Image MRO Aerobrake.jpg thumb 300px right An artist s conception of aerobraking with the Mars Reconnaissance Orbiter Aerobraking is a spaceflight maneuver that reduces the high point of an elliptical orbit ... Drag physics drag slows the spacecraft . Aerobraking is used when a spacecraft requires ..., aerobraking can be used to reduce fuel requirements. The use of a relatively small burn allows the spacecraft to be captured into a very elongated elliptic orbit . Aerobraking is then used to circularize ... to slow a spacecraft as needed. However, aerobraking is typically done with many orbital passes through ... any single pass. When aerobraking is done in this way, there is sufficient time after each pass to measure ... require several hundred passes through the atmosphere of the planet or moon. After the last aerobraking ... needed date March 2011 The kinetic energy dissipated by aerobraking is converted to heat , meaning that a spacecraft ..., but the temperatures and pressures associated with aerobraking are not as severe as those of atmospheric reentry or aerocapture . Simulations of the Mars Reconnaissance Orbiter aerobraking use a force ... on MGS ref that was exerted on the Mars Observer , during aerobraking is comparable to the force ... the theory of aerobraking is well developed, utilising the technique is difficult because a very ... . Citation needed date March 2011 NASA has used aerobraking four times to modify a spacecraft ... web last Prince, Jill L. H. Powell, Richard W. Murri, Dan title Autonomous Aerobraking A Design, Development ... September 2011 ref On 19 March 1991, aerobraking was demonstrated by the Hiten spacecraft. This was the first aerobraking maneuver by a deep space probe. ref http solarsystem.nasa.gov missions profile.cfm .... Tucker, http www.ion.org search view abstract.cfm?jp p&idno 4975 Navigation for Muses A HITEN Aerobraking ... s Space Page MUSES A Hiten ref Another aerobraking maneuver was conducted on 30 March. In May 1993, aerobraking was used during the extended Venus ian mission of the Magellan spacecraft . It was used ... more details
wiktionary aerodynamic Aerodynamics is the science of the motion of air. Aerodynamic may also refer to Aerodynamic song Aerodynamic , a song by Daft Punk Aerodynamic center See also Aerobraking Automotive aerodynamics disambiguation ... more details
spacecraft undergoes aerocapture in the film incorrectly called aerobraking , which is demonstrated ... reentry Aerobraking Aerogravity assist Asteroid capture Category Spacecraft propulsion spacecraft stub ... more details
Refimprove date December 2009 Orbit insertion is the spaceflight operation of adjusting a spacecraft s momentum to allow for entry into a stable orbit around a planet , moon , or other celestial body. ref cite web url http library.thinkquest.org 03oct 02144 spacecraft orbit.htm Thinkquest.org title Orbital Insertion ref This maneuver involves either deceleration from a speed in excess of the respective body s escape velocity , or acceleration to it from a lower speed. Deceleration The first kind of orbit insertion is used when capturing into orbit around a celestial body other than Earth, owing to the excess speed of interplanetary transfer orbits relative to their destination orbits. This shedding of excess velocity is typically achieved via a rocket firing known as an orbit insertion burn. For such a maneuver, the spacecraft s engine thrusts in its direction of travel for a specified duration to slow its velocity relative to the target body enough to enter into orbit. ref cite web url http www.astronomy.com link.aspx? id 8d44e60f 5911 4e5a ae09 158e39ad8655 Astronomy.com title MESSENGER poised for Mercury orbit insertion ref Another technique, used when the destination body has a tangible atmosphere, is called aerobraking , which uses the friction of atmospheric drag to slow a spacecraft. Generally aerobraking is used to circularize a highly elliptical capture orbit while minimizing the use of on board fuel. To date, only a handful of aerocapture maneuvers have been attempted by NASA. ref cite web url http trs new.jpl.nasa.gov dspace bitstream 2014 17918 1 99 1368.pdf jpl.nasa.gov title AEROBRAKING AT VENUS AND MARS A COMPARISON OF THE MAGELLAN AND MARS GLOBAL SURVEYOR AEROBRAKING PHASES ref Acceleration The second type of orbit insertion is used for newly launched satellite s and other spacecraft. The majority of space launch vehicle s used today can only launch a payload into a very narrow range of orbits. The angle relative to the equator and maximum altitude o ... more details
An aerogravity assist , or AGA , is a spacecraft maneuver designed to change velocity when arriving at a body with an atmosphere . A pure gravity assist uses only the gravity of a body to change the direction of the spacecraft trajectory. The change in direction is limited by the mass of the body, and how closely it can be approached. An aerogravity assist uses a closer approach to the planet, dipping into the atmosphere, so the spacecraft can also use lift force aerodynamic lift to further curve the trajectory. This enables the spacecraft to deflect through a larger angle, resulting in a higher delta v change in velocity . This in turn allows a shorter travel time, a larger payload fraction of the spacecraft, or a smaller spacecraft for a given payload. The related techniques of aerocapture , aerobraking , and atmospheric re entry also attempt to use the body s atmosphere to help reduce propulsion requirements. In an aerogravity assist, however, the goal is not to use the atmosphere to slow the spacecraft down, but instead use it to achieve a larger change in direction. Aerogravity assists are so far theoretical and have not yet been used. See also Aerocapture Aerobraking Atmospheric reentry References cite conference title Hypersonic maneuvering to provide planetary gravity assist author McDonald, Angus D., Randolph, James E. booktitle AIAA 1990 539, 28th Aerospace Sciences Meeting location Reno, NV date Jan 8 11,1990 cite journal doi 10.1016 0094 5765 94 00195 R title Aerogravity assist trajectories to the outer planets author Sims, JA and Longuski, JM and Patel, MR journal Acta Astronautica volume 35 pages 297 297 year 1995 publisher Pergamon Press Category Spaceflight Category Space technology Category Spacecraft propulsion ... more details
. this timeline should be considered closed, and new events should go in the orbital insertion and aerobraking timeline Orbital insertion Aerobraking timeline Image MRO First Image crop.jpg thumb right ... its periapsis by 94 km, in preparation to begin aerobraking . April 7, 2006 MRO begins a seven month long Aerobraking Stage to reduce its highly elliptical orbit to a circular, low Mars orbit by mid November. August 30, 2006 Aerobraking ended with a 6 minute burn of MRO s Trajectory Correction ... 11, 2006 The second of two burns to finalize MRO s orbit was performed, officially ending the Aerobraking ... more details
with aerobraking shield on top and shock absorbing landing ring at the bottom Alternatively, the incoming ... Aerobraking Aerocapture Aerogravity assist Asteroid capture Atmospheric reentry Skip reentry References ... more details
orphan date August 2010 The mission characteristic velocity also mission velocity or characteristic velocity is an important parameter describing space mission s. It is the total delta v needed for all maneuvers of the mission, typically given in km s. To achieve low earth orbit it is approximately 8 km s, while to escape from Earth needs 11.2 km s, both ideal minimus figures for neglecting various inefficiencies that typically range from 10 to 20 . For the Apollo program Apollo lunar landings with return to Earth it was of the order of 20 km s. Because the mass ratio required for a given mission is exponential in the mission velocity divided by the effective exhaust velocity of the rocket propulsion system, high mission velocities rapidly become extremely expensive for chemical rockets, so that the mission velocity, along with the payload, is a key parameter in assessing the overall difficulty of a given mission. Missions that would at first appear to be infeasible due to high mission velocity can sometimes be done by means of various tricks, such as gravity assist encounters with planets along the way, aerobraking , staging to intermediate bases, etc. Some of these have been described in the large literature of astronautics , e.g. Arthur C Clarke s Interplanetary Flight , and many others. Category Spaceflight Category Physics space stub tr Karakteristik u u h z ... more details
solve the problem of deceleration from orbital speeds through using atmospheric drag aerobraking provide ... the atmospheric drag effect of aerobraking . Intentional aerobraking is achieved by orienting ... more details
. This particular mission seems to have been revised into an expanded mission to demonstrate aerobraking ... and human habitation 2016 Mars Sample Return mission with NASA 2018 A technology demonstrator for aerobraking ... of Mars. 2016? Mars Sample Return mission with NASA 2018? A technology demonstrator for aerobraking ... more details
For the indian soap star Hiten Tejwani cleanup date May 2010 Infobox spacecraft Name Hiten Hagoromo Muses A Image File Hiten.gif 150px Caption Hiten spacecraft Organization Institute of Space and Astronautical Science ISAS Major Contractors Mission Type Orbiter Flyby Of Satellite Of Moon Orbital Insertion Date 19 March 1990 Launch 11 46, 24 January 1990 UTC Launch Vehicle Mu 3S II no. 5 Decay Mission Duration Age 1990 1 24 1993 4 10 years, 2 months NSSDC ID 1990 007A Webpage http nssdc.gsfc.nasa.gov nmc spacecraftDisplay.do?id 1990 007A Hiten Mass 197.4 kg Power Orbital elements Semimajor Axis Eccentricity Inclination Orbital Period Apoapsis Periapsis Orbits 10 The Hiten Spacecraft IPA ja hite , given the English name Celestial Maiden ref name Uesugi 2003 and known before launch as MUSES A Mu rocket family Mu Space Engineering Spacecraft A , part of the MUSES Program , was built by the Institute of Space and Astronautical Science of Japan and launched on January 24, 1990. It was Japan s first lunar probe , the first robotic lunar probe since the Soviet Union s Luna 24 in 1976, and the first lunar probe launched by a country other than Soviet Union or the United States . ref name NASA Hiten Hagoromo Hiten was to have been placed into a highly elliptical Earth orbit with an apogee of 476,000 km, which would be swing past the moon. However, the injection took place with a delta v deficit of 50 m s, resulting in an apogee of only 290,000 km ref name nasa . The deficiency was corrected and the probe continued on its mission. On the first lunar swing by, Hiten released a small orbiter, Hagoromo named after the feather mantle of Hiten , into lunar orbit. The transmitter on Hagoromo failed, but its orbit was visually confirmed from Earth. After the eighth swing by, Hiten successfully demonstrated the aerobraking technique on March 19, 1991. This was the first aerobraking maneuver by a deep space probe. ref name Siddiqi After the ninth lunar swing by and second ae ... more details
File Mars Surveyor 2001 Rover.jpg thumb right 200px Mock up of canceled Mars Surveyor 2001 rover, based on Mars Pathfinder s Sojourner The Mars Surveyor 2001 project was a multi part Mars exploration mission intended as a follow up to Mars Surveyor 1998 . After the two probes of the 1998 project, Mars Climate Orbiter and Mars Polar Lander , were both lost, NASA s better, faster, cheaper exploration philosophy was re evaluated, with a particular eye on the two 2001 project probes. As a result, the Mars Surveyor 2001 Lander was canceled in May 2000, but the decision was made to go ahead with its orbiter counterpart. The Mars Surveyor 2001 Orbiter , renamed 2001 Mars Odyssey , was launched April 7, 2001 reached Mars on October 24, 2001. After aerobraking from October 2001 until January 2002, Mars Odyssey began mapping the planet on February 19, 2002. By December 15, 2010 the orbiter broke the record for longest serving spacecraft at Mars, with 3,340 days of operation, claiming the title from NASA s Mars Global Surveyor , which had arrived sooner than Odyssey but failed in 2006. ref http mars.jpl.nasa.gov odyssey news whatsnew index.cfm?FuseAction ShowNews&NewsID 1091 Press Release ref Some other active orbital missions during this period include Mars Express since 2003 and Mars Reconnaissance Orbiter since 2006 , in addition there were a few landers and flybys. References Cite web url http nssdc.gsfc.nasa.gov nmc spacecraftDisplay.do?id MS2001L accessdate February 4, 2010 title NASA NSSDC Spacecraft Details Cite web url http www.solarviews.com eng odyssey.htm accessdate February 4, 2010 title 2001 Mars Odyssey Spacecraft Cite web url http www.xs4all.nl carlkop dustmar.html accessdate February 4, 2010 title Mars Surveyor 2001 Notes reflist Links http nssdc.gsfc.nasa.gov nmc masterCatalog.do?sc MS2001R Mars Surveyor 2001 rover Category Missions to Mars Category NASA programs Category 2001 Mars Odyssey US spacecraft stub de Mars Surveyor fr Mars Surveyor 2001 ja ... more details
Field propulsion is the concept of spacecraft propulsion where no propellant is necessary but instead momentum of the spacecraft is changed by an interaction of the spacecraft with external force fields. Examples are a gravity assist trajectory, which uses planetary gravity fields and orbital momentum, schemes that use electromagnetic field s such as radiation pressure , e.g. solar sails or photonic drive, and aerodynamic fields such as solar wind and aerobraking . Other concepts that have been proposed are more speculative, using frontier physics that may or may not become engineering practice in the future. Although speculative, ideas such as coupling to the momentum flux of the zero point electromagnetic wave field hypothesized in stochastic electrodynamics have a plausible basis for further investigation within the existing theoretical physics paradigm. Examples of proposals for field propulsion that rely on physics outside the present paradigms are various schemes for faster than light , warp drive and antigravity , and often amount to little more than catchy descriptive phrases, with no known physical basis. Any such schemes worthy of discussion must rely on energy and momentum transfer to the spacecraft from some external source such as a local force field, which in turn must obtain it from still other momentum and or energy sources in the cosmos, in order to satisfy conservation of both energy and momentum. One possible method gaining some credibility involves magnetohydrodynamics , in which the entire vehicle acts like the armature of an electric motor and the external environment acts as the stator. Instead of the engine being a separate or distinct part of the vehicle, in this system the vehicle s power source, controls, payload and occupants are all inside the engine itself. This system seems to satisfy many of the requirements of a field propulsion system and is based on known field theory. It represents a radical departure from current ideas of aeronau ... more details
to protect it from the heating induced by the aerobraking . Once released, the antenna extends ... Mars orbit on March 10, 2006. The aerobraking phase, needed to reach the operational orbit ... more details
refimprove date August 2010 Infobox spacecraft Image File Zond L1 drawing.png 150px Caption Zond 5 Name Zond 5 Soyuz 7K L1 s n 5 Major Contractors OKB 1 Bus Soyuz 7K L1 Mission Type Lunar flyby br Spacecraft test Launch Date 15 September 1968 br 21 42 11 UTC Carrier Rocket Proton K Block D D Launch Site Baikonur Cosmodrome Baikonur Landing Site 32 38 S 65 33 E Mass convert 5375 kg Zond 5 , a formal member of the Soviet Zond program and unmanned version of Soyuz 7K L1 manned moon flyby spacecraft, was launched from a Tyazheliy Sputnik 68 076B in Earth parking orbit to make scientific studies during a lunar flyby and to return to Earth. Zond 5 became the first spacecraft to circle the Moon and return to land on Earth. On September 18, 1968, the spacecraft flew around the Moon. The closest distance was 1,950 km. High quality photographs of the Earth were taken at a distance of 90,000 km. A biological payload of two russian tortoise s, wine fly wine flies , meal worm s, plant s, seed s, bacteria , and other living matter was included in the flight. September 21, 1968, the reentry capsule entered the Earth s atmosphere, aerobraking braked aerodynamically by means of skip reentry , and deployed its parachutes at 7 km. The capsule splashed down in the Indian Ocean and was successfully recovered by the USSR recovery vessels Borovichy and Vasiliy Golovin . ref http books.google.com books?id QdBP8E4di0sC&pg PA320&lpg PA320&dq zond 5 Borovichy&source bl&ots kgIETdSo70&sig BefzLjM5VnjTGUalEG9yToip RQ&hl en&ei UEn TO2qK5TksQPVqIWwCw&sa X&oi book result&ct result&resnum 1&ved 0CBUQ6AEwAA v onepage&q zond 205 20Borovichy&f false Zond 5, Recovery Ship, Miss Distance , Red Moon By Michael Cassutt page 320, Recovery Ship and Miss Distance. ref ref https sse.jpl.nasa.gov missions profile.cfm?Sort Alpha&Alias Zond 2005&Letter Z&Display ReadMore Zond 5, Landing Point, Miss Distance , NASA Solar System Exploration Zond 5, Landing Point, Miss Distance. ref The biological pa ... more details
for the animal moose imagestack Image Operation MOOSE figure 110 .PNG thumb 250px Fig. 110 from Analysis and Design of Space Vehicle Flight Control Systems Image Operation MOOSE figure 111 .PNG thumb 250px Fig. 111 from Analysis and Design of Space Vehicle Flight Control Systems Image Operation MOOSE figure 112 .PNG thumb 250px Fig. 112 from Analysis and Design of Space Vehicle Flight Control Systems MOOSE , originally an acronym for Man Out Of Space Easiest but later changed to the more professional sounding Manned Orbital Operations Safety Equipment , was a proposed emergency bail out system capable of bringing a single astronaut safely down from Earth orbit to the planet s surface. The design was proposed by General Electric in the early 1960s. The system was quite compact, weighing 200 pounds 90 kilograms and fitting inside a suitcase sized container. It consisted of a small twin nozzle rocket motor sufficient to deorbit the astronaut, a PET film biaxially oriented PET film bag six feet 1.8 metres long with a flexible quarter inch thick ablative heat shield on the back, two pressurized canisters to fill it with polyurethane foam , a parachute , radio equipment and a survival kit. The astronaut would leave his vehicle in a space suit , climb inside the plastic bag, and then fill it with foam. The bag had the shape of a blunt cone, with the astronaut embedded in its base facing outward. The rocket pack would protrude from the bag and be used to slow the astronaut s orbital momentum enough so that he would reenter Earth s atmosphere , and the foam filled bag would act as insulation during the subsequent aerobraking . Finally, once the astronaut had descended to 30,000 feet 9 km where the air was sufficiently dense, the parachute would automatically deploy and slow the astronaut s fall to 17 mph 7.6 metres per second . The foam heat shield would serve a final role as cushioning when the astronaut touched down and as a flotation device should he land on water. The ra ... more details
Infobox Spacecraft Name Venera 8 3V V 72 Image Image Venera 8.jpg 300px Caption Venera 8 Organization USSR Major Contractors Mission Type Lander Satellite Of Venus Orbital Insertion Date Landed on 22 July 1972 Launch 1972 03 27 at 04 15 01 UTC Launch Vehicle Proton Booster Plus Upper Stage and Escape Stages Decay Mission Duration 1972 03 27 to 22 July 1972 NSSDC ID 1972 021A Webpage Mass 1180 kg Power Orbital elements Semimajor Axis Eccentricity Inclination Orbital Period Apoapsis Periapsis Orbits Venera 8 lang ru 8 manufacturer s designation 3V V 72 was a Space probe probe in the Soviet space program Soviet Venera program for the exploration of Venus . Venera 8 was a Venus atmospheric probe and lander. Its instrumentation included temperature, pressure, and light sensors as well as an altimeter , gamma ray spectrometer , gas analyzer , and radio transmitters. The spacecraft took 117 days to reach Venus with one mid course correction on 6 April 1972, separating from the bus which contained a cosmic ray detector, solar wind detector, and ultraviolet spectrometer and entering the atmosphere on 22 July 1972 at 08 37 UT. A refrigeration system attached to the bus was used to pre chill the descent capsule s interior prior to atmospheric entry in order to prolong its life on the surface. Descent speed was reduced from 41,696 km h to about 900 km h by aerobraking . The 2.5 meter diameter parachute opened at an altitude of 60 km. Image Venera 8 capsule.jpg thumb left Venera 8 landing capsule Venera 8 transmitted data during the descent. A sharp decrease in illumination was noted at 35 to 30 km altitude and wind speeds of less than 1 km s were measured below 10 km. Venera 8 landed at 09 32 UT in what is now called Vasilisa Region , within 150 km radius of Venus coords and quad cat 10.70 S 335.25 E , in sunlight, about 500 km from the morning terminator solar terminator . The lander mass was 495 kg. It continued to send back ... more details
s speed, which allowed it to be captured into orbit around Mars. Odyssey used a technique called aerobraking ... was able to save more than Convert 200 kg sp us of propellant. Aerobraking ended in January, and Odyssey ..., by monitoring atmospheric conditions during months when the newly arrived orbiter used aerobraking ... more details
hemisphere. Aerobraking After orbit insertion, Surveyor performed a series of orbit changes to lower ... used this aerobraking technique over a period of four months to lower the high point of its orbit ... team performed a maneuver to raise the periapsis out of the atmosphere. This suspension of aerobraking ... damaged shortly after launch in November 1996. Aerobraking was resumed on 7 November after flight team members concluded that aerobraking was safe, provided that it occurs at a more gentle pace than proposed ..., aerobraking occurred with the low point of the orbit at an average altitude of Convert 120 km 0 abbr .... During these six months, aerobraking reduced the orbit period to between 12 and 6 hours. From May to November 1998, aerobraking was temporarily suspended to allow the orbit to drift into the proper .... Without this hiatus, Surveyor would complete aerobraking with its orbit in the wrong solar orientation ... point of each orbit. Finally, from November 1998 to March 1999, aerobraking continued and shrank ... Mars once every two hours. Aerobraking was scheduled to terminate at the same time the orbit drifted ... more details
Encyclopedia
top
