digital computer, analog flight control computer, emergency detection system, inertial guidance platform, control accelerometers, and control rate gyros.
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The plaque for the unit has the following inscription: > The Saturn V rocket, which sent astronauts to the Moon, used inertial > guidance, a self-contained system that guided the rocket's trajectory. The > rocket booster had a guidance system separate from those on the command and > lunar modules. It was contained in an instrument unit like this one, a ring > located between the rocket's third stage and the command and lunar modules. > The ring contained the basic guidance system components—a stable platform, > accelerometers, a digital computer, and control electronics—as well as > radar, telemetry, and other units.
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The thrust vector control (TVC) of HQ-9 is the most obvious visual identification that distinguish it from S300V: TVC of HQ-9 is exposed and thus can be observed from the side, while TVC of S300V is not exposed. The HQ-9's guidance system is composed of inertial guidance plus mid- course uplink and active radar terminal guidance systems. The system first used a missile in a box-like launcher canted at an angle, just like the MIM-104 Patriot. However the missile was very large because of China's limited experience with solid-fuel rockets in the 1990s.
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R-95-300 turbofan It is powered by a single 400 kgf Ukrainian-made, Motor Sich JSC R95-300 turbofan engine, with pop-out wings for cruising efficiency. It can be launched from both high and low altitudes, and flies at subsonic speeds at low levels (under 110 m/300 ft altitude). After launch, the missile's folded wings, tail surfaces and engine deploy. It is guided through a combination of an inertial guidance system plus a terrain contour-matching guidance system which uses radar and images stored in the memory of an onboard computer to find its target.
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Chrysler were responsible for the overall contract, while Rocketdyne handled the first stage propulsion and Jet Propulsion Laboratory handled the upper stage propulsion. The first three were converted Jupiter missiles, however all remaining boosters were built as Juno IIs from the beginning. The main differences between the Juno II and Jupiter were stretched propellant tanks for increased burn time (the first stage burn time was approximately 20 seconds longer than on the Jupiter), a reinforced structure to support the added weight of upper stages, and the inertial guidance system replaced with a radio ground guidance package, which was moved to the upper stages.
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Embedded systems that use dates for either computation or diagnostic logging are most likely to be affected by the 2038 problem. Many transportation systems from flight to automobiles use embedded systems extensively. In automotive systems, this may include anti-lock braking system (ABS), electronic stability control (ESC/ESP), traction control (TCS) and automatic four-wheel drive; aircraft may use inertial guidance systems and GPS receivers.GPS suffers its own time counter overflow problem known as GPS Week Number Rollover. However, this does not imply that all these systems will suffer from the Y2038 problem, since many such systems do not require access to dates.
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In May 1970, MIT formally divested itself of the Instrumentation Lab, which under the direction of Charles Stark Draper had developed the gyroscope and the inertial guidance system and had guided Apollo XI to the moon in July 1969. Dr. Hill, still vice president of research, became the chairman of the independent board of directors of the laboratory, renamed the Charles Stark Draper Laboratory in honor of its founder. Draper Lab remained a division of MIT for three years and became independent in 1973. In 1984, the Draper Laboratory dedicated the Albert G. Hill Building at One Hampshire Street in Cambridge.
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The USAF sought a precision navigation system for maintaining route accuracy and target tracking at very high speeds. Nortronics, Northrop's electronics development division, had developed an astro-inertial navigation system (ANS), which could correct inertial navigation errors with celestial observations, for the SM-62 Snark missile, and a separate system for the ill-fated AGM-48 Skybolt missile, the latter of which was adapted for the SR-71.Morrison, Bill, SR-71 contributors, Feedback column, Aviation Week and Space Technology, 9 December 2013, p.10 It uses star positioning to fine-tune the accuracy of the inertial guidance system after launch.
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The AFMDC and the 6571st lab were inactivated on August 1, 1970; more than 450 military and 570 civilian positions were lost; and the AFSWC's 6585th Test Group was established as a tenant of Tactical Air Command, to which Holloman AFB transferred. Associate units and programs transferred to other locations within Air Force Systems Command. In addition to the Holloman High Speed Test Track operated by the 6585th's "Armaments Division" in 1974, (cited by NRHP nomination) remaining facilities included the Central Inertial Guidance Test Facility (CIGTF), the Radar Target Scatter Facility (RATSCAT), and the Target Drone Facility.
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The Jupiter missile, a joint effort of Chrysler and the Redstone Arsenal in Huntsville, Alabama, was originally designed to attack high-value targets like airfields, train switching yards and command and control sites with extremely high accuracy. The Redstone team, under the direction of Wernher von Braun, ultimately delivered an inertial guidance system that was accurate to about . During development, the US Navy became involved in the Jupiter program, with the objective of arming submarines with a ballistic missile. This led to the Jupiter's squat shape, which allowed it to be stored within the confines of a submarine hull.
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Instead, the new missile's designs are strikingly similar to the United States Tomahawk cruise missile. It is powered by a turbofan engine, and has a maximum payload of of conventional explosive. The guidance systems consist of Inertial guidance system and Global Positioning System. Hyunmoo-3A, which was nicknamed "Eagle-1" (독수리-1) during the testing, has a range of 500 km, while Hyunmoo-3B, nicknamed "Eagle-2" (독수리-2) Cheonryong (천룡 순항 미사일), has a range of 1,000 km. Hyunmoo-3C, or "Eagle-3" (독수리-3), will be capable of striking its target up to 1,500 km away.
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The Kipper's long range enabled it to be launched, hypothetically, from beyond the range of any shipboard surface-to-air missiles or anti-aircraft guns of that time. The only defense against the Kipper was the naval jet fighter aircraft, operating from either an aircraft carrier or a shore airfield. In flight tests, the Kipper cruised on its approach to a target at an altitude of about 10,000 meters, using inertial guidance until it reaches a range of about 100 to 110 kilometers from the target, where it enters a shallow 15 degree dive, commanded by a mid-course update via radio link.
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Ty Bennett (Carl Lumbly), born April 11, 1963 at Camp Foster Marine Base, is a karate and kung fu expert who was previously a combat trainer with the NSA, serving as the sensei for John Casey. When he first appears in present day, he is working as a global arms dealer and steals an inertial guidance system from the Global Launch Agency. Bennett attempts to recruit Casey, but Casey rejects the offer with disdain. Following a protracted abduction and hand-to-hand battle, Casey becomes the first known agent to force Bennett to "tap out," contributing to Bennett's apprehension.
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On March 5, 1960, Missile 19D was undergoing a propellant loading exercise at 576-A2 at VAFB when a fuel leak started a fire on the pad that led to the explosion of the missile. The launch facility was written off due to the damage and not used again for almost 5 years. On March 8, 1960, Missile 44D launched from LC-11 on the first test of the AIG (All Inertial Guidance System) and experienced a 90° roll transient at liftoff. The AIG managed to correct this problem and the missile completed a successful 3000 mile lob downrange.
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Nevertheless, the flight was operated under a Turkish Airlines flight number. The preliminary investigation report found that the aircraft descended late and captured a false glideslope. On capturing the false glide slope, the 3 auto pilots then initiated the descent of the plane in low visibility conditions. Initially all three auto pilots were engaged (LAND 3) the false glideslope was lost 15 seconds after it was acquired and AP CAUTION and FMA FAULT 2 events were recorded meaning that the auto pilots would continue to descend the aircraft on a 3 degree slope using inertial guidance.
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The design immediately ran into serious difficulties over the inertial guidance bombing and navigation system, which, had the bomber been approved for production, would have pushed deployment back to at least 1963. The problems were rendered moot when Air Force headquarters cancelled the project in 1957, citing stringent budget limitations and higher priorities for other weapon systems. Recognizing that the medium tactical bomber design was still years away, plans were carried forward instead to continue using an Air Force version of the Navy's Douglas A3D, which was designated B-66 Destroyer. Two planned XB-68 prototypes and one static test model were cancelled, and none were built.
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Early ARMs, such as the AGM-45 Shrike, were not particularly intelligent; they would simply home in on the source of radiation and explode when they got near it. SAM operators learned to turn their radar off when an ARM was fired at them, then turn it back on later, greatly reducing the missile's effectiveness. This led to the development of more advanced ARMs such as the AGM-78 Standard ARM, AGM-122 Sidearm, and AGM-88 HARM missiles, which have inertial guidance systems (INS) built-in. This allows them to remember the radar's direction if it is turned off and continue to fly towards it.
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Lock-on after launch, or LOAL, is a capability of missile systems to lock-on to its target after being launched from its carrier vehicle. The term is normally used in reference to airborne weapons, especially air-to-air missiles. LOAL is an important part of modern weapon systems as it allows the weapons to be carried internally to increase stealth and then acquire the target once it has left the launching aircraft. LOAL systems normally rely on cuing from a helmet mounted sight or onboard sensors like radar or FLIR, and use a simple strapdown inertial guidance system to know where to look after launch.
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An inertial navigation system is a navigation aid that uses a computer and motion sensors (accelerometers) to continuously calculate via dead reckoning the position, orientation, and velocity (direction and speed of movement) of a moving object without the need for external references. Other terms used to refer to inertial navigation systems or closely related devices include inertial guidance system, inertial reference platform, and many other variations. An accelerometer alone is unsuitable to determine changes in altitude over distances where the vertical decrease of gravity is significant, such as for aircraft and rockets. In the presence of a gravitational gradient, the calibration and data reduction process is numerically unstable.
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Nortronics, Northrop Corporation's electronics development division, had developed an astro-inertial guidance system (ANS), which could correct inertial navigation system errors with celestial observations, for the SM-62 Snark missile, and a separate system for the ill-fated AGM-48 Skybolt missile, the latter of which was adapted for the SR-71.Morrison, Bill, SR-71 contributors, Feedback column, Aviation Week and Space Technology, 9 December 2013, p.10 Before takeoff, a primary alignment brought the ANS's inertial components to a high degree of accuracy. In flight, the ANS, which sat behind the reconnaissance systems officer's (RSO's), position, tracked stars through a circular quartz glass window on the upper fuselage.
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At the time that the Polaris project went live, submarine navigation systems were and at this time that standard was sufficient enough to sustain effective military efforts given the existing weapons systems in use by the Army, Air Force and Navy. Initially, developers of Polaris were set to utilize the existing 'Stable Platform' configuration of the inertial guidance system. Created at the MIT Instrumentation Laboratory, this Ships Inertial Navigation System (SINS) was supplied to the Navy in 1954. The developers of Polaris encountered many issues from the birth of the project, however, perhaps the most unsettling for them was the outdated technology of the gyroscopes they would be implementing.
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Iraq had lacked the required material for the motor case as well as the airframe and thus encountered difficulties in forming and aligning cylindrical shapes required for motor cases resulting in decreased accuracy. Iraq also lacked mixers and bowls required for mixing the propellant as they had already been used for the Badr-2000 cruise missile project and thus frequency of motor accidents increased. Iraq had reportedly imported gyroscopes and accelerometers from Belarus for its guided version, it was estimated that the Inertial guidance system for the guided version would allow the missile to achieve a CEP of 150 m at 150 km range.
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Inspection of MM III missile guidance system Inertial guidance uses sensitive measurement devices to calculate the location of the missile due to the acceleration put on it after leaving a known position. Early mechanical systems were not very accurate, and required some sort of external adjustment to allow them to hit targets even the size of a city. Modern systems use solid state ring laser gyros that are accurate to within metres over ranges of 10,000 km, and no longer require additional inputs. Gyroscope development has culminated in the AIRS found on the MX missile, allowing for an accuracy of less than 100 m at intercontinental ranges.
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Missile 151, nicknamed "Tune Up", on December 16, 1958, just prior to its launch from Vandenberg Air Force Base. The successful test was conducted a year after the base was activated. Phase II testing with the AC Spark Plug inertial guidance system began 7 December with the first successful flight on 19 December 1957.James N. Gibson, Nuclear Weapons of the United States, An Illustrated History, pp. 167–168, Schiffer Publishing Ltd., Atglen, PA, 1996 The operational variant of the Thor, the DM-18A, began testing in the autumn of 1958, but Missile 138 (5 November) went out of control shortly after liftoff and had to be destroyed.
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The fully operational D-series Atlas was similar to the R&D; model Atlas B and C, but incorporated a number of design changes implemented as a result of lessons learned during test flights. In addition, the D-series had the full-up Rocketdyne MA-2 propulsion system with 360,000 pounds of thrust versus the 250,000 pounds of thrust in the Atlas B/C's engines. Operational Atlas D missiles retained radio ground guidance aside from a few R&D; launches which tested the inertial guidance system designed for the Atlas E/F, and the Atlas D would be the basis for most space launcher variants of Atlas.
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The Nimrod's navigational functions were computerised, and were managed from a central tactical compartment housed in the forward cabin; various aircraft functions such as weapons control and information from sensors such as the large forward doppler radar were displayed and controlled at the tactical station.Neal 1970, p. 122. The flight systems and autopilot could be directly controlled by navigator's stations in the tactical compartment, giving the navigator nearly complete aircraft control. The navigational systems comprised digital, analogue, and electro- mechanical elements; the computers were integrated with most of the Nimrod's guidance systems such as the air data computer, astrocompass, inertial guidance and doppler radar.
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While some models of the MB-339 are primarily intended for training operations, other are instead principally equipped to perform light fighter and fighter-bomber roles. Combat-orientated aircraft are typically outfitted with more advanced avionics, such as improved inertial guidance systems, digital nav/attack computers, a MIL-STD-1553B databus, and hands-on throttle- and-stick (HOTAS)-compatible flight controls. Furthermore, various defensive systems, such as a radio jammer, radar warning receiver (RWR), electronic countermeasures (ECM), along with larger wingtip tanks, would typically be adopted. The MB.339K carries a pair of 30mm DEFA cannon while a total of six underwing hard points can accommodate up to 1,815 kilograms (4,000 lb) of external stores.
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The LSFW missile was required to be equally as effective against soft targets as the naval guns and the unguided rockets that it was intended to replace. Studies regarding the guidance system of the LFSW were conducted by the Applied Physics Laboratory, which determined that the ideal solution for the new missile was for it to utilise inertial guidance during the midcourse phase of its flight. Terminal guidance would be provided by a tracking beacon, operated by the troops in the battle area. The missile, having locked onto the beacon, would offset from the beacon's position by an amount specified in the beacon signal, thereby striking the target with a high degree of accuracy.
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Most anti-ship missiles are of the sea skimming variety, and many use a combination of inertial guidance and active radar homing. A good number of other anti-ship missiles use infrared homing to follow the heat that is emitted by a ship; it is also possible for anti-ship missiles to be guided by radio command all the way. The first anti-ship missiles, which were developed and built by Nazi Germany, used radio command guidance. These saw some success in the Mediterranean Theater in 1943–44, sinking or heavily damaging at least 31 ships with the Henschel Hs 293 and more than seven with the Fritz X, such as the Italian battleship Roma or the cruiser .
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The Joint Direct Attack Munition (JDAM) is a guidance kit that converts unguided bombs, or "dumb bombs", into all-weather precision-guided munitions. JDAM-equipped bombs are guided by an integrated inertial guidance system coupled to a Global Positioning System (GPS) receiver, giving them a published range of up to . JDAM-equipped bombs range from to . The JDAM's guidance system was jointly developed by the United States Air Force and United States Navy, hence the "joint" in JDAM. When installed on a bomb, the JDAM kit is given a GBU (Guided Bomb Unit) nomenclature, superseding the Mark 80 or BLU (Bomb, Live Unit) nomenclature of the bomb to which it is attached.
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The main difference from a conventional ICBM was in the design of the re-entry vehicle, which is fitted with a single 2.4 Mt warhead, a de-orbit engine, and control block. The control system independently uses inertial guidance and a radar altimeter which measure orbit parameters twice, once at the beginning of the orbital trajectory and again just before the firing of engines for de-orbiting. The silo launcher and command point were hardened against a nuclear blast. The Soviet Union constructed two surface pads at Baikonur for R-36 tests at LC-67/1 and LC-67/2, and six silos (two at LC-80 and one each at LC-140, LC-141, and LC-142).
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Transit-1-Satellite Prototype The orbits of the Transit satellites were chosen to cover the entire Earth; they crossed over the poles and were spread out at the equator. Since only one satellite was usually visible at any given time, fixes could be made only when one of the satellites was above the horizon. At the equator this delay between fixes was several hours; at mid-latitudes the delay decreased to an hour or two. For its intended role as an updating system for SLBM launch, Transit sufficed, since submarines took periodic fixes to reset their inertial guidance system, but Transit lacked the ability to provide high-speed, real- time position measurements.
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On 1 August 1970, per Air Force Systems Command Special Order G-94, the AFMDC was inactivated and Tactical Air Command assumed host responsibilities for Holloman Air Force Base. Associate units and programs transferred to other locations within Air Force Systems Command. The Test & Evaluation activities that remained were the Central Inertial Guidance Test Facility (CIGTF), the High Speed Test Track, the Radar Target Scatter Facility (RATSCAT), and the Target Drone Facility. These organizations were combined to form the nucleus of a Holloman AFB tenant organization, the 6585th Test Group, with the Air Force Special Weapons Center (AFSWC) at Kirtland Air Force Base, New Mexico, designated as the headquarters for the Test Group.
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While the metal itself is radioactive, its high density makes it more effective than lead in halting radiation from strong sources such as radium. Other uses of depleted uranium include counterweights for aircraft control surfaces, as ballast for missile re-entry vehicles and as a shielding material. Due to its high density, this material is found in inertial guidance systems and in gyroscopic compasses. Depleted uranium is preferred over similarly dense metals due to its ability to be easily machined and cast as well as its relatively low cost.. The main risk of exposure to depleted uranium is chemical poisoning by uranium oxide rather than radioactivity (uranium being only a weak alpha emitter).
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Total thrust of the MA-3 was 375,000 pounds. Atlas E/F used the ARMA inertial guidance system rather than Atlas D's radio ground guidance; some IOC (Initial Operational Capability) Atlas D flights tested the ARMA system instead of the standard GE Mod II radio guidance. Aside from minor differences in the ARMA on the Atlas E and F, the major difference between the two consisted of differently-placed quick fill lines for the two silo systems used. Most refurbished Atlas F space launches used solid-fueled upper stages, a notable exception being Missile 23F which launched Seasat, a NASA oceanography satellite, on June 27, 1978, the very last Atlas-Agena vehicle flown.
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The Atlas went in for a repeat performance on April 8 when Missile 48D, launched from LC-11 and intended as the first closed-loop test of the AIG (All Inertial Guidance System), experienced combustion instability again, this time in the B-2 engine. The first indication of trouble was a pressure surge in the B-2 combustion chamber, followed by unstable thrust, engine shutdown, and an explosion that started a thrust section fire. The B-1 engine then shut down, followed by the sustainer and verniers. Since the propulsion system had not attained sufficient thrust, the launcher hold-down mechanism did not release the missile, which stayed in place and burned on the pad.
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The pointing direction was determined during data processing, using the inertial guidance system of the SIV-B stage combined with information from two visible star sensors which formed part of the experiment. Galactic X-ray sources were observed with the S150 experiment. The experiment was designed to detect 4.0-10.0 nm photons. It consisted of a single large (~1500 cm2) proportional counter, electrically divided by fine wire ground planes into separate signal-collecting areas and looking through collimator vanes. The collimators defined 3 intersecting fields of view (~2 × 20°) on the sky, which allowed source positions to be determined to ~ 30'. The front window of the instrument consisted of a 2 µm thick plastic sheet.
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The Thor-Able vehicle had a stronger airframe than the standard Thor IRBM and had the inertial guidance system replaced by a radio guidance package mounted on the Able stages. It saw its first test on 23 April 1958 when Vehicle 116 was launched from LC-17A with a biological nose cone containing a mouse named MIA (Mouse In Able). At 19:10 EST, the Thor's engine roared to life and drove the Able stage and its tiny passenger into the evening sky. Two minutes and fifteen seconds after launch, at an altitude of 50 miles (80 km), the Thor exploded and sent the hapless rodent into the Atlantic Ocean instead of space.
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To facilitate development of the long-range Navaho surface-to- surface cruise missile, North American Aviation (NAA) developed the RTV-A-5 (Research Test Vehicle, Air Force), or X-10 in 1951. This vehicle was to prove out critical flight technology for the design of the cruise vehicle of the Navaho missile design. These included proving the basic aerodynamics out to Mach 2, flight testing the inertial guidance unit and flight control avionics to the same speed, and finally validate the recovery system for the next phase in the Navaho program. Preliminary design of the X-10 was completed in February 1951 and the first vehicle was delivered to Edwards Air Force Base in May 1953. The first flight occurred on 14 October 1953.
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The second generation of Standard missile, the Standard Missile 2, was developed for the Aegis combat system, and New Threat Upgrade program that was planned for existing Terrier and Tartar ships. The destroyer served as the test platform for the development of the CG/SM-2 (ER) missile program project. The principal change over the Standard missile 1 is the introduction of inertial guidance for each phase of the missile's flight except the terminal phase where semi-active homing was retained. This design change was made so that missiles could time share illumination radars and enable equipped ships to defend against saturation missile attacks. Terrier ships reequipped as part of the New Threat Upgrade were refit to operate the RIM-67B (SM-2ER Block II) missile.
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Prior to H-II, NASDA had to use components licensed by the United States in its rockets. In particular, crucial technologies of H-I and its predecessors were from the Delta rockets. Although the H-I did have some domestically produced components, such as LE-5 engine on the second stage and inertial guidance system, the most crucial part, the first stage engine, was a licence-built version of the Thor-ELT of the US. By developing the LE-7 liquid-fuel engine and the solid booster rockets for the first stage, all stages of H-II had become "domestically developed". The H-II was developed under the following policies, according to a NASDA press release: #Develop the launch vehicle with Japanese space technology.
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As first explained by Maximilian Schuler in a 1923 paper, a pendulum whose period exactly equals the orbital period of a hypothetical satellite orbiting just above the surface of the earth (about 84 minutes) will tend to remain pointing at the center of the earth when its support is suddenly displaced. This principle, called Schuler tuning, is used in inertial guidance systems in ships and aircraft that operate on the surface of the Earth. No physical pendulum is used, but the control system that keeps the inertial platform containing the gyroscopes stable is modified so the device acts as though it is attached to such a pendulum, keeping the platform always facing down as the vehicle moves on the curved surface of the Earth.
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Chow was born in Taiyuan, Shanxi in 1918. He received a B.S. in Electrical Engineering from National Chiao Tung University (now Shanghai Jiao Tong University) in 1940 and an M.S. in EE from the Massachusetts Institute of Technology in 1942. Chow, working for the Arma Division of the American Bosch Arma Corporation, pioneered the use of digital computers in missile, satellite and spacecraft guidance systems, leading the design of the United States Air Force Atlas E/F ICBM (Inter-Continental Ballistic Missile) all-inertial guidance system and guidance computer, the first production airborne digital computer. Mr. Chow personally formulated the design of the first all solid state, high reliability, space-borne digital computer and established the basic systems approach and mechanization of America's ICBM guidance systems.
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Although Litton Industries lacked capital in the beginning, Thornton thought that the U.S. Department of Defense would need more sophisticated weapons and that the demand for another large electronics company will increase. During the years, Litton Industries acquired several other smaller companies and had merged with Monroe Calculating Machine. Monroes used Litton's technological assets and Litton required Monroe's sales and service outlets. During the late 1950s and early 1960s. 50% of Litton's business was with the U.S. Government; besides calculators, they were also producing inertial guidance systems for aircraft, potentiometers, duplexers, etc. In 1961, Litton acquired Ingalls Shipbuilding for $8 million and subsequently ventured into the production of submarines and oil-drilling equipment. By 1963, Litton Industries reached $500 million with a revenue of $393.8 million.
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Mindling & Bolton, p. 234 The squadron was equipped with the B model of the Mace, which was deployed so that a single crew was able to launch all missiles located at a single launch site directly from the underground bunkers in which they were stored. The 874th was one of the first squadrons equipped with the TM-76B, which used an inertial guidance system.Mindling & Bolton, p. 215 During the Cuban Missile Crisis, the squadron was placed on high alert status. Missile down time for routine maintenance was not permitted, and when a malfunction required taking a missile off alert, its planned target had to be covered by placing a Republic F-105 Thunderchief on cockpit alert at the end of Kadena's runway.Mindling & Bolton, p.
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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.
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The first accounts of the effects of rotation on this form of interferometer were published in 1913 by Georges Sagnac, who mistakenly believed that his ability to detect a "whirling of the ether" disproved relativity theory. The sensitivity of present-day Sagnac interferometers far exceeds that of Sagnac's original arrangement. The sensitivity to rotation is proportional to the area circumscribed by the counter-rotating beams, and fibre optic gyroscopes, present-day descendants of the Sagnac interferometer, use thousands of loops of optical fibre rather than mirrors, such that even small to medium-sized units easily detect the rotation of the Earth. Ring laser gyroscopes (not illustrated) are another form of Sagnac rotation sensor that have important applications in inertial guidance systems.
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A total of 733 aircraft were produced and delivered to six countries. The Block 32H/J aircraft assigned to the USAF Thunderbird flight demonstration squadron were built in 1986 and 1987 and are some of the oldest operational F-16s in the Air Force. The Air National Guard procured many upgrades for their fleet of aging block 30/32s including the addition of improved inertial guidance systems, improved electronic warfare suite (AN/ALQ-213), and upgrades to carry the Northrop Grumman LITENING targeting pod. The standard Inertial Navigation Unit (INU) was first changed to a ring laser gyro, and later upgraded again to an Embedded GPS/INS (EGI) system which combines a Global Positioning System (GPS) receiver with an Inertial navigation system (INS).
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Inertial navigation is significantly less accurate; the JDAM achieves a published circular error probable (CEP) of 13 m under GPS guidance, but typically only 30 m under inertial guidance (with free fall times of 100 seconds or less).U.S. Air Force Factsheets: Joint Direct Attack MunitionJDAM Specifications HOPE/HOSBO of the Luftwaffe with a combination of GPS/INS and electro-optical guidance The precision of these weapons is dependent both on the precision of the measurement system used for location determination and the precision in setting the coordinates of the target. The latter critically depends on intelligence information, not all of which is accurate. According to a CIA report, the accidental bombing of the Chinese embassy in Belgrade during Operation Allied Force by NATO aircraft was attributed to faulty target information.
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The new engine was too large to fit in the existing R-5 airframe, so a conical tail section was added to hold the engine. Nikolay Pilyugin, head of the leading control system bureau, convinced Yangel to introduce a fully autonomous control system in the R-12 instead of the traditional radio control that had been used on earlier missiles. The R-5, for instance, used an inertial guidance system that had to be "fine tuned" by commands from ground radio stations that it passed over during its flight. Pilyugin felt that newer inertial systems would have the accuracy needed to hit targets at 2,000 km without the mid-course updates. According to the official NPO Yuzhnoye history, Yangel's design was approved on 13 February 1953 by the Council of Ministers of the USSR.
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The pilot or weapon systems officer uses the crosshairs to mark a target, which can then be attacked with laser-guided bombs or other guided weapons from the designating aircraft or other, friendly forces. Because it is designed for use by single-seat aircraft, it has a novel automatic lock-on feature, which keeps the laser focused on the target without further operator intervention (using an inertial guidance system, it can generally keep the laser on target even if the beam is temporarily interrupted by clouds). ATLIS II is used by the SEPECAT Jaguar, Mirage F1, Mirage 2000, Mirage 2000N, and some Pakistani F-16s. It is compatible with various U.S. and French laser-guided bombs, with the French Aerospatiale AS-30L missile, and even with some Russian bombs and guided weapons.
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Polyphem-S missile The Polyphem was a proposed light-weight fibre-optic wire- guided surface-to-surface missile with a range of 60 km. It uses a sealed round, a solid propellant booster rocket to launch the missile out of its canister to an initial height, so that the wings and control surfaces can unfold, and a more fuel economic turbojet cruise engine kicks in to propel the missile. The missile can be programmed to follow a preset course, using GPS or inertial guidance. An infrared seeker can be used to automatically pick a target and for the terminal guidance phase, but it is also possible to transfer the thermal images back to the launching platform via a 200 MBit/s data link provided by an optical fibre, and manually select the target.
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Vessels of the California-class cruisers, Virginia- class cruisers and Kidd-class destroyer had their Tartar systems upgraded to modification 14 or 15 standard which enabled them to employ the Standard Missile 2 as part of the New Threat Upgrade (NTU) program. The New Threat Upgrade equipped vessels could utilize the inertial guidance systems on the SM-2 and time share illumination radars for semi-active homing in the terminal phase of the intercept, increasing the number of targets the Tartar system could attack at the same time. The New Threat Upgrade Tartar ships could function nearly as well as Aegis Combat System equipped vessels, except for dealing with saturation missile attacks. The NTU still requires the AN/SPG-51 radar to acquire a lock on the target and illuminate it just before intercept.
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Retrieved 31 July 2011. In the Falklands War in 1982, 10 Harrier GR.3s of No. 1 Squadron operated from the aircraft carrier .Duffner, Robert W. "Conflict In The South Atlantic: The Impact of Air Power." Air University Review, March–April 1984. Retrieved 31 July 2011. As the RAF Harrier GR.3 had not been designed for naval service, the 10 aircraft had to be rapidly modified prior to the departure of the task force. Special sealants against corrosion were applied and a new deck-based inertial guidance aid was devised to allow the RAF Harrier to land on a carrier as easily as the Sea Harrier. Transponders to guide aircraft back to the carriers during night-time operations were also installed, along with flares and chaff dispensers.Jefford 2006, pp. 85–86.
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The Litton LN-3 was one of the first inertial navigators on a production aircraft, but other systems, either inertial navigators or inertial measurement units, of other brands and for various applications with comparable technology existed. The Autonetics Radar Enhanced Inertial Navigation System (REINS) of the North American A-5 Vigilante was more or less comparable to the LN-3/PHI-4. This system was derived from the XN-6 system developed for the SM-64 Navaho, the N5G system for the AGM-28 Hound Dog and the N2C/N2J/N3A/N3B system for the XB-70, and was related to the N6A-1 navigation system used in the USS Nautilus (SSN-571) and the N10 inertial guidance system for the LGM-30 Minuteman. Note that the Boeing history claims the REINS to be the first inertial navigation in a production airplane.
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Huan Yong - China's modern plant taxonomy founder, Chen Haozhu - Career in medicine for many years, has won the national, military science and technology progress award more than 20 other awards Albert Chan (professor) - a Hong Kong professor of chemistry and traditional Chinese medicine. Huang Cuifen one of the founders, successive Chinese Academy of Military Medical Institute of Basic Medical researcher Liang Sili - Chinese Engineer. Chief Designer of inertial guidance platforms for Chinese ballistic missiles. Chen Guoda - Expertise in Mechanical Engineering Huang Benli - Chinese Academy of Sciences, Xiamen University, Professor, Huang has won many awards: 2 2nd-class Major Science and Technology Achievements Awards of Chinese Academy of Science Zhangyou Qi - Computational mechanics, civil engineering experts Xue Shepu - Researcher in cell proliferation and differentiation Huan Yong - Is one of the founders of modern science of plant classification.
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The avionics of the T-4 are digital in nature; this approach was chosen in order to reduce both the size and weight of the avionics while also increasing their reliability. Typically, these systems and components have been indigenously produced, albeit with the incorporation of some base technologies from several American industries; examples of this include the inertial guidance system, which uses Honeywell-built laser gyroscopes, while the air data computer uses Sperry-supplied transducers. The majority of onboard systems are of a conventional nature; however, according to Flight International, the use of a licensed onboard oxygen generation system (OBOGS) is an unusual choice for a trainer aircraft and had required considerable effort to adapt it for use aboard the T-4. A British-sourced artificial feel system is also used by the type, the components for which being locally manufactured.
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The German engineer (5 February 1882 in Zweibrücken – 30 July 1972) Maximilian Joseph Johannes Eduard Schuler is best known for discovering the principle known as Schuler tuning which is fundamental to the operation of a gyrocompass or inertial guidance system that will be operated near the surface of the earth. Schuler's cousin Hermann Anschütz-Kaempfe founded a firm near Kiel, Germany, to manufacture navigational devices using gyroscopes in 1905, and Schuler joined the firm in 1906. For many years they struggled with the problem of maintaining a vertical reference as a craft moved around on the surface of the earth. In 1923 Schuler published his discovery that if the gyrocompass was tuned to have an 84.4 minute period of oscillation (the Schuler period) then it would resist errors due to sideways acceleration of the ship or aircraft in which it was installed.
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June 26, 1971: serial number 6L – dummy Soyuz 7K-LOK (Soyuz 7K-L1E No.1) and dummy LK module-spacecraft Soon after lift-off, due to unexpected eddies and counter-currents at the base of Block A (the first stage), the N-1 experienced an uncontrolled roll beyond the capability of the control system to compensate. The KORD computer sensed an abnormal situation and sent a shutdown command to the first stage, but as noted above, the guidance program had since been modified to prevent this from happening until 50 seconds into launch. The roll, which had initially been 6° per second, began rapidly accelerating. At T+39 seconds, the booster was rolling at nearly 40° per second, causing the inertial guidance system to go into gimbal lock and at T+48 seconds, the vehicle disintegrated from structural loads.
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The inertial guidance systems in their fresh F-4E Phantom IIs would prove consequential for piloting and target location in an environment largely lacking in aerial navigation aids, especially after the 1 March loss of the only TACAN site in northern Laos. On 17 March, the volunteer FACs began supplying the necessary tactical air power for General Vang Pao's Hmong guerrillas to sweep through Operation Raindance. In April, the "Tigers" were considered for night FAC duties, but rejected. By July, the "Tiger" FACs were so immersed in directing close air support, they were allotted four sorties per day. Between July and September 1969, the "Tigers" were credited with 34 enemy killed by air, 12 antiaircraft sites destroyed, 246 interdictory road cuts of enemy supply lines, 15 enemy supply trucks destroyed, 403 structures destroyed, 360 fires caused by explosions, and 681 secondary explosions of munitions and fuel.
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Joel Stanley Engel (February 4, 1936) is an American engineer, known for fundamental contributions to the development of cellular network. Born in New York City, he obtained a B.Sc. in engineering at City College of New York (1957). While working at the Massachusetts Institute of Technology in the research staff at Draper Laboratory on inertial guidance and stabilization systems, he also obtained an M.Sc. in electrical engineering (1959). He then moved to New Jersey and worked for Bell Labs most of his active research career (1959–83), and also earned a Ph.D. from Polytechnic Institute of Brooklyn on a thesis on data transmission over telephone lines (1964). He then worked at Bellcomm on guidance systems for the Apollo Program (1965) and at Page Communications Engineers in Washington, D.C. (1965–67) before returning to Bell Labs where he joined the mobile phone system research group.
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The investigation cited the pilot's lack of night flying experience, the co-pilots misreading of the emergency procedures related to the landing gear issue, and the aircraft's poor mechanical condition as contributing factors to the accident. According to the report, dated February 1988, Lieutenant Villar had logged just 5.3 hours of night flying in the 90 days preceding the accident, 3.3 of them in the previous 60 days, and had not flown at night in at least 30 days before the crash. The copilot, First Lieutenant César Morales, had logged only one hour of night flying in the 90 days preceding the accident, half an hour in the preceding 60 days, and had also not flown at night in at least 30 days. Additionally, the F27's maintenance log, which was handed to the pilot before takeoff, showed a series of mechanical defects including lacking an inertial guidance system, poor UHF radio performance, a VOR receiving unit with inadequate reception, a malfunctioning radar altimeter and a worn front landing gear indicator light switch.
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In 2014, Raytheon began testing Block IV improvements to attack sea and moving land targets. The new passive radar seeker will pick up the electromagnetic radar signature of a target and follow it, and actively send out a signal to bounce off potential targets before impact to discriminate its legitimacy before impact. Mounting the multi-mode sensor on the missile's nose would remove fuel space, but company officials believe the Navy would be willing to give up space for the sensor's new technologies.Facing End of Tomahawk Production, Raytheon Plays Industrial Base Card - Nationaldefensemagazine.org, 2 April 2014 The previous Tomahawk Anti-Ship Missile, retired over a decade earlier, was equipped with inertial guidance and the seeker of the Harpoon missile and there was concern with its ability to clearly discriminate between targets from a long distance, since at the time Navy sensors did not have as much range as the missile itself, which would be more reliable with the new seeker's passive detection and millimeter-wave active radar homing.
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