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140-634: Shuttle-Centaur was a version of the Centaur upper stage rocket designed to be carried aloft inside the Space Shuttle and used to launch satellites into high Earth orbits or probes into deep space. Two variants were developed: Centaur G-Prime , which was planned to launch the Galileo and Ulysses robotic probes to Jupiter , and Centaur G , a shortened version planned for use with United States Department of Defense Milstar satellites and

280-660: A Titan 34D in October 1982, when it placed two military satellites in geosynchronous orbit . It was then used on a Space Shuttle mission, STS-6 in April 1983, to deploy the first tracking and data relay satellite (TDRS-1), but the IUS's nozzle changed its position by one degree, resulting in the satellite being placed in the wrong orbit. It took two years to determine what had gone wrong and how to prevent it happening again. The decision to go with Centaur pleased planetary scientists and

420-610: A 4.6-meter (15 ft) aluminum structure that handled communications between the Space Shuttle and the Centaur upper stage. It helped keep the number of modifications to the Space Shuttle to a minimum. When the cargo doors opened, the CISS would pivot 45 degrees into a ready position to launch Centaur. After twenty minutes, the Centaur would be launched by a set of twelve coil springs with a 10-centimeter (4 in) stroke known as

560-403: A 5:1 fuel ratio. The Centaur G stage had two RL10-3-3B engines, each with 66,700 newtons (15,000 lb f ) thrust, and specific impulse of 440.4 seconds, with a 6:1 fuel ratio. The engines were capable of multiple restarts after long periods of coasting in space and had a hydraulic gimbal actuation system powered by the turbopump . The Centaur G and G-Prime avionics were the same as that of

700-470: A Jupiter orbiter, the orbiter being launched in February 1984 and the probe following a month later. The orbiter would be in orbit around Jupiter when the probe arrived, allowing it to perform its role as a relay. Separating the two spacecraft was estimated to cost another $ 50 million (equivalent to $ 169 million in 2023). NASA hoped to be able to recoup some of this through separate competitive bidding on

840-764: A champion in Congressman Edward P. Boland , who considered the IUS too underpowered for deep space missions, although he did not oppose its development for other purposes. He was impressed by Centaur's ability to put Galileo in Jupiter orbit with just two years' flight and saw potential military applications for it as well. He chaired the House Intelligence Committee and the House Independent Agencies Appropriations Subcommittee of

980-495: A configuration with three stages, two large and one small, that could be used for a planetary mission like Galileo . NASA contracted with Boeing for its development. Congress approved funding for the Jupiter Orbiter Probe on 12 July 1977. The following year the spacecraft was renamed Galileo after Galileo Galilei , the 17th-century astronomer who had discovered the largest four of Jupiter's moons, now known as

1120-421: A decrease in strength as temperatures get extremely high. The Young's Modulus of the material, defined as the ratio between stress and strain experienced by the material, decreases as the temperature increases. Young's Modulus is critical in the selection of materials for wing, as a higher value lets the material resist the yield and shear stress caused by the lift and thermal loads. This is because Young's Modulus

1260-513: A deployment attempt as early as seven hours after launch, both crews were entirely composed of astronauts who had already flown in space at least once before and were known to not suffer from it. The two launches would only have a one-hour launch window and there would be just five days between them. Because of this, two launch pads would be used: Launch Complex 39A for STS-61-G and Atlantis and Launch Complex 39B for STS-61-F and Challenger . The latter had only recently been refurbished to handle

1400-406: A function of the lift force, first and second moments of inertia , and length of the spar. When there are more spars and stringers, the load in each member is reduced, and the area of the stringer can be reduced to meet critical stress requirements. However, the increase in temperature caused by energy flowing from the air (heated by skin friction at these high speeds) adds another load factor, called

1540-564: A gentler ascent with more horizontal velocity and less vertical velocity, which reduces deceleration to survivable levels in the event of a launch abort and ballistic reentry occurring at any point in the flight. Centaur V is the upper stage of the new Vulcan launch vehicle developed by the United Launch Alliance to meet the needs of the National Security Space Launch (NSSL) program. Vulcan

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1680-443: A half times more energy than the upper stage ULA currently flies. “But that’s just the tip of the iceberg,” Bruno elaborated. “I’m going to be pushing up to 450, 500, 600 times the endurance over just the next handful of years. That will enable a whole new set of missions that you cannot even imagine doing today.” Vulcan finally launched on 8 January 2024 and the stage performed flawlessly on its maiden flight. On 4 October 2024, in

1820-538: A lucrative segment of the satellite launch business. The USAF, though disappointed with NASA's decision to drop the three-stage IUS, foresaw a need for USAF satellites to carry more propellant than previously to engage in avoidance maneuvers against anti-satellite weapons. Two groups, in particular, were unhappy with the decision: Boeing and the Marshall Space Flight Center. Other aerospace companies were disappointed that NASA had decided to adapt

1960-472: A new propellant fill, drain and dump system; and an S band transmitter and RF system compatible with the TDRS system. Considerable effort was put into making Centaur safe, with redundant components to overcome malfunctions and a propellant draining, dumping and venting system so that the propellants could be dumped in case of emergency. Both versions were cradled in the Centaur integrated support system (CISS),

2100-556: A payload was something being carried into space like a satellite. The 1981 Memorandum of Agreement between the Johnson Space Center and the Lewis Research Center defined the Centaur as an element. The engineers at the Lewis Research Center initially preferred to have it declared a payload, because time was short and this minimized the amount of interference in their work by the Johnson Space Center. Centaur

2240-465: A possible experimental resource for testing in-space cryogenic fluid management techniques. In October 2009, the Air Force and United Launch Alliance (ULA) performed an experimental demonstration on the modified Centaur upper stage of DMSP-18 launch to improve "understanding of propellant settling and slosh , pressure control, RL10 chilldown and RL10 two-phase shutdown operations. DMSP-18

2380-530: A pre-recorded message during the broadcast of the Vulcan Cert-2 mission, Upgrades Development Director Amanda Bacchetti had stated that ULA would be developing a "LEO Optimized Centaur" set to launch aboard a Vulcan launch vehicle sometime in 2025. She had stated that this variant of Centaur V would be shorter (and therefore more mass efficient for LEO orbits), however specifications for this variant were not given. The Centaur concept originated in 1956 when

2520-805: A shortened version, reduced in length from approximately 9 to 6 m (30 to 20 ft), planned for U.S. DoD payloads and the Magellan Venus probe. After the Space Shuttle Challenger accident , and just months before the Shuttle-Centaur had been scheduled to fly, NASA concluded that it was too risky to fly the Centaur on the Shuttle. The probes were launched with the much less powerful solid-fueled IUS , with Galileo needing multiple gravitational assists from Venus and Earth to reach Jupiter. The capability gap left by

2660-420: A thermal load, to the spars. This thermal load increases the force felt by the stringers, and thus the area of the stringers must be increased in order for the critical stress requirement to be met. Another issue that aerodynamic heating causes for aircraft design is the effect of high temperatures on common material properties. Common materials used in aircraft wing design, such as aluminum and steel, experience

2800-472: A vigorous campaign to save it. The staff formed a committee to save the center, and began lobbying Congress. The committee enlisted Ohio Senator John Glenn and representatives Mary Rose Oakar , Howard Metzenbaum , Donald J. Pease , and Louis Stokes in their efforts to persuade Congress to keep the center open. McCarthy retired in July 1982, and Andrew Stofan became the director of the Lewis Research Center. He

2940-478: A year; he thought that twelve was more likely, and given that only the newest two orbiters, Discovery and Atlantis could lift his largest payloads, there might not be enough Space Shuttle flights. Reagan was persuaded to revise his policy to permit a mixed fleet of ELVs and Space Shuttles, and the USAF ordered ten Titan IV rockets in 1984. NASA historian T. A. Heppenheimer noted that in retrospect, "it

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3080-521: Is an important factor in the equations for calculating the critical buckling load for axial members and the critical buckling shear stress for skin panels. If the Young's Modulus of the material decreases at high temperatures caused by aerodynamic heating, then the wing design will call for larger spars and thicker skin segments in order to account for this decrease in strength as the aircraft goes supersonic. There are some materials that retain their strength at

3220-547: Is available on a reasonable schedule or with comparable costs." Centaur provided important advantages over the IUS. The main one was that it was far more powerful. The Galileo probe and orbiter could be recombined and the probe could be delivered directly to Jupiter in two years' flight time. Longer travel times meant that components would age and the onboard power supply and propellant would be depleted. The radioisotope thermoelectric generators (RTGs) on Ulysses and Galileo produced about 570 watts at launch, which decreased at

3360-415: Is capable of up to twelve restarts, limited by propellant, orbital lifetime, and mission requirements. Combined with the insulation of the propellant tanks, this allows Centaur to perform the multi-hour coasts and multiple engine burns required on complex orbital insertions. The reaction control system (RCS) also provides ullage and consists of twenty hydrazine monopropellant thrusters located around

3500-402: Is made up of spars , stringers , and skin segments . In a wing that normally experiences subsonic speeds, there must be a sufficient number of stringers to withstand the axial and bending stresses induced by the lift force acting on the wing. In addition, the distance between the stringers must be small enough that the skin panels do not buckle, and the panels must be thick enough to withstand

3640-775: Is the upper stage of the Atlas V rocket. Earlier Common Centaurs were propelled by the RL10-A-4-2 version of the RL-10. Since 2014, Common Centaur has flown with the RL10-C-1 engine, which is shared with the Delta Cryogenic Second Stage , to reduce costs. The Dual Engine Centaur (DEC) configuration will continue to use the smaller RL10-A-4-2 to accommodate two engines in the available space. The Atlas V can fly in multiple configurations, but only one affects

3780-630: The Magellan Venus probe. The powerful Centaur upper stage allowed for heavier deep space probes, and for them to reach Jupiter sooner, prolonging the operational life of the spacecraft. However, neither variant ever flew on a Shuttle. Support for the project came from the United States Air Force (USAF) and the National Reconnaissance Office , which asserted that its classified satellites required

3920-494: The Atlas I was the Centaur I stage, derived from earlier models of Centaur that also flew atop Atlas boosters. Centaur I featured two RL-10-A-3A engines burning liquid hydrogen and liquid oxygen, making the stage extremely efficient. To help slow the boiloff of liquid hydrogen in the tanks, Centaur featured fiberglass insulation panels that were jettisoned 25 seconds after the first stage booster engines were jettisoned. Centaur I

4060-620: The Convair division of General Dynamics began studying a liquid hydrogen fueled upper stage. The ensuing project began in 1958 as a joint venture among Convair, the Advanced Research Projects Agency (ARPA), and the U.S. Air Force . In 1959, NASA assumed ARPA's role. Centaur initially flew as the upper stage of the Atlas-Centaur launch vehicle, encountering a number of early developmental issues due to

4200-536: The Director of Defense Research and Engineering , in September 1973, and reached an informal agreement that the USAF would develop an interim upper stage (IUS) for the Space Shuttle, to be used for launching satellites in higher orbits pending the development of the space tug. After some debate, Pentagon officials agreed to commit to the IUS on 11 July 1974. The Secretary of Defense , James R. Schlesinger , confirmed

4340-676: The European Space Agency (ESA) each providing one spacecraft, but the American one was canceled in 1981, and NASA's contribution was limited to the power supply, launch vehicle, and tracking via the NASA Deep Space Network . The object of the mission was to gain an enhanced knowledge of the heliosphere by putting a satellite into a polar orbit around the Sun. Because Earth's orbit is inclined only 7.25 degrees to

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4480-517: The Galilean moons . During the early 1980s, Galileo struggled with both technical and funding difficulties, and the Office of Management and Budget (OMB) targeted NASA for budget cuts. The intervention of the USAF saved Galileo from cancellation. It was interested in the development of autonomous spacecraft like Galileo that could take evasive action in the face of anti-satellite weapons , and in

4620-615: The Galileo probe was moved to the Vertical Processing Facility at the Kennedy Space Center, where it was mated with Centaur. Of the four safety reviews required of the Shuttle-Centaur missions, three had been completed, although some issues arising from the last two remained to be resolved. The final review was originally scheduled for late January. Some more safety changes had been incorporated into

4760-456: The Galileo project's engineers decided to switch from a pressurized atmospheric entry probe to a vented one. This added 100 kilograms (220 lb) to its weight, and another 165 kilograms (364 lb) was added in structural changes to improve reliability, all of which would require extra fuel in the IUS. But the three-stage IUS was itself overweight, by about 3,200 kilograms (7,000 lb) against its design specifications. Lifting Galileo and

4900-684: The House Appropriations Committee , and had the Appropriations Committee instruct NASA to use Centaur if weight problems with Galileo prompted a further postponement. Orders from a Congressional committee had no legal standing, so NASA was free to disregard this. Appearing before the Senate , Frosch was non-committal, saying only that NASA had the matter under consideration. NASA decided to split Galileo into two separate spacecraft: an atmospheric probe and

5040-678: The Integrated Vehicle Fluids (IVF) feature expected to allow the extension of upper stage on-orbit life from hours to weeks. Centaur V uses two different versions of the RL10-C engine with nozzle extensions to improve the fuel consumption for the heaviest payloads. This increased capability over Common Centaur was intended to permit ULA to meet NSSL requirements and retire both the Atlas V and Delta IV Heavy rocket families earlier than initially planned. The new rocket publicly became

5180-528: The Space Shuttle external tank and Space Shuttle main engines (SSME). Throughout the 1960s and 1970s, Centaur was used as the upper stage of Atlas-Centaur launch vehicles, which helped launch seven Surveyor missions, five Mariner missions, and the Pioneer 10 and 11 probes. In the 1970s, Centaur was also placed atop the USAF's Titan III booster to create the Titan IIIE launch vehicle, which

5320-551: The TRL of the Advanced Cryogenic Evolved Stage Centaur successor. Although Centaur has a long and successful flight history, it has experienced a number of mishaps: Aerodynamic heating "For high speed aircraft and missiles aerodynamic heating is the conversion of kinetic energy into heat energy as a result of their relative motion in stationary air and the subsequent transfer through

5460-658: The Titan IV , which made its first flight in 1994. Over the next 18 years, Titan IV and Centaur G-Prime placed eighteen military satellites in orbit. Centaur is an upper stage rocket that used liquid hydrogen as fuel and liquid oxygen as an oxidizer . It was developed by General Dynamics in the late 1950s and early 1960s and powered by twin Pratt & Whitney RL10 engines. Rockets utilizing liquid hydrogen as fuel theoretically can lift 40 percent more payload per kilogram of liftoff weight than rockets burning kerosene , but

5600-754: The Vulcan Centaur in March 2018. In May 2018, the Aerojet Rocketdyne RL10 was announced as Centaur V's engine following a competitive procurement process against the Blue Origin BE-3 . Each stage will mount two engines. In September 2020, ULA announced that ACES was no longer being developed, and that Centaur V would be used instead. Tory Bruno, ULA's CEO, stated that the Vulcan's Centaur 5 will have 40% more endurance and two and

5740-401: The shear stress and shear flow present in the panels due to the lifting force on the wing. However, the weight of the wing must be made as small as possible, so the choice of material for the stringers and the skin is an important factor. At supersonic speeds, aerodynamic heating adds another element to this structural analysis. At normal speeds, spars and stringers experience a load which is

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5880-413: The 1970s and 1980s. By the end of 1989, Centaur-D had been used as the upper stage for 63 Atlas rocket launches, 55 of which were successful. The Saturn I was designed to fly with a S-V third stage to enable payloads to go beyond low Earth orbit (LEO). The S-V stage was intended to be powered by two RL-10A-1 engines burning liquid hydrogen as fuel and liquid oxygen as oxidizer. The S-V stage

6020-553: The 1970s, Centaur was fully mature and had become the standard rocket stage for launching larger civilian payloads into high Earth orbit, also replacing the Atlas-Agena vehicle for NASA planetary probes. An updated version, called Centaur-D1A (powered by RL10A-3-3 engines), was used on the Atlas-SLV3D came into use during the 1970s. The Centaur-D1AR was used for the Atlas-SLV3D and Atlas G came into use during

6160-425: The 1983 NASA appropriations bill that would have forbidden further work on Centaur, but his position was undermined by Aldridge and Beggs, who contended that the early Space Shuttle flights showed that classified Department of Defense satellites would require more shielding, which would add more weight, and therefore require the power of Centaur. Aldridge and Beggs announced that they would soon conclude an agreement for

6300-469: The Atlas booster and finesse of the upper stage. Initial Atlas-Centaur launches used developmental versions, labeled Centaur-A through -C. The only Centaur-A launch on 8 May 1962 ended in an explosion 54 seconds after liftoff when insulation panels on the Centaur separated early, causing the LH 2 tank to overheat and rupture. This version was powered by two RL10A-1 engines. After extensive redesigns,

6440-609: The CISS. The Space Shuttle main engines would have been run at 109 percent of the rated power level. The payloads needed to be deployed on the first day in orbit, so the missions would be flown by four-person crews composed of astronauts who had already flown in space and were known to not suffer from space adaptation syndrome . The first Centaur G-Prime was rolled out from the General Dynamics factory in Kearny Mesa, San Diego , on 13 August 1985. Just months before

6580-497: The Centaur G-Prime CISS 2,961 kilograms (6,528 lb). The CISS was fully reusable for ten flights and would be returned to Earth. The Space Shuttles Challenger and Atlantis were modified to carry the CISS. These changes included additional plumbing to load and vent Centaur's cryogenic propellants, and controls on the aft flight deck for loading and monitoring the Centaur upper stage. By June 1981,

6720-642: The Centaur Gs being built for the USAF, but had not made it to SC-1 and SC-2 owing to the strict deadline. After the disaster, $ 75 million (equivalent to $ 254 million in 2023) was earmarked for Centaur safety enhancements. Centaur (rocket stage) The Centaur is a family of rocket propelled upper stages that has been in use since 1962. It is currently produced by U.S. launch service provider United Launch Alliance , with one main active version and one version under development. The 3.05 m (10.0 ft) diameter Common Centaur/Centaur III flies as

6860-683: The Chairman of the House Subcommittee on Science, Technology and Space, Congressman Ronnie G. Flippo , whose district in Alabama encompassed the Marshall Space Flight Center. In July 1982, the proponents of Centaur added $ 140 million (equivalent to $ 374 million in 2023) to the Emergency Supplemental Appropriations Act, which was signed into law by Reagan on 18 July 1982. As well as allocating

7000-478: The IUS would require the use of the special lightweight version of the Space Shuttle external tank, the Space Shuttle orbiter stripped of all non-essential equipment, and the SSME running at full power—109 percent of their rated power level. This necessitated the development of a more elaborate engine cooling system. By late 1979, delays in the Space Shuttle program pushed the launch date for Galileo back to 1984, when

7140-416: The Lewis Research Center had awarded four contracts for Centaur G-Prime worth a total of $ 7,483,000 (equivalent to $ 20 million in 2023): General Dynamics was to develop the Centaur rockets; Teledyne, the computer and multiplexers ; Honeywell , the guidance and navigation systems; and Pratt & Whitney, the four RL10A-3-3A engines. Christopher C. Kraft Jr. , William R. Lucas , and Richard G. Smith ,

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7280-466: The Lewis Research Center manage the project. In November 1982, Andrew Stofan , the director of the Lewis Research Center, and Lew Allen , the director of the JPL, signed a Memorandum of Agreement on the Galileo project; JPL was responsible for the design and management of the mission, and the Lewis Research Center for integrating the Galileo spacecraft with the Centaur and the Space Shuttle. The future of

7420-491: The Lewis Research Center reduced the amount of propellant in the Centaur. This limited the number of possible launch days to just six. Concerned that this was too few, Nieberding gave a presentation to key management officials in which he made the case to Moore for the Space Shuttle engines to be run at 109 percent. Moore approved the request over the objections of representatives of the Marshall Space Flight Center and Johnson Space Center who were present. The astronauts considered

7560-409: The Lewis Research Center to determine the feasibility of integrating Centaur with the Space Shuttle. The engineers at Lewis concluded that it was both feasible and safe. A source inside NASA told The Washington Post journalist Thomas O'Toole that the cost of modifying Centaur so it could be carried on the Space Shuttle would be worth it, as the performance benefit of Centaur would mean that Galileo

7700-517: The Lewis Research Center was uncertain in the 1970s and early 1980s. The cancellation of the NERVA nuclear rocket engine had caused a round of layoffs in the 1970s, and many of the more experienced engineers had elected to retire. Between 1971 and 1981, staff numbers fell from 4,200 to 2,690. In 1982, the staff became aware that the Reagan administration was considering closing the center, and they mounted

7840-456: The Orbiter and the Centaur were routed through the CISS. Electrical power for the Centaur was provided by a 150-ampere-hour (540,000 C) silver zinc battery . Power for the CISS was provided by two 375-ampere-hour (1,350,000 C) batteries. Since the CISS was also plugged into the Orbiter, this provided two-failure redundancy. The Centaur G CISS weighed 2,947 kilograms (6,497 lb) and

7980-560: The Shuttle-Centaur group within the Space Transportation Engineering Division. Spurlock and Nieberding hired many young engineers, giving the Shuttle-Centaur project a mixture of youth and experience. The Shuttle-Centaur Project had to be ready to launch in May 1986, which was just three years away. The cost of a delay was estimated at $ 50 million (equivalent to $ 118 million in 2023). Failure to meet

8120-489: The Shuttle-Centaur missions to be riskiest Space Shuttle missions yet, referring to Centaur as the " Death Star ". The main safety issue that concerned them involved what would happen in the case of an aborted mission , a failure of the Space Shuttle systems to put them into orbit. In that case, the crew would dump the Centaur's propellant and attempt to land. This was an extremely dangerous maneuver, but also an extremely unlikely contingency (in fact, one that would never occur in

8260-550: The Shuttle-Centaur was scheduled to fly, the Challenger disaster occurred, and the project was canceled. The Galileo and Ulysses probes were ultimately launched using the much less powerful solid-fueled Inertial Upper Stage (IUS), Galileo needing multiple gravitational assists from Venus and Earth to reach Jupiter. The USAF mated a variant of the Centaur G-Prime upper stage with its Titan rocket to produce

8400-592: The Space Shuttle Challenger for 15 May 1986, and STS-61-G for Galileo in the Space Shuttle Atlantis for 20 May. Crews were assigned in May 1985: STS-61-F would be commanded by Frederick Hauck , with Roy D. Bridges Jr. as the pilot and mission specialists John M. Lounge and David C. Hilmers ; STS-61-G would be commanded by David M. Walker , with Ronald J. Grabe as pilot and James van Hoften and John M. Fabian , who

8540-639: The Space Shuttle with Centaur; it had more experience with Centaur than any of the other NASA centers; it had developed the Centaur; managed the Titan-Centaur project in which Centaur was mated with the Titan III booster; had experience with space probes through the Surveyor, Viking and Voyager projects; and had a highly skilled workforce where the average engineer had thirteen years of experience. In May 1981, Lovelace informed Lucas of his decision to have

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8680-469: The Space Shuttle's cargo bay, which could accommodate loads up to 18.3 meters (60 ft) long and 4.6 meters (15 ft) wide. The longer the Centaur, the less space for the payload and vice versa. From this arose two new versions of Centaur: Centaur G and Centaur G-Prime. Centaur G was intended for USAF missions, specifically to place satellites into geostationary orbits, and the $ 269 million (equivalent to $ 719 million in 2023) to design and develop it

8820-449: The Space Shuttle's cost-effectiveness. Moreover, Titan had been developed by and was owned and controlled by, the USAF, and its use would mean that NASA would have to work closely with the USAF, something that NASA management hoped to avoid as much as possible. While NASA and the USAF collaborated and depended on each other to some extent, they were also rivals, and NASA resisted attempts by United States Department of Defense (DoD) to manage

8960-400: The Space Shuttle, which the three directors regarded as a complex system that only their centers understood. Engineers at the Lewis Research Center saw matters differently. The director of the Lewis Research Center, John F. McCarthy Jr. , wrote to Lovelace in March, providing reasons why the Lewis Research Center was the best choice: it had led the project to evaluate the feasibility of mating

9100-478: The Space Shuttle. The first Centaur G-Prime, SC-1, was rolled out from the General Dynamics factory in Kearny Mesa, San Diego , on 13 August 1985. The theme music from Star Wars was played, a crowd of 300, mostly General Dynamics employees, was in attendance, as were astronauts Fabian, Walker and Hauck, and speeches were given by dignitaries. SC-1 was then flown to the Kennedy Space Center, where it

9240-478: The Sun's equator, the solar poles cannot be observed from Earth. Scientists hoped to gain a greater understanding of the solar wind , the interplanetary magnetic field , cosmic rays and cosmic dust . The Ulysses probe had the same initial destination as Galileo , as it would first have to travel out to Jupiter and then use a slingshot maneuver to leave the ecliptic plane and enter a solar polar orbit. Another mission for Shuttle-Centaur subsequently appeared in

9380-435: The Sun, was required. Fuel could be lost through microscopic holes that only hydrogen could leak through, but sealing the fuel tank created another problem. Even when insulated, heat leaks could cause the temperature to rise and boil the hydrogen; pressure in the tank can then build up and rupture it unless proper venting is provided, but too much venting will cause the loss of excessive amounts of fuel. These challenges dogged

9520-502: The Super*Zip separation ring. The Centaur upper stage would then coast at a speed of 0.30 meters per second (1 ft/s) for 45 minutes before starting its main burn a safe distance from the Space Shuttle. For most missions, only a single burn was required. Once the burn was complete, the spacecraft would separate from the Centaur upper stage, which could still maneuver to avoid striking the spacecraft. All electrical connections between

9660-540: The aerodynamic heating and erodes the material rather than heating the capsule. The surface of the heat shield for the Mercury spacecraft had a coating of aluminium with glassfiber in many layers. As the temperature rose to 1,100 °C (1,400 K) the layers would evaporate and take the heat with it. The spacecraft would become hot but not harmfully so. The Space Shuttle used insulating tiles on its lower surface to absorb and radiate heat while preventing conduction to

9800-424: The amount of fuel carried by Centaur. Surprised by the board's approval of Centaur, Hauck offered his crew the opportunity to resign from the mission with his support, but no one accepted the offer. On 28 January 1986, Challenger lifted off on STS-51-L . A failure of the solid rocket booster 73 seconds into flight tore Challenger apart, resulting in the deaths of all seven crew members. The Challenger disaster

9940-533: The astronaut who was chief of the Shuttle office, took their concerns to the Johnson Space Center Configuration Control Board, which ruled the risk acceptable. Engineers at the Lewis Research Center, the JPL and General Dynamics dismissed the astronauts' concerns about liquid hydrogen, pointing out that the Space Shuttle was propelled by liquid hydrogen and at liftoff the Space Shuttle's external tank contained 25 times

10080-411: The best option. Magellan was tentatively scheduled for launch in April 1988. The USAF adopted Shuttle-Centaur in 1984 for the launch of its Milstar satellites. These military communications satellites were hardened against interception, jamming and nuclear attack. Telephone conversations with General Dynamics regarding the project had to be conducted over secure lines. Having the USAF on board had saved

10220-411: The challenges of using liquid hydrogen required new technology to be developed. Liquid hydrogen is a cryogenic fuel , meaning that it condenses at extremely low temperatures, and must be stored below −253 °C (−423 °F) to keep it from boiling. Thus, insulation from all sources of heat, including the rocket exhaust, the relatively warm liquid oxygen, aerodynamic heating , and the radiant heat of

10360-502: The deadline meant waiting another year until the planets were properly aligned again. The project adopted a mission logo depicting a mythical centaur emerging from the Space Shuttle and firing an arrow at the stars. Larry Ross, the Director of Space Flight Systems at the Lewis Research Center, had the logo emblazoned on project stationery and memorabilia like drink coasters and campaign buttons . A special Shuttle-Centaur project calendar

10500-506: The decision to terminate Saturn V production in 1970 and the abandoning of plans to build a space station. The space tug became an upper stage, to be carried into space by the Space Shuttle. As a hedge against further cutbacks or technical difficulties, NASA also commissioned studies of reusable Agena and Centaur upper stages. With funding tight, NASA sought to offload Space Shuttle-related projects onto other organizations. NASA Deputy Administrator George Low met with Malcolm R. Currie ,

10640-586: The decision when he met with NASA Administrator James C. Fletcher and Low four days later. A series of study contracts were let, resulting in a decision that the IUS would be an expendable solid-fuel upper stage. A call for bids was then issued, and the competition was won by Boeing in August 1976. The IUS was renamed the Inertial Upper Stage in December 1977. The Marshall Space Flight Center

10780-453: The development of Centaur with technical difficulties, such as fuel leaking through the welds, and the shrinking of the metal bulkhead when coming into sudden contact with the cryogenic temperatures of liquid hydrogen. Further complicating matters was the explosion of an RL10 on an engine test stand during a demonstration for United States Air Force (USAF) and National Air and Space Administration (NASA) officials. The project's management

10920-565: The directors of the Johnson Space Center , Marshall Space Flight Center and Kennedy Space Center respectively, did not like NASA Headquarters' decision to assign Shuttle-Centaur to the Lewis Research Center. In a January 1981 letter to Alan M. Lovelace , the acting Administrator of NASA, they argued that management of the Shuttle-Centaur project should instead be assigned to the Marshall Space Flight Center, which had some experience with cryogenic propellants and more experience with

11060-469: The engine end of the stage. Most payloads launch on Single Engine Centaur (SEC) with one RL10 . This is the variant for all normal flights of the Atlas V (indicated by the last digit of the naming system, for example Atlas V 421). A dual engine variant with two RL-10 engines is available, but only for launching the CST-100 Starliner crewed spacecraft. The higher thrust of two engines allows

11200-485: The existing Centaur upper stage rather than develop a new high energy upper stage (HEUS) or the orbital transfer vehicle (OTV), as the space tug was now called. The OMB was not opposed to Centaur on any technical grounds, but it was a discretionary expense and in the budget-cutting atmosphere of 1981, one that the OMB felt could be dropped for the fiscal year 1983 budget, which was submitted to Congress in February 1982. Galileo

11340-521: The first time in 20 years, 190 new engineers being hired. In the process, the Lewis Research Center drifted away from fundamental research and became involved in the management of major projects like Shuttle-Centaur. William H. Robbins was appointed the head of the Shuttle-Center Project Office at the Lewis Research Center in July 1983. Most of his experience was with NERVA, and this was his first experience with Centaur, but he

11480-445: The first to orbit it, while the probe it carried would be the first to enter its atmosphere. In December 1984, Galileo project manager John R. Casani proposed that Galileo make a flyby of asteroid 29 Amphitrite while en route. It would be the first time a US space mission visited an asteroid. NASA Administrator James M. Beggs endorsed the proposal as a secondary objective for Galileo . To enhance reliability and reduce costs,

11620-491: The following general specifications: Shuttle-Centaur was a proposed Space Shuttle upper stage. To enable its installation in shuttle payload bays, the diameter of the Centaur's hydrogen tank was increased to 4.3 m (14 ft), with the LOX tank diameter remaining at 3.0 m (10 ft). Two variants were proposed: Centaur G Prime, which was planned to launch the Galileo and Ulysses robotic probes, and Centaur G,

11760-748: The form of the Venus Radar Mapper, later renamed Magellan . The first mission integration panel meeting for this probe was held at the Lewis Research Center on 8 November 1983. Several Space Shuttle upper stages were considered, including the Orbital Sciences Corporation Transfer Orbit Stage (TOS), the Astrotech Corporation Delta Transfer Stage, and the Boeing IUS, but the meeting chose Centaur as

11900-429: The funding, it directed NASA and Boeing to cease work on the two-stage IUS for Galileo . Flippo fought this decision. He argued that Centaur was too expensive, as it cost $ 140 million in the current year with the whole Shuttle-Centaur project estimated to cost around $ 634 million (equivalent to $ 1694 million in 2023); that it was of limited use, since it was only required for two deep space missions; and that it

12040-570: The high temperatures that aerodynamic heating induces. For example, Inconel X-750 was used on parts of the airframe of the X-15 , a North American aircraft that flew at hypersonic speeds in 1958. Titanium is another high-strength material, even at high temperatures, and is often used for wing frames of supersonic aircraft. The SR-71 used titanium skin panels painted black to reduce the temperature and corrugated to accommodate expansion. Another important design concept for early supersonic aircraft wings

12180-530: The joint development of Shuttle-Centaur. Flippo's amendment was defeated by a vote of 316 to 77, clearing the way for the Shuttle-Centaur project. On 30 August 1982, a meeting of representatives of the NASA centers and Centaur contractors was held at General Dynamics in San Diego to discuss the requirements of the project. The principal constraint was that both the satellite and Centaur upper stage had to fit inside

12320-586: The life of the Space Shuttle program). In such an emergency, all the propellant could be drained through valves on both sides of the Space Shuttle's fuselage in 250 seconds, but their proximity to the main engines and the Orbital Maneuvering System was a concern for the astronauts, who feared fuel leaks and explosions. The Space Shuttle orbiter would then have to land with Centaur still on board, and its center of gravity would be further aft than on any previous mission. Hauck and John Young ,

12460-614: The liquid-fuel engines on Centaur could be shut down and restarted. This gave Centaur flexibility in the form of mid-course corrections and multi-burn flight profiles, which increased the chances of a successful mission. Finally, Centaur was proven and reliable. The only concern was about safety; solid-fuel rockets were considered far safer than liquid-fuel ones, especially ones containing liquid hydrogen. NASA engineers estimated that additional safety features might take up to five years to develop and cost up to $ 100 million (equivalent to $ 284 million in 2023). The IUS made its first flight atop

12600-478: The manner in which the JPL was designing Galileo to withstand the intense radiation of the magnetosphere of Jupiter , which had application in surviving nearby nuclear detonations. The Galileo project aimed for a launch window in January 1982 when the alignment of the planets would be favorable to using Mars for a slingshot maneuver to reach Jupiter. Galileo would be the fifth spacecraft to visit Jupiter, and

12740-490: The mass of the tanks, maximizing the stage's overall performance. A common bulkhead separates the LOX and LH 2 tanks, further reducing the tank mass. It is made of two stainless steel skins separated by a fiberglass honeycomb. The fiberglass honeycomb minimizes heat transfer between the extremely cold LH 2 and less cold LOX. The main propulsion system consists of one or two Aerojet Rocketdyne RL10 engines. The stage

12880-400: The mission would take months or years longer to reach Jupiter. The IUS was constructed in a modular fashion, with two stages: a large one with 9,700 kilograms (21,400 lb) of propellant and a smaller one with 2,700 kilograms (6,000 lb), which was sufficient for most satellites. It could also be configured with two large stages to launch multiple satellites. The USAF asked NASA to develop

13020-421: The only Centaur-B flight on 26 November 1963 was successful. This version was powered by two RL10A-3 engines. Centaur-C flew three times between 1964 and 1965, with two failures and one launch declared successful although the Centaur failed to restart. This version was also powered by two RL10A-3 engines. Centaur-D was the first version to enter operational service in 1965 , with fifty-six launches. It

13160-403: The oxygen tank. The next Titan-Centaurs launched Helios 1 , Viking 1 , Viking 2 , Helios 2 , Voyager 1 , and Voyager 2 . The Titan booster used to launch Voyager 1 had a hardware problem that caused a premature shutdown, which the Centaur stage detected and successfully compensated for. Centaur ended its burn with less than 4 seconds of fuel remaining. The Centaur D-1T had

13300-669: The payload capacity of Atlas-Centaur, and incorporated improved thermal insulation, allowing an orbital lifespan of up to five hours, an increase over the 30 minutes of the Atlas-Centaur. The first launch of Titan IIIE in February 1974 was unsuccessful, with the loss of the Space Plasma High Voltage Experiment (SPHINX) and a mockup of the Viking probe. It was eventually determined that Centaur's engines had ingested an incorrectly installed clip from

13440-418: The payload to 9.3 meters (31 ft). The dry weight of the Centaur G-Prime was 2,761 kilograms (6,088 lb), and it weighed 22,800 kilograms (50,270 lb) fully loaded. The two versions were very similar, 80 percent of their components being the same. The Centaur G-Prime stage had two RL10-3-3A engines, each with 73,400 newtons (16,500 lb f ) thrust, and a specific impulse of 446.4 seconds, with

13580-414: The pioneering nature of the effort and the use of liquid hydrogen. In 1994 General Dynamics sold their Space Systems division to Lockheed-Martin . The Centaur was originally developed for use with the Atlas launch vehicle family . Known in early planning as the 'high-energy upper stage', the choice of the mythological Centaur as a namesake was intended to represent the combination of the brute force of

13720-432: The planets would no longer be aligned so that a Mars slingshot would be sufficient to reach Jupiter. An alternative to the IUS was to use Centaur as an upper stage with the Space Shuttle. Shuttle-Centaur would require neither 109 percent power from the SSME, nor a slingshot maneuver to send the 2,000 kilograms (4,500 lb) to Jupiter. NASA's Associate Administrator for Space Transportation Systems, John Yardley , directed

13860-799: The power of Centaur. The USAF agreed to pay half the design and development costs of Centaur G, and the National Aeronautics and Space Administration (NASA) paid the other half. Both versions were cradled in the reusable Centaur integrated support system (CISS), an aluminum structure that handled communications between the Space Shuttle and the Centaur. All Centaur stages periodically vented hydrogen, which needs to be stored below −253 °C (−423 °F) to keep it from boiling. Two Shuttle-Centaur missions were scheduled, with one-hour launch windows six days apart, so two separate spacecraft and launch pads were required. The Space Shuttles Challenger and Atlantis were modified to carry

14000-543: The project from cancellation, but the USAF asked for design changes and performance enhancements. One such change was to allow the Milstar to have a direct connection with Centaur that would be separated using explosive bolts, which required further testing to ascertain the effect of the resulting shock. NASA Administrator Robert A. Frosch stated in November 1979 that he was not in favor of using Centaur, but Centaur found

14140-408: The rate of 0.6 watts per month. Some of the gravity assist options also involved flying closer to the Sun, which would induce thermal stresses. Another advantage that Centaur had over the IUS was while it was more powerful, Centaur generated its thrust more slowly, thereby minimizing jerk and the chance of damage to the payload. Also, unlike solid-fuel rockets, which burned to depletion once ignited,

14280-438: The skin into the structure and interior of the vehicle. Some heat is produced by fluid compression at and near stagnation points such as the vehicle nose and wing leading edges. Additional heat is generated from air friction along the skin inside the boundary layer". These two regions of skin heating are shown by van Driest. Boundary layer heating of the skin may be known as kinetic heating. The effects of aerodynamic heating on

14420-664: The space program. On 13 November 1981, President Ronald Reagan issued National Security Decision Directive Number 8, which directed that the Space Shuttle would be the primary launch system for all military and civil government missions, but Edward C. Aldridge Jr. , the Under Secretary of the Air Force (and secretly the Director of the National Reconnaissance Office ) doubted that NASA could meet its target of twenty-four Space Shuttle launches

14560-700: The stage in two 2-thruster pods and four 4-thruster pods. For propellant, 150 kg (340 lb) of Hydrazine is stored in a pair of bladder tanks and fed to the RCS thrusters with pressurized helium gas, which is also used to accomplish some main engine functions. As of 2024, two Centaur variants are in use: Centaur III on Atlas V, and Centaur V on Vulcan Centaur. All of the many other Centaur variants have been retired. Centaur engines have evolved over time, and three versions (RL10A-4-2, RL10C-1 and RL10C-1-1) are in use as of 2024 (see table below). All versions utilize liquid hydrogen and liquid oxygen. Common Centaur

14700-421: The standard Centaur and were still mounted in the forward equipment module. They used a 24- bit Teledyne Digital Computer Unit with 16 kilobytes of RAM to control guidance and navigation. They still used the same pressurized steel tank, but with more insulation including a two-layer foam blanket over the forward bulkhead and a three-layer radiation shield. Other changes included new forward and aft adapters ;

14840-403: The stringers, and thus the area, and weight, of the stringers must be increased. Some designs for hypersonic missiles have used liquid cooling of the leading edges (usually the fuel en route to the engine). The Sprint missile 's heat shield needed several design iterations for Mach 10 temperatures. Heating caused by the very high reentry speeds (greater than Mach 20) is sufficient to destroy

14980-598: The temperature of the skin, and subsequent heat transfer into the structure, the cabin, the equipment bays and the electrical, hydraulic and fuel systems, have to be incorporated in the design of supersonic and hypersonic aircraft and missiles. One of the main concerns caused by aerodynamic heating arises in the design of the wing. For subsonic speeds, two main goals of wing design are minimizing weight and maximizing strength. Aerodynamic heating, which occurs at supersonic and hypersonic speeds, adds an additional consideration in wing structure analysis. An idealized wing structure

15120-522: The termination of the Shuttle-Centaur program was filled by a new launch vehicle, the Titan IV . The 401A/B versions used a Centaur upper stage with a 4.3-meter (14 ft) diameter hydrogen tank. In the Titan 401A version, a Centaur-T was launched nine times between 1994 and 1998. The 1997 Cassini-Huygens Saturn probe was the first flight of the Titan 401B, with an additional six launches wrapping up in 2003 including one SRB failure. The upper stage of

15260-480: The two. But while the atmospheric probe was light enough to launch with the two-stage IUS, the Jupiter orbiter was too heavy to do so, even with a gravitational slingshot around Mars, so the three-stage IUS was still required. By late 1980, the estimated cost of the development of the two-stage IUS had risen to $ 506 million (equivalent to $ 1571 million in 2023). The USAF could absorb this cost overrun (and indeed had anticipated that it might cost far more), but NASA

15400-615: The upper stage of the Atlas V launch vehicle, and the 5.4 m (18 ft) diameter Centaur V has been developed as the upper stage of ULA's new Vulcan rocket. Centaur was the first rocket stage to use liquid hydrogen (LH 2 ) and liquid oxygen (LOX) propellants , a high-energy combination that is ideal for upper stages but has significant handling difficulties. Common Centaur is built around stainless steel pressure stabilized balloon propellant tanks with 0.51 mm (0.020 in) thick walls. It can lift payloads of up to 19,000 kg (42,000 lb). The thin walls minimize

15540-403: The vehicle unless special techniques are used. The early space capsules such as used on Mercury , Gemini , and Apollo were given blunt shapes to produce a stand-off bow shock , allowing most of the heat to dissipate into the surrounding air. Additionally, these vehicles had ablative material that sublimates into a gas at high temperature. The act of sublimation absorbs the thermal energy from

15680-530: The way Centaur integrates with the booster and fairing: the 5.4 m (18 ft) diameter Atlas V payload fairing attaches to the booster and encapsulates the upper stage and payload, routing fairing-induced aerodynamic loads into the booster. If the 4 m (13 ft) diameter payload fairing is used, the attachment point is at the top (forward end) of Centaur, routing loads through the Centaur tank structure. The latest Common Centaurs can accommodate secondary payloads using an Aft Bulkhead Carrier attached to

15820-511: The weight-saving features pioneered by the Atlas rocket family : a monocoque steel shell that held its shape only when pressurized, hydrogen and oxygen tanks separated by a common bulkhead, and no internal bracing or insulation surrounding the propellant tanks. The technology for handling liquid hydrogen in Centaur was also used the S-II and S-IVB upper stages of the Saturn V rocket, and later by

15960-424: Was America's worst space disaster at the time. The Centaur team, many of whom witnessed the disaster, was devastated. On 20 February, Moore ordered the Galileo and Ulysses missions postponed. Too many key personnel were involved in the analysis of the accident for the two missions to proceed. They were not canceled, but the earliest they could be flown was in thirteen months. Engineers continued to perform tests and

16100-517: Was a low mass payload, with approximately 28% (5,400 kg (11,900 lb)) of LH 2 /LOX propellant remaining after separation. Several on-orbit demonstrations were conducted over 2.4 hours, concluding with a deorbit burn . The initial demonstration was intended to prepare for more-advanced cryogenic fluid management experiments planned under the Centaur-based CRYOTE technology development program in 2012–2014, and will increase

16240-589: Was a mistake not to go with the Titan IIIE-Centaur", given the delays and higher costs ultimately involved in using the Shuttle, but this was not apparent in 1984. Although Galileo was the only American planetary mission scheduled, there was another mission in preparation: the International Solar Polar Mission, which was renamed Ulysses in 1984. It was originally conceived in 1977 as a two-spacecraft mission, NASA and

16380-487: Was a prime example of faulty procurement, because an important contract was being given to General Dynamics without any form of tender process . He enlisted the support of Congressman Don Fuqua , the Chairman of the House Committee on Science, Space and Technology . Centaur was defended by Congressman Bill Lowery , whose San Diego district included General Dynamics. On 15 September, Flippo moved an amendment to

16520-399: Was also a problem with the drain valves, which was found and corrected. Shuttle-Centaur was certified as flight ready by NASA Associate Administrator Jesse Moore in November 1985. The Johnson Space Center committed to lifting 29,000 kilograms (65,000 lb) but the engineers at Lewis Research Center were aware that the Space Shuttle was unlikely to be able to lift that amount. To compensate,

16660-404: Was an associate administrator at NASA Headquarters, whose involvement with Centaur dated back to 1962 and who had headed the Atlas-Centaur and Titan-Centaur Offices in the 1970s. Under Stofan, the Lewis Research Center budget went from $ 133 million in 1979 (equivalent to $ 450 million 2023) to $ 188 million in 1985 (equivalent to $ 452 million in 2023). This permitted an increase in staff for

16800-468: Was an experienced project manager. He handled the project's administration and financial arrangements. Vernon Weyers was his deputy. USAF Major William Files also became a deputy project manager. He brought with him six USAF officers who assumed key roles in the Project Office. Marty Winkler headed the Shuttle-Centaur program at General Dynamics. Steven V. Szabo, who had worked on Centaur since 1963,

16940-531: Was declared to be a payload in 1983, but the drawbacks soon became evident. Payload status was originally conceived as being for inert pieces of cargo. Complying with the requirements of this status resulted in a series of safety waivers. The difficulty of compliance was compounded by the Johnson Space Center, which added more for Centaur. Both centers wanted to make the Centaur as safe as possible, but differed over what trade-offs were acceptable. Two Shuttle-Centaur missions were scheduled: STS-61-F for Ulysses in

17080-624: Was designated the lead center for managing IUS work. In April 1978, the quote for the development of the IUS was $ 263 million (equivalent to $ 965 million in 2023), but by December 1979 it was renegotiated for $ 430 million (equivalent to $ 1456 million in 2023). The main drawback of the IUS was that it was not powerful enough to launch a payload to Jupiter without resorting to gravitational slingshot maneuvers around other planets to garner more speed, something most engineers regarded as inelegant, and which planetary scientists at NASA's Jet Propulsion Laboratory (JPL) disliked because it meant that

17220-402: Was faced with a quote of $ 179 million (equivalent to $ 508 million in 2023) for the development of the three-stage version, which was $ 100 million (equivalent to $ 284 million in 2023) more than it had budgeted. At a press conference on 15 January 1981, Frosch announced that NASA was withdrawing support for the three-stage IUS and going with Centaur because "no other alternative upper stage

17360-495: Was flown four times on missions SA-1 through SA-4 , all four of these missions had the S-V's tanks filled with water to be used a ballast during launch. The stage was not flown in an active configuration. The Centaur D-1T (powered by RL10A-3-3 engines) was an improved version for use on the far more powerful Titan III booster in the 1970s, with the first launch of the resulting Titan IIIE in 1974. The Titan IIIE more than tripled

17500-630: Was head of the Lewis Research Center's Space Transportation Engineering Division, responsible for the technical side of the activities related to the integration of the Space Shuttle and Centaur, which included the propulsion, pressurization, structural, electrical, guidance, control and telemetry systems. Edwin Muckley was in charge of the Mission Integration Office, which was responsible for the payloads. Frank Spurlock managed trajectory mission design, and Joe Nieberding took charge of

17640-615: Was initially intended to enter service with an upgraded variant of the Common Centaur, with an upgrade to the Advanced Cryogenic Evolved Stage (ACES) planned after the first few years of flights. In late 2017, ULA decided to bring elements of the ACES upper stage forward and begin work on Centaur V. Centaur V will have ACES' 5.4 m (18 ft) diameter and advanced insulation, but does not include

17780-572: Was mated with CISS-1, which had arrived two months before. SC-2 and CISS-2 followed in November. The USAF made its Shuttle Payload Integration Facility at the Cape Canaveral Air Force Station available in November and December so SC-1 and SC-2 could be processed at the same time. A problem was detected with the propellant level indicator in the oxygen tank in SC-1, which was promptly redesigned, fabricated, and installed. There

17920-409: Was never intended to operate beyond low Earth orbit , but many satellites needed to be higher, particularly communications satellites , for which geostationary orbits were preferred. The Space Shuttle concept originally called for a crewed space tug , which would be launched by a Saturn V. It would use a space station as a base and be serviced and refueled by the Space Shuttle. Budget cutbacks led to

18060-529: Was no longer tied to a 1982 launch window. A third possibility considered was to launch Galileo using a Centaur upper stage atop a Titan IIIE, but this would have required rebuilding the launch complex at Cape Canaveral , which would have added at least $ 125 million (equivalent to $ 423 million in 2023) to the cost of the $ 285 million (equivalent to $ 965 million in 2023) Galileo project. Beggs insisted that expendable launch vehicles (ELVs) were obsolete and that any money spent on them would only undermine

18200-473: Was powered by two RL10A-3-1 or RL10A-3-3 engines. On 30 May 1966, an Atlas-Centaur boosted the first Surveyor lander towards the Moon. This was followed by six more Surveyor launches over the next two years, with the Atlas-Centaur performing as expected. The Surveyor program demonstrated the feasibility of reigniting a hydrogen engine in space and provided information on the behavior of LH 2 in space. By

18340-413: Was produced, with 28 months on it, covering January 1984 to April 1986. The cover sported the logo, with the project motto, co-opted from the movie Rocky III : "Go for it!" When it came to integrating Centaur with the Space Shuttle, there were two possible approaches: as an element or a payload. Elements were components of the Space Shuttle like the external tank and the solid rocket boosters ; whereas

18480-578: Was reconfigured for a 1985 launch using the two-stage IUS, which would take four years to get to Jupiter and reduce the number of moons visited by half when it got there. Senator Harrison Schmitt , the Chairman of the Senate Subcommittee on Science, Technology and Space, and a former astronaut who had walked on the Moon on Apollo 17 , was opposed to the OMB decision, as were the House and Senate Appropriations Committees. Support for it came from

18620-547: Was replaced by Norman Thagard in September, as mission specialists. As well as being the STS-61-F commander, Hauck was the Shuttle-Centaur project officer at the Astronaut Office . He and Walker attended key senior management project meetings, which was unusual for astronauts. The four-person crews would be the smallest since STS-6 in April 1983, and they would fly into a low 170-kilometer (110 mi) orbit, which

18760-412: Was split 50–50 with the USAF. It was 6.1 meters (20 ft) long, allowing for large USAF payloads up to 12.2 meters (40 ft) long. Its dry weight was 3,060 kilograms (6,750 lb) and it weighed 16,928 kilograms (37,319 lb) fully loaded. Centaur G-Prime was intended for deep space missions and was 9.0 meters (29.5 ft) long, allowing it to carry more propellant, but restricting the length of

18900-509: Was the highest that the Space Shuttle could achieve with a fully fueled Centaur on board. Centaur would periodically vent boiling hydrogen to maintain the proper internal pressure. The high rate of hydrogen boil-off from the Centaur meant that deploying it as soon as possible was essential to ensure it had sufficient fuel. Payload deployments were not normally scheduled for the first day to allow time for astronauts who came down with space adaptation syndrome to recover. To avoid this so as to permit

19040-592: Was the last version of the stage to feature separating insulation panels. Centaur II was initially developed for use on the Atlas II series of rockets. Centaur II also flew on the initial Atlas IIIA launches. Atlas IIIB introduced the Common Centaur, a longer and initially dual engine Centaur II. Source: Atlas V551 specifications, as of 2015. Most Common Centaurs launched on Atlas V have hundreds to thousands of kilograms of propellants remaining on payload separation. In 2006 these propellants were identified as

19180-528: Was transferred from NASA's Marshall Space Flight Center in Huntsville, Alabama , to its Lewis Research Center in Ohio in October 1962, and Abe Silverstein , a strong advocate of liquid hydrogen, took charge. He insisted on a thorough testing regime, which both identified problems and suggested solutions to them. The technical problems of the Centaur project were gradually overcome. The design notably included

19320-474: Was used to launch the Viking , Helios , and Voyager missions. By 1980, Centaur upper stages had flown 55 times, failing only twice. The 1972 decision to develop the Space Shuttle augured badly for the projects to explore the Solar System with robotic probes, which were coming under intense scrutiny by an increasingly cost-conscious Nixon administration and United States Congress . The Space Shuttle

19460-433: Was using a small thickness-to-chord ratio , so that the speed of the flow over the airfoil does not increase too much from the free stream speed. As the flow is already supersonic, increasing the speed even more would not be beneficial for the wing structure. Reducing the thickness of the wing brings the top and bottom stringers closer together, reducing the total moment of inertia of the structure. This increases axial load in

19600-600: Was welcomed by the communications industry, because it meant that larger satellites could be placed into geostationary orbits, whereas the Shuttle and IUS were limited to 3,000-kilogram (6,600 lb) payloads. NASA Headquarters liked Shuttle-Centaur as an answer to the ESA's Ariane rocket family ; by 1986, new versions of the Ariane under development were expected to be able to lift payloads heavier than 3,000 kilograms (6,600 lb) into geostationary orbits, thereby cutting NASA out of

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