38 Sentences With "circularize" | Random Sentence Generator

"If you have the right mass of planet and the right mass of gas, you can damp the orbit and circularize it," he said.

A burn lasting nearly two minutes aimed to circularize the kick stage's orbit at an altitude of around 310 miles before release of the mission's six satellite passengers.

They made one more burn of the Agena to circularize their orbit to .

All three satellites were successfully deployed, one at a time, and their booster stages fired automatically to lift them to geosynchronous transfer orbits. Their respective owners assumed charge, and later fired the onboard kickmotors at apogee, to circularize the orbits and align them with the equator.

Also, according to Aviation Week, the shuttle initially entered a x orbit, at an inclination of 28.45 degrees to the equator. It then executed three Orbital Maneuvering System (OMS) burns, the last being executed on the fourth orbit. The first burn was conducted to circularize the shuttle's orbit at . The mission lasted 3 days, 1 hour, and 33 minutes.

Rocket Lab has also developed an optional third stage designed to circularize the orbits of its satellite payloads. The stage also puts satellites into a more accurate orbit in less time. This "kick" stage employs a new rocket engine, named Curie, that is capable of performing multiple burns, uses an unspecified "green" bipropellant, and is 3D printed. It was first used during Electron's second flight.

It then executed three Orbital Manoeuvering System (OMS) burns, the last on its fourth orbit. The first burn was to circularize the orbit at . The satellite was deployed on the 7th orbit, and ignited its Inertial Upper Stage (IUS) booster at the ascending node of the 8th orbit, successfully placing it in a geosynchronous transfer orbit. This was the 8th IUS launched aboard the shuttle, and the seventh successfully deployed.

On 1 June, SpaceX announced that the next launch window would open Monday, 13 July and extend through Tuesday, 14 July, with a daily window to open at 21:00 UTC (09:00 local time). The launch on Monday, 13 July was successful, placing RazakSAT into its initial parking orbit. Thirty-eight minutes later, the rocket's second-stage engine fired again to circularize the orbit. The payload was then successfully deployed.

It has been calculated that the Salacia system should have undergone enough tidal evolution to circularize their orbits, which is consistent with the low measured eccentricity, but that the primary need not have been tidally locked. The ratio of its semi-major axis to its primary's Hill radius is 0.0023, the tightest trans-Neptunian binary with a known orbit. Salacia and Actaea will next occult each other in 2067.

He also asked that they receive a "go/no go" decision before they passed behind the Moon on each orbit. As they reappeared for their second pass in front of the Moon, the crew set up equipment to broadcast a view of the lunar surface. Anders described the craters that they were passing over. At the end of this second orbit, they performed an 11-second LOI-2 burn of the SPS to circularize the orbit to .

A recent study of human circRNAs revealed that these molecules are usually composed of 1–5 exons. Each of these exons can be up to 3x longer than the average expressed exon, suggesting that exon length may play a role in deciding which exons to circularize. 85% of circularized exons overlap with exons that code for protein, although the circular RNAs themselves do not appear to be translated. During circRNA formation, exon 2 is often the upstream "acceptor" exon.

The mission was expected to last until November 1985. By 1981, the plan was for the spacecraft to launch in 1987 and to use aerobraking to circularize its orbit, whereupon it would be able to generate radar coverage of the entire planet over a period of 126 days. Data transmission rates were 1 Mbit per second, matching the imaging and recording speed. It would have two resolutions: mapping mode of 600 m per line-pair, then a high-resolution mode at 150 m per line-pair.

The mission's primary payload was a Tracking and Data Relay Satellite (TDRS-D), which became TDRS-4 after deployment, and its attached Inertial Upper Stage (IUS). The satellite was deployed from the shuttle's payload bay less than six hours after launch, at 3:12 a.m. EST. The first-stage orbit burn of the IUS took place an hour later, and the second burn to circularize the orbit occurred 12 hours and 30 minutes into the mission. The satellite was stationed at 41.0° West longitude.

They based this prediction on models of Io's interior that took into account the massive amount of heat produced by the varying tidal pull of Jupiter on Io resulting from Io's Laplace resonance with Europa and Ganymede not allowing its orbit to circularize. Their calculations suggested that the amount of heat generated for an Io with a homogeneous interior would be three times greater than the amount of heat generated by radioactive isotope decay alone. This effect would be even greater with a differentiated Io.

StarTram is a proposal to launch vehicles directly to space by accelerating them with a mass driver. Vehicles would float by maglev repulsion between superconductive magnets on the vehicle and the aluminum tunnel walls while they were accelerated by AC magnetic drive from aluminum coils. The power required would probably be provided by superconductive energy storage units distributed along the tunnel. Vehicles could coast up to low or even geosynchronous orbital height; then a small rocket motor burn would be required to circularize the orbit.

This allows a fixed nozzle, which saves cost and weight versus a hot joint. A single-impulse launch results in an elliptical orbit, with a high apogee and low perigee. The use of three stages, plus the coast period between second- and third-stage firings, help to circularize the orbit, ensuring the perigee clears the Earth's atmosphere. If the Pegasus launch had begun at low altitude, the coast period or thrust profile of the stages would have to be modified to prevent skimming of the atmosphere after one pass.

If a planet has an eccentric orbit, then tidal heating can provide another source of energy besides stellar radiation. This means that eccentric planets in the radiative habitable zone can be too hot for liquid water. Tides also circularize orbits over time so there could be planets in the habitable zone with circular orbits that have no water because they used to have eccentric orbits. Eccentric planets further out than the habitable zone would still have frozen surfaces but the tidal heating could create a subsurface ocean similar to Europa's.

Miura 5 (previously called Arion 2) is a planned two-stage orbital recoverable launch vehicle of the Spanish company PLD Space. Miura 5 will be 25 m long, capable of inserting 300 kg of payload into a 500 km sun-synchronous orbit (SSO), featuring an optional kick stage that can circularize the orbits of satellites. All stages are planned to be liquid-propelled and its technology is inherited from Miura 1. The first stage is planned to be reusable through the combined use of its engines and parachutes for retrieval.

The CTS is an upper stage developed by the China Academy of Launch Vehicle Technology (CALT) to improve the performance of the Long March 2C to high (>400 km of altitude) LEO missions like SSO. The two stage LM-2 delivers the payload and stage to an elliptical orbit with the desired apogee and the CTS points the stack in the direction of the correct vector and activates the solid rocket motor (SRM) main engine to circularize it. It then dispenses the spacecraft and does a passivisation procedure.

Yuanzheng () is a restartable upper stage developed by the China Academy of Launch Vehicle Technology (CALT) for the Long March rocket family. The Yuanzheng stage enables the Chinese launch vehicles to deploy payloads directly to high-energy orbits such as medium Earth orbit (MEO) and geosynchronous orbit (GSO). Since the Long March third stage cannot restart, it cannot circularize a GSO or GEO orbit from a geosyncronous transfer orbit (GTO). With its restart capability, Yuanzheng has enabled the deployment of satellite pairs for the BeiDou Navigation Satellite System in MEO and communications satellites in GSO.

Ram accelerators have been proposed as a cheap method to get payloads into space. Impulsive launched projectiles need some means to circularize their trajectory for orbit insertion, so rockets, such as those designed in the 1960s in Project HARP, are typically incorporated into the projectiles. With multi-stage rocket projectiles the launch cost was estimated at US$500 per kilogram in 2004. There are also envisions of the technology for military applications, such as ultra-long range striking and intercepting capabilities against stationary and on-the-move threats.

This limited maneuvering capability is still quite useful. By varying the magnetic sail's field strength over the course of its orbit, a magnetic sail can give itself a "perigee kick" raising the altitude of its orbit's apogee. Repeating this process with each orbit can drive the magnetic sail's apogee higher and higher, until the magnetic sail is able to leave the planetary magnetosphere and catch the solar wind. The same process in reverse can be used to lower or circularize the apogee of a magsail's orbit when it arrives at a destination planet.

The first of several orbit changing maneuvers happened as planned at 07:54:45, with a 63-second burn to circularize the orbit. Based on United States Space Command orbital elements, it was in a 332 by 336 km (206 by 209 statute miles) orbit. After about an hour and a half, the hatch between the re-entry and orbital modules was opened and, for the first time, crew were able to enter the second living compartment of the Shenzhou spacecraft. Fèi Jùnlóng was the first to enter, while Niè Hǎishèng remained in the reentry module.

The burn lasted 367 seconds and simulated the throttle pattern to be used during the landing on the Moon. After they returned, a fifth firing of the SPS was made, designed to circularize Apollo9's orbit in preparation for the rendezvous. This took place at 54:26:12.3, raising the craft's orbit to . The fourth day's program (March 6) was for Schweickart to exit the hatch on the LM and make his way along the outside of the spacecraft to the CM's hatch, where Scott would stand by to assist, demonstrating that this could be done in the event of an emergency.

Io is in a 2:1 mean-motion orbital resonance with Europa and a 4:1 mean-motion orbital resonance with Ganymede, completing two orbits of Jupiter for every one orbit completed by Europa, and four orbits for every one completed by Ganymede. This resonance helps maintain Io's orbital eccentricity (0.0041), which in turn provides the primary heating source for its geologic activity. Without this forced eccentricity, Io's orbit would circularize through tidal dissipation, leading to a geologically less active world. Like the other Galilean satellites and the Moon, Io rotates synchronously with its orbital period, keeping one face nearly pointed toward Jupiter.

SES-9 is a large communications satellite operating in geostationary orbit at the 108.2° East, providing communications services to Northeast Asia, South Asia and Indonesia, maritime communications for vessels in the Indian Ocean, and mobility beams for "seamless in-flight connectivity" for domestic Asian airlines of Indonesia and the Philippines. The satellite was built by Boeing, using a model BSS-702HP satellite bus. SES-9 had a mass of approximately at launch, the largest Falcon 9 payload yet to a highly-energetic geosynchronous transfer orbit (GTO). SES S.A. used the spacecraft's own propulsion capabilities to circularize the trajectory to a geostationary orbit.

Lambda Virginis is a double-lined spectroscopic binary with an orbital period of 206.7 days and an eccentricity of 0.0610. The semi- major axis has an angular size of 0.02 arcseconds, which, at the distance of this system, is equivalent to a physical span of AU. The orbit is inclined by an angle of 110° to the line of sight from the Earth. Tidal theory predicts that eventually the orbit of the stars will circularize and their rotation rates will become synchronized with their orbital motion. However, this will occur over a time scale of more than 1.2 billion years, whereas their estimated age is 935 million years.

Experiments have been flown by NASA, and SpaceX is developing large-scale on-orbit propellant transfer technology. Another approach to debris mitigation is to explicitly design the mission architecture to always leave the rocket second- stage in an elliptical geocentric orbit with a low-perigee, thus ensuring rapid orbital decay and avoiding long-term orbital debris from spent rocket bodies. Such missions will often complete the payload placement in a final orbit by the use of low-thrust electric propulsion or with the use of a small kick stage to circularize the orbit. The kick stage itself may be designed with the excess-propellant capability to be able to self-deorbit.

Extra fuel is required to compensate for the fact that the bursts take time; this is minimized by using high-thrust engines to minimize the duration of the bursts. For transfers in Earth orbit, the two burns are labelled the perigee burn and the apogee burn (or apogee kickJonathan McDowell, "Kick In the Apogee: 40 years of upper stage applications for solid rocket motors, 1957-1997", 33rd AIAA Joint Propulsion Conference, July 4, 1997. abstract. Retrieved 18 July 2017.); more generally, they are labelled periapsis and apoapsis burns. Alternately, the second burn to circularize the orbit may be referred to as a circularization burn.

Early spaceplanes were used to explore hypersonic flight (e.g. X-15). Some air-breathing engine-based designs (cf X-30) such as aircraft based on scramjets or pulse detonation engines could potentially achieve orbital velocity or go some useful way to doing so; however, these designs still must perform a final rocket burn at their apogee to circularize their trajectory to avoid returning to the atmosphere. Other, reusable turbojet-like designs like Skylon which uses precooled jet engines up to Mach 5.5 before employing rockets to enter orbit appears to have a mass budget that permits a larger payload than pure rockets while achieving it in a single stage.

Hohmann transfer orbit, 2, from an orbit (1) to a higher orbit (3) A Hohmann transfer orbit is the simplest maneuver which can be used to move a spacecraft from one altitude to another. Two burns are required: the first to send the craft into the elliptical transfer orbit, and a second to circularize the target orbit. To raise a circular orbit at v_1, the first posigrade burn raises velocity to the transfer orbit's periapsis velocity: :\Delta v_1\ = v_p - v_1 The second posigrade burn, made at apoapsis, raises velocity to the target orbit's velocity: :\Delta v_2\ = v_2 - v_a A maneuver to lower the orbit is the mirror image of the raise maneuver; both burns are made retrograde.

The second stage then fired to circularize the orbit, after which it released the satellite and, using its attitude control jets, began a retrograde maneuver to enter a lower orbit to avoid any possibility of collision with its payload. In addition to the Communication and Reconnaissance missions described above, which placed the payload into stationary (24-hour) orbit, the IUS was also used to boost spacecraft towards planetary trajectories. For these missions, the second IUS stage was separated and ignited immediately after first stage burnout. Igniting the second stage at low altitude (and thus, high orbital speed) provided the extra velocity the spacecraft needed to escape from Earth orbit (see Oberth effect).

Gliese 876 d is located in an orbit with a semimajor axis of only 0.0208 AU (3.11 million km). At this distance from the star, tidal interactions should in theory circularize the orbit; however, measurements reveal that it has a high eccentricity of 0.207, comparable to that of Mercury in the Solar System. Models predict that, if its non-Keplerian orbit could be averaged to a Keplerian eccentricity of 0.28, then tidal heating would play a significant role in the planet's geology to the point of keeping it completely molten. Predicted total heat flux is approximately 104–5 W/m2 at the planet's surface; for comparison the surface heat flux for Io is around 3 W/m2.

This is greater than the Δv required for an escape orbit: 10.93 − 7.73 = 3.20 km/s. Applying a Δv at the Low Earth orbit (LEO) of only 0.78 km/s more (3.20−2.42) would give the rocket the escape speed, which is less than the Δv of 1.46 km/s required to circularize the geosynchronous orbit. This illustrates the Oberth effect that at large speeds the same Δv provides more specific orbital energy, and energy increase is maximized if one spends the Δv as quickly as possible, rather than spending some, being decelerated by gravity, and then spending some more to overcome the deceleration (of course, the objective of a Hohmann transfer orbit is different).

Based on a prograde orbit model, Xiangliu orbits Gonggong at a distance of around and completes one orbit in 25.22 days. Using the same prograde orbit model, the discovery team has estimated that its orbit is inclined to the ecliptic by about 83 degrees, implying that Gonggong is being viewed at a nearly pole-on configuration under the assumption that Xiangliu's orbit has a low inclination to Gonggong's equator. The orbit of Xiangliu is highly eccentric. The value of 0.29 is thought to have been caused by either an intrinsically eccentric orbit or by slow tidal evolution, in which the time for its orbit to circularize is comparable to the age of the Solar System.

Hohmann Transfer Orbit: a spaceship leaves from point 2 in Earth's orbit and arrives at point 3 in Mars' (not to scale) For many years economical interplanetary travel meant using the Hohmann transfer orbit. Hohmann demonstrated that the lowest energy route between any two orbits is an elliptical "orbit" which forms a tangent to the starting and destination orbits. Once the spacecraft arrives, a second application of thrust will re-circularize the orbit at the new location. In the case of planetary transfers this means directing the spacecraft, originally in an orbit almost identical to Earth's, so that the aphelion of the transfer orbit is on the far side of the Sun near the orbit of the other planet.

The placement into a supersynchronous transfer orbit enables an inclination plane change with a lower subsequent expenditure of propellant by the satellite's kick motor. In this approach, the launch vehicle places the satellite into a supersynchronous elliptical Geostationary transfer orbit, an orbit with a somewhat larger apogee than the more typical Geostationary transfer orbit (GTO) typically utilized for communication satellites. This technique was used, for example, on the launch and transfer orbit injection of the first two SpaceX Falcon 9 v1.1 GTO launches in December 2013 and January 2014, SES-8 and Thaicom 6 (-apogee), respectively. In both cases, the satellite owner uses the propulsion built into the satellite to reduce the apogee and circularize the orbit to a geostationary orbit.

Summary of Mars Odyssey mission start Animation of 2001 Mars Odysseys trajectory around Sun Animation of 2001 Mars Odyssey trajectory around Mars from October 24, 2001 to October 24, 2002 Mars Odyssey as imaged by Mars Global Surveyor Mars Odyssey launched from Cape Canaveral on April 7, 2001, and arrived at Mars about 200 days later on October 24. The spacecraft's main engine fired in order to decelerate, which allowed it to be captured into orbit around Mars. Odyssey then spent about three months aerobraking, using aerodynamic drag from the upper reaches of the Martian atmosphere to gradually slow down and reduce and circularize its orbit. By using the atmosphere of Mars to slow the spacecraft in its orbit rather than firing its engine or thrusters, Odyssey was able to save more than 200 kilograms (440 lb) of propellant. This reduction in spacecraft weight allowed the mission to be launched on a Delta II 7925 launch vehicle, rather than a larger, more expensive launcher. Aerobraking ended in January 2002, and Odyssey began its science mapping mission on February 19, 2002.