STS Credit - NASA Media Gallery

The manned reusable space system which was designed to slash the cost of space transport and replace all expendable launch vehicles. It did neither, but did keep NASA in the manned space flight business for 30 years (and counting...) 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.

Manufacturer: NASA. Launches: 118. Failures: 1. Success Rate: 99.15%. First Launch Date: 1981-04-12. Last Launch Date: 2007-06-08. Launch data is: continuing. LEO Payload: 24,400 kg (53,700 lb). to: 204 km Orbit. at: 28.50 degrees. Payload: 12,500 kg (27,500 lb). to a: space station orbit, 407 km, 51.6 deg inclination trajectory. Apogee: 600 km (370 mi). Associated Spacecraft: ACTS, AERCam, AFP-675, AS 4000, ASC, Atlantis, BremSat, Challenger, Chandra, Columbia, CRO, CTA, Discovery, DSCS III, DSP Block 14, Endeavour, ERBS, Eureca, Galileo, Galileo Probe, GLOMR, GRO, HS 376, HS 381, HS 601, HST, IAE, IBSS, Insat 1, IRT. Other Associated Spacecraft: ISS Unity, KH-12, Lacrosse, Lageos, LDEF, Magellan, Magnum, Mightysat 1, Mir-Shuttle Docking Module, MPEC, NUSAT, OAST-Flyer, ODERACS, ORFEUS, PAMS, PDP, SAC-A, SDS-2, Simplesat, Spacebus 100, Spacehab, Spacelab, Spartan, SPAS, SSF, Starshine, TDRS, TSS. Further Associated Spacecraft: UARS, Ulysses, WSF, NASDA Japanese Experiment Module, Transhab Module, Space Station Options 1993, Alpha Lifeboat, Spacedock, X-38, International Space Station, NASA ACRV, Space Station Fred, Industrial Space Facility. Liftoff Thrust: 25,751.600 kN (5,789,190 lbf). Total Mass: 2,029,633 kg (4,474,574 lb). Core Diameter: 8.70 m (28.50 ft). Total Length: 56.00 m (183.00 ft). Development Cost $: 10,100.000 million. in: 1977 average dollars. Launch Price $: 245.000 million. in: 1988 price dollars. Total Production Built: 5. Flyaway Unit Cost $: 63.000 million. in: 1988 unit dollars. Cost comments: Shuttle has high fixed costs and low marginal costs. Cost per mission dependent on rate. Flyaway cost is marginal cost for extra mission. Launch cost is cost per flight at 6 per year.

• Stage Number: 0. 2 x Stage: Shuttle SRB. Gross Mass: 589,670 kg (1,299,990 lb). Empty Mass: 86,183 kg (190,000 lb). Thrust (vac): 11,519.999 kN (2,589,799 lbf). Isp: 269 sec. Burn time: 124 sec. Isp(sl): 237 sec. Diameter: 3.71 m (12.17 ft). Span: 5.10 m (16.70 ft). Length: 38.47 m (126.21 ft). Propellants: Solid. No Engines: 1. Engine: SRB. Other designations: Solid Rocket Booster. Status: Study 1987.

• Stage Number: 1. 1 x Stage: Shuttle Tank. Gross Mass: 750,975 kg (1,655,616 lb). Empty Mass: 29,930 kg (65,980 lb). Thrust (vac): 0 N ( lbf). Isp: 455 sec. Burn time: 480 sec. Isp(sl): 363 sec. Diameter: 8.40 m (27.50 ft). Span: 8.70 m (28.50 ft). Length: 46.88 m (153.80 ft). Propellants: Lox/LH2. No Engines: 0. Engine: None. Other designations: External Tank. Status: Study 1972.

• Stage Number: 2. 1 x Stage: Shuttle Orbiter. Gross Mass: 99,318 kg (218,958 lb). Empty Mass: 99,117 kg (218,515 lb). Thrust (vac): 6,834.303 kN (1,536,412 lbf). Isp: 455 sec. Burn time: 480 sec. Isp(sl): 363 sec. Diameter: 4.90 m (16.00 ft). Span: 23.79 m (78.05 ft). Length: 37.24 m (122.17 ft). Propellants: Lox/LH2. No Engines: 3. Engine: SSME. Other designations: Shuttle; STS (Space Transportation System). Status: In production.

1968 October 30 - Launch Vehicle: Shuttle.

• 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.References: 44.

• 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.References: 44.

• 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. References: 16.

• 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.References: 44.

• 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.References: 44.

• Two major directions were identified for NASA manned space flight in the next decade. Nation: USA. Program: Skylab. Spacecraft: Skylab, Columbia. Flight: Skylab B. 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 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.References: 44.

• 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. References: 44.

• 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
  References: 44.

• 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.References: 44.

• 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.References: 44.

• 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.References: 44.

• 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.References: 44.

• Shuttle specifications revised Nation: USA. Further minor changes were made as a result of the NASA 90-day review in October. References: 44.

• 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. References: 44.

• 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.References: 44.

• 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.References: 44.

• 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.References: 44.

• 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. References: 44.

• James C Fletcher sworn in as NASA Administrator Nation: USA. 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.References: 16.

• 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.References: 44.

• 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.References: 44.

• 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). References: 44.

• 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!References: 44.

• 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.References: 44.

• 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.References: 44.

• 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.
  References: 44.

• 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.References: 44.

• 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. References: 44.

• 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. References: 44.

• 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.References: 44.

• 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.References: 44.

• 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.References: 44.

• Shuttle go-ahead. Nation: USA. Program: STS. Rockwell receives authority to proceed, space shuttle orbiter References: 15.

• 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. References: 44.

• Shuttle solid rocket booster contract Nation: USA. United Space Boosters and Thiokol receive the contract. References: 44.

• 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. References: 44.

• Shuttle Enterprise construction begins. Nation: USA. Program: STS. Spacecraft: Enterprise. Structural assembly of the crew module for shuttle Enterprise (OV-101) begins at Plant 42 in Palmdale. References: 15, 44.

• 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.References: 44.

• 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.References: 44.

• Shuttle SSME engine chamber Test Nation: USA. The first full thrust chamber test is completed. References: 44.

• Shuttle SSME first test. Nation: USA. Program: STS. Space shuttle main engine first main stage test at NSTL References: 15.

• First SSME 60-second duration test, NSTL Nation: USA. Program: STS. References: 15.

• Enterprise final assembly complete. Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Complete final assembly and closeout system installation. References: 15.

• 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). References: 44.

• 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. References: 44.

• 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. References: 44.

• Boeing 747 shuttle carrier aircraft delivered Nation: USA. Program: STS. Boeing 747 shuttle carrier aircraft delivered to Edwards References: 15.

• First inert captive flight Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Conduct first inert captive flight, Edwards (2 hours, 5 minutes), Enterprise (OV-101) References: 15.

• Second inert captive flight Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Conduct second inert captive flight, Edwards (3 hours, 13 minutes), Enterprise (OV-101) References: 15.

• Third inert captive flight Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Conduct third inert captive flight, Edwards (2 hours, 28 minutes), Enterprise (OV-101) References: 15.

• Fourth inert captive flight Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Conduct fourth inert captive flight, Edwards (2 hours, 11 minutes), Enterprise (OV-101) References: 15.

• Fifth inert captive flight Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Conduct fifth inert captive flight, Edwards (1 hour, 39 minutes), Enterprise (OV-101) References: 15.

• Shuttle SSME Tests resumed Nation: USA. 25 tests will be run on two engines over the next year. References: 44.

• 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. References: 44.

• 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. References: 44.

• Enterprise flight 1 Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Flight Crew: Fullerton, Haise. First manned captive active flight. Enterprise (OV-101)/shuttle carrier aircraft, Edwards (55 minutes, 46 seconds) References: 15.

• 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. References: 44.

• Enterprise flight 2 Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Flight Crew: Engle, Truly. Second manned captive active flight. Enterprise (OV-101)/shuttle carrier aircraft, Edwards (1 hour, 2 minutes) References: 15.

• DM-1 Shuttle SRB development static firing Nation: USA. The first firing of a shuttle Solid Rocket Booster motor. References: 44.

• Enterprise flight 3 Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Flight Crew: Fullerton, Haise. Third manned captive active flight. Enterprise (OV-101)/shuttle carrier aircraft, Edwards (59 minutes, 50 seconds) References: 15.

• 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. References: 44.

• Enterprise flight 4 Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Flight Crew: Fullerton, Haise. Conduct first free flight, ALT, tail cone on, Edwards (5 minutes, 21 seconds), Enterprise (OV-101), lake bed Runway 17 References: 15.

• Enterprise flight 5 Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Flight Crew: Engle, Truly. Second free flight, ALT, tail cone on, Edwards (5 minutes, 28 seconds), Enterprise (OV-101), lake bed Runway 17 References: 15.

• Enterprise flight 6 Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Flight Crew: Fullerton, Haise. Third free flight , ALT, tail cone on, Edwards (5 minutes, 34 seconds), Enterprise (OV-101), lake bed Runway 15 References: 15.

• SRB Hydroburst test Nation: USA. A flight-representative shuttle Solid Rocket Booster was subjected to water pressure until the casing burst. References: 44.

• Enterprise flight 7 Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Flight Crew: Engle, Truly. Fourth free flight, ALT, first tail cone off, Edwards (2 minutes, 34 seconds), Enterprise (OV-101), lake bed Runway 17 References: 15.

• Enterprise flight 8 Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Flight Crew: Fullerton, Haise. Fifth free flight, ALT, final tail cone off, Edwards (2 minutes, 1 second), Enterprise (OV-101), concrete Runway 04 References: 15.

• First ferry flight test, Edwards Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. First ferry flight test, Edwards (3 hours, 21 minutes), Enterprise (OV-101) References: 15.

• Second ferry flight test, Edwards Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Second ferry flight test, Edwards (4 hours, 17 minutes), Enterprise (OV-101) References: 15.

• Third ferry flight test, Edwards Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Third ferry flight test, Edwards (4 hours, 13 minutes), Enterprise (OV-101) References: 15.

• Fourth ferry flight test, Edwards Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Fourth ferry flight test, Edwards (3 hours, 37 minutes), Enterprise (OV-101) References: 15.

• Complete approach and landing flight tests Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Enterprise. Complete approach and landing flight tests, including ferry flights, Enterprise (OV-101) References: 15.

• 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. References: 44.

• DM-2 Shuttle SRB development static firing Nation: USA. The second firing of a shuttle Solid Rocket Booster motor. References: 44.

• Shuttle Enterprise delivered. Nation: USA. References: 44.

• 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. References: 44.

• 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. References: 44.

• Shuttle MPTA long duration test Nation: USA. The engine assembly is run for several minutes, and engine restart is demonstrated. References: 44.

• 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. References: 44.

• 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. References: 44.

• 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.References: 44.

• DM-3 Shuttle SRB development static firing Nation: USA. The third firing of a shuttle Solid Rocket Booster motor. References: 44.

• DM-4 Shuttle SRB development static firing Nation: USA. The fourth firing of a shuttle Solid Rocket Booster motor. References: 44.

• 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. References: 44.

• Shuttle carrier aircraft/Columbia test flight Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Columbia. Shuttle carrier aircraft/Columbia (OV-102) test flight at NASA Edwards References: 15.

• 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.References: 44.

• 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. References: 44.

• QM-1 Shuttle SRB qualification static firing Nation: USA. The fifth firing of a shuttle Solid Rocket Booster motor. References: 44.

• 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. References: 44.

• Start long-lead fabrication crew module, Discovery Nation: USA. Program: STS. Class: Manned. Type: Spaceplane. Spacecraft: Discovery. References: 15.

• Shuttle SSME Failure Nation: USA. In a test run, a liquid oxygen turbopump fails 9.7 seconds into the burn. References: 44.

• QM-2 Shuttle SRB qualification static firing Nation: USA. The sixth firing of a shuttle Solid Rocket Booster motor. References: 44.

• 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.References: 44.

• 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. References: 44.

• 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. References: 44.

• 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. References: 44.

• SRB Hydroburst test Nation: USA. A production-representative shuttle Solid Rocket Booster was subjected to water pressure until the casing burst. References: 44.

• Shuttle MPTA-098 625-second firing. Nation: USA. This firing used the three flight engines, which had been removed from Columbia. References: 44.

• 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. References: 44.

• STS-1 Nation: USA. Program: STS. Payload: Columbia F01 / DFI. Mass: 4,909 kg (10,822 lb). Class: Manned. Type: Spaceplane. Spacecraft: Columbia. Agency: NASA JSC. Perigee: 240 km (140 mi). Apogee: 251 km (155 mi). Inclination: 40.30 deg. Period: 89.40 min. COSPAR: 1981-034A. USAF Sat Cat: 12399. Duration: 2.26 days. Decay Date: 1981-04-14. Flight Crew: Crippen, Young. Flight: STS-1. First flight of Space Transportation System (aka Space Shuttle).. Payloads: Development Flight Instrumentation and Aerodynamic Coefficient Identification Package. References: 1, 2, 5, 6, 7, 33.

• DFI Nation: USA. Program: STS. Payload: DFI PLT. Agency: NASA. COSPAR: 1981-034xx. USAF Sat Cat: 12399. Decay Date: 1981-04-14. References: 279.

• STS-2 Nation: USA. Program: STS. Payload: Columbia F02 / DFI. Mass: 8,517 kg (18,776 lb). Class: Manned. Type: Spaceplane. Spacecraft: Columbia. Agency: NASA JSC. Perigee: 222 km (137 mi). Apogee: 231 km (143 mi). Inclination: 38.00 deg. Period: 89.00 min. COSPAR: 1981-111A. USAF Sat Cat: 12953. Duration: 2.26 days. Decay Date: 1981-11-14. Flight Crew: Engle, Truly. Flight: STS-2. Second shuttle test flight. Payloads: Office of Space and Terrestrial Applications (OSTA)-1 experiments, Orbiter Experiments (OEX). References: 1, 2, 5, 6, 7, 33.

• DFI Nation: USA. Program: STS. Payload: DFI PLT. Agency: NASA. COSPAR: 1981-111xx. USAF Sat Cat: 12953. Decay Date: 1981-11-14. References: 279.

• OSTA-1 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1981-111xx. USAF Sat Cat: 12953. Decay Date: 1981-11-14. References: 279.

• STS-3 Nation: USA. Program: STS. Payload: Columbia F03 / OSS-1. Mass: 10,301 kg (22,709 lb). Class: Manned. Type: Spaceplane. Spacecraft: Columbia. Agency: NASA JSC. Perigee: 241 km (149 mi). Apogee: 249 km (154 mi). Inclination: 38.00 deg. Period: 89.40 min. COSPAR: 1982-022A. USAF Sat Cat: 13106. Duration: 8.00 days. Decay Date: 1982-03-30. Flight Crew: Fullerton, Lousma. Flight: STS-3. Manned two crew. Payloads: Office of Space Science (OSS) experiments, Monodisperse Latex Reactor (MLR), Electro-phoresis Verification Test (EEVT), Plant Lignification Experiment. References: 1, 2, 5, 6, 7, 33.

• OSS-1 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1982-022xx. USAF Sat Cat: 13106. Decay Date: 1982-03-30. References: 279.

• DFI Nation: USA. Program: STS. Payload: DFI PLT. Agency: NASA. COSPAR: 1982-022xx. USAF Sat Cat: 13106. Decay Date: 1982-03-30. References: 279.

• STS-4 Nation: USA. Program: STS. Payload: Columbia F04 / DoD 82-1. Mass: 11,109 kg (24,491 lb). Class: Manned. Type: Spaceplane. Spacecraft: Columbia. Agency: NASA JSC. Perigee: 295 km (183 mi). Apogee: 302 km (187 mi). Inclination: 28.50 deg. Period: 90.30 min. COSPAR: 1982-065A. USAF Sat Cat: 13300. Duration: 7.05 days. Decay Date: 1982-07-04. Flight Crew: Hartsfield, Mattingly. Flight: STS-4. 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.References: 1, 2, 5, 6, 7, 33.

• DoD 82-1 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1982-065xx. USAF Sat Cat: 13300. Decay Date: 1982-07-04. References: 279.

• DFI Nation: USA. Program: STS. Payload: DFI PLT. Agency: NASA. COSPAR: 1982-065xx. USAF Sat Cat: 13300. Decay Date: 1982-07-04. References: 279.

• STS-5 Nation: USA. Program: STS. Payload: Columbia F05 / SBS 3 [PAM-D] / Anik C3 [PAM-D]. Mass: 14,551 kg (32,079 lb). Class: Manned. Type: Spaceplane. Spacecraft: Columbia. Agency: NASA JSC. Perigee: 294 km (182 mi). Apogee: 317 km (196 mi). Inclination: 28.50 deg. Period: 90.50 min. COSPAR: 1982-110A. USAF Sat Cat: 13650. Duration: 5.09 days. Decay Date: 1982-11-16. Flight Crew: Allen, Brand, Lenoir, Overmyer. Flight: STS-5. 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.References: 1, 2, 5, 6, 7, 33.

• SBS 3 Nation: USA. Program: SBS. Payload: SBS 3 [PAM-D]. Mass: 1,117 kg (2,462 lb). Class: Communications. Spacecraft: HS 376. Agency: SBS. Perigee: 35,855 km (22,279 mi). Apogee: 35,910 km (22,310 mi). Inclination: 7.80 deg. Period: 1,441.00 min. COSPAR: 1982-110B. USAF Sat Cat: 13651. Completed Operations Date: 1995-06-01. 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).References: 1, 2, 5, 6.

• Anik C3 (Telesat 6) Nation: Canada. Program: Anik. Payload: Anik C3 [PAM-D]. Mass: 632 kg (1,393 lb). Class: Communications. Spacecraft: HS 376. Agency: Telesat. Perigee: 35,871 km (22,289 mi). Apogee: 35,902 km (22,308 mi). Inclination: 7.90 deg. Period: 1,441.20 min. COSPAR: 1982-110C. USAF Sat Cat: 13652. Completed Operations Date: 1997-06-17. 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.References: 1, 2, 5, 6.

• DFI Nation: USA. Program: STS. Payload: DFI PLT. Agency: NASA. COSPAR: 1982-110xx. USAF Sat Cat: 13650. Decay Date: 1982-11-16. References: 279.

• STS-6 Nation: USA. Program: STS. Payload: Challenger F01 / TDRS 1 [IUS]. Mass: 21,305 kg (46,969 lb). Class: Manned. Type: Spaceplane. Spacecraft: Challenger. Agency: NASA JSC. Perigee: 288 km (178 mi). Apogee: 295 km (183 mi). Inclination: 28.50 deg. Period: 90.40 min. COSPAR: 1983-026A. USAF Sat Cat: 13968. Duration: 5.02 days. Decay Date: 1983-04-09. Flight Crew: Bobko, Musgrave, Peterson, Weitz. Flight: STS-6. 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).References: 1, 2, 5, 6, 7, 33.

• TDRS 1 Nation: USA. Program: STS. Payload: TDRS A. Mass: 2,268 kg (5,000 lb). Class: Communications. Spacecraft: TDRS. Agency: NASA GSF. Perigee: 35,835 km (22,266 mi). Apogee: 35,976 km (22,354 mi). Inclination: 7.40 deg. Period: 1,442.20 min. COSPAR: 1983-026B. USAF Sat Cat: 13969. 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.References: 1, 2, 5, 6.

• STS-7 Nation: USA. Program: STS. Payload: Challenger F02 / OSTA-2. Mass: 16,839 kg (37,123 lb). Class: Manned. Type: Spaceplane. Spacecraft: Challenger. Agency: NASA JSC. Perigee: 299 km (185 mi). Apogee: 307 km (190 mi). Inclination: 28.30 deg. Period: 90.60 min. COSPAR: 1983-059A. USAF Sat Cat: 14132. Duration: 6.10 days. Decay Date: 1983-06-24. Flight Crew: Crippen, Fabian, Hauck, Ride, Thagard. Flight: STS-7. 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).References: 1, 2, 5, 6, 7, 33.

• Anik C2 (Telesat 7) Nation: Canada. Program: Anik. Payload: Anik C2 [PAM-D]. Mass: 1,238 kg (2,729 lb). Class: Communications. Spacecraft: HS 376. Agency: Telesat. Perigee: 35,949 km (22,337 mi). Apogee: 36,273 km (22,538 mi). Inclination: 7.80 deg. Period: 1,452.70 min. COSPAR: 1983-059B. USAF Sat Cat: 14133. Completed Operations Date: 1998-01-07. 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.References: 1, 2, 5, 6.

• Palapa B1 Nation: Indonesia. Program: Palapa. Payload: Palapa B1 [PAM-D. Mass: 1,200 kg (2,600 lb). Class: Communications. Spacecraft: HS 376. Agency: Perumtel. Perigee: 35,803 km (22,246 mi). Apogee: 35,840 km (22,260 mi). Inclination: 8.60 deg. Period: 1,437.90 min. COSPAR: 1983-059C. USAF Sat Cat: 14134. Completed Operations Date: 1995-10-01. 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.References: 1, 2, 5, 6.

• SPAS-01 Nation: USA. Payload: Challenger F2 / SPAS 1. Class: Military. Type: SDI. Spacecraft: SPAS. Agency: MBB. Perigee: 295 km (183 mi). Apogee: 300 km (180 mi). Inclination: 28.50 deg. Period: 90.50 min. COSPAR: 1983-059F. USAF Sat Cat: 14142. Decay Date: 1983-06-22. 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.References: 1, 2, 5, 6.

• OSTA-2 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1983-059xx. USAF Sat Cat: 14132. Decay Date: 1983-06-24. References: 279.

• STS-8 Nation: USA. Program: STS. Payload: Challenger F03 / PFTA. Mass: 13,642 kg (30,075 lb). Class: Manned. Type: Spaceplane. Spacecraft: Challenger. Agency: NASA JSC. Perigee: 306 km (190 mi). Apogee: 313 km (194 mi). Inclination: 28.50 deg. Period: 90.70 min. COSPAR: 1983-089A. USAF Sat Cat: 14312. Duration: 6.05 days. Decay Date: 1983-09-05. Flight Crew: Bluford, Brandenstein, Gardner, Thornton Bill, Truly. Flight: STS-8. 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.References: 1, 2, 5, 6, 7, 33.

• Insat-1B; Insat 1B Nation: India. Program: Insat. Payload: Insat 1B. Mass: 1,152 kg (2,539 lb). Class: Communications. Spacecraft: Insat 1. Agency: ISRO. Perigee: 35,811 km (22,251 mi). Apogee: 35,824 km (22,259 mi). Inclination: 3.60 deg. Period: 1,437.70 min. COSPAR: 1983-089B. USAF Sat Cat: 14318. Completed Operations Date: 1993-08-03. 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.References: 1, 2, 5, 6.

• PFTA Nation: USA. Program: STS. Agency: NASA. COSPAR: 1983-089xx. USAF Sat Cat: 14312. Decay Date: 1983-09-05. References: 279.

• DFI/USPS Nation: USA. Program: STS. Payload: DFI PLT. Agency: NASA. COSPAR: 1983-089xx. USAF Sat Cat: 14312. Decay Date: 1983-09-05. References: 279.

• STS-9 Nation: USA. Program: STS. Payload: Columbia F06 / Spacelab 1 Pallet. Mass: 15,088 kg (33,263 lb). Class: Manned. Type: Spaceplane. Spacecraft: Columbia. Agency: NASA JSC. Perigee: 241 km (149 mi). Apogee: 254 km (157 mi). Inclination: 57.00 deg. Period: 89.50 min. COSPAR: 1983-116A. USAF Sat Cat: 14523. Duration: 10.32 days. Decay Date: 1983-12-08. Flight Crew: Garriott, Lichtenberg, Merbold, Parker, Shaw, Young. Flight: STS-9. 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.References: 1, 2, 5, 6, 7, 33.

• Spacelab 1 Pallet Nation: USA. Program: Spacelab. Payload: SL 1 PLT. Class: Manned. Type: Spacelab. Spacecraft: Spacelab. Agency: NASA. COSPAR: 1983-116xx. USAF Sat Cat: 14523. Decay Date: 1983-12-08. References: 279.

• Spacelab 1 Nation: USA. Program: Spacelab. Payload: SL 1 LM. Class: Manned. Type: Spacelab. Spacecraft: Spacelab. Agency: NASA. COSPAR: 1983-116xx. USAF Sat Cat: 14523. Decay Date: 1983-12-08. References: 279.

• Shuttle Columbia overhauled at Palmdale. Nation: USA. Program: STS. 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.References: 44.

• STS-41-B Nation: USA. Program: STS. Payload: Challenger F04 / SPAS 1A. Mass: 15,362 kg (33,867 lb). Class: Manned. Type: Spaceplane. Spacecraft: Challenger. Agency: NASA JSC. Perigee: 307 km (190 mi). Apogee: 316 km (196 mi). Inclination: 28.50 deg. Period: 90.80 min. COSPAR: 1984-011A. USAF Sat Cat: 14681. Duration: 7.97 days. Decay Date: 1984-02-11. Flight Crew: Brand, Gibson, McCandless, McNair, Stewart. Flight: STS-41-B. 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).References: 1, 2, 5, 6, 7, 33.

• Westar 6 Nation: USA. Program: Westar. Payload: Westar 6 [PAM-D]. Mass: 1,200 kg (2,600 lb). Class: Communications. Spacecraft: HS 376. Agency: WUTC. Perigee: 307 km (190 mi). Apogee: 1,220 km (750 mi). Inclination: 27.70 deg. Period: 100.10 min. COSPAR: 1984-011B. USAF Sat Cat: 14688. Decay Date: 1984-11-16. 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.References: 1, 2, 5, 6.

• IRT Nation: USA. Payload: Challenger F4 / Westar 6 [PAM-D] / Palapa B2 [PAM-. Mass: 91 kg (200 lb). Class: Technology. Spacecraft: IRT. Agency: NASA JSC. Perigee: 279 km (173 mi). Apogee: 288 km (178 mi). Inclination: 28.50 deg. Period: 90.20 min. COSPAR: 1984-011C. USAF Sat Cat: 14689. Decay Date: 1984-02-11. Deployed from STS 41B on 5 February 1984; Integrated Rendezvous Target. References: 1, 2, 5, 6.

• Palapa B2 Nation: Indonesia. Program: Palapa. Payload: Palapa B2 [PAM-D]. Mass: 1,200 kg (2,600 lb). Class: Communications. Spacecraft: HS 376. Agency: Perumtel. Perigee: 280 km (170 mi). Apogee: 1,190 km (730 mi). Inclination: 28.20 deg. Period: 99.50 min. COSPAR: 1984-011D. USAF Sat Cat: 14692. Decay Date: 1984-11-16. Deployed from STS 41B 4 February 1984; failed to reach proper orbit; recovered by STS-51A. References: 1, 2, 5, 6.

• MMU 3 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1984-011xx. References: 279.

• MMU 2 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1984-011xx. References: 279.

• SPAS 1A Nation: USA. Class: Military. Type: SDI. Spacecraft: SPAS. Agency: NASA. COSPAR: 1984-011xx. USAF Sat Cat: 14681. Decay Date: 1984-02-11. 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). References: 279.

• STS-41-C Nation: USA. Program: STS. Payload: Challenger F05 / LDEF 1 / MMU 3. Mass: 17,357 kg (38,265 lb). Class: Manned. Type: Spaceplane. Spacecraft: Challenger. Agency: NASA JSC. Perigee: 222 km (137 mi). Apogee: 468 km (290 mi). Inclination: 28.50 deg. Period: 91.40 min. COSPAR: 1984-034A. USAF Sat Cat: 14897. Duration: 6.99 days. Decay Date: 1984-04-13. Flight Crew: Crippen, Hart, Nelson, Scobee, van Hoften. Flight: STS-41-C. 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.References: 1, 2, 5, 6, 7, 33.

• LDEF Nation: USA. Payload: Challenger F5 / LDEF 1. Mass: 3,625 kg (7,991 lb). Class: Earth. Type: Micrometeoroid. Spacecraft: LDEF. Agency: NASA LaR. Perigee: 344 km (213 mi). Apogee: 348 km (216 mi). Inclination: 28.50 deg. Period: 91.50 min. COSPAR: 1984-034B. USAF Sat Cat: 14898. Decay Date: 1990-01-20. 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). References: 1, 2, 5, 6.

• MMU 3 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1984-034xx. USAF Sat Cat: 14897. Decay Date: 1984-04-13. References: 279.

• MMU 2 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1984-034xx. USAF Sat Cat: 14897. Decay Date: 1984-04-13. References: 279.

• SMRM-FSS Nation: USA. Program: STS. Agency: NASA. COSPAR: 1984-034xx. USAF Sat Cat: 14897. Decay Date: 1984-04-13. References: 279.

• Shuttle Discovery Pad Abort Nation: USA. Program: STS. Spacecraft: Discovery. Flight: STS-41-D. 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-D Nation: USA. Program: STS. Payload: Discovery F01 / SBS 4[PAM-D] / Telstar 302[PAM-D]. Mass: 21,552 kg (47,514 lb). Class: Manned. Type: Spaceplane. Spacecraft: Discovery. Agency: NASA JSC. Perigee: 300 km (180 mi). Apogee: 307 km (190 mi). Inclination: 28.50 deg. Period: 90.60 min. COSPAR: 1984-093A. USAF Sat Cat: 15234. Duration: 6.04 days. Decay Date: 1984-09-05. Flight Crew: Coats, Hartsfield, Hawley, Mullane, Resnik, Walker. Flight: STS-41-D. 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.References: 1, 2, 5, 6, 7, 33.

• SBS 4 Nation: USA. Program: SBS. Payload: SBS D / PAM-D. Mass: 1,117 kg (2,462 lb). Class: Communications. Spacecraft: HS 376. Agency: SBS. Perigee: 35,780 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 6.80 deg. Period: 1,436.20 min. COSPAR: 1984-093B. USAF Sat Cat: 15235. 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.References: 1, 2, 5, 6.

• Syncom IV-2 Nation: USA. Payload: Discovery F1 / SBS 4 [PAM-D] / Telstar 302 [PAM-D]. Mass: 1,315 kg (2,899 lb). Class: Communications. Spacecraft: HS 381. Agency: HCI. Perigee: 36,448 km (22,647 mi). Apogee: 36,741 km (22,829 mi). Inclination: 13.00 deg. Period: 1,477.60 min. COSPAR: 1984-093C. USAF Sat Cat: 15236. Completed Operations Date: 1996-10-10. 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.References: 1, 2, 5, 6.

• Telstar 3C Nation: USA. Program: Telstar. Payload: Telstar 302 [PAM-D]. Mass: 625 kg (1,377 lb). Class: Communications. Spacecraft: HS 376. Agency: AT&T. Perigee: 35,901 km (22,307 mi). Apogee: 35,948 km (22,337 mi). Inclination: 5.70 deg. Period: 1,443.20 min. COSPAR: 1984-093D. USAF Sat Cat: 15237. Completed Operations Date: 1997-09-05. 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.References: 1, 2, 5, 6.

• OAST 1 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1984-093xx. USAF Sat Cat: 15234. Decay Date: 1984-09-05. References: 279.

• STS-41-G Nation: USA. Program: STS. Payload: Challenger F06 / ERBS / LFC / ORS. Mass: 10,643 kg (23,463 lb). Class: Manned. Type: Spaceplane. Spacecraft: Challenger. Agency: NASA JSC. Perigee: 350 km (210 mi). Apogee: 390 km (240 mi). Inclination: 51.70 deg. Period: 92.00 min. COSPAR: 1984-108A. USAF Sat Cat: 15353. Duration: 8.22 days. Decay Date: 1984-10-13. Flight Crew: Crippen, Garneau, Leestma, McBride, Ride, Scully-Power, Sullivan. Flight: STS-41-G. 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. In response to the American Strategic Defence Initiative and continued military use of the shuttle, the Soviet Union fired a 'warning shot' from the Terra-3 laser complex at Sary Shagan. The facility tracked Challenger with a low power laser on 10 October 1984. This caused malfunctions to on-board equipment and discomfort / temporary blinding of the crew, leading to a US diplomatic protest.References: 1, 2, 5, 6, 7, 33.

• ERBS Nation: USA. Payload: Challenger F6 / ERBS. Mass: 226 kg (498 lb). Class: Earth. Type: Magnetosphere. Spacecraft: ERBS. Agency: NASA GSF. Perigee: 576 km (357 mi). Apogee: 589 km (365 mi). Inclination: 57.00 deg. Period: 96.30 min. COSPAR: 1984-108B. USAF Sat Cat: 15354. Earth Radiation Budget Satellite. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• LFC/ORS Nation: USA. Program: STS. Payload: MPESS. Agency: NASA. COSPAR: 1984-108xx. USAF Sat Cat: 15353. Decay Date: 1984-10-13. References: 279.

• OSTA-3 Nation: USA. Program: STS. Agency: NASA. COSPAR: 1984-108xx. USAF Sat Cat: 15353. Decay Date: 1984-10-13. References: 279.

• STS-51-A Nation: USA. Program: STS. Payload: Discovery F02 / PLT. Mass: 20,550 kg (45,300 lb). Class: Manned. Type: Spaceplane. Spacecraft: Discovery. Agency: NASA JSC. Perigee: 289 km (179 mi). Apogee: 297 km (184 mi). Inclination: 28.40 deg. Period: 90.40 min. COSPAR: 1984-113A. USAF Sat Cat: 15382. Duration: 7.99 days. Decay Date: 1984-11-16. Flight Crew: Allen, Fisher, Gardner, Hauck, Walker Dave. Flight: STS-51-A. 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.References: 1, 2, 5, 6, 7, 33.

• Anik D2 Nation: Canada. Program: Anik. Payload: Anik D2 [PAM-D]. Mass: 1,100 kg (2,400 lb). Class: Communications. Spacecraft: HS 376. Agency: Telesat. Perigee: 36,076 km (22,416 mi). Apogee: 36,271 km (22,537 mi). Inclination: 6.70 deg. Period: 1,455.90 min. COSPAR: 1984-113B. USAF Sat Cat: 15383. Completed Operations Date: 1995-02-10. 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.References: 1, 2, 5, 6.

• Syncom IV-1 Nation: USA. Payload: Discovery F2 / Anik D2 / Syncom-4 1. Mass: 1,315 kg (2,899 lb). Class: Communications. Spacecraft: HS 381. Agency: HCI. Perigee: 36,152 km (22,463 mi). Apogee: 36,403 km (22,619 mi). Inclination: 7.60 deg. Period: 1,461.20 min. COSPAR: 1984-113C. USAF Sat Cat: 15384. Completed Operations Date: 1992-09-26. 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.References: 1, 2, 5, 6.

• STS-51-C Nation: USA. Program: STS. Payload: Discovery F03 / Magnum 1 [IUS]. Class: Manned. Type: Spaceplane. Spacecraft: Discovery. Agency: NASA JSC. Perigee: 332 km (206 mi). Apogee: 341 km (211 mi). Inclination: 28.40 deg. Period: 91.30 min. COSPAR: 1985-010A. USAF Sat Cat: 15496. Duration: 3.06 days. Decay Date: 1985-01-27. Flight Crew: Buchli, Mattingly, Onizuka, Payton, Shriver. Flight: STS-51-C. 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.References: 1, 2, 5, 6, 7, 33.

• USA 8 Nation: USA. Payload: Magnum 1 [IUS]. Class: Sigint. Spacecraft: Magnum. Agency: NRO/USAF. Perigee: 341 km (211 mi). Apogee: 34,670 km (21,540 mi). Inclination: 28.40 deg. Period: 612.30 min. COSPAR: 1985-010B. USAF Sat Cat: 15543. 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. References: 1, 2, 5, 6, 172.

• STS-51-D Nation: USA. Program: STS. Payload: Discovery F04 / Anik C1[PAM-D] / Syncom-4 3 /Orbus. Mass: 16,249 kg (35,822 lb). Class: Manned. Type: Spaceplane. Spacecraft: Discovery. Agency: NASA JSC. Perigee: 445 km (276 mi). Apogee: 535 km (332 mi). Inclination: 28.50 deg. Period: 94.40 min. COSPAR: 1985-028A. USAF Sat Cat: 15641. Duration: 7.00 days. Decay Date: 1985-04-19. Flight Crew: Bobko, Garn, Griggs, Hoffman, Seddon, Walker, Williams Donald. Flight: STS-51-D. 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).References: 1, 2, 5, 6, 7, 33.

• Anik C1 Nation: Canada. Program: Anik. Payload: Anik C1 [PAM-D]. Mass: 1,238 kg (2,729 lb). Class: Communications. Spacecraft: HS 376. Agency: Telesat. Perigee: 35,783 km (22,234 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.20 min. COSPAR: 1985-028B. USAF Sat Cat: 15642. Completed Operations Date: 2000-04-14. Released by STS 51D 4/13/85; 107.5 deg W. Telecommunications. O