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Shuttle

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Shuttle Evolution
Improvements suggested to the shuttle derived from the design as flown.
Credit: © Mark Wade

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AKA: Space Transportation System;STS. First Launch: 1981-04-12. Last Launch: 2011-07-08. Number: 135 . Payload: 24,400 kg (53,700 lb). Thrust: 2,625,932.00 kN (590,332,997 lbf). Gross mass: 2,029,633 kg (4,474,574 lb). Height: 56.00 m (183.00 ft). Diameter: 8.70 m (28.50 ft). Apogee: 600 km (370 mi).

In the mid-1960's the US Air Force conducted a series of classified studies on next-generation space transportation systems. These were to reduce the cost of launching military payloads while supporting a projected robust manned military presence in space - including large space stations and reconnaissance and strike missions. These Air Force studies finally concluded that a partially reusable vehicle was the most attractive, epitomized by Lockheed's Starlifter, which had a large drop tank but returned the engines and avionics of the vehicle for reuse. The Air Force probably spent around $ 1 billion on 'black' technology development tests at this time, including work on linear aerospike engines and high fineness lifting body shapes that would re-emerge again 30 years later in Lockheed's X-33 space shuttle successor.

NASA also had ambitious plans - for large space stations, lunar bases, nuclear interplanetary rocket stages, and manned Mars expeditions. NASA went through a long iterative process in designing and selecting the space shuttle, leading ultimately to the same conclusion as the Air Force.

By mid-1969, the ambitious new NASA Administrator, Tom Paine, had proposed an extensive manned space exploration program as the logical follow-on to Apollo. A new, modular, reusable space transportation system would be required to set up bases on the Moon and Mars during the 1970s and 1980s. This system would consist of a reusable space shuttle to low earth orbit space stations and interorbital and interplanetary nuclear and chemical space tugs. The first major goal was a 12-man space station by 1975. NASA awarded $2.9-million study contracts to North American Rockwell and McDonnell-Douglas in July 1969. The space station was to evolve into a 50-man space base by 1980. Additional way-stations to Mars would be deployed in geostationary, lunar and Mars orbit during the 1980s.

George Mueller headed the space shuttle portion of this effort, which accelerated as the Apollo project grew to a close. NASA awarded four $0.3-million space shuttle / Integral Launch and Re-entry Vehicle ILRV Phase A study contracts to North American Rockwell, McDonnell-Douglas, Lockheed and General Dynamics in January 1969. Martin Marietta's bid was rejected, but the company continued to participate using its own funds. The ILRV requirement was for a booster/spacecraft combination with 12-crew / 2.3 - 22.7 metric ton payload capability, a 720 km re-entry cross range, and first flight by 1974. The most important mission was expected to be space station resupply payloads weighing about 11,300 kg. 120 different permutations were investigated by the contractors.

The assumption of a massive cost-is-no-object future space program was that only fully reusable vertical takeoff/horizontal landing, two-stage-to-orbit concepts for the space shuttle were considered at first. NASA's Shuttle task group had already calculated the potential life-cycle costs of three classes of 22,680-kilogram payload reusable launch vehicles based on prior USAF studies:

• An advanced low-cost expendable rocket plus reusable spacecraft would cost $2.5 billion to develop and $43.1 million per launch.
• An ILRV/Starlifter-type partially reusable single-stage-to-orbit vehicle would cost of $3.9 billion to develop and $5.3-12.6 million per launch, depending on the estimated cost of the expendable propellant tanks.
• A fully reusable two-stage-to-orbit configuration such as the General Dynamics Triamese concept would cost $4.5 billion to develop but only $3.2 million per launch.

In August 1969, in post-moon landing euphoria, NASA directed the Phase A contractors to concentrate only on fully reusable shuttle concepts. These were two stages, both either winged or lifting bodies, and both recovered at the launch site for reuse. Only as an afterthought, some alternate concepts were still evaluated, including Lockheed's LS200 single orbiter with drop tank, and Chrysler's SERV ballistic single-stage-to-orbit vehicle.

The Phase B designs were more refined but still used the same two-stage approach. Mueller set up a NASA space shuttle task group headed by LeRoy Day to evaluate potential uses of the vehicle. The shuttle requirements had changed considerably as a result of the new post-Apollo program which required a total of 546 shuttle launches in 1975-85. In May 1970, Mueller instructed the task group to increase the payload capability to 22,680 kg to comply with US Air Force requirements, but also because there would be a need to launch vast quantities of low-density rocket propellants into Earth orbit for future space stations in geostationary and lunar orbit. The mission requirements also grew significantly more complex and diverse as the Shuttle also now had to be capable of launching unmanned satellites and planetary probes. At this point a controversy developed over the basic design approach. There were over large cross-range winged designs, medium cross-range lifting body designs, and minimal cross-range stub-wing designs. NASA's Max Faget, who had dictated the spacecraft design for the Mercury, Gemini, and Apollo programs, advocated the stub-wing design.

Then the Nixon administration burst NASA's balloon. The future NASA budget would be only a fraction of Apollo-program levels. There would be no moon bases, no flights to Mars, no nuclear interplanetary stages, no space stations, no more Saturn V's, no space tugs. There wouldn't even be a space shuttle unless NASA could get the development cost down and also convince the US Air Force to use the shuttle for its launch requirements. A USAF requirement was a large cross-range to allow recovery of the shuttle orbiter at the Vandenberg AFB launch point after a single polar orbit of the earth. This was necessary for abort-once-around, quick satellite deployment, strike, or quick-look reconnaissance scenarios. This, together with wind tunnel studies indicating that Faget's straight wing was unstable at re-entry speeds, drove NASA to the delta wing. The reduction in development cost led NASA to throw away the concept of reusing anything but the engines and guidance systems. Instead the shuttle would be boosted by cheap solid fuel boosters and, taking a concept from the Air Force, the propellants would be put in a big expendable drop tank.

Following the usual charade of competitive bidding, NASA picked the same prime contractor as for X-15 and Apollo, who could be trusted to build precisely the vehicle NASA had in mind. North American Rockwell was selected to build the orbiter, with its Rocketdyne Division making the main engines. Thiokol was selected on political grounds for the solid rocket boosters. Martin Marietta would build the External Tank, but at the government Saturn IC factory at Michoud.

To finance the Shuttle, already-built Apollo hardware that would have supported a second Skylab mission was sent to museums and American manned space flight went into a long hiatus in the 1970's. Budget cuts and overruns eventually reduced the number of shuttles built from five to four and delayed the first flight from 1978 to 1981 (thereby ruining the plan to save Skylab 1 on an early shuttle mission). But the development cost was indeed minimized - the shuttle ended up costing $ 6.744 billion in 1971 dollars, versus $ 5.15 billion estimated - less than a quarter of the Apollo program cost and a very modest overrun in comparison to some other programs.

The pretext for the shuttle was that it would be much cheaper than expendable launch vehicles and would replace them all. Production was accordingly terminated by the US government of Delta, Atlas, and Titan vehicles. NASA staff and contractors were under incredible pressure to justify this decision by increasing the shuttle launch rate, lowering the turn-around time, and thereby reducing the cost per launch. When the shuttle Challenger exploded and the entire US space lift program was shut down for almost a year, the fallacy of this decision was exposed. The US Air Force and commercial users returned to use of expendable launch vehicles. When the shuttle began flying again, it was only for NASA programs.

In the final analysis the shuttle came up short in three areas. First, the shuttle orbiter ended up almost 20% over its specified weight - resulting in it being unable to boost the US Air Force's payloads into polar orbits from Vandenberg. Lighter filament-wound casing Solid Rocket Boosters were being developed for use in flights from Vandenberg, but even this did not seem enough. After the Challenger explosion the USAF was able to extricate itself from the Shuttle program. The Vandenberg launch complex, built at the cost of billions, was mothballed. The Air Force started a new costly development program to design the Titan 4 expendable rocket for its large military payloads.

The second shortcoming of the shuttle was that it failed utterly to reduce the cost of putting payloads into orbit. The shuttle program inherited from Apollo huge fixed costs - the Manned Spaceflight Center in Houston, the cadres of government and contractor workers at the Kennedy Space Center, and so on. The result was that there was a fixed base cost of around $ 2.8 billion per year, just to keep all those people and facilities in place, even if no flights were undertaken at all (as occurred after the shuttle disaster). The marginal cost of each flight added to this base was under $ 100 million. Seen this way the shuttle was almost competitive expendable boosters - but didn't come anywhere near the reductions NASA promised when development started. But if the usual number of flights per year was divided by the total annual costs, the cost per launch was $ 245 million, significantly more than a Titan or Proton launch with the same payload.

The final shortcoming was that the shuttle was designed as if it had the inherent operating safety of an airliner. It was not equipped with any provision for crew rescue in case of booster failure during ascent to orbit, or being stranded in orbit, or structural failure during re-entry. The crew was not even provided with spacesuits, despite the lessons of the Soviet space program. This seemed an extraordinary act of engineering hubris, given that contemporary military aircraft were equipped with pressure suits and ejection seats. But the weight problem also meant that there was no margin for crew safety measures without (to NASA) unacceptable impact to the net payload.

If the shuttle failed as a space truck, it succeeded in keeping America in the manned spaceflight business in the face of low public interest and political support. With the excuse of delivering payloads to orbit, NASA got to fly up to seven astronauts and run a host of supplementary experiments and payloads with each flight.

With construction of the international space station beginning, NASA was looking forward to finally using the shuttle for its intended purpose. Due to the lower than planned flight rate, NASA's contractors were confident they could keep the existing shuttles flying through 2030. The real test came when (as was inevitable) another shuttle was lost. Following the Columbia disaster, NASA finally realized it could not make the shuttle safe. The only way to continue American manned spaceflight would be to develop a replacement manned spacecraft with an escape system, and meanwhile fly the shuttle as little as possible. NASA decided to complete the International Space Station in order to keep its international partners happy, then retire the shuttle by 2010. It was to be replaced by a modernized Apollo capsule, dubbed the Orion. The shuttle turned out to be a fifty-year detour to nowhere.

When the Orion program started, NASA hoped to have the sort of lunar base by 2020 they would have had by 1980 if Apollo had been continued in lieu of the shuttle. Instead the Constellation program to go to the moon or Mars was in turn cancelled by the Obama administration. In order to keep Congressman happy, the Orion spacecraft continued a costly slow-paced development program for possible future deep-space missions. For access to the International Space Station, the United States had to pay for seats aboard the Russian Soyuz spacecraft. Bizarrely, instead of completing Orion in a timely manner, NASA funded two other American replacements, the SpaceX Dragon and Boeing CST-100. These would not fly until 2017, only a few years before the planned retirement of the ISS.

Spacemaster American winged orbital launch vehicle. Martin-Marietta shuttle Phase A design. X-24B type lifting body orbiter with unique catamaran-configuration booster.

Shuttle FR-3 American winged orbital launch vehicle. General Dynamics shuttle proposal phase A of October 1969. Unwinged flat-bottom configuration booster and orbiter with V butterfly-tails.

Shuttle LS A American winged orbital launch vehicle. Lockheed shuttle proposal phase A of December 1969. X-24B lifting body orbiter with delta-wing booster.

Shuttle NAR A North American's Phase A shuttle design was completed under contract NAS9-9205 in December 1969. North American had learned that the way to win a NASA design competition was to adhere to the design favored by Max Faget, so they proposed a two-stage-to-orbit vehicle, with both booster and orbiter being of Faget's straight-wing, low cross-range configuration.

Shuttle MDC American winged orbital launch vehicle. The McDonnell Douglas Space Shuttle Phase A studies were conducted under contract NAS9-9204. Their baseline Class III vehicle design was completed in November 1969 after 13 alternate configurations had been considered. The two-stage-to-orbit vehicle had a gross mass of 1,550,000 kg and a 11,300 kg payload was accommodated in a 4.6 m x 9.2 m payload bay.

Shuttle MDC A Alternate American winged orbital launch vehicle. McDonnell-Douglas shuttle proposal phase A of November 1969. Delta wing first stage and HL-10 lifting body second stage.

Shuttle HCR American winged orbital launch vehicle. McDonnell-Douglas/Martin Marietta shuttle high cross-range proposal phase B of December 1970. Swept wing booster, delta wing orbiter.

Shuttle DC-3 American winged orbital launch vehicle. Marshall Spaceflight Center shuttle concept of April 1970 using Faget low cross range stub-winged booster and orbiter.

Shuttle R134C American winged orbital launch vehicle. Rockwell/General Dynamics shuttle proposal phase B, November 1970. Delta wing high-cross range orbiter and booster.

Shuttle R134G American winged orbital launch vehicle. Rockwell/General Dynamics shuttle proposal phase B, November 1970. Straight wing low-cross range orbiter.

Shuttle LS200 American winged orbital launch vehicle. Lockheed Skunk Works alternate shuttle proposal of June 1971. X-24B lifting body orbiter with wrap-around external tank.

SERV American VTOVL orbital launch vehicle. Chrysler ballistic single stage to orbit alternate shuttle proposal of June 1971. This was the most detailed design study ever performed on a VTOVL SSTO launch vehicle. The 2,040 metric ton SERV was designed to deliver a 53 metric ton payload to orbit in a capacious 7 m x 18 m payload bay.

Shuttle LRB 1972 American winged orbital launch vehicle. Original design for a shuttle with liquid rocket boosters, completed in March 1972 as part of the shuttle design decision process

Saturn Shuttle American orbital launch vehicle. A winged recoverable Saturn IC stage was considered instead of solid rocket boosters after the final shuttle design was selected.

Enterprise American manned spaceplane. Study 1974. Enterprise was the first Space Shuttle Orbiter. It was rolled out on September 17, 1976.

EDIN05 American winged orbital launch vehicle. In February 1976 this version of the shuttle was proposed. A single liquid rocket booster under the external tank would replace the two solid rocket boosters.

Boeing SDV American orbital launch vehicle. The Boeing SDV Class I vehicle would lead to the Shuttle-C, using the shuttle aft fuselage with SSME engines to power a cargo canister into orbit.

Space Shuttle American winged orbital launch vehicle. The version of the space shuttle that went into production. Redesign of the shuttle with reliability in mind after the Challenger disaster reduced maximum payload to low earth orbit from 27,850 kg to 24,400 kg.

Columbia American manned spaceplane. Columbia, the first orbiter in the Shuttle fleet, was named after the sloop that accomplished the first American circumnavigation of the globe.

Challenger American manned spaceplane.

Martin Marietta SDV American orbital launch vehicle. The Martin Marietta Class I SDV would lead to the Shuttle-C, using the shuttle aft fuselage with SSME engines to power a cargo canister into orbit.

Discovery American manned spaceplane. merican manned spaceplane.

Shuttle LRB American winged orbital launch vehicle. Shuttle with Liquid Rocket Boosters in place of Solid Rocket Boosters.

Atlantis American manned spaceplane. The space shuttle Atlantis was the fourth orbiter to become operational at Kennedy Space Center, and the last of the original production run.

Shuttle LRB 1989 American orbital launch vehicle. In July 1989 a NASA Langley/George Washington University joint study was made of various Liquid Rocket Booster configurations.

Shuttle C American orbital launch vehicle. NASA Marshall design for a cargo version of the shuttle system. The shuttle orbiter would be replaced by an unmanned recoverable main engine pod. The same concept was studied earlier as the Interim Heavy Lift Launch Vehicle (IHLLV) and as the Class I Shuttle Derived Vehicle (SDV). The Phase I two-SSME configuration would have a payload of 45,000 kg to low earth orbit. Design carried to an advanced phase in 1987-1990, but then abandoned when it was found the concept had no cost advantage over existing expendable launch vehicles.

Shuttle C Block II American orbital launch vehicle. In August 1989 NASA studied a version of the Shuttle-C with two Advanced Solid Rocket Motors (ASRM's) in place of the standard RSRM's. This would increase the payload by 4500 kg, but also require use of a new 10 m x 30 m payload module.

Shuttle Z American orbital launch vehicle. Shuttle-Z was Shuttle-C on steroids, the ultimate development of the shuttle to be used to put Mars expeditions into orbit. It would use 4 SSME's, and a third stage with 181,000 kg of propellant powered by 1 SSSME. But such designs would require new handling facilities due to the extra height of the vehicle.

Ares Mars Direct American orbital launch vehicle. The Ares launch vehicle was designed for support of Zubrin's Mars Direct expedition. It was a shuttle-derived design taking maximum advantage of existing hardware. It would use shuttle Advanced Solid Rocket Boosters, a modified shuttle external tank for handling vertically-mounted payloads, and a new LOx/LH2 third stage for trans-Mars or trans-lunar injection of the payload. Ares would put 121 metric tons into a 300 km circular orbit , boost 59 metric tons toward the moon or 47 metric tons toward Mars. Without the upper stage 75 metric tons could be placed in low earth orbit.

Endeavour American manned spaceplane. merican manned spaceplane. Built as a replacement after the loss of the Challenger; named after the first ship commanded by James Cook.

Shuttle ASRM American winged orbital launch vehicle. Shuttle using Advanced Solid Rocket Motors (development cancelled 1993).

Shuttle ISS American winged orbital launch vehicle. Redesign of the shuttle with reliability in mind after the Challenger disaster reduced maximum payload to low earth orbit from 27,850 kg to 24,400 kg. When the decision was made to move the International Space Station to a high-inclination 51.6 degree orbit, net payload to the more challenging orbit dropped to unacceptable limits. The situation was improved by introduction of the Super Lightweight External Tank, which used 2195 Aluminum-Lithium alloy as the main structural material in place of the 2219 aluminum alloy of the original design. This saved 3,500 kg in empty mass, increasing shuttle payload by the same amount. The tank was first used on STS-91 in June 1998.

Ares American heavy-lift orbital launch vehicle. The design selected to boost America's Orion manned spacecraft into space in the 21st Century was a family of launch vehicles dubbed Ares. Originally sold as being derivatives of space shuttle technology, tinkering by NASA engineers and necessary changes during development quickly resulted in the designs being essentially all-new. Following inevitable cost growth and schedule slippage, it was cancelled in 2010. However continued development and eventual production of one derivative or another continued to be funded by Congress for many years afterwards.

Ares I-X American heavy-lift orbital launch vehicle. Shuttle-derived launch vehicle design selected by NASA Administrator Mike Griffin to boost the manned CEV Crew Exploration Vehicle into low earth orbit. A single five-segment version of the shuttle solid rocket booster would be mated with a LOx/LH2 upper stage powered by a single J-2S engine.

Photo Gallery

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Shuttle Cockpit Upgraded Shuttle MEDS Credit: NASA via Marcus Lindroos

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• Phase A Space Shuttle studies. - . Nation: USA.

  NASA began the design, bidding, and source selection process leading to a single national space shuttle. At the beginning the design was known by the same nomenclature previously used by the USAF - Integrated Launch and Re-entry Vehicle (ILRV). The development program was seen as: Phase A: Advanced Studies; Phase B: Project Definition; Phase C: Vehicle Design; and Phase D: Production and Operations. Four contractors or contractor teams were to be selected in Phase A; two contractors or teams for Phase B; and then a single contractor for Phases C and D (which were later combined). NASA Houston and Huntsville jointly issued the Request for Proposal for eight-month Phase A ILRV studies. The requirements were for 2,300 to 23,000 kg of payload to be delivered into a 500-km altitude orbit. The re-entry vehicle should have a cross range of at least 725 km (NASA persisted in this requirement even though it knew the USAF needed more). General Dynamics, Lockheed, McDonnell-Douglas, Martin Marietta, and North American Rockwell all were invited to bid.

  The Space Shuttle Main Engine competition was run in parallel with the main shuttle development project, and also had four phases. Oversight for this program came from the USAF Space Division and its subcontractor, the Aerospace Corporation. Despite promising classified work on linear and conventional aerospike engines at the time, NASA dictated that the design had to use a conventional bell nozzle.

• Space Shuttle Phase A contracts - . Nation: USA.

  Following evaluation of proposals submitted against the October 1968 request for proposal, NASA issued Advanced Design contracts for the shuttle to General Dynamics, Lockheed, McDonnell Douglas, and North American Rockwell. Martin Marietta did not receive a contract but was allowed to continue using company funds.

  Rocketdyne and Pratt & Whitney were selected for the Phase A, advanced study phase of the competition. The same basic engine (combustion chamber and turbomachinery) was to be used in both stages of the planned two-stage fully-recoverable shuttle. The orbiter would be equipped with a two-position deployable nozzle, with expansion ratios of 58:1 for the low altitude portion of the ascent, and 120:1 with the extension deployed for the vacuum portion of the flight to orbit. The engine was to have a thrust of 270,000 kgf in vacuum, 235,000 kgf at sea level, and be throttleable from 73% to 100% of the rated thrust. The engine for the booster was to use a 5:1 ratio expansion nozzle, producing 227,000 kgf at sea level. Pratt & Whitney seemed to have a clear lead in this portion of the competition, having produced the XLR-129-P-1, a prototype high-pressure Lox/LH2 engine under USAF contract. This produced 188,000 kgf using a smaller fixed nozzle. Most of the shuttle bidders proposed use of this engine in their Phase A vehicle designs.

  The Space Task Group put together to run the shuttle design process was composed of various agencies of the federal government. Each group favoured differing basic configurations for the shuttle, reflecting controversies extending back over ten years to the time of DynaSoar development. Faget at NASA Houston favoured a straight-wing orbiter, the bottom surface being essentially a cross shape cut out of the spherical section of one of the Apollo or Mercury heat shields he had designed. This had minimal cross range, but was supposed to have the advantages of minimum weight and good subsonic glide performance. NASA Langley and Edwards AFB favoured a lifting body, based on the HL-10 shape under test there. This had supposed weight advantages over a winged vehicle, more cross range than Faget's straight wing, but less cross range than a delta wing. USAF Flight Dynamics Laboratory and Draper Laboratories favoured a swept delta wing spaceplane, like the Dynasoar, for maximum cross range on re-entry.

  Faget favoured a small net payload to orbit (6800 kg) while the other government centres favoured heavier payloads, at least 11,300 kg, and up to 29,500 kg. As in the case of earlier USAF ILRV studies, the Space Task Group had initially considered three categories of launch solutions. Class I used an existing expendable launch vehicle (the Titan 3MV or Saturn IB) and a reusable orbiter. Class II were 1.5 stage to orbit designs, using an orbiter vehicle and a drop tank. Class III were fully reusable two-stage-to-orbit designs. In contrast to the USAF studies, which favoured immediate development of a Class I vehicle, followed by a Class II vehicle, Task Group's preferred solution was to proceed immediately with a Class III vehicle.

• Nixon forms Space Task Group - . Nation: USA.

  Vice President Agnew was made chairman of the group, which was to formulate a Post-Apollo Space Program, providing policy direction for future American efforts after the moon landing. The Groups final report proposed three alternate future programs:

  • At a funding level of $8 to $ 10 billion a year indefinitely, NASA could do it all - a manned expedition to Mars, permanent manned space bases in lunar orbit and the lunar surface, a 50-person space station in earth orbit, and a reusable space shuttle to support all of these projects on an economical basis
  • All of the objectives could be achieved, but the funding level kept at $ 8 billion per year, by deleting the manned lunar orbit station
  • At $ 5 billion per year, a program consisting of just the earth orbit station and the space shuttle could be funded - but no further manned exploration of the moon or planets

  Nixon rejected all of the alternatives and wanted something even cheaper.

• Space Shuttle Task Group formed - . Nation: USA. Program: STS. The Director of Apollo Test in the NASA Hq. Apollo Program Office, LeRoy E. Day, was detailed to head the MSF Space Shuttle Task Group. The group would provide NASA with material for a report on the Space Shuttle to the President's Space Task Group..

• USAF selects three companies to prepare design concepts for a reusable space vehicle for the STS. - . SAMSO selected General Dynamics/Convair, Lockheed Missiles and Space Company, North American Rockwell, and McDonnell Douglas to prepare design concepts for a reusable space vehicle for the STS..

• Faget shuttle concept attacked - . Nation: USA.

  The first report comes out attacking the Faget straight wing design. Another follows in November 1969; with the dispute becoming public with AIAA papers published in October 1970 and January 1971. These dissidents at other NASA centres calculated that a Faget orbiter was unsafe, as it could not withstand the re-entry thermal environment and aerodynamic stresses. NASA's Flight Research Center pushed a lifting body design, while the US Air Force noted that in any case the Faget design did not meet its cross-range requirements.

• USAF contracts to study Space Transportation System (STS) design concepts. - .

  SAMSO awarded contracts to North American Rockwell, McDonnell Douglas, General Dynamics/Convair, and Lockheed Missiles and Space Company to study Space Transportation System (STS) design concepts. SAMSO awarded contracts to North American Rockwell, McDonnell Douglas, General Dynamics/Convair, and Lockheed Missiles and Space Company to study Space Transportation System (STS) design concepts.

• No government approval for NASA's shuttle program - . Nation: USA.

  NASA decided to take the minimum program proposed by the Space Task Group (just the space station and the shuttle), and then implement it over a very long period in phases. At first only a reusable space shuttle would be developed. When that was completed, work on a space station could start. However as of the fall of 1970, NASA was unable to obtain the Nixon administration's approval of even this limited program.

• Two major directions were identified for NASA manned space flight in the next decade. - . Nation: USA. Program: Skylab. Flight: Skylab B. Spacecraft: Columbia, Skylab.

  Two major directions were identified for manned space flight in the next decade. These were further exploration of the Moon, with possibly the establishment of a lunar surface base, and the continued development of manned flight in Earth orbit, leading to a permanent manned space station supported by a low-cost shuttle system. To maintain direction, the following key milestones were proposed: 1972 - AAP operations using a Saturn V launched Workshop 1973 - Start of post-Apollo lunar exploration 1974 - Start of suborbital flight tests of Earth to orbit shuttle - Launch of a second Saturn V Workshop 1975 - Initial space station operations - Orbital shuttle flights 1976 - Lunar orbit station - Full shuttle operations 1977 - Nuclear stage flight test 1978 - Nuclear shuttle operations-orbit to orbit 1979 - Space station in synchronous orbit By 1990 - Earth orbit space base - Lunar surface base - Possible Mars landing

• NASA and the Air Force agree on shuttle development - . NASA and the Air Force agreed on development of a reusable space vehicle that would meet both civilian and military space requirements. NASA proposed a two-stage shuttle with a cargo area 60x15 feet..

• NASA Houston in-house study of shuttle concepts - . Nation: USA.

  The study was in an attempt to resolve disputes between the centres as to the best approach. Houston's Faget straight-wing two-stage vehicle was in competition with concepts from other centres - recoverable versions of Saturn boosters, and an advanced single-stage-to-orbit Aerospaceplane. Payload for the Faget vehicle was to be only 5,700 to 6,800 kg to low earth orbit, and the system was to be operational by the end of 1975, after the last Apollo flight.

• Space Transportation System (STS) for both NASA and USAF - .

  Space Transportation System (STS) to provide maximum utility to both military and civilian users at lower operating costs. NASA would manage STS development, and a NASA-USAF Committee would review the program to guarantee that it met Defense Department and NASA requirements.

• DC-3 drop tests - . Nation: USA. NASA conducted drop tests of a 1/10 scale model of Faget's 'DC-3' straight-wing shuttle design. The model was 4 m long, weighed 270 kg, and was dropped from 3,700 m altitude. Recovery was by parachute..

• Independent studies of NASA's shuttle ordered. - . Nation: USA.

  The new NASA Administrator, James Fletcher, had found that the NASA internal estimates of the cost to develop and operate the space shuttle were treated by the Office of Management of the Budget with great scepticism. Therefore he authorised several independent studies. Lockheed was to report on how the shuttle could reduce payload costs. Aerospace Corporation was to make an independent estimate of the cost of developing and operating the shuttle. Mathematica was to use these studies to make a definitive report comparing the cost of the shuttle with that of using existing expendable boosters.

  The Mathematica study would become notorious, for it forecast enormous savings in the use of the shuttle. It became very influential in government and congressional circles in shifting opinion to support the project. This, as NASA Administrator Low would dryly comment later, was 'unfortunate'. All earlier studies for the USAF and NASA, notably a RAND study in 1970, showed no cost advantage for reusable boosters when research and development costs were taken into account. RAND had concluded that a manned space station supported by expendable boosters would be cheaper, and more flexible and useful.

  Fletcher also directed NASA to take US Air Force requirements for the shuttle into account. The US Defence Department's requirements included the ability to carry 18 m long payloads, and deliver a mass of 18,000 kg to a polar orbit from Vandenberg AFB, or 30,000 kg to a low earth orbit from Cape Canaveral. The 4.5 m diameter for the payload bay was a NASA requirement, established by the planned diameter of future space station modules. 18 m x 4.5 m also corresponded to the dimensions of a liquid hydrogen tank with a mass of 30,000 kg, the lowest-density payload imaginable. The USAF also wanted an 1800 to 2400 km cross range on re-entry, and an initial operational capability of December 1977.

  The Aerospace Corporation study of NASA Phase A proposals concluded that the weight of a shuttle's thermal protection system would vary in relation to the fourth root of the required cross range. Aerospace also believed that sequential ignition of the booster and orbiter was a better approach than the triamese-type all-engines running at lift-off. It also declared that the USAF's desired operational date was unrealistic -- the earliest a shuttle could be available was mid to late 1979.

• NASA completes Shuttle Phase A evaluations - . Nation: USA.

  After over 200 man-years of NASA and contractor effort, the Agency reached the following conclusions at the end of Phase A:

  • The common orbiter/booster engine planned would have to have a lower thrust then proposed, with more used per booster. This was due to the need for the orbiter to have several engines instead of one or two in order to give it abort capabilities in the event of a single engine failure. It was recommended that a 180,000 kgf engine be developed for the shuttle instead of the 230,000 kgf previously planned.
  • Lifting body configurations were not suited for the launch vehicle application. This was due to the required complex internal arrangement of tanks and equipment within the curving hull, difficulty of fabricating the airframe and tanks, and poor subsonic lift/drag performance.
  • Variable geometry wings were not desirable, since they resulted in a heavier weight to body area ratio during re-entry, and thereby more re-entry heating problems. They also required complex mechanical and pneumatic/hydraulic systems for operation, which meant more maintenance, more complexity, and extra failure modes. There considerable advantages - a lower spacecraft weight fraction and the highest lift/drag in subsonic flight - did not offset these disadvantages.
  As a result of these conclusions, NASA published its specification for the Phase B Integral Launch and Recovery Vehicle Shuttle System on 1 June. The requirements in this specification were:
  • Two-stage-to-orbit, vertical takeoff, horizontal landing configuration
  • Initial operational capability by the end of 1977
  • 6,800 kg payload to a 500 km, 55 deg inclination orbit when launched from Cape Canaveral
  • 4.6 m x 18.3 m payload bay
  • Two orbiter alternates were to be proposed by the contractors, one with a 370 km cross-range (NASA requirement), one with a 2784 km cross range (USAF requirement). This implied a minimum L/D for the high cross-range vehicle of 1.8, and a total heat load 5 to 7 times greater than the low cross-range alternative.
  • Seven-day orbital mission capability.
  • Go-around capability on landing in case of a missed approach. This implied the use of airbreathing engines. Phase A studies showed that use of gaseous H2 from the orbiter's tanks as fuel for such engines drastically reduced the orbiter weight compared to use of conventional JP-4 jet fuel housed in separate tanks.
  • Design to be capable of 25 to 70 launches a year, with a turnaround time of two weeks
  • G-forces limited to 3G on ascent
  • Two crew housed in a pressure cabin without spacesuits
  • 43 hour countdown time after assembly
  • Stage separation without the use of rocket devices
  • No in-flight refuelling allowed
  • Capable of landing under FAA Category 2 conditions on a 3,000 m runway
  • All systems fail-operational - e.g. they would remain operational after any single component failure, and remain fail-safe for crew survival even after two subsystem failures
  • Quick safeing of vehicle systems after landing
  • No propellant cross-feed allowed between booster and orbiter

• Shuttle Phase B Contracts - . Nation: USA.

  Phase B contracts were issued for preliminary design for a space shuttle to two industrial teams - McDonnell Douglas and Martin Marietta; and North American Rockwell and General Dynamics. The specifications were as laid out in the NASA specificaiton on 1 June. In addition, both teams were mandated to study, as a baseline, alternate orbiters, consisting of the MSC-002 straight-wing Faget configuration for the low cross-range alternative, and a delta wing configuration for the high cross-range alternative. The booster configuration, on the other hand, was left up to the contractors.

  Engine contracts were let to Pratt and Whitney, Rocketdyne, and Aerojet. The engine specification called for a Lox/LH2 engine with a bell nozzle, capable of gimballing plus/minus 7 deg, producing 188,000 kgf at sea leval and 216,000 kgf at altitude. The booster engines would be equipped with a 6:1 expansion nozzle, and the orbiter with a two-position nozzle to bring the expansion ratio up to 120:1 at altitude. The engine had to throttle between 50% and 115% of the rated thrust (the latter rating for abort engine-out situations). The engine was to be equipped with a digital engine controller and be compact and reusable.

• Alternate Space Shuttle Concepts (ASSC) - . Nation: USA.

  NASA Huntsville, dissatisfied with the shuttle concepts being pursued by NASA Houston, let contracts to Chrysler and Lockheed for alternate technical approaches to the configuration dictated to Phase B contractors by NASA Houston. Later a further contract was let to a Grumman/Boeing team. In all, 29 configurations of partially reusable to fully-reusable vehicles were explored. The baseline engine for these studies had a thrust of 250,000 kgf and a two-position bell nozzle.

• Shuttle specifications revised - . Nation: USA.

  In response to US Air Force criticism, the payload requirement was increased to 11,500 kg (still well short of the USAF 30,000 kg requirement). The use of JP-4 jet fuel was required for the airbreathing flyback engines. The payload by was to be capable of carrying a passenger module for ferry of space station crews.

• Shuttle specifications revised - . Nation: USA. Further minor changes were made as a result of the NASA 90-day review in October..

• Shuttle Phase B preliminary proposals - . Nation: USA. The teams of McDonnell Douglas/Martin Marrietta and North American Rockwell/General Dynamics made their preliminary proposals under shuttle Phase B contracts..

• Shuttle external tank concept studied - . Nation: USA.

  On 29 December 1970 Grumman and Boeing received contract NAS9-11160 to study two-stage-to-orbit shuttle configurations using both internal and external liquid hydrogen tanks. Reviews with NASA in January and March 1971 showed there could be significant weight, risk, and cost reductions through use of a booster with a heat-sink airframe and an orbiter equipped with an external liquid hydrogen tank.

• Shuttle SSME Award - . Nation: USA.

  North American Rockwell's Rocketdyne division was awarded NASA contract NAS8-40000 for development of the space shuttle main engine, beating out Pratt and Whitney and Aerojet. This was the only large liquid propellant rocket motor scheduled to be developed in the United States for decades and a crushing blow to the losers. Both felt that their designs were superior to that of Rocketdyne, but Rocketdyne had become NASA's 'house' for main rocket engines.

• Shuttle Phase B Final Reports - . Nation: USA.

  Taking into account NASA and USAF comments on the draft proposals, and specification revisions, the teams of McDonnell Douglas/Martin Marrietta and North American Rockwell/General Dynamics made their final proposals under shuttle Phase B contracts. Based on the strict specifications of NASA, the low cross-range and high-cross range versions of the orbiter stages were similar. The associate contractors provided considerably different winged booster stage designs. One common feature was the use of aluminium structures and non-metallic thermal protection systems. In late 1969 the USAF had indicated a preference for all-aluminium structures in the shuttle due to a titanium shortage. This requirement forced a move to non-metallic thermal protection systems, which at the time it was thought would weigh 15% less but cost 300% more. Thermal protection shingles for a titanium structure would weigh 2300 to 4500 kg less, but an aluminium structure would weight about 1800 kg more - meaning there was no essential weight difference between the two approaches. Therefore at the aluminium structure was accepted as a specification requirement. In retrospect it could hardly have been necessary to apply this requirement on a project where only a few flight vehicles were be built. It made the shuttle much more vulnerable to any breach of heat shield integrity and would lead to the death of the Columbia crew 35 years later. The resulting need for a non-metallic thermal protection system would also have enormous cost and schedule consequences for the actual program.

• Shuttle SSME Protest - . Nation: USA. Pratt and Whitney filed a protest against NASA's award to Rocketdyne of the SSME contract. This action prevented further work on Rocketdyne's contract until the issue was adjudicated..

• James C Fletcher sworn in as NASA Administrator - . Nation: USA. Related Persons: Fletcher, Low, George, Nixon, Paine. Program: Apollo.

  James C. Fletcher was sworn in as NASA Administrator at a White House ceremony. Fletcher decided to push for Congressional approval of the stalled space shuttle program, but found that would only be forthcoming if the US Air Force agreed to participate. In order for that to happen, NASA would have to incorporate the USAF requirements for the shuttle that it had so far ignored (greater payload, higher cross-range). In another attempt to share the cost of the shuttle with other nations, previous NASA Administrator Thomas Paine had already tried to obtain international partners. But the only remnants of that effort were the Canadian robotic arm for the shuttle, and the European Space Agency Spacelab module. Neither represented a significant amount of the total program cost.

  President Nixon had nominated Fletcher for the position on March 1, and the Senate had confirmed the nomination on March 11. George M. Low, NASA Deputy Administrator, had been Acting Administrator since the resignation of Paine on September 15, 1970.

• NASA budget constraints - . Nation: USA.

  Nixon's Office of Management of the Budget (OMB) tells NASA to expect no budget increases in the next five years (e.g. $ 3.2 billion per year, meaning no more than $1 billion per year could be spent on the shuttle). Since the peak funding to develop a two-stage-to-orbit shuttle as defined in Phase B studies would be $2 billion, this meant that development of a fully reusable shuttle would not be possible.

• Shuttle design decision - . Nation: USA.

  Based on funding constraints defined in May, NASA decides its shuttle configuration will have to be a partially reusable orbiter, with an external liquid hydrogen tank. Grumman had been the main advocate of this approach, but it was the same conclusion reached in the USAF ILRV studies in 1968. The in-house design reflecting this change was MSC-020, with a liquid oxygen/liquid hydrogen tank housing all propellants outside of the orbiter.

• Shuttle delta wings - . Nation: USA. NASA Houston finally abandoned its straight wing design and studied a series of delta wing orbiters with external tanks through the summer of 1971 (MSC-020B, MSC-036, MSC-046, MSC-040)..

• Delta wing selected for shuttle - . Nation: USA.

  NASA, taking note of the criticisms of the Faget straight-wing design by NASA Flight Research Center and the US Air Force, officially selected a delta wing configuration as the most stable and the one best able to meet the USAF cross-range requirement. But NASA Houston stubbornly continued to push the configuration anyway - even after its own studies showed the orbiter would have a tendency to spin at hypersonic speeds and couldn't take the thermal environment on re-entry. Houston refused to give up, and continued to tinker with aspect ratio, wing sweep, and tail location, reaching the 43th design iteration - MSC-043 - at the end of 1971. One of the alternatives studied was the 'Blue Goose' design of 1970, perhaps the ugliest spacecraft ever conceived. The wing of the long-necked abomination shifted 3.7 m during flight to compensate for centre of gravity changes. The payload bay was forward, followed by the liquid oxygen, then the liquid hydrogen tank. The design was found to have *extreme* aerodynamic heating and structural problems!

• Shuttle Phase B-Prime - . Nation: USA.

  The Phase B contractors, plus Grumman/Boeing and Lockheed, are given further study contracts to produce shuttle designs based on the expendable external tank approach. Lockheed was asked to evaluate the NASA Houston design using an MSC-040 configuration orbiter, external tank, including the MSC040C using three high-performance engines. While the USAF was driving the shuttle design criteria, it had so far not committed to any significant funding for the shuttle. The USAF contribution was limited to allowing NASA use the government-owned Plant 42 at Palmdale, paying for any launch facilities at Vandenberg AFB needed for USAF launches, and providing flight test support at Edwards AFB.

• Shuttle Phase C/D Request for Proposal - . Nation: USA.

  Request for Proposals were sent to Grumman/Boeing, McDonnell-Douglas/Martin Marrietta, and North American Rockwell for final proposals for Shuttle full-scale development. However the NASA specifications kept shifting. In December 1971 NASA decided to require parallel burn of the shuttle orbiter and booster stages, so the bid due date was shifted from 15 December 1971 to 1 June 1972.

• Shuttle Phase B Double Prime - . Nation: USA.

  In yet another iteration of shuttle design studies, $ 2.8 million contracts were given to Grumman/Boeing, Lockheed, McDonnell-Douglas/Martin Marrietta, and North American Rockewell. The development costs for the Phase B Prime contracts had still been over the Nixon administration's budget cap, and still further ways to reduce development cost had to be found. The studies were to run through 15 March 1972 and study lower cost booster concepts: a fully recoverable stage but with a new pressure-fed engine; a Saturn V first stage modified to serve as a flyback booster; and solid rocket motors. The staging velocity was to be under 6600 kph (e.g. lower than in earlier studies). The studies assumed a series burn, with the shuttle orbiter igniting at altitude.

  The studies indicated :

  • The Saturn S-IC flyback booster would use expendable engines, considered a drawback.
  • The new-design pressure fed liquid propellant booster would cost $4.2 billion to develop, plus a recurring cost of $275/kg to orbit.
  • Solid boosters would stage at 5800 kph. A solid booster shuttle would have a 2,221,000 gross lift-off weight equipped with 2 x 156 inch diameter solid rocket motors, loaded with 1.25 million kg of propellant and having a 130 second burn time. Lift-off thrust would be 1,332,000 kgf. Development cost would be $ 3.7 billion, and recurring shuttle cost to orbit would be $ 500/kg.

• Nixon announces $5.5 billion space shuttle program - . Related Persons: , Nixon. President Richard M. Nixon announced that NASA would manage a $5.5 billion program to develop a space shuttle to be the workhorse of future U.S. space efforts and replace all present launch vehicles..

• Shuttle booster decision - . Nation: USA.

  NASA decided that the shuttle booster will be 2 x 156 inch solid rocket motors. This would reduce the total development cost by $700 million, from $ 5.85 billion to $ 5.15 billion. It was also decided to delete the requirement for the shuttle to be equipped with air-breathing engines for final approach and ferry, and to add Abort Solid Rocket Motors that would pull the shuttle away from the external tank in case of a failure of the solid rocket boosters or external tank during the first portion of the ascent to orbit.

• Shuttle SSME Judgement - . Nation: USA. Pratt and Whitney's protest against the award of the shuttle engine development contract was rejected. Contract award to Rocketdyne could now proceed..

• Request for proposals for the Space Shuttle. - . NASA asked the aerospace industry to submit proposals for the development of the Space Shuttle..

• Kennedy Space Center and Vandenberg AFB to be the operational bases for the Shuttle. - . Related Persons: , Kennedy.

  NASA announced that the Kennedy Space Center in Florida and Vandenberg AFB in California would be the operational bases for the future Space Transportation System (STS). The research and development launches of the Space Shuttle would be made from Cape Canaveral, as would the civilian space launches, while the military Space Shuttle launches would be from Vandenberg AFB. SAMSO was the responsible Defense Department agency for defining the military applications and requirements for the Space Shuttle and for cooperating with NASA in the development of the STS.

• Shuttle SSME Contract - . Nation: USA. Rocketdyne finally receives the contact for development of the shuttle main engine. By the end of the century the total value will have exceeded $5.6 billion..

• Shuttle Phase C/D Proposals - . Nation: USA.

  Given that NASA had dictated in great detail the final design, the contractors' proposals differed only in detail. Grumman's orbiter had a 747-type hump-backed configuration, while Lockheed's featured a double-deck crew space. McDonnell-Douglas proposed an alternate auxiliary liquid propellant rocket motor for aborts in place of the mandated Abort Solid Rocket Motors. North American Rockwell's design featured a rounded double-delta wing. All contractors struggled with thermal protection system issues. Ablative materials were lighter, but the bad experience with the use of spray-on ablator on the X-15A-2 made such a solution for an operational vehicle problematic.

• Shuttle orbiter contract - . Nation: USA.

  North American Rockwell received NASA contract NAS9-14000, valued at $2.6 billion, for development of the space shuttle orbiter. Included are two flight articles, the STA Structural Test Article, and the MPTA Main Propulsion Test Article. Later production of two additional orbiters will be added, bringing the final contract value to $ 5.815 billion by 1996.

• Safety in Earth Orbit - . Nation: USA.

  North American Rockwell issues a study on safety concepts for the space shuttle. These include putting an Apollo command module in the shuttle payload bay as an emergency re-entry capsule in case of inability of the shuttle to re-enter due to heat shield damage or a propulsion system failure. The study finds that all solutions have unacceptable weight penalties, and that any upper stages carried in the payload bay had to be man-rated in order to ensure crew safety. Liquid propellant upper stages (such as Centaur and the planned Space Tug) were probably too dangerous to be taken to orbit by the shuttle.

• Contract awarded for shuttle OV-102. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Contract for development of the Space Shuttle. - . NASA awarded a $2.6 billion contract to North American Rockwell (now Rockwell International) for the development of the national Space Transportation System (STS) and the Space Shuttle..

• Shuttle go-ahead. - . Nation: USA. Program: STS. Rockwell receives authority to proceed, space shuttle orbiter.

• DOD to develop the shuttle's Interim Upper Stage. - . An Air Force Program Memorandum on DOD Space Shuttle Utilization was completed that assumed the DOD would develop the shuttle's Interim Upper Stage (IUS) needed for high energy missions..

• Shuttle solid rocket booster contract - . Nation: USA. United Space Boosters and Thiokol receive the contract..

• Shuttle external tank contract - . Nation: USA. Boeing Michoud received the production contract, using facilities already built for Saturn V first stage construction. By 1996 the contract will have totalled $6.7 billion and covered the production of 120 external tanks..

• Air Force plan for the Space Transportation System. - . The Air Force completed a revised Program Memorandum on DoD Space Shuttle Utilization that was to become the basis for Air Force planning for the Space Transportation System..

• Shuttle configuration changes - . Nation: USA. Between the March 1972 Authority to Proceed and June 1974 six major configuration changes are made to the shuttle design..

• Shuttle Enterprise construction begins. - . Nation: USA. Program: STS. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Structural assembly of the crew module for shuttle Enterprise (OV-101) begins at Plant 42 in Palmdale..

• Structural assembly of crew module for OV-102 begun. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Shuttle carrier aircraft purchased - . Nation: USA.

  NASA purchases used American Airlines 747 N9668 for use as a carrier to ferry the shuttle orbiter between factory, landing sites, and launch sites. Modification of a 747 to carry the orbiter on its back was chosen over two more costly alternatives that would have suspended it from a wing connecting two fuselages: a new design proposed by NASA LaRC, and a Lockheed proposal for two C-5A transports joined together.

• Shuttle Enterprise fuselage assembly starts. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Start structural assembly aft fuselage, Enterprise (OV-101).

• IUS studies begun. - .

  The Air Force awarded firm-fixed-price (FFP) level of effort contracts of about $635,000 to $640,000 each to Martin Marietta Corporation, Lockheed Missiles and Space Company, General Dynamics Convair Division, The Boeing Company, and McDonnell Douglas Astronautics Company for nine-month IUS System Study efforts.^ These companies had in-production, existing operational upper stages and the studies would provide baseline data for future acquisition efforts.

• DOD space shuttle mission operations to be controlled by a predominantly NASA team. - .

  HQ USAF issued a Program Management Directive specifying that initial DOD space shuttle mission operations would be planned and controlled by a predominantly NASA team rather than by a DOD team. The Program Management Directive also directed that action be taken to minimize the impact of DOD communications security requirements on shuttle operations.

• Lower-cost shuttle external tank - . Nation: USA.

  Grumman completes a study of a lower-cost external tank. It would use a Nomex core, aluminium liner, and E-glass/epoxy exterior. Although lower in cost than the baseline aluminium tank, it would be slightly heavier. Given the critical weight growth problem with the shuttle, it was not proceeded with. In fact, a continuous program of weight reduction for the baseline tank was introduced. Batch 1 External Tanks were already from 500 to 1040 kg lighter than the first tank. Batch 2, set for delivery from June 1982 to Vandenberg AFB for USAF launches, were 2700 kg lighter. The final "lightweight tank" was over 4500 kg lighter. All of these translated into equivalent additional payload for the shuttle.

• Shuttle Enterprise fuselage complete. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Shuttle Columbia fuselage assembly starts. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Start long-lead fabrication aft fuselage, Columbia (OV-102).

• Enterprise wings complete. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Wings on dock, Palmdale-less elevons, seals and main gear doors-Enterprise (OV-101).

• Enterprise vertical stabilizer complete. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Vertical stabilizer on dock, Palmdale (main fin box only), Enterprise (OV-101).

• Shuttle SSME engine chamber Test - . Nation: USA. The first full thrust chamber test is completed..

• Shuttle Enterprise final assembly. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Start final assembly and closeout system installation, Enterprise (OV-101).

• Interim Upper Stage for use with the Space Transportation System. - . Dr. Walter LaBerge, Assistance Secretary of the Air Force for Research and Development, announced an Interim Upper Stage to be developed for use with the Space Transportation System..

• Enterprise aft fuselage complete. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Aft fuselage on dock, Palmdale, Enterprise (OV-101).

• Shuttle SSME first test. - . Nation: USA. Program: STS. Space shuttle main engine first main stage test at NSTL.

• Enterprise lower fuselage complete. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Lower forward fuselage on dock, Palmdale, Enterprise (OV-101).

• Columbia crew module started. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Start long-lead fabrication of crew module, Columbia (OV-102).

• DOD to use NASA's mission operations system for the space shuttle - . HQ USAF decided that the DOD would not acquire its own mission operations system for the space shuttle but would use NASA's system instead..

• Enterprise upper forward fuselage complete. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Upper forward fuselage on dock, Palmdale, Enterprise (OV-101).

• First SSME 60-second duration test, NSTL - . Nation: USA. Program: STS.

• Crew module on dock, Palmdale, Enterprise (OV-101) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Interim Upper Stage to be used with the Titan III - .

  A joint DOD/NASA study was carried out on the consolidation of expendable launch vehicles during transition to the space shuttle. The study recommended that the Interim Upper Stage, being developed for the space shuttle, be used with the Titan III during the transition period.

• Payload bay doors on dock, Palmdale, Enterprise - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Payload bay doors on dock, Palmdale, Enterprise (OV-101).

• Shuttle SSME Test - . Nation: USA. The full engine is run at 65% power for 42.5 seconds before a fuel turbopump failure curtails the test (50 second duration planned)..

• Enterprise final assembly complete. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Complete final assembly and closeout system installation..

• Start functional checkout, Enterprise - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Start functional checkout, Enterprise (OV-101)..

• $125 million to modify NASA's space shuttle mission control center for use by the DOD. - . A joint USAF/NASA study concluded that it would cost $125 million to modify NASA's space shuttle mission control center so that it could be used by the DOD..

• Body flap on dock, Palmdale, Enterprise (OV-101) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Complete functional checkout, Enterprise (OV-101) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Start horizontal ground vibration tests Enterprise - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Start horizontal ground vibration tests and proof load tests, Enterprise (OV-101).

• SSME dummy set on dock, Palmdale. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. SSME dummy set on dock, Palmdale, Enterprise (OV-101).

• Optimum configuration for the space shuttle launch pad at Vandenberg AFB. - . Tests were conducted at NASA's Marshall Space Flight Center to determine the optimum configuration for the space shuttle launch pad to be built at Vandenberg AFB..

• Design criteria for space shuttle facilities at Vandenberg. - . Contract FO4701-76-C-0081 was distributed to Martin Marietta for the preparation of design criteria for space shuttle facilities at Vandenberg AFB. The target price of the contract was $28 million..

• Shuttle carrier aircraft - . Nation: USA. Work begins on modification of 747 N9668 to carry the shuttle on its back in a $30 million contract. After completion the aircraft is rolled out as N905NA..

• Start Delta F modification, Enterprise (OV-101) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Shuttle Enterprise - dummy OMS pods delivered. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Reaction control system/orbital maneuvering system pods (simulated), approach and landing tests, on dock, Palmdale, Enterprise.

• Contract for validation phase of the Interim Upper Stage. - . A contract was distributed to the Boeing Aerospace Company for the validation phase of the Interim Upper Stage development program. The contract carried a target price of $21 million..

• Complete Delta F modifications, Enterprise - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Start preparations for first rollout, Enterprise - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• The roll-out of the first space shuttle vehicle took place. - .

• Start Delta F retest, Enterprise (OV-101) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Shuttle ejection seat tests - . Nation: USA. Tests begin on the rocket sled at Holloman AFB of the ejection seats to be used in shuttle Columbia, using an upper fuselage. The test series is completed on November 18..

• Complete Delta F retest, Enterprise (OV-101) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Complete integrated checkout, Enterprise (OV-101) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Process selected for manufacturing hydrazine fuels for the Titan III and the space shuttle. - . SAMSO selected the Sisler process as the best of three competing methods for manufacturing hydrazine fuels for the Titan III and the space shuttle..

• DOD mission operations system for the space shuttle. - .

  Briefings were presented to HQ AFSC, HQ USAF, and SAF/SS outlining three alternative methods of providing the DOD with a mission operations system for the space shuttle. These were: modification of NASA facilities at the Johnson Space Center, expansion of the Air Force Satellite Control Facility, and construction of an all-new DOD facility to be called the STS Operations and Planning Center.

• Start assembly upper forward fuselage, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Space shuttle facilities at Vandenberg AFB, California. - . The U.S. Army Corps of Engineers began designing the mate/demate facility, the airfield, and the tow route to be used by the space shuttle at Vandenberg AFB, California..

• Start assembly vertical stabilizer, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Boeing 747 shuttle carrier aircraft delivered - . Nation: USA. Program: STS. Boeing 747 shuttle carrier aircraft delivered to Edwards.

• Mockup SSME's delivered for Enterprise - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Mass simulated SSMEs on dock, Palmdale, Enterprise (OV-101).

• Mass simulated SSMEs on dock, Palmdale, Enterprise - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Enterprise (OV-101) transported to Edwards AFB - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

• Enterprise (OV-101)/shuttle carrier aircraft mate - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Enterprise (OV-101)/shuttle carrier aircraft mate start.

• Midfuselage on dock, Palmdale, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Enterprise (OV-101)/shuttle carrier aircraft mated - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Complete Enterprise (OV-101)/shuttle carrier aircraft mated.

• First inert captive flight - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Conduct first inert captive flight, Edwards (2 hours, 5 minutes), Enterprise (OV-101).

• Second inert captive flight - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Conduct second inert captive flight, Edwards (3 hours, 13 minutes), Enterprise (OV-101).

• Third inert captive flight - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Conduct third inert captive flight, Edwards (2 hours, 28 minutes), Enterprise (OV-101).

• Fourth inert captive flight - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Conduct fourth inert captive flight, Edwards (2 hours, 11 minutes), Enterprise (OV-101).

• Fifth inert captive flight - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Conduct fifth inert captive flight, Edwards (1 hour, 39 minutes), Enterprise (OV-101).

• Shuttle SSME Tests resumed - . Nation: USA. 25 tests will be run on two engines over the next year..

• Shuttle ejection seat tests - . Nation: USA. Another test series is held at Holloman at speeds of zero to 725 kph in support of the impending ALT shuttle glide tests..

• Complete integrated checkout of Enterprise - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Complete integrated checkout and hot-fire ground test, Edwards, Enterprise (OV-101).

• IUS 85-second test firing. - . A rocket nozzle for the IUS was subjected to an 85 second test firing at the Rocket Propulsion Laboratory. The test was successful. A second successful test took place on 15 July..

• Shuttle SRB Drop test - . Nation: USA. An unloaded shuttle solid rocket motor is dropped from an NB-52 in a test of the parachute recovery system..

• Enterprise flight 1 - . Call Sign: Enterprise. Crew: Fullerton, Haise. Nation: USA. Related Persons: Fullerton, Haise. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. First manned captive active flight. Enterprise (OV-101)/shuttle carrier aircraft, Edwards (55 minutes, 46 seconds).

• Titan 34D/IUS launch vehicle begun. - . HQ USAF directed AFSC to begin developing the Titan 34D/IUS launch vehicle..

• Shuttle MPTA shipped to National Space Technology Laboratories - . Nation: USA. The test article of the shuttle orbiter's aft structure is mated to External Tank MPTA-ET (ET number one) and three prototype SSME engines..

• Enterprise flight 2 - . Call Sign: Enterprise. Crew: Engle, Truly. Nation: USA. Related Persons: Engle, Truly. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Second manned captive active flight. Enterprise (OV-101)/shuttle carrier aircraft, Edwards (1 hour, 2 minutes).

• Secure use of NASA's Johnson Space Center for classified DOD missions. - .

  A joint DOD/NASA committee was formed to find an economical method of securing NASA's Johnson Space Center so that it could be used for mission control when classified DOD missions were flown. The committee handed in its final report in November, recommending that the Johnson Space Center be secured through what it called the "controlled mode" of operation.

• DM-1 Shuttle SRB development static firing - . Nation: USA. The first firing of a shuttle Solid Rocket Booster motor..

• Enterprise flight 3 - . Call Sign: Enterprise. Crew: Fullerton, Haise. Nation: USA. Related Persons: Fullerton, Haise. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Third manned captive active flight. Enterprise (OV-101)/shuttle carrier aircraft, Edwards (59 minutes, 50 seconds).

• Launch complex for the space shuttle at Vandenberg AFB - . Sverdrup and Parcel began designing the launch complex to be used by the space shuttle at Vandenberg AFB, California..

• Shuttle SRB Drop test - . Nation: USA. An unloaded shuttle solid rocket motor is dropped from an NB-52 in a test of the parachute recovery system..

• Enterprise flight 4. The space shuttle made its first free flight. - . Call Sign: Enterprise. Crew: Fullerton, Haise. Nation: USA. Related Persons: Fullerton, Haise. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise.

  After being carried aloft by a Boeing 747, it was released and made an unassisted landing at Edwards AFB, California. This was part of a series of approach and landing tests carried out at Edwards from February to October. Conduct first free flight, ALT, tail cone on, Edwards (5 minutes, 21 seconds), Enterprise (OV-101), lake bed Runway 17

• Deliver wings on dock, Palmdale, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Lower forward fuselage on dock, Palmdale, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Enterprise flight 5 - . Call Sign: Enterprise. Crew: Engle, Truly. Nation: USA. Related Persons: Engle, Truly. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Second free flight, ALT, tail cone on, Edwards (5 minutes, 28 seconds), Enterprise (OV-101), lake bed Runway 17.

• Enterprise flight 6 - . Call Sign: Enterprise. Crew: Fullerton, Haise. Nation: USA. Related Persons: Fullerton, Haise. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Third free flight , ALT, tail cone on, Edwards (5 minutes, 34 seconds), Enterprise (OV-101), lake bed Runway 15.

• SRB Hydroburst test - . Nation: USA. A flight-representative shuttle Solid Rocket Booster was subjected to water pressure until the casing burst..

• Contract to integrate payloads into the space shuttle. - . Martin Marietta was awarded a contract to develop plans, procedures, analytical tools and models, and general expertise that would be required to integrate payloads into the space shuttle..

• Large USAF structure to be carried into orbit aboard the shuttle. - . Competitive contracts were awarded to the Denver Division of Martin Marietta and the Convair Division of General Dynamics to design a large structure to be carried into orbit aboard the shuttle..

• Rocket nozzle for the IUS tested - . A rocket nozzle for the IUS was subjected to a 145 second test firing at the Rocket Propulsion Laboratory. The test was successful..

• Enterprise flight 7 - . Call Sign: Enterprise. Crew: Engle, Truly. Nation: USA. Related Persons: Engle, Truly. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Fourth free flight, ALT, first tail cone off, Edwards (2 minutes, 34 seconds), Enterprise (OV-101), lake bed Runway 17.

• Enterprise flight 8 - . Call Sign: Enterprise. Crew: Fullerton, Haise. Nation: USA. Related Persons: Fullerton, Haise. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Fifth free flight, ALT, final tail cone off, Edwards (2 minutes, 1 second), Enterprise (OV-101), concrete Runway 04.

• Lower forward fuselage on dock, Palmdale, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Deliver aft fuselage on dock, Palmdale, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Start final assembly Columbia. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Start final assembly and closeout system installation, Palmdale, Columbia (OV-102).

• First ferry flight test, Edwards - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. First ferry flight test, Edwards (3 hours, 21 minutes), Enterprise (OV-101).

• Second ferry flight test, Edwards - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Second ferry flight test, Edwards (4 hours, 17 minutes), Enterprise (OV-101).

• Third ferry flight test, Edwards - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Third ferry flight test, Edwards (4 hours, 13 minutes), Enterprise (OV-101).

• Fourth ferry flight test, Edwards - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Fourth ferry flight test, Edwards (3 hours, 37 minutes), Enterprise (OV-101).

• Complete approach and landing flight tests - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Complete approach and landing flight tests, including ferry flights, Enterprise (OV-101).

• Start modification of Enterprise for ground vibe tests - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Start removal for mated vertical ground vibration test modification at Edwards, Enterprise (OV-101).

• STS Program Office reorganized - . The Deputy for Launch Vehicles reorganized the STS Program Office to support expanding STS programs..

• Shuttle SRB Drop test - . Nation: USA. An unloaded shuttle solid rocket motor is dropped from an NB-52 in a test of the parachute recovery system..

• IUS program status - . The status of the IUS program was briefed to the Air Force Systems Acquisition Review Council. The Council requested additional information on funding, requirements and costs, and program alternatives.

• IUS motor test fired - . A full scale IUS motor was successfully test fired at the Arnold Engineering Development Center..

• Vertical stabilizer on dock, Palmdale, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• DM-2 Shuttle SRB development static firing - . Nation: USA. The second firing of a shuttle Solid Rocket Booster motor..

• Space shuttle environmental impact statement - .

  The final version of the space shuttle environmental impact statement was released to the Council on Environmental Quality. The statement described how the construction and operation of space shuttle facilities would affect the environment of Vandenberg AFB.

• Complete final assembly, STA-099, Palmdale - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Challenger.

• STA-099 on dock, Lockheed facility, Palmdale - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Challenger.

• Crew module on dock, Palmdale, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Body flap on dock, Palmdale, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Complete modification for mated vibe tests. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Complete modification for mated vertical ground vibration test, Edwards, Enterprise (OV-101).

• Upper forward fuselage on dock, Palmdale, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Ferry Enterprise from Edwards to Texas. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry Enterprise (OV-101) atop shuttle carrier aircraft from Edwards to Ellington Air Force Base, Texas (approximately 3 hours, 38 min).

• Shuttle Enterprise delivered. - . Nation: USA.

• Ferry Enterprise from Texas to Huntsville - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry Enterprise (OV-101) atop shuttle carrier aircraft from Ellington AFB to Marshall Space Flight Center, Huntsville, Ala..

• Aft payload bay doors on dock, Palmdale, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Validation phase of the Inertial Upper Stage completed. - .

  SAMSO briefed the Defense Systems Acquisition Review Council (DSARC) on the results of the validation phase of the development of the space shuttle's Inertial Upper Stage. The DSARC recommended that the program be allowed to continue into full scale development.

• Titan III 34D/IUS not to be used as backup for launch of a Tracking and Data Relay Satellite. - . Spacecraft: TDRS. NASA withdrew its requirement for a Titan III 34D/IUS to be used as backup for a space shuttle launch of a Tracking and Data Relay Satellite in 1980..

• Contract for space shuttle's Inertial Upper Stage - . A contract for full-scale development of the space shuttle's Inertial Upper Stage was distributed to the Boeing Aerospace Company..

• Cost growth in the Titan III 34D/IUS development program. - . SAMSO representatives briefed HQ AFSC officials on possible alternatives to deal with the cost growth problem in the Titan III 34D/IUS development program..

• Shuttle MPTA First test - . Nation: USA. For the first time three SSME engines are run on the MPTA test article mated to an external tank - for 2.5 seconds..

• Columbia ready for power-on. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Complete final assembly and closeout system installation, ready for power-on, Columbia (OV-102).

• Start precombined systems test, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Forward payload bay doors on dock, Columbia. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Forward payload bay doors on dock, Palmdale, Columbia (OV-102).

• Space Shuttle Orbiter 101 began vibration tests - . Space Shuttle Orbiter 101 began undergoing vibration tests at the Marshall Space Flight Center in Huntsville, Alabama..

• Contract for integration of payloads into the space shuttle's Inertial Upper Stage. - . A contract for integration of payloads into the space shuttle's Inertial Upper Stage was distributed to the Boeing Aerospace Company. The value of the contract was $10.72 million..

• Shuttle SRB Drop test - . Nation: USA. An unloaded shuttle solid rocket motor is dropped from an NB-52 in a test of the parachute recovery system..

• Modifications to the main engine of the space shuttle orbiter - . Modifications to the main engine of the space shuttle orbiters began to be evaluated in a series of test firings..

• Upper forward fuselage mate, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Complete forward RCS structure, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• New carbon-carbon nozzle for Inertial Upper Stage. - . A carbon-carbon nozzle, manufactured for the space shuttle's Inertial Upper Stage propulsion system by a new low-cost process, underwent a test firing at the Air Force Rocket Propulsion Laboratory..

• Start Enterprise (OV-101)/ ET mated vibe test - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Start Enterprise (OV-101)/ ET mated vertical ground vibration test, MSFC.

• Ground support system for the space shuttle at Vandenberg AFB. - . Martin Marietta was awarded a follow-on contract to perform systems integration during the acquisition of the ground support system for the space shuttle at Vandenberg AFB..

• Radio guidance for Titan 34D. - .

  SAMSO was authorized by the Office of the Secretary of the Air Force to develop a radio guidance system for Titan III34Ds launched from Vandenberg instead of the IUS inertial guidance system. This program change would reduce development costs for the Titan III34D program.

• Shuttle MPTA long duration test - . Nation: USA. The engine assembly is run for several minutes, and engine restart is demonstrated..

• Complete mate payload bay doors, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Complete mate forward and aft payload bay doors, Columbia (OV-102).

• Reconfigure from boost to launch, vibe test - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Reconfigure from boost to launch, mated vertical ground vibration test, MSFC, Enterprise (OV-101).

• Test failure of space shuttle main engine - . Testing of modifications to the main engine of the space shuttle orbiters was suspended when a high pressure oxygen pump failed..

• Shuttle SRB Drop test - . Nation: USA. An unloaded shuttle solid rocket motor is dropped from an NB-52 in a test of the parachute recovery system..

• Shuttle computer equipment installation begun at Vandenberg AFB. - . Installation of the Vandenberg Launch Processing System began at Vandenberg AFB. The system was made up of data processing equipment that would be used in conducting launch operations for the shuttle..

• Complete forward RCS, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Testing of the main engine of the space shuttle orbiters .. resumed. - . Testing of the main engine of the space shuttle orbiters was resumed after a failure of the high pressure oxygen pump was determined to have been caused by test instrumentation..

• Shuttle SRB Drop test - . Nation: USA. An unloaded shuttle solid rocket motor is dropped from an NB-52 in a test of the parachute recovery system..

• Shuttle tests at NASA Huntsville - . Nation: USA.

  The shuttle Enterprise is first mated to an external tank for vertical ground vibration tests and simulated high-altitude aborts. Thereafter two SRB's are mounted for the first full-size shuttle static tests. This initial test series is completed on 5 December 1978.

• Start precombined system test, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Johnson Space Center to support DoD shuttle operations. - . HQ USAF directed the implementation of the so-called controlled mode at the Johnson Space Center. This was a special method of operation that would allow the Center to support DoD shuttle operations..

• Shuttle Structural Test began structural bending tests. - . Space Shuttle Orbiter 99, the Structural Test Article, began undergoing structural bending tests..

• Test of the Kevlar case for the large Inertial Upper Stage motor. - . A test was conducted on the Kevlar case used to hold propellant in the space shuttle's large Inertial Upper Stage motor. The case burst at a pressure lower than the predicted pressure..

• DM-3 Shuttle SRB development static firing - . Nation: USA. The third firing of a shuttle Solid Rocket Booster motor..

• Space shuttle to include additional strap-on solid rocket motors. - . NASA decided to augment the thrust of the space shuttle orbiter by attaching a single strap-on solid rocket motor to each of the orbiter's two solid rocket boosters..

• Complete precombined system test, Columbia. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Failure of the main engine of the space shuttle orbiter. - .

  Testing of the main engine of the space shuttle orbiters was suspended when the engine failed, apparently because of a malfunctioning of its main oxidizer valve. This and previous test failures caused the scheduling of the first orbiter test flight to slip from March 1979 to the end of CY 1979 or the beginning of CY 1980.

• The Army Corps of Engineers awarded a $3.8 million contract to Morrison-Knudsen, Inc. - . It was for site preparation at the space shuttle launch facility, Vandenberg AFB. Site preparation was the first phase of a three-phase construction effort at the launch facility. Ground-breaking took place on 24 January..

• Complete combined systems test, Palmdale, Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• DM-4 Shuttle SRB development static firing - . Nation: USA. The fourth firing of a shuttle Solid Rocket Booster motor..

• A Critical Design Review was held for the Inertial Upper Stage. - .

  SAMSO felt that the design presented at this Review was not really complete, and it directed the contractor, Boeing, to do further work in the areas of software, rocket motors, and interface with the space shuttle and the Satellite Control Facility. Boeing was to present the results of its efforts at a follow-on design review to be held later in the year.

• Space shuttle launch facilities at Vandenberg AFB delayed. - .

  HQ USAF stretched out the schedule for construction of space shuttle launch facilities at Vandenberg AFB, and it changed the Initial Operational Capability date for those facilities from mid-1983. The extra time was needed because NASA was adding strap-on solid rocket motors to the shuttle to augment its performance, and the launch facilities had to be modified to accommodate those motors.

• Airlock on dock, Palmdale, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Final shuttle tests at NASA Huntsville - . Nation: USA. These verified loadings on the full mated shuttle stack with the external tank and solid rocket motors loaded with water to simulate the weights at various flight phases. 36 x 670 N and 20 x 4400 N exciters were used to vibrate the vehicle..

• Complete mated vertical ground vibe test program - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Complete mated vertical ground vibration test program at MSFC, Enterprise (OV-101).

• Complete postcheckout, Palmdale, Columbia (OV-102) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

• Improved IUS performance - . A change order was added to the IUS contract, directing the contractor to take various steps to improve the performance of the vehicle.

• Columbia (OV-102) transported overland to Edwards. - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Columbia (OV-102) transported overland from Palmdale to Edwards (38 miles).

• Shuttle carrier aircraft/Columbia test flight - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Shuttle carrier aircraft/Columbia (OV-102) test flight at NASA Edwards.

• Large rocket motor for the Inertial Upper Stage was fired - .

  The large rocket motor for the Inertial Upper Stage was test fired at the Arnold Engineering Development Center. The firing lasted 145 seconds and generated more than 50,000 pounds of thrust. This was the first development test firing of the large motor, and it was entirely successful.

• Ferry flight, Edwards to El Paso - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Ferry flight, shuttle carrier aircraft/Columbia (OV-102) from Edwards to Biggs Army Air Base, El Paso, Texas (3 hours, 20 minutes).

• Ferry flight El Paso to Kelly AFB - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Ferry flight, shuttle carrier aircraft/Columbia (OV-102) from Biggs Army Air Base to Kelly AFB, San Antonio, Texas (1 hr, 39 min).

• Shuttle orbiter 102 flown from Edwards to Cape Canaveral,. - . NASA brought space shuttle orbiter 102 from Edwards AFB, California, to Cape Canaveral, Florida. Orbiter 102 would be the first orbiter to go into space, and Cape Canaveral would be the launch site..

• Ferry flight, Kelly AFB to Eglin AFB, Fla - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Ferry flight, shuttle carrier aircraft/Columbia (OV-102) from Kelly AFB to Eglin AFB, Fla. (2 hours, 12 minutes).

• Ferry flight, Eglin AFB to KSC - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Ferry flight, shuttle carrier aircraft/Columbia (OV-102) from Eglin AFB to KSC (1 hour, 33 minutes).

• Shuttle Enterprise delivered to Kennedy Space Centre - . Nation: USA.

  The decision was taken not to convert the Enterprise to a flight orbiter due to the numerous structural design changes made since its construction. Static test article OV-099 would be used for that instead. So Enterprise became a pathfinder vehicle at Cape Canaveral to verify fit and handling of ground facilities in the Vertical Assembly Building and LC39.

• Ferry flight, MSFC to KSC - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry flight, shuttle carrier aircraft/Enterprise (OV-101) from MSFC to KSC (1 hour, 52 minutes).

• Complete left-hand OMS/RCS Phase I qualification - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Complete left-hand OMS/RCS Phase I qualification, WSTF May 1 Enterprise (OV-101)/ ET/SRBs mated on mobile launcher platform,.

• First shuttle roll-out - . Nation: USA. Non-flight shuttle Enterprise, mated to External Tank number 2, and two inert solid rocket motors, is rolled out to LC39A for facility checks..

• Deliver right-hand OMS/RCS for Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Deliver right-hand OMS/RCS from McDonnell Douglas, St. Louis, to KSC, Columbia (OV-102).

• Deliver left-hand OMS/RCS for Columbia - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Deliver left-hand OMS/RCS from McDonnell Douglas to KSC, Columbia (OV-102).

• USAF space shuttle mission controllers. - . SAMSO Det 2 was established at NASA's Johnson Space Center to train AF officers to become space shuttle mission controllers..

• QM-1 Shuttle SRB qualification static firing - . Nation: USA. The fifth firing of a shuttle Solid Rocket Booster motor..

• Start assembly crew module, Challenger (OV-099) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Challenger.

• First test firing of the small motor for the Inertial Upper Stage . - . The small rocket motor for the Inertial Upper Stage was test fired at the Arnold Engineering Development Center. This was the first development test firing of the small motor..

• Major Shuttle SSME failure - . Nation: USA. Engine 2002 explodes violently during a test run due to a hydrogen leak. The MPTA test article sustains major structural damage due to overpressure of the heat shield support..

• Consolidated Space Operations Center (CSOC). - .

  A special working group with HQ USAF finished a concept of operations for the Consolidated Space Operations Center (CSOC). CSOC would serve both the space shuttle program and the Air Force Satellite Control Facility, functioning as a Shuttle Operations and Planning Center and a Satellite Operations Center.

• First test STS stack move from VAB to LC39A - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Enterprise (OV-101), ET, SRBs transported on mobile launcher platform from Launch Complex 39-A to Vehicle Assembly Building at KSC.

• Start long-lead fabrication crew module, Discovery - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Discovery.

• Complete limit test (STA-099) - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Complete limit test (STA-099), Lockheed facility, Palmdale.

• Ferry flight, KSC to Atlanta - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry flight, shuttle carrier aircraft/Enterprise (OV-101), KSC to Atlanta (1 hour, 55 minutes).

• Ferry flight, Atlanta to St. Louis - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry flight, shuttle carrier aircraft/Enterprise (OV-101), Atlanta to St. Louis (1 hour, 50 minutes).

• Ferry flight, St. Louis to Tulsa - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry flight, shuttle carrier aircraft/Enterprise (OV-101), St. Louis to Tulsa (1 hour, 35 minutes).

• Ferry flight, Tulsa to Denver - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry flight, shuttle carrier aircraft/Enterprise (OV-101), Tulsa to Denver (2 hours).

• Ferry flight, Denver to Hill AFB, Ogden, Utah - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry flight, shuttle carrier aircraft/Enterprise (OV-101), Denver to Hill AFB, Ogden, Utah (1 hour, 30 minutes).

• Ferry flight, Ogden to Vandenberg AFB - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry flight, shuttle carrier aircraft/Enterprise (OV-101), Ogden to Vandenberg AFB (2 hours, 20 minutes).

• Ferry flight, Vandenberg AFB to Edwards - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Ferry flight, shuttle carrier aircraft/Enterprise (OV-101), Vandenberg AFB to Edwards (1 hour, 10 minutes).

• Enterprise / shuttle carrier demate, Edwards - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. Enterprise (OV-101)/ shuttle carrier demate, Edwards.

• Start long-lead fabrication crew module, Discovery - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Discovery.

• Teal Ruby to be flown on the space shuttle in November 1982. - . Under Secretary of Defense William J. Perry decided that Teal Ruby would be built and flown on the space shuttle in November 1982. His decision was made in response to earlier suggestions within DOD that the program be cancelled because of cost overruns..

• STS-2A (cancelled) - . Crew: Haise, Lousma. Nation: USA. Related Persons: Haise, Lousma. Program: STS. Flight: STS-2A. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

  In late 1977 shuttle orbital missions were due to start in 1979. STS-2, the second shuttle flight, was to have rendezvoused with the Skylab space station and released a small Skylab Reboost Module. This would dock to Skylab and boost the station to a higher orbit for later use. But the shuttle program also was hit with delays and before the first shuttle flew, Skylab burned up in the atmosphere and crashed into the Australian outback on July 11, 1979.

• Shuttle SSME Failure - . Nation: USA. In a test run, a liquid oxygen turbopump fails 9.7 seconds into the burn..

• QM-2 Shuttle SRB qualification static firing - . Nation: USA. The sixth firing of a shuttle Solid Rocket Booster motor..

• First Shuttle SSME full-duration test - . Nation: USA.

  The first completely successful firing of the orbiter's engines is completed Three engines are run from 100% to 70% thrust for 514 seconds. Engines 2004, 2005, 2006, and 2007 were to have been certified ready for flight in the first half on 1979. This involved each engine being given a 1.5 second start verification firing; a 100 second calibration firing; and a 520 second flight demonstration test. But continued failures resulted in multiple rebuilds of each engine to add required modifications. The result was a two-year delay to this schedule.

• Shuttle TPS Tests - . Nation: USA. Shuttle thermal protection system tiles are tested mounted of F-15 and F-104 aircraft at speeds of up to Mach 1.4 and dynamic pressures of 470 N / sq m..

• QM-3 Shuttle SRB qualification static firing - . Nation: USA. The seventh and final firing of a shuttle Solid Rocket Booster motor prior to the first launch. None of the ground tests subjected the motors to expected flight loads..

• Shuttle ejection seat tests - . Nation: USA. Another series of tests of the shuttle ejection seat are held at Holloman AFB in support of the first shuttle orbital flights..

• SRB Hydroburst test - . Nation: USA. A production-representative shuttle Solid Rocket Booster was subjected to water pressure until the casing burst..

• Shuttle MPTA-098 625-second firing. - . Nation: USA. This firing used the three flight engines, which had been removed from Columbia..

• Shuttle flight readiness firing - . Nation: USA. The 20 second test on the pad at Cape Canaveral finally cleared the engines for the first shuttle launch..

• STS-1 - . Call Sign: Columbia. Crew: Crippen, Young. Payload: Columbia F01 / DFI. Mass: 4,909 kg (10,822 lb). Nation: USA. Related Persons: Crippen, Young. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-1. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Duration: 2.26 days. Decay Date: 1981-04-14 . USAF Sat Cat: 12399 . COSPAR: 1981-034A. Apogee: 251 km (155 mi). Perigee: 240 km (140 mi). Inclination: 40.30 deg. Period: 89.40 min. First flight of Space Transportation System (aka Space Shuttle).. Payloads: Development Flight Instrumentation and Aerodynamic Coefficient Identification Package..

• DFI - . Payload: DFI PLT. Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: DFI. Decay Date: 1981-04-14 . USAF Sat Cat: 12399 . COSPAR: 1981-034xx. Apogee: 272 km (169 mi). Perigee: 260 km (160 mi). Inclination: 40.30 deg. Period: 89.80 min.

• STS-2 - . Call Sign: Columbia. Crew: Engle, Truly. Payload: Columbia F02 / DFI. Mass: 8,517 kg (18,776 lb). Nation: USA. Related Persons: Engle, Truly. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-2. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Duration: 2.26 days. Decay Date: 1981-11-14 . USAF Sat Cat: 12953 . COSPAR: 1981-111A. Apogee: 231 km (143 mi). Perigee: 222 km (137 mi). Inclination: 38.00 deg. Period: 89.00 min. Second shuttle test flight. Payloads: Office of Space and Terrestrial Applications (OSTA)-1 experiments, Orbiter Experiments (OEX)..

• DFI - . Payload: DFI PLT. Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: DFI. Decay Date: 1981-11-14 . USAF Sat Cat: 12953 . COSPAR: 1981-111xx. Apogee: 265 km (164 mi). Perigee: 255 km (158 mi). Inclination: 38.00 deg. Period: 89.70 min.

• OSTA-1 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1981-11-14 . USAF Sat Cat: 12953 . COSPAR: 1981-111xx. Apogee: 265 km (164 mi). Perigee: 255 km (158 mi). Inclination: 38.00 deg. Period: 89.70 min.

• STS-3 - . Call Sign: Columbia. Crew: Fullerton, Lousma. Payload: Columbia F03 / OSS-1. Mass: 10,301 kg (22,709 lb). Nation: USA. Related Persons: Fullerton, Lousma. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-3. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Duration: 8.00 days. Decay Date: 1982-03-30 . USAF Sat Cat: 13106 . COSPAR: 1982-022A. Apogee: 249 km (154 mi). Perigee: 241 km (149 mi). Inclination: 38.00 deg. Period: 89.40 min. Manned two crew. Payloads: Office of Space Science (OSS) experiments, Monodisperse Latex Reactor (MLR), Electro-phoresis Verification Test (EEVT), Plant Lignification Experiment..

• OSS-1 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1982-03-30 . USAF Sat Cat: 13106 . COSPAR: 1982-022xx. Apogee: 245 km (152 mi). Perigee: 220 km (130 mi). Inclination: 38.00 deg. Period: 89.20 min.

• DFI - . Payload: DFI PLT. Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: DFI. Decay Date: 1982-03-30 . USAF Sat Cat: 13106 . COSPAR: 1982-022xx. Apogee: 245 km (152 mi). Perigee: 220 km (130 mi). Inclination: 38.00 deg. Period: 89.20 min.

• STS-4 - . Call Sign: Columbia. Crew: Hartsfield, Mattingly. Payload: Columbia F04 / DoD 82-1. Mass: 11,109 kg (24,491 lb). Nation: USA. Related Persons: Hartsfield, Mattingly. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-4. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Duration: 7.05 days. Decay Date: 1982-07-04 . USAF Sat Cat: 13300 . COSPAR: 1982-065A. Apogee: 302 km (187 mi). Perigee: 295 km (183 mi). Inclination: 28.50 deg. Period: 90.30 min.

  Manned two crew. Fourth space shuttle test flight. Payloads: Induced Environment Contamination Monitor (IECM), Monodisperse Latex Reactor (MLR), Continuous Flow Electrophoresis System (CFES), Development Flight Instrumentation (DFl), Orbiter Experiments (OEX), first NASA getaway special (GAS), Night/Day Optical Survey of Lightning (NOSL) experiment, Vapor Phase Compression (VPC) freezer heat exchanger dynamics for freezing samples, Aerodynamic Coefficient Identification Package (AClP) experiment.

• DFI - . Payload: DFI PLT. Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: DFI. Decay Date: 1982-07-04 . USAF Sat Cat: 13300 . COSPAR: 1982-065xx. Apogee: 319 km (198 mi). Perigee: 306 km (190 mi). Inclination: 28.50 deg. Period: 90.80 min.

• DoD 82-1 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: DoD 82-1. Decay Date: 1982-07-04 . USAF Sat Cat: 13300 . COSPAR: 1982-065xx. Apogee: 319 km (198 mi). Perigee: 306 km (190 mi). Inclination: 28.50 deg. Period: 90.80 min. Cirris cryogenic infrared radiance instrument to obtain spectra of rocket and aircraft target exhausts. Lens cap failed to deploy..

• STS-5 - . Call Sign: Columbia. Crew: Allen, Brand, Lenoir, Overmyer. Payload: Columbia F05 / SBS 3 [PAM-D] / Anik C3 [PAM-D]. Mass: 14,551 kg (32,079 lb). Nation: USA. Related Persons: Allen, Brand, Lenoir, Overmyer. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-5. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Duration: 5.09 days. Decay Date: 1982-11-16 . USAF Sat Cat: 13650 . COSPAR: 1982-110A. Apogee: 317 km (196 mi). Perigee: 294 km (182 mi). Inclination: 28.50 deg. Period: 90.50 min.

  Manned four crew. First mission to deploy commercial communications satellites (SBS 3, Anik C3). Payloads: : Satellite Business Systems (SBS)-C with Payload Assist ; (PAM)-D; Telesat-E (Canadian communications satellite) with PAM-D. Monodisperse Latex Reactor (MLR), Continuous Flow Electrophoresis System (CFES), three getaway specials (GAS), Student experiments, GLOW experiment, Vestibular experiment, Oxygen Interaction With Materials experiment.

• Anik C3 (Telesat 6) - . Payload: Anik C3 [PAM-D]. Mass: 632 kg (1,393 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1997-06-17 . USAF Sat Cat: 13652 . COSPAR: 1982-110C. Apogee: 35,902 km (22,308 mi). Perigee: 35,871 km (22,289 mi). Inclination: 7.90 deg. Period: 1,441.20 min.

  Deployed from STS-5 11 November 1982. Telecommunications, operated by Telesat Canada. Transmit power 11.2 W per frequency at input of transmit antenna (typical saturated carrier). Anik C-3 Transmit frequency (MHz): 11730, 11743, 11791, 11804, 11852 , 11865, 11913, 11926, 11974, 11987, 12035, 12048, 12096, 12109 , 12157, 12170. Positioned in geosynchronous orbit at 117.5 deg W in 1982-1989; 115 deg W in 1989-1997 As of 5 September 2001 located at 15.95 deg E drifting at 1.305 deg W per day. As of 2007 Mar 10 located at 114.85W drifting at 1.353W degrees per day.

• SBS 3 - . Payload: SBS 3 [PAM-D]. Mass: 1,117 kg (2,462 lb). Nation: USA. Agency: SBS. Program: SBS. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1995-06-01 . USAF Sat Cat: 13651 . COSPAR: 1982-110B. Apogee: 35,910 km (22,310 mi). Perigee: 35,855 km (22,279 mi). Inclination: 7.80 deg. Period: 1,441.00 min.

  Deployed from STS-5 11 November 1982. Positioned in geosynchronous orbit at 94 deg W in 1982-1983; 95 deg W in 1983-1993; 74 deg W in 1994-1995 As of 4 September 2001 located at 41.59 deg E drifting at 1.235 deg W per day. As of 2007 Mar 11 located at 117.46E drifting at 1.221W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• DFI - . Payload: DFI PLT. Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: DFI. Decay Date: 1982-11-16 . USAF Sat Cat: 13650 . COSPAR: 1982-110xx. Apogee: 287 km (178 mi). Perigee: 277 km (172 mi). Inclination: 28.50 deg. Period: 90.20 min.

• STS-6 - . Call Sign: Challenger. Crew: Bobko, Musgrave, Peterson, Weitz. Payload: Challenger F01 / TDRS 1 [IUS]. Mass: 21,305 kg (46,969 lb). Nation: USA. Related Persons: Bobko, Musgrave, Peterson, Weitz. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-6. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 5.02 days. Decay Date: 1983-04-09 . USAF Sat Cat: 13968 . COSPAR: 1983-026A. Apogee: 295 km (183 mi). Perigee: 288 km (178 mi). Inclination: 28.50 deg. Period: 90.40 min.

  Manned four crew. First flight of space shuttle Challenger; deployed TDRSS. Payloads: Deployment of Tracking and Data Relay Satellite (TDRS)-A with Inertial Upper Stage (lUS)-2, Continuous Flow Electrophoresis System (CFES), Monodisperse Latex Reactor (MLR), Night/Day Optical Survey of Lightning (NOSL) experiment, three getaway specials (GAS).

• TDRS 1 - . Payload: TDRS A. Mass: 2,268 kg (5,000 lb). Nation: USA. Agency: NASA Greenbelt. Program: STS. Class: Communications. Type: Civilian communications satellite. Spacecraft: TDRS. USAF Sat Cat: 13969 . COSPAR: 1983-026B. Apogee: 35,976 km (22,354 mi). Perigee: 35,835 km (22,266 mi). Inclination: 7.40 deg. Period: 1,442.20 min.

  Element of satellite communications network, deployed from STS-6 5 April 1983. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 67 deg W in 1983; 41 deg W in 1983-1989; 79 deg W in 1989-1990; 170 deg W in 1990-1993; 85 deg E in 1994-1995; 49 deg W in 1996-on. As of 5 September 2001 located at 49.36 deg W drifting at 0.010 deg E per day. As of 2007 Mar 9 located at 48.98W drifting at 0.029W degrees per day.

• EVA STS-6-1 - . Crew: Musgrave, Peterson. EVA Duration: 0.17 days. Nation: USA. Related Persons: Musgrave, Peterson. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-6. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Tested EMU Manoeuvring Unit. Tested EVA emergency procedures..

• STS-7 - . Call Sign: Challenger. Crew: Crippen, Fabian, Hauck, Ride, Thagard. Payload: Challenger F02 / OSTA-2. Mass: 16,839 kg (37,123 lb). Nation: USA. Related Persons: Crippen, Fabian, Hauck, Ride, Thagard. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-7. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 6.10 days. Decay Date: 1983-06-24 . USAF Sat Cat: 14132 . COSPAR: 1983-059A. Apogee: 307 km (190 mi). Perigee: 299 km (185 mi). Inclination: 28.30 deg. Period: 90.60 min.

  Manned five crew. Deployed Anik C2, Palapa B1; deployed and retrieved SPAS platform. Payloads: Office of Space and Terrestrial Applications (OSTA)-2 experiments, deployment of PALAPA-B1 communications satellite for Indonesia with Payload Assist Module (PAM)-D and Telesat-F communications satellite for Canada with PAM-D, German Shuttle Pallet Satellite (SPAS)-01, seven getaway specials (GAS), Monodisperse Latex Reactor (MLR), Continuous Flow Electrophoresis System (CFES).

• Anik C2 (Telesat 7) - . Payload: Anik C2 [PAM-D]. Mass: 1,238 kg (2,729 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1998-01-07 . USAF Sat Cat: 14133 . COSPAR: 1983-059B. Apogee: 36,273 km (22,538 mi). Perigee: 35,949 km (22,337 mi). Inclination: 7.80 deg. Period: 1,452.70 min.

  Deployed by STS-7 6/19/83. Telecommunications. Operating entity TELESAT Canada. Longitude 110 W. Transmit power 11.2 W on each frequency. Frequencies 11730, 11743, 11791, 11804, 11852, 11865, 11913, 11926, 11974, 11987, 12035, 12048, 12096, 12109, 12157, 12170 MHz. Positioned in geosynchronous orbit at 112 deg W in 1983; 105 deg W in 1983-1985; 110 deg W in 1985-1991; 109 deg W in 1991-1993;76 deg W in 1993-1997; 115 deg W in 1997-1998 As of 4 September 2001 located at 113.76 deg E drifting at 4.144 deg W per day. As of 2007 Mar 10 located at 68.60E drifting at 4.154W degrees per day.

• OSTA-2 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1983-06-24 . USAF Sat Cat: 14132 . COSPAR: 1983-059xx. Apogee: 295 km (183 mi). Perigee: 289 km (179 mi). Inclination: 28.50 deg. Period: 90.40 min.

• Palapa B1 - . Payload: Palapa B1 [PAM-D. Mass: 1,200 kg (2,600 lb). Nation: Indonesia. Agency: Perumtel. Program: Palapa. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1995-10-01 . USAF Sat Cat: 14134 . COSPAR: 1983-059C. Apogee: 35,840 km (22,260 mi). Perigee: 35,803 km (22,246 mi). Inclination: 8.60 deg. Period: 1,437.90 min.

  Deployed by STS-7 6/18/83. Palapa B satellites were four times as powerful and twice the size of their predecessors, the Palapa A series. While the A series was designed for domestic/regional communications within Indonesia, the new system also served the Philippines, Thailand, Malaysia and Singapore. Palapa B2 was originally placed into a useless orbit due to malfunctions of its PAM-D upper stage. The Indonesian government claimed $75 million insurance and ordered a replacement (B2P), which was successfully orbited 3 years later. The original B2 was recovered by the STS-51A mission on November 12, 1984 under an arrangement between the satellite's insurers, NASA and Hughes. The satellite was then sold by the insurers to an intermediary company, refurbished, and then resold back to Indonesia following its launch in 1990. Spacecraft: Based on Hughes HS-376 design. Cylindrical structure. Spin stabilised. Hydrazine propulsion system for attitude control, orbit maintenance. Body mounted solar cells provide 1060 W BOL. Despun antenna platform. Payload: Each carried 24 C-band transponders (+6 spares). Positioned in geosynchronous orbit at 108 deg E in 1983-1990; 118 deg E in 1990-1992; 134 deg E in 1992-1995 As of 1 September 2001 located at 156.84 deg E drifting at 0.192 deg W per day. As of 2007 Mar 11 located at 169.93W drifting at 0.283W degrees per day.

• SPAS-01 - . Payload: Challenger F2 / SPAS 1. Mass: 3,230 kg (7,120 lb). Nation: USA. Agency: MBB. Class: Military. Type: Strategic defense satellite. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SPAS. Decay Date: 1983-06-22 . USAF Sat Cat: 14142 . COSPAR: 1983-059F. Apogee: 300 km (180 mi). Perigee: 295 km (183 mi). Inclination: 28.50 deg. Period: 90.50 min.

  Ten experiments mounted on Shuttle Pallet Satellite (SPAS-01) performed research in forming metal alloys in microgravity and use of remote sensing scanner. Orbiter's small control rockets fired while SPAS-01 held by remote manipulator system to test movement on extended arm.

• STS-8 - . Call Sign: Challenger. Crew: Bluford, Brandenstein, Gardner, Thornton, Bill, Truly. Payload: Challenger F03 / PFTA. Mass: 13,642 kg (30,075 lb). Nation: USA. Related Persons: Bluford, Brandenstein, Gardner, Thornton, Bill, Truly. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-8. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 6.05 days. Decay Date: 1983-09-05 . USAF Sat Cat: 14312 . COSPAR: 1983-089A. Apogee: 313 km (194 mi). Perigee: 306 km (190 mi). Inclination: 28.50 deg. Period: 90.70 min.

  First night launch and night landing. Deployed Insat 1B. Payloads: Deployment of INSAT (lndia communica-tion satellite) with Payload Assist Module (PAM)-D, Payload Flight Test Article (PFTA)/ Payload Deployment Retrieval System (PDRS), Continuous Flow Electrophoresis (CFES), biomedical experiments. 250,000 express mail envelopes with special cachet for U.S. Postal Service were carried for a first-day cover.

• DFI/USPS - . Payload: DFI PLT. Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: DFI. Decay Date: 1983-09-05 . USAF Sat Cat: 14312 . COSPAR: 1983-089xx. Apogee: 223 km (138 mi). Perigee: 216 km (134 mi). Inclination: 28.50 deg. Period: 88.90 min.

• PFTA - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: PFTA. Decay Date: 1983-09-05 . USAF Sat Cat: 14312 . COSPAR: 1983-089xx. Apogee: 223 km (138 mi). Perigee: 216 km (134 mi). Inclination: 28.50 deg. Period: 88.90 min.

• Insat 1B - . Mass: 1,152 kg (2,539 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Insat 1. Completed Operations Date: 1993-08-03 . USAF Sat Cat: 14318 . COSPAR: 1983-089B. Apogee: 35,824 km (22,259 mi). Perigee: 35,811 km (22,251 mi). Inclination: 3.60 deg. Period: 1,437.70 min.

  Released from STS 8 8/31/83; also carried transponders for domestic communications. Operational multipurpose satellite for telecommunications, meteorological imaging and data relay, radio and television programme distribution and direct television broadcasting for community reception. Geostationary longitude 74.0 +/ - 0.1 deg E. Deployment from US Space Transportation System flight no 8, orbiter Challenger, on 31 Aug 1983. Positioned in geosynchronous orbit at 74 deg E in 1983-1992; 93 deg E in 1992-1993 As of 26 August 2001 located at 125.27 deg E drifting at 0.152 deg E per day. As of 2007 Mar 10 located at 80.35E drifting at 0.392E degrees per day.

• STS-9 - . Call Sign: Columbia. Crew: Garriott, Lichtenberg, Merbold, Parker, Shaw, Young. Payload: Columbia F06 / Spacelab 1 Pallet. Mass: 15,088 kg (33,263 lb). Nation: USA. Related Persons: Garriott, Lichtenberg, Merbold, Parker, Shaw, Young. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-9. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Duration: 10.32 days. Decay Date: 1983-12-08 . USAF Sat Cat: 14523 . COSPAR: 1983-116A. Apogee: 254 km (157 mi). Perigee: 241 km (149 mi). Inclination: 57.00 deg. Period: 89.50 min.

  Carried ESA Spacelab. Payloads: Payload: Spacelab-1 experiments, habitable Spacelab and pallet, carried 71 experiments. The six-man crew was divided into two 12-hour-day red and blue teams to operate experiments. First high-inclination orbit of 57 degrees.

• Spacelab 1 Pallet - . Payload: SL 1 PLT. Nation: USA. Agency: NASA. Program: Spacelab. Class: Manned. Type: Manned space laboratory. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1983-12-08 . USAF Sat Cat: 14523 . COSPAR: 1983-116xx. Apogee: 239 km (148 mi). Perigee: 231 km (143 mi). Inclination: 57.00 deg. Period: 89.20 min.

• Spacelab 1 - . Payload: SL 1 LM. Nation: USA. Agency: NASA. Program: Spacelab. Class: Manned. Type: Manned space laboratory. Spacecraft: Spacelab. Decay Date: 1983-12-08 . USAF Sat Cat: 14523 . COSPAR: 1983-116xx. Apogee: 239 km (148 mi). Perigee: 231 km (143 mi). Inclination: 57.00 deg. Period: 89.20 min.

• Shuttle Columbia overhauled at Palmdale. - . Nation: USA. Program: STS. Spacecraft Bus: Shuttle. Spacecraft: Columbia.

  The ejection seats and flight instrumentation used for the first manned shuttle flights were removed. Head-up display and GPS avionics were installed. Orbiter 5.4 structural modifications were made; the disconnect valves, thermal protection system, and brakes were brought up to date. Provisions were made for use of the Manned Maneuvering Unit and 231 Master Change Requests were implemented.

• STS-41-B - . Call Sign: Challenger. Crew: Brand, Gibson, McCandless, McNair, Stewart. Payload: Challenger F04 / SPAS 1A. Mass: 15,362 kg (33,867 lb). Nation: USA. Related Persons: Brand, Gibson, McCandless, McNair, Stewart. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-41-B. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 7.97 days. Decay Date: 1984-02-11 . USAF Sat Cat: 14681 . COSPAR: 1984-011A. Apogee: 316 km (196 mi). Perigee: 307 km (190 mi). Inclination: 28.50 deg. Period: 90.80 min.

  Manned five crew. Deployed Westar 6, Palapa B2; tested Manned Maneuvering Unit (MMU). Payloads: PALAPA-B2 (Indonesian communications satellite) with Payload Assist Module (PAM)-D and WESTAR (Western Union communications satellite)-Vl with PAM-D. Both satellites were deployed but the PAM-D in each satellite failed to ignite, leaving both satellites in earth orbit. Both satellites were retrieved and returned to earth for renovation on the STS-51-A mission. The manned maneuvering unit (MMU) was tested with extravehicular astronauts as free flyers without tethers as far as 98 m from the orbiter. Shuttle Pallet Satellite (SPAS)-01 experiments, Monodisperse Latex Reactor (MLR), Isoelectric Focusing Experiment (lEF), Acoustic Containerless Experiment System (ACES), Cinema 360 cameras, five getaway specials (GAS), Aerodynamic Coefficient Identification (ACIP)/High Resolution Accelerom-eter Package (HIRAP).

• Palapa B2 - . Payload: Palapa B2 [PAM-D]. Mass: 1,200 kg (2,600 lb). Nation: Indonesia. Agency: Perumtel. Program: Palapa. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Decay Date: 1984-11-16 . USAF Sat Cat: 14692 . COSPAR: 1984-011D. Apogee: 1,190 km (730 mi). Perigee: 280 km (170 mi). Inclination: 28.20 deg. Period: 99.50 min. Deployed from STS 41B 4 February 1984; failed to reach proper orbit; recovered by STS-51A..

• SPAS 1A - . Mass: 3,230 kg (7,120 lb). Nation: USA. Agency: NASA. Class: Military. Type: Strategic defense satellite. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SPAS. Decay Date: 1984-02-11 . USAF Sat Cat: 14681 . COSPAR: 1984-011xx. Apogee: 294 km (182 mi). Perigee: 270 km (160 mi). Inclination: 28.60 deg. Period: 90.20 min. German-built Shuttle Pallet Satellite (SPAS), first flown on STS-7, became first satellite refurbished and flown again. SPAS remained in payload bay due to electrical problem with Remote Manipulator System (RMS)..

• MMU 2 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft: Shuttle MMU. COSPAR: 1984-011xx.

• MMU 3 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft: Shuttle MMU. COSPAR: 1984-011xx.

• Westar 6 - . Payload: Westar 6 [PAM-D]. Mass: 1,200 kg (2,600 lb). Nation: USA. Agency: WUTC. Program: Westar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Decay Date: 1984-11-16 . USAF Sat Cat: 14688 . COSPAR: 1984-011B. Apogee: 1,220 km (750 mi). Perigee: 307 km (190 mi). Inclination: 27.70 deg. Period: 100.10 min.

  Deployed from STS 41B 4 February 1984; failed to reach proper orbit; recovered by STS-51A. The Westar series of geostationary spacecraft provide commercial communications services for Western Union. Westar 6 failed to achieve geosynchronous orbit after being deployed from the Space Shuttle. It was later retrieved by another Shuttle mission (November 14, 1984) and returned for refurbishment and relaunch. All Westars have been launched by NASA on a reimbursable basis. Spacecraft: Westar uses the Hughes HS-376 spacecraft design. Spin stabilised with a despun antenna section. Body mounted solar cells. Once on orbit, an outer cylinder deploys downward in 'dixie-cup' fashion to increase the solar panel area. Payload: Westar spacecraft typically carried 12 to 24 transponders in the 4-6 GHz range. A single antenna reflector (72 inch diameter) is used with an array of offset feed horns. The reflector uses two polarisation-selective surfaces for horizontal and vertical polarised signals.

• IRT - . Payload: Challenger F4 / Westar 6 [PAM-D] / Palapa B2 [PAM-. Mass: 91 kg (200 lb). Nation: USA. Agency: NASA Houston. Class: Technology. Type: Navigation technology satellite. Spacecraft: IRT. Decay Date: 1984-02-11 . USAF Sat Cat: 14689 . COSPAR: 1984-011C. Apogee: 288 km (178 mi). Perigee: 279 km (173 mi). Inclination: 28.50 deg. Period: 90.20 min. Deployed from STS 41B on 5 February 1984; Integrated Rendezvous Target..

• EVA STS-10-1 - . Crew: McCandless, Stewart. EVA Duration: 0.23 days. Nation: USA. Related Persons: McCandless, Stewart. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-10. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Tested MMU manoeuvring unit in free flight..

• EVA STS-10-2 - . Crew: McCandless, Stewart. EVA Duration: 0.25 days. Nation: USA. Related Persons: McCandless, Stewart. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-10. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Tested MMU manoeuvring unit in free flight..

• STS-41-C - . Call Sign: Challenger. Crew: Crippen, Hart, Nelson, Scobee, van Hoften. Payload: Challenger F05 / LDEF 1 / MMU 3. Mass: 17,357 kg (38,265 lb). Nation: USA. Related Persons: Crippen, Hart, Nelson, Scobee, van Hoften. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-41-C. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 6.99 days. Decay Date: 1984-04-13 . USAF Sat Cat: 14897 . COSPAR: 1984-034A. Apogee: 468 km (290 mi). Perigee: 222 km (137 mi). Inclination: 28.50 deg. Period: 91.40 min.

  Manned five crew. First repair on orbit of a satellite, Solar Maximum Mission, by James van Hoften and George Nelson. Deployed LDEF. Payloads:Solar Maximum Mission (SMM) repair, manned maneuvering unit (MMU) satellite support, deployment of Long-Duration Exposure Facility (LDEF) in earth orbit free drift. LDEF contained 57 experiments and weighed about 10,000 kg. Cinema 360 and IMAX 70-mm cameras.

• MMU 2 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft: Shuttle MMU. Decay Date: 1984-04-13 . USAF Sat Cat: 14897 . COSPAR: 1984-034xx. Apogee: 496 km (308 mi). Perigee: 494 km (306 mi). Inclination: 28.50 deg. Period: 94.50 min.

• LDEF - . Payload: Challenger F5 / LDEF 1. Mass: 3,625 kg (7,991 lb). Nation: USA. Agency: NASA Langley. Class: Earth. Type: Micrometeoroid satellite. Spacecraft: LDEF. Decay Date: 1990-01-20 . USAF Sat Cat: 14898 . COSPAR: 1984-034B. Apogee: 348 km (216 mi). Perigee: 344 km (213 mi). Inclination: 28.50 deg. Period: 91.50 min. Long Duration Exposure Facility; deployed from STS 41C 7 April 1984; retrieved by STS-32 20 January 1990. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

• SMRM-FSS - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: FSS. Decay Date: 1984-04-13 . USAF Sat Cat: 14897 . COSPAR: 1984-034xx. Apogee: 496 km (308 mi). Perigee: 494 km (306 mi). Inclination: 28.50 deg. Period: 94.50 min.

• MMU 3 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft: Shuttle MMU. Decay Date: 1984-04-13 . USAF Sat Cat: 14897 . COSPAR: 1984-034xx. Apogee: 496 km (308 mi). Perigee: 494 km (306 mi). Inclination: 28.50 deg. Period: 94.50 min.

• EVA STS-41-C-1 - . Crew: Nelson, van Hoften. EVA Duration: 0.12 days. Nation: USA. Related Persons: Nelson, van Hoften. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-41-C. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Attempted capture of Solar Max satellite..

• EVA STS-41-C-2 - . Crew: Nelson, van Hoften. EVA Duration: 0.30 days. Nation: USA. Related Persons: Nelson, van Hoften. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-41-C. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Successfully captured and repaired Solar Max satellite..

• Shuttle Discovery Pad Abort - . Nation: USA. Program: STS. Flight: STS-41-D. Spacecraft Bus: Shuttle. Spacecraft: Discovery. The countdown for the second launch attempt for Discovery's maiden flight ended at T- 4 seconds when the orbiter's computers detected a sluggish valve in main engine #3. The main engine was replaced and Discovery was finally launched on August 30, 1984..

• STS-41-E (cancelled) - . Crew: Buchli, Detroye, Mattingly, Onizuka, Shriver. Backup Crew: Sundberg. Support Crew: Watterson. Payload: DoD Mission. Nation: USA. Program: STS. Flight: STS-41-E. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Planned Department of Defense shuttle mission. Cancelled due to IUS failure..

• STS-41-F (cancelled) - . Crew: Bobko, Griggs, Hoffman, Seddon, Williams, Donald. Payload: Communications satellites. Nation: USA. Related Persons: Bobko, Griggs, Hoffman, Seddon, Williams, Donald. Program: STS. Flight: STS-41-F. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Planned shuttle mission for deployment of commercial communications satellites. Cancelled due to payload delays..

• STS-41-D - . Call Sign: Discovery. Crew: Coats, Hartsfield, Hawley, Mullane, Resnik, Walker. Payload: Discovery F01 / SBS 4[PAM-D] / Telstar 302[PAM-D]. Mass: 21,552 kg (47,514 lb). Nation: USA. Related Persons: Coats, Hartsfield, Hawley, Mullane, Resnik, Walker. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-41-D. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Duration: 6.04 days. Decay Date: 1984-09-05 . USAF Sat Cat: 15234 . COSPAR: 1984-093A. Apogee: 307 km (190 mi). Perigee: 300 km (180 mi). Inclination: 28.50 deg. Period: 90.60 min.

  Manned six crew. First flight of space shuttle Discovery; deployed SBS 4, Leasat 1, Telstar 3C. Payloads: Satellite Business System (SBS)-D commu-nications satellite with Payload Assist Module (PAM)-D deployment, Syncom IV-2 communica-tions satellite with its unique stage deployment, Telstar (American Telephone and Telegraph) 3-C with PAM-D deployment, Office of Aeronautics and Space Technology (OAST)-1 experiments. Deployment and restowing of large solar array. Continuous Flow Electrophoresis (CFES). IMAX camera.

• Telstar 3C - . Payload: Telstar 302 [PAM-D]. Mass: 625 kg (1,377 lb). Nation: USA. Agency: ATT. Program: Telstar series. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1997-09-05 . USAF Sat Cat: 15237 . COSPAR: 1984-093D. Apogee: 35,948 km (22,337 mi). Perigee: 35,901 km (22,307 mi). Inclination: 5.70 deg. Period: 1,443.20 min.

  Released from STS 41D 9/1/84; stationed at 125 deg W. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 86 deg W in 1984-1987; 85 deg W in 1987-1997; 97 deg W in 1997 As of 26 August 2001 located at 148.40 deg W drifting at 1.778 deg W per day. As of 2007 Mar 10 located at 128.46W drifting at 1.794W degrees per day.

• Syncom IV-2 - . Payload: Discovery F1 / SBS 4 [PAM-D] / Telstar 302 [PAM-D]. Mass: 1,315 kg (2,899 lb). Nation: USA. Agency: HCI. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 381. Completed Operations Date: 1996-10-10 . USAF Sat Cat: 15236 . COSPAR: 1984-093C. Apogee: 36,741 km (22,829 mi). Perigee: 36,448 km (22,647 mi). Inclination: 13.00 deg. Period: 1,477.60 min.

  Released from STS 41D 8/31/84; 105 deg W; leased to U.S. government. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 105 deg W in 1984-1987; 177 deg W in 1987; 72 deg E in 1988-1990; 177 deg W in 1990-1996 As of 1 September 2001 located at 17.02 deg W drifting at 10.139 deg W per day. As of 2007 Mar 10 located at 57.99E drifting at 10.147W degrees per day.

• OAST 1 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: OAST. Decay Date: 1984-09-05 . USAF Sat Cat: 15234 . COSPAR: 1984-093xx. Apogee: 297 km (184 mi). Perigee: 294 km (182 mi). Inclination: 28.50 deg. Period: 90.40 min.

• SBS 4 - . Payload: SBS D / PAM-D. Mass: 1,117 kg (2,462 lb). Nation: USA. Agency: SBS. Program: SBS. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 15235 . COSPAR: 1984-093B. Apogee: 35,795 km (22,241 mi). Perigee: 35,780 km (22,230 mi). Inclination: 6.80 deg. Period: 1,436.20 min.

  Released from STS 41D 8/31/84; 101 deg W. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 101 deg W in 1984-1985; 91 deg W in 1985-1993; 77 deg W in 1993-on. As of 1 September 2001 located at 77.06 deg W drifting at 0.019 deg W per day. As of 2007 Mar 9 located at 113.88W drifting at 5.445W degrees per day.

• STS-41-G - . Call Sign: Challenger. Crew: Crippen, Garneau, Leestma, McBride, Ride, Scully-Power, Sullivan. Payload: Challenger F06 / ERBS / LFC / ORS. Mass: 10,643 kg (23,463 lb). Nation: USA. Related Persons: Crippen, Garneau, Leestma, McBride, Ride, Scully-Power, Sullivan. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-41-G. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 8.22 days. Decay Date: 1984-10-13 . USAF Sat Cat: 15353 . COSPAR: 1984-108A. Apogee: 390 km (240 mi). Perigee: 350 km (210 mi). Inclination: 51.70 deg. Period: 92.00 min.

  Manned seven crew. Deployed ERBS; performed high resolution Earth imagery. Payloads: Earth Radiation Budget Satellite (ERBS) deployment, Office of Space and Terrestrial Applications (OSTA)-3 experiments, Large Format Camera (LFC). First use of Orbital Refueling System (ORS) with extravehicular activity (EVA) astronauts, IMAX camera.

• LFC/ORS - . Payload: MPESS. Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: LFC/ORS. Decay Date: 1984-10-13 . USAF Sat Cat: 15353 . COSPAR: 1984-108xx. Apogee: 227 km (141 mi). Perigee: 214 km (132 mi). Inclination: 57.00 deg. Period: 88.90 min. Larger Format Camera/ Orbital Refueling System payload carried in shuttle bay..

• OSTA-3 - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1984-10-13 . USAF Sat Cat: 15353 . COSPAR: 1984-108xx. Apogee: 227 km (141 mi). Perigee: 214 km (132 mi). Inclination: 57.00 deg. Period: 88.90 min.

• ERBS - . Payload: Challenger F6 / ERBS. Mass: 226 kg (498 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ERBS. USAF Sat Cat: 15354 . COSPAR: 1984-108B. Apogee: 589 km (365 mi). Perigee: 576 km (357 mi). Inclination: 57.00 deg. Period: 96.30 min. Earth Radiation Budget Satellite. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

• EVA STS-41-G-1 - . Crew: Leestma, Sullivan. EVA Duration: 0.15 days. Nation: USA. Related Persons: Leestma, Sullivan. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-41-G. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Simulated refuelling of satellite..

• STS-51-A - . Call Sign: Discovery. Crew: Allen, Fisher, Gardner, Hauck, Walker, Dave. Payload: Discovery F02 / PLT. Mass: 20,550 kg (45,300 lb). Nation: USA. Related Persons: Allen, Fisher, Gardner, Hauck, Walker, Dave. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-A. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Duration: 7.99 days. Decay Date: 1984-11-16 . USAF Sat Cat: 15382 . COSPAR: 1984-113A. Apogee: 297 km (184 mi). Perigee: 289 km (179 mi). Inclination: 28.40 deg. Period: 90.40 min.

  Manned five crew. First retrieval of two satellites (PALAPA B-2 and WESTAR Vl) for return to earth. Deployed Anik D2, Leasat 2; recovered Westar 6, Palapa B2. Payloads: Telesat (Canada communications satellite)-H with Payload Assist Module (PAM)-D deploy-ment, Syncom IV-1 communications satellite deployment with its unique stage, retrieval of PALAPA B-2 and WESTAR VI communications satellites with PAM-D which failed to ignite on the STS-41-B mission. Manned maneuvering unit (MMU) used for retrieval. Diffusive Mixing of Organic Solutions (DMOS) experiment.

• Syncom IV-1 - . Payload: Discovery F2 / Anik D2 / Syncom-4 1. Mass: 1,315 kg (2,899 lb). Nation: USA. Agency: HCI. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 381. Completed Operations Date: 1992-09-26 . USAF Sat Cat: 15384 . COSPAR: 1984-113C. Apogee: 36,403 km (22,619 mi). Perigee: 36,152 km (22,463 mi). Inclination: 7.60 deg. Period: 1,461.20 min.

  Released from STS 51A 10 November 1984; 105 deg W; leased to U.S. government. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 15 deg W in 1984-1992 As of 3 September 2001 located at 170.37 deg W drifting at 6.220 deg W per day. As of 2007 Mar 10 located at 100.08W drifting at 6.233W degrees per day.

• Anik D2 - . Payload: Anik D2 [PAM-D]. Mass: 1,100 kg (2,400 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1995-02-10 . USAF Sat Cat: 15383 . COSPAR: 1984-113B. Apogee: 36,271 km (22,537 mi). Perigee: 36,076 km (22,416 mi). Inclination: 6.70 deg. Period: 1,455.90 min.

  Released 9 November 1984 from STS 51A; 82 deg W. Telecommunications. Longitude 111.5 deg W. Operating entity Telesat Canada. Transmitter power 8.9 watts at each frequency. Frequencies 3720 to 4180 MHz spaced by 20 MHz. Positioned in geosynchronous orbit at 111 deg W in 1984-1986; 110 deg W in 1986-1991; 82 deg W in 1991-1993; 20 deg E in 1993-1995 As of 28 August 2001 located at 178.69 deg W drifting at 4.912 deg W per day. As of 2007 Mar 10 located at 25.98W drifting at 4.913W degrees per day.

• EVA STS-51-A-1 - . Crew: Allen, Gardner. EVA Duration: 0.26 days. Nation: USA. Related Persons: Allen, Gardner. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-A. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Retrieved Palapa satellite..

• EVA STS-51-A-2 - . Crew: Allen, Gardner. EVA Duration: 0.25 days. Nation: USA. Related Persons: Allen, Gardner. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-A. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Retrieved Westar satellite..

• The Space Shuttle orbiter Enterprise arrives - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft Bus: Shuttle. Spacecraft: Enterprise. The Space Shuttle orbiter Enterprise arrived at Vandenberg AFB for a series of facility verification tests..

• STS-51-C - . Call Sign: Discovery. Crew: Buchli, Mattingly, Onizuka, Payton, Shriver. Payload: Discovery F03 / Magnum 1 [IUS]. Mass: 116,884 kg (257,685 lb). Nation: USA. Related Persons: Buchli, Mattingly, Onizuka, Payton, Shriver. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-C. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Duration: 3.06 days. Decay Date: 1985-01-27 . USAF Sat Cat: 15496 . COSPAR: 1985-010A. Apogee: 341 km (211 mi). Perigee: 332 km (206 mi). Inclination: 28.40 deg. Period: 91.30 min.

  Manned five crew. Deployed USA 8 (Aquacade ELINT spacecraft). Orbits of Earth: 48. Landed at: Runway 15 at Kennedy Space Center, Florida. Landing Speed: 342 kph. Touchdown miss distance: 839.00 m. Landing Rollout: 2,240.00 m. Payloads: Department of Defence classified payloads.

• USA 8 - . Payload: Orion 1. Mass: 2,500 kg (5,500 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Magnum. USAF Sat Cat: 15543 . COSPAR: 1985-010B. Apogee: 35,800 km (22,200 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.00 deg. Period: 1,440.00 min. New Magnum model geostationary ELINT satellite model replaced earlier Rhyolite/Aquacade. Deployed from STS-51C 24 January 1985. Boosted to geostationary orbit. As of 2003 Apr 30 located at 69.16E drifting at 0.038W degrees per day..

• STS-51-E (cancelled) - . Crew: Baudry, Bobko, Garn, Griggs, Hoffman, Seddon, Williams, Donald. Payload: TDRS/IUS. Nation: USA. Related Persons: Baudry, Bobko, Garn, Griggs, Hoffman, Seddon, Williams, Donald. Program: STS. Flight: STS-51-E. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Planned TDRS/IUS deployment shuttle mission. Cancelled due to IUS failure..

• STS-51-AA (cancelled) - . Crew: Creighton, Fabian, Jarvis, Lucid, Nagel, Walker. Backup Crew: Konrad. Nation: USA. Program: STS. Flight: STS-51-AA. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Planned shuttle mission. Cancelled due to payload delays..

• STS-51-D - . Call Sign: Discovery. Crew: Bobko, Garn, Griggs, Hoffman, Seddon, Walker, Williams, Donald. Payload: Discovery F04 / Anik C1[PAM-D] / Syncom-4 3 /Orbus. Mass: 16,249 kg (35,822 lb). Nation: USA. Related Persons: Bobko, Garn, Griggs, Hoffman, Seddon, Walker, Williams, Donald. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-D. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Duration: 7.00 days. Decay Date: 1985-04-19 . USAF Sat Cat: 15641 . COSPAR: 1985-028A. Apogee: 535 km (332 mi). Perigee: 445 km (276 mi). Inclination: 28.50 deg. Period: 94.40 min.

  Manned seven crew. Payloads: Telesat (Canada communications satellite)-I with Payload Assist Module (PAM)-D deployment, Syncom IV-3 communications satellite deploy-ment with its unique stage (unique stage failed to ignite), Continuous Flow Electrophoresis (CFES), Phase Partitioning Experiment (PPE), student experiments, two getaway specials (GAS) Informal science studies (Toys in Space).

• Syncom IV-3 - . Payload: Discovery F4 / Anik C1 [PAM-D] / Syncom-4 3 [Orbus. Mass: 1,315 kg (2,899 lb). Nation: USA. Agency: HCI. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 381. Completed Operations Date: 1996-09-30 . USAF Sat Cat: 15643 . COSPAR: 1985-028C. Apogee: 37,080 km (23,040 mi). Perigee: 36,401 km (22,618 mi). Inclination: 14.40 deg. Period: 1,485.10 min.

  Released by STS 51D 4/13/85; failed to orbit and subsequently repaired by STS 51-I on 8/31/85; 178 deg E; leased by U.S. government. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 175 deg W in 1985-1987; 105 deg W in 1987-1996 As of 31 August 2001 located at 106.85 deg E drifting at 11.920 deg W per day. As of 2007 Mar 10 located at 158.41W drifting at 11.917W degrees per day.

• Anik C1 - . Payload: Anik C1 [PAM-D]. Mass: 1,238 kg (2,729 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 2000-04-14 . USAF Sat Cat: 15642 . COSPAR: 1985-028B. Apogee: 35,792 km (22,240 mi). Perigee: 35,783 km (22,234 mi). Inclination: 0.00 deg. Period: 1,436.20 min.

  Released by STS 51D 4/13/85; 107.5 deg W. Telecommunications. Operating entity TELESAT Canada. Longitude 107.5 W. Transmit power 11.2 W on each frequency. Frequencies 11730, 11743, 11791, 11804, 11852, 11865, 11913, 11926, 11974, 11987, 12035, 12048, 12096, 12109, 12157, 121 70 MHz. Positioned in geosynchronous orbit at 107 deg W in 1985-1991; 109 deg W in 1991-1993; 72 deg W in 1993-1997; 118 deg W in 1997-1998; 106 deg W in 1998-1999 As of 5 September 2001 located at 63.20 deg W drifting at 0.009 deg W per day. As of 2007 Mar 2 located at 112.29E drifting at 2.201W degrees per day.

• EVA STS-51-D-1 - . Crew: Griggs, Hoffman. EVA Duration: 0.13 days. Nation: USA. Related Persons: Griggs, Hoffman. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-D. Spacecraft Bus: Shuttle. Spacecraft: Discovery. RMS 'Ryswatters' installed..

• STS-51-B - . Call Sign: Challenger. Crew: Gregory, Lind, Overmyer, Thagard, Thornton, Bill, van den Berg, Lodewijk, Wang. Payload: Challenger F07 / SL 3 MPESS. Mass: 14,245 kg (31,404 lb). Nation: USA. Related Persons: Gregory, Lind, Overmyer, Thagard, Thornton, Bill, van den Berg, Lodewijk, Wang. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-B. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 7.01 days. Decay Date: 1985-05-06 . USAF Sat Cat: 15665 . COSPAR: 1985-034A. Apogee: 353 km (219 mi). Perigee: 346 km (214 mi). Inclination: 57.00 deg. Period: 91.50 min.

  Manned seven crew. Deployed Nusat; carried Spacelab 3. Payloads: Spacelab-3 experiments, habitable Spacelab and mission peculiar experiment support structure. The experiments represented a total of five different disciplines: materials processing in space, environmental observa-tions, life science, astrophysics, and technology experiments. Two getaway specials (GAS). The flight crew was split into gold and silver shifts working 12-hour days during the flight.

• NUSAT-1 - . Payload: Challenger F7 / Nusat / GLOMR [1]. Mass: 52 kg (114 lb). Nation: USA. Agency: Weber. Class: Surveillance. Type: Radar calibration target. Spacecraft: NUSAT. Decay Date: 1986-12-15 . USAF Sat Cat: 15666 . COSPAR: 1985-034B. Apogee: 354 km (219 mi). Perigee: 345 km (214 mi). Inclination: 57.00 deg. Period: 91.50 min. Air traffic control radar calibration. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

• Spacelab 3 - . Payload: SL 3 LM. Nation: USA. Agency: NASA. Program: Spacelab. Class: Manned. Type: Manned space laboratory. Spacecraft: Spacelab. Decay Date: 1985-05-06 . USAF Sat Cat: 15665 . COSPAR: 1985-034xx. Apogee: 359 km (223 mi). Perigee: 346 km (214 mi). Inclination: 57.00 deg. Period: 91.60 min.

• SL 3 MPESS - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1985-05-06 . USAF Sat Cat: 15665 . COSPAR: 1985-034xx. Apogee: 359 km (223 mi). Perigee: 346 km (214 mi). Inclination: 57.00 deg. Period: 91.60 min.

• GLOMR - . Nation: USA. Agency: NASA. Program: STS. Spacecraft: GLOMR. Decay Date: 1985-05-06 . USAF Sat Cat: 15665 . COSPAR: 1985-034xx. Apogee: 359 km (223 mi). Perigee: 346 km (214 mi). Inclination: 57.00 deg. Period: 91.60 min.

• STS-51-G - . Call Sign: Discovery. Crew: Al-Saud, Baudry, Brandenstein, Creighton, Fabian, Lucid, Nagel. Payload: Discovery F05 / Morelos 1[PAM-D] / Telstar 303. Mass: 20,174 kg (44,476 lb). Nation: USA. Related Persons: Al-Saud, Baudry, Brandenstein, Creighton, Fabian, Lucid, Nagel. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-G. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Duration: 7.07 days. Decay Date: 1985-06-24 . USAF Sat Cat: 15823 . COSPAR: 1985-048A. Apogee: 369 km (229 mi). Perigee: 358 km (222 mi). Inclination: 28.50 deg. Period: 91.80 min.

  Deployed and retrieved Spartan 1; launched Morelos 1, Arabsat 1B, Telstar 3D.Payloads: Shuttle Pointed Autono-mous Research Tool for Astronomy (SPARTAN)-1; Automated Directional Solidification Furnace (ADSF); High Precision Tracking Experiment (HPTE); Orbiter Experiments (OEX); French Echocardiograph Experiment (FEE) and French Pocket Experiment (FPE).

• Telstar 3D - . Payload: Telstar 303 / PAM-D. Mass: 630 kg (1,380 lb). Nation: USA. Agency: ATT. Program: Telstar series. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1999-02-04 . USAF Sat Cat: 15826 . COSPAR: 1985-048D. Apogee: 35,911 km (22,314 mi). Perigee: 35,888 km (22,299 mi). Inclination: 5.40 deg. Period: 1,441.90 min.

  Released by STS 51G 19 June 1985; stationed at 76 deg W. Positioned in geosynchronous orbit at 125 deg W in 1985-1992; 123 deg W in 1992-1996; 120 deg W in 1996-1999 As of 31 August 2001 located at 16.95 deg W drifting at 1.400 deg W per day. As of 2007 Mar 10 located at 6.47W drifting at 1.400W degrees per day.

• Morelos 1 - . Payload: Morelos-A / PAM-D. Mass: 512 kg (1,128 lb). Nation: Mexico. Agency: Morelos. Program: Morelos. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1994-03-04 . USAF Sat Cat: 15824 . COSPAR: 1985-048B. Apogee: 36,030 km (22,380 mi). Perigee: 35,999 km (22,368 mi). Inclination: 6.30 deg. Period: 1,447.80 min.

  Released by STS 51G 17 June 1985; 113.5 deg W. Coverage of the national territory with television, radio and telephony signals and data transmission. Geostationary satellite. Positioned in geosynchronous orbit at 113 deg W in 1985-1994 As of 4 September 2001 located at 123.32 deg W drifting at 2.909 deg W per day. As of 2007 Mar 10 located at 176.84E drifting at 2.883W degrees per day.

• Arabsat 1B - . Payload: Discovery F5 / Morelos 1 [PAM-D] / Telstar 303 [PA. Mass: 592 kg (1,305 lb). Nation: Arab States. Agency: Arabsat. Program: Arabsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 100. Completed Operations Date: 1992-06-01 . USAF Sat Cat: 15825 . COSPAR: 1985-048C. Apogee: 35,746 km (22,211 mi). Perigee: 35,737 km (22,205 mi). Inclination: 1.90 deg. Period: 1,433.80 min. Released by STS 51G 18 June 1985; 26 deg E. Positioned in geosynchronous orbit at 26 deg E in 1985-1992 As of 5 September 2001 located at 135.45 deg W drifting at 0.555 deg E per day. As of 2007 Mar 9 located at 165.57E drifting at 0.400E degrees per day..

• Spartan 1 - . Payload: Spartan 101. Mass: 1,008 kg (2,222 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: Spartan. Decay Date: 1985-06-24 . USAF Sat Cat: 15831 . COSPAR: 1985-048E. Apogee: 395 km (245 mi). Perigee: 359 km (223 mi). Inclination: 28.50 deg. Period: 92.10 min. Released by STS 51G 20 June 1985, retrieved 22 June 1985..

• STS-51-DA (cancelled) - . Crew: Cleave, O Connor, Shaw, Spring. Payload: TDRS/IUS. Nation: USA. Related Persons: Cleave, O Connor, Shaw, Spring. Program: STS. Flight: STS-51-DA. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Planned TDRS/IUS deployment shuttle mission. Cancelled due to IUS failure..

• Shuttle Challenger Pad Abort - . Nation: USA. Program: STS. Flight: STS-51-F. Spacecraft Bus: Shuttle. Spacecraft: Challenger. The countdown for Challenger's launch was halted at T-3 seconds when on-board computers detected a problem with a coolant valve on main engine #2. The valve was replaced and Challenger was launched on July 29, 1985..

• STS-51-F - . Call Sign: Challenger. Crew: Acton, Bartoe, Bridges, England, Fullerton, Henize, Musgrave. Payload: Challenger F08 / PDP / Spacelab 2 PLT. Mass: 15,603 kg (34,398 lb). Nation: USA. Related Persons: Acton, Bartoe, Bridges, England, Fullerton, Henize, Musgrave. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-F. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 7.95 days. Decay Date: 1985-08-06 . USAF Sat Cat: 15925 . COSPAR: 1985-063A. Apogee: 337 km (209 mi). Perigee: 203 km (126 mi). Inclination: 49.50 deg. Period: 89.90 min.

  Manned seven crew. At 5 minutes, 45 seconds into ascent the number one engine shut down prematurely due to a a sensor problem and an abort to orbit was declared. Despite the anomaly the mission continued. Launched PDP; carried Spacelab 2. Payloads: Spacelab-2 with 13 experiments, Shuttle Amateur Radio Experiment (SAREX), Protein Crystal Growth (PCG). The flight crew was divided into a red and blue team. Each team worked 12-hour shifts for 24-hour-a-day operation.

• Spacelab 2 PLT - . Nation: USA. Agency: NASA. Program: Spacelab. Class: Manned. Type: Manned space laboratory. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1985-08-06 . USAF Sat Cat: 15925 . COSPAR: 1985-063xx. Apogee: 328 km (203 mi). Perigee: 300 km (180 mi). Inclination: 49.50 deg. Period: 90.80 min.

• Spacelab 2 PLT - . Nation: USA. Agency: NASA. Program: Spacelab. Class: Manned. Type: Manned space laboratory. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1985-08-06 . USAF Sat Cat: 15925 . COSPAR: 1985-063xx. Apogee: 328 km (203 mi). Perigee: 300 km (180 mi). Inclination: 49.50 deg. Period: 90.80 min.

• Spacelab 2 PLT - . Nation: USA. Agency: NASA. Program: Spacelab. Class: Manned. Type: Manned space laboratory. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: SLP. Decay Date: 1985-08-06 . USAF Sat Cat: 15925 . COSPAR: 1985-063xx. Apogee: 328 km (203 mi). Perigee: 300 km (180 mi). Inclination: 49.50 deg. Period: 90.80 min.

• PDP - . Payload: Challenger F8 / PDP. Mass: 285 kg (628 lb). Nation: USA. Agency: NASA Huntsville. Class: Earth. Type: Magnetosphere satellite. Spacecraft: PDP. Decay Date: 1985-08-06 . USAF Sat Cat: 15929 . COSPAR: 1985-063B. Apogee: 321 km (199 mi). Perigee: 311 km (193 mi). Inclination: 49.50 deg. Period: 90.90 min. Plasma Diagnostics Package; released by STS 51F 8/1/85, retrieved 8/2/85. .

• CRNE - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: CRNE. Decay Date: 1985-08-06 . USAF Sat Cat: 15925 . COSPAR: 1985-063xx. Apogee: 328 km (203 mi). Perigee: 300 km (180 mi). Inclination: 49.50 deg. Period: 90.80 min.

• STS-51-I - . Call Sign: Discovery. Crew: Covey, Engle, Fisher, William, Lounge, van Hoften. Payload: Discovery F06 / Syncom-4 4 [Orbus-7S] / Aussat A1. Mass: 19,952 kg (43,986 lb). Nation: USA. Related Persons: Covey, Engle, Fisher, William, Lounge, van Hoften. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-I. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Duration: 7.10 days. Decay Date: 1985-09-03 . USAF Sat Cat: 15992 . COSPAR: 1985-076A. Apogee: 364 km (226 mi). Perigee: 351 km (218 mi). Inclination: 28.50 deg. Period: 91.70 min.

  Manned five crew. Launched Aussat 1, ASC 1, Leasat 4; repaired Leasat 3. Payloads: Deploy ASC (American Satellite Company)-1 with Payload Assist Modue (PAM)-D. Deploy AUSSAT (Australian communications satellite)-1 with PAM-D. Deploy Syncom IV-4 communications satellite with its unique stage. Retrieve Leasat-3 communications satellite, repair and deploy by extravehicular activity (EVA) astronauts. Physical Vapor Transport Organic Solids (PVTOS) experiment.

• Aussat A1 - . Payload: Aussat A1 [PAM-D]. Mass: 1,260 kg (2,770 lb). Nation: Australia. Agency: Aussat. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 376. Completed Operations Date: 1993-08-24 . USAF Sat Cat: 15993 . COSPAR: 1985-076B. Apogee: 35,934 km (22,328 mi). Perigee: 35,922 km (22,320 mi). Inclination: 7.00 deg. Period: 1,443.30 min.

  Released by STS 51I 8/27/85. Aussat A1 was decommissioned in early 1993 at the ned of its nominal life. It is currently in a non-synchronous graveyard orbit.. It spent its active life at 160 deg. E. Positioned in geosynchronous orbit at 160 deg E in 1985-1993 As of 5 September 2001 located at 174.28 deg W drifting at 1.831 deg W per day. As of 2007 Feb 27 located at 120.19E drifting at 1.838W degrees per day.

• ASC-1 - . Mass: 1,271 kg (2,802 lb). Nation: USA. Agency: new. Program: GTE. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: AS 3000. Spacecraft: ASC. Completed Operations Date: 1994-08-01 . USAF Sat Cat: 15994 . COSPAR: 1985-076C. Apogee: 35,796 km (22,242 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Released by STS 51I 8/27/85; stationed at 81 deg E. C, Ku band communications satellite. Positioned in geosynchronous orbit at 128 deg W in 1985-1994 As of 5 September 2001 located at 99.97 deg W drifting at 0.156 deg W per day. As of 2007 Mar 10 located at 119.21W drifting at 0.126W degrees per day.

• Syncom IV-4 - . Payload: Discovery F6 / Syncom-4 4 [Orbus-7S] / Aussat A1 [. Mass: 1,388 kg (3,060 lb). Nation: USA. Agency: HCI. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 381. Completed Operations Date: 1996-10-30 . USAF Sat Cat: 15995 . COSPAR: 1985-076D. Apogee: 36,503 km (22,681 mi). Perigee: 36,486 km (22,671 mi). Inclination: 9.50 deg. Period: 1,472.40 min.

  Released by STS 51I 8/29/85; 178 deg E; leased by U.S. government. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 177 deg W in 1985-1987 As of 3 September 2001 located at 149.81 deg W drifting at 8.908 deg W per day. As of 2007 Mar 10 located at 84.34W drifting at 8.912W degrees per day.

• EVA STS-51-I-1 - . Crew: Fisher, William, van Hoften. EVA Duration: 0.31 days. Nation: USA. Related Persons: Fisher, William, van Hoften. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-I. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Captured Syncom F3 and began repairs..

• EVA STS-51-I-2 - . Crew: Fisher, William, van Hoften. EVA Duration: 0.19 days. Nation: USA. Related Persons: Fisher, William, van Hoften. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-I. Spacecraft Bus: Shuttle. Spacecraft: Discovery. Completed Syncom F3 repairs and redeployed satellite..

• SLC-6 at Vandenberg declared operation for shuttle flights. - . Nation: USA.

  The launch complex and support buildings had been built on the old Manned Orbiting Laboratory facilities at a total cost of $ 5.5 billion. Checks of the facilities with non-flight shuttle Enterprise, an external tank, and inert solid rocket boosters were conducted from late 1984 to early 1985. Later fundamental design flaws were found that would cost another $1 billion and two years to fix. The US Air Force was no longer interested in the shuttle as a booster for its payloads, and the facility was mothballed without ever launching a shuttle.

• STS-51-J - . Call Sign: Atlantis. Crew: Bobko, Grabe, Hilmers, Pailes, Stewart. Payload: Atlantis F01 / DSCS-3 2 / DSCS-3 3 [IUS]. Mass: 115,900 kg (255,500 lb). Nation: USA. Related Persons: Bobko, Grabe, Hilmers, Pailes, Stewart. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-J. Spacecraft Bus: Shuttle. Spacecraft: Atlantis. Duration: 4.07 days. Decay Date: 1985-10-07 . USAF Sat Cat: 16115 . COSPAR: 1985-092A. Apogee: 486 km (301 mi). Perigee: 476 km (295 mi). Inclination: 28.50 deg. Period: 94.20 min.

  Manned five crew. Atlantis (first flight); deployed USA 11, USA 12. Reusable space transportation system.

  Orbits of Earth: 63. Landed at: Runway 23 dry lake bed at Edwards Air Force Base, . Touchdown miss distance: 754.00 m. Landing Rollout: 2,455.00 m. Payloads: Classified DoD Mission - Record altitude (as of 5/93).

• USA 11 - . Payload: DSCS III F-2. Mass: 2,613 kg (5,760 lb). Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 16116 . COSPAR: 1985-092B. Apogee: 35,963 km (22,346 mi). Perigee: 35,434 km (22,017 mi). Inclination: 0.30 deg. Period: 1,436.00 min. Released from STS 51J 10/4/85. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit; at 12 deg W in 1986; 42 deg W in 1995..

• USA 12 - . Payload: DSCS III F-3. Mass: 2,613 kg (5,760 lb). Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 16117 . COSPAR: 1985-092C. Apogee: 35,963 km (22,346 mi). Perigee: 35,633 km (22,141 mi). Inclination: 0.30 deg. Period: 1,436.00 min.

  Released from STS 51J 4 October 1985; boosted into orbit with DSCS 3 F3 on single IUS booster. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit; at 180 deg E in 1994.

• STS-61-A - . Call Sign: Challenger. Crew: Bluford, Buchli, Dunbar, Furrer, Hartsfield, Messerschmid, Nagel, Ockels. Payload: Challenger F09 / GLOMR 1. Mass: 14,451 kg (31,859 lb). Nation: USA. Related Persons: Bluford, Buchli, Dunbar, Furrer, Hartsfield, Messerschmid, Nagel, Ockels. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-61-A. Spacecraft Bus: Shuttle. Spacecraft: Challenger. Duration: 7.03 days. Decay Date: 1985-11-06 . USAF Sat Cat: 16230 . COSPAR: 1985-104A. Apogee: 331 km (205 mi). Perigee: 319 km (198 mi). Inclination: 57.00 deg. Period: 91.00 min.

  Manned eight crew. Launched GLOMR; carried Spacelab D1. Payloads: Spacelab D-1 with habitable module and 76 experiments. Six of the eight crew members were divided into a blue and red team working 12-hour shifts for 24-hour-a-day operation. The remaining two crew members were 'switch hitters.'.

• GLOMR; GLOMAR - . Payload: Challenger F9 / GLOMR 1. Mass: 52 kg (114 lb). Nation: USA. Agency: USN. Class: Communications. Type: Military communications satellite. Spacecraft: GLOMR. Decay Date: 1986-12-26 . USAF Sat Cat: 16231 . COSPAR: 1985-104B. Apogee: 332 km (206 mi). Perigee: 317 km (196 mi). Inclination: 57.00 deg. Period: 91.00 min. Released from STS 61A 11/1/85. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

• Spacelab D-1 - . Payload: Spacelab Long Module. Nation: USA. Agency: NASA. Program: Spacelab. Class: Manned. Type: Manned space laboratory. Spacecraft: Spacelab. Decay Date: 1985-11-06 . USAF Sat Cat: 16230 . COSPAR: 1985-104xx. Apogee: 332 km (206 mi). Perigee: 322 km (200 mi). Inclination: 57.00 deg. Period: 91.10 min.

• USS - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: USS. Decay Date: 1985-11-06 . USAF Sat Cat: 16230 . COSPAR: 1985-104xx. Apogee: 332 km (206 mi). Perigee: 322 km (200 mi). Inclination: 57.00 deg. Period: 91.10 min.

• STS-51-H (cancelled) - . Payload: EOM-1. Nation: USA. Program: STS. Flight: STS-51-H. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Planned EOM-1/2 shuttle mission. Cancelled due to payload delays..

• STS-61-B - . Call Sign: Atlantis. Crew: Cleave, Neri Vela, O Connor, Ross, Shaw, Spring, Walker. Payload: Atlantis F02 / EASE / ACCESS. Mass: 21,791 kg (48,040 lb). Nation: USA. Related Persons: Cleave, Neri Vela, O Connor, Ross, Shaw, Spring, Walker. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-61-B. Spacecraft Bus: Shuttle. Spacecraft: Atlantis. Duration: 6.88 days. Decay Date: 1985-12-03 . USAF Sat Cat: 16273 . COSPAR: 1985-109A. Apogee: 370 km (220 mi). Perigee: 361 km (224 mi). Inclination: 28.50 deg. Period: 91.90 min.

  Manned seven crew. Deployed Morelos 2, Aussat 2, Satcom K2, OEX. Payloads: Deploy SATCOM (RCA-Satellite Communi-cations) Ku-2 with Payload Assist Module (PAM)-D II. Deploy Morelos (Mexico communications satellite)-B with PAM-D. Deploy AUSSAT (Australian communications satellite)-2 with PAM-D. EASE/ACCESS (Assembly of Structures— Assembly Concept for Construction of Erectable Space Structures) by extravehicular activity (EVA) astronauts, Continuous Flow Electrophore-sis System (CFES), Diffusive Mixing of Organic Solutions (DMOS), IMAX camera, one getaway special (GAS), Linhof camera and Hasseblad camera.

• OEX Target - . Payload: Atlantis F2 / Aussat A2 [PAM-D] / Morelos 2 [PAM-D. Mass: 16 kg (35 lb). Nation: USA. Agency: NASA Houston. Program: STS. Class: Technology. Type: Technology satellite. Spacecraft: OEX Target. Decay Date: 1987-03-02 . USAF Sat Cat: 16277 . COSPAR: 1985-109E. Apogee: 386 km (239 mi). Perigee: 373 km (231 mi). Inclination: 28.40 deg. Period: 92.10 min. Released from STS 61B 11/30/85; shuttle autopilot software test target. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

• Morelos 2 - . Payload: Morelos-B / PAM-D. Mass: 645 kg (1,421 lb). Nation: Mexico. Agency: Morelos. Program: Morelos. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 16274 . COSPAR: 1985-109B. Apogee: 35,792 km (22,240 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Released by STS 61B 11/27/85. Coverage of the national territory with television, radio and telephony signals and data transmission. Geostationary satellite. Positioned in geosynchronous orbit at 116 deg W in 1985-1998; 120 deg W in 1999. As of 5 September 2001 located at 120.20 deg W drifting at 0.004 deg W per day. As of 2007 Mar 10 located at 148.53W drifting at 2.555W degrees per day.

• Aussat A2 - . Payload: Aussat A2 [PAM-D]. Mass: 1,259 kg (2,775 lb). Nation: Australia. Agency: Aussat. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: HS 376. USAF Sat Cat: 16275 . COSPAR: 1985-109C. Apogee: 35,886 km (22,298 mi). Perigee: 35,866 km (22,286 mi). Inclination: 6.70 deg. Period: 1,440.70 min.

  Released by STS 61B 11/28/85; 156 deg E. Positioned in geosynchronous orbit at 156 deg E in 1985-1993; 164 deg E in 1993-1999 As of 1 September 2001 located at 24.67 deg W drifting at 1.153 deg W per day. As of 2007 Feb 27 located at 133.30E drifting at 1.163W degrees per day.

• EASE/ACCESS - . Nation: USA. Agency: NASA. Program: STS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: EASE/ACCESS. Decay Date: 1985-12-03 . USAF Sat Cat: 16273 . COSPAR: 1985-109xx. Apogee: 385 km (239 mi). Perigee: 323 km (200 mi). Inclination: 28.50 deg. Period: 91.60 min.

• Satcom K2 - . Payload: Satcom-K 2 / PAM-D2. Mass: 1,812 kg (3,994 lb). Nation: USA. Agency: RCA Amer. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 4000. USAF Sat Cat: 16276 . COSPAR: 1985-109D. Apogee: 36,002 km (22,370 mi). Perigee: 35,944 km (22,334 mi). Inclination: 4.20 deg. Period: 1,445.60 min.

  Released by STS 61B 11/28/85; 81 deg W. Positioned in geosynchronous orbit at 81 deg W in 1985-1996; 85 deg W in 1996-1997; 81 deg W in 1997-1999 As of 6 September 2001 located at 80.95 deg W drifting at 0.009 deg W per day. As of 2007 Mar 9 located at 157.11W drifting at 2.398W degrees per day.

• EVA STS-61-B-1 - . Crew: Ross, Spring. EVA Duration: 0.23 days. Nation: USA. Related Persons: Ross, Spring. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-61-B. Spacecraft Bus: Shuttle. Spacecraft: Atlantis. Began EASE/ACCESS (Assembly of Structures / Assembly Concept for Construction of Erectable Space Structures) structural assembly experiments..

• EVA STS-61-B-2 - . Crew: Ross, Spring. EVA Duration: 0.28 days. Nation: USA. Related Persons: Ross, Spring. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-61-B. Spacecraft Bus: Shuttle. Spacecraft: Atlantis. Completed EASE/ACCESS (Assembly of Structures / Assembly Concept for Construction of Erectable Space Structures) structural assembly experiments..

• STS-61-C - . Call Sign: Columbia. Crew: Bolden, Cenker, Chang-Diaz, Gibson, Hawley, Nelson, Nelson, Bill. Payload: Columbia F07 Satcom-K 1 [PAM-D2]. Mass: 14,724 kg (32,460 lb). Nation: USA. Related Persons: Bolden, Cenker, Chang-Diaz, Gibson, Hawley, Nelson, Nelson, Bill. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-61-C. Spacecraft Bus: Shuttle. Spacecraft: Columbia. Duration: 6.09 days. Decay Date: 1986-01-18 . USAF Sat Cat: 16481 . COSPAR: 1986-003A. Apogee: 338 km (210 mi). Perigee: 331 km (205 mi). Inclination: 28.50 deg. Period: 91.20 min.

  Manned seven crew. Launched Satcom K1. Payloads: Deploy SATCOM (RCA-Satellite Communi-cations) Ku-1 with Payload Assist Module (PAM)-D II. Materials Science Laboratory, Comet Halley Active Monitoring Experiment (CHAMP), Hitchhiker (HH) Goddard (G)-1, thirteen getaway specials (GAS), student experiment, Initial Blood Storage Equipment (lBSE), Characterization of Space Motion Sickness (SMS).