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Cape Canaveral LC36A

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First Launch: 1962-05-08. Last Launch: 2004-08-31. Number: 69 . Longitude: -80.54 deg. Latitude: 28.47 deg.

This complex was built for the Atlas/Centaur development program, and it was operated under NASA's sponsorship from that program's inception until the late 1980s. The site was built and occupied as a single launch pad complex in February 1961. Complex 36 hosted many historic Surveyor, Mariner, Pioneer and Intelsat IV and V missions over the years. Under NASA's sponsorship, Complex 36 supported its first Fleet Satellite Communications (Fltsatcom) launch on 9 February 1978. Six more Fltsatcom missions were launched from the complex over the next decade. Following the Fltsatcom F-8 mission in late September 1989, NASA surrendered Complex 36 to the Air Force and General Dynamics for military and commercial space operations. The site was modified to handled Atlas/Centaur missions. The first military Atlas II/Centaur mission was launched from Pad 36A on 11 February 1992. In all, the complex supported 118 major launches between 8 May 1962 and the end of October 1998.

• Research and development test - . Nation: USA. Agency: NASA. Apogee: 6.00 km (3.70 mi).

  The first attempt to launch an Atlas/Centaur from the Atlantic Missile Range was unsuccessful when the Centaur stage blew up at T+55 seconds due to a second stage structural failure. Despite this failure, the launch marked the first U.S. use of a space vehicle fueled by a liquid hydrogen engine. First Centaur flight (unsuccessful).

• Atlas Centaur 2 - . Payload: Centaur 2B. Mass: 4,620 kg (10,180 lb). Nation: USA. Agency: NASA Cleveland. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. USAF Sat Cat: 694 . COSPAR: 1963-047A. Apogee: 1,478 km (918 mi). Perigee: 469 km (291 mi). Inclination: 30.40 deg. Period: 104.60 min.

  Launched from Cape Canaveral, Atlas/Centaur (AC-2) was the first successful use of the high-energy liquid hydrogen/ liquid oxygen Centaur upper stage vehicle developed for NASA by General Dynamics. The spent Centaur stage entered orbit. Launch vehicle test. Launch vehicle put dummy payload into geosynchronous transfer orbit. First successful Centaur (liquid hydrogen-fueled) flight.

• Centaur AC-3 - . Payload: Centaur 1C. Mass: 4,815 kg (10,615 lb). Nation: USA. Agency: NASA. Decay Date: 1964-06-30 . Apogee: 500 km (310 mi). Centaur test. Launch vehicle was to have put payload into geosynchronous transfer orbit.

• Surveyor SD-1 - . Payload: Surveyor SD-1. Mass: 2,944 kg (6,490 lb). Nation: USA. Agency: JPL, NASA. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. Decay Date: 1964-12-12 . USAF Sat Cat: 951 . COSPAR: 1964-082A. Apogee: 178 km (110 mi). Perigee: 165 km (102 mi). Inclination: 30.70 deg. Period: 87.80 min. Launch vehicle test. Centaur AC-4 put dummy Surveyor payload into geosynchronous transfer orbit.

• Surveyor SD-1 - . Payload: Surveyor SD-1. Mass: 951 kg (2,096 lb). Nation: USA. Agency: NASA. Spacecraft: Surveyor. Decay Date: 1965-03-02 . Launch vehicle test. Launch vehicle was to have put payload into geosynchronous transfer orbit.

• Surveyor 1 - . Payload: Surveyor SC-1. Mass: 269 kg (593 lb). Nation: USA. Agency: JPL, NASA. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. Decay Date: 1966-06-02 . USAF Sat Cat: 2185 . COSPAR: 1966-045A.

  The first operational Atlas/Centaur (AC-10) carried the NASA Surveyor I spacecraft to the moon in a direct ascent lunar transfer trajectory. This was the first in a series of seven Surveyors designed to develop soft-landing technology and to provide basic scientific and engineering data in support of Project Apollo. On 2 June, Surveyor I became the first U.S. spacecraft to soft-land on the moon and transmit television pictures Surveyor 1 soft landed on the moon in the Ocean of Storms and began transmitting the first of more than 11,150 clear, detailed television pictures to Jet Propulsion Laboratory's Deep Space Facility, Goldstone, Calif. The landing sequence began 3,200 kilometers above the moon with the spacecraft traveling at a speed of 9,700 kilometers per hour. The spacecraft was successfully slowed to 5.6 kilometers per hour by the time it reached 4-meter altitude and then free-fell to the surface at 13 kilometers per hour. The landing was so precise that the three footpads touched the surface within 19 milliseconds of each other, and it confirmed that the lunar surface could support the LM. It was the first U.S. attempt to soft land on the moon.

• Surveyor 2 - . Payload: Surveyor SC-2. Mass: 292 kg (643 lb). Nation: USA. Agency: JPL, NASA. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. Decay Date: 1966-09-23 . USAF Sat Cat: 2425 . COSPAR: 1966-084A.

  Soft lunar landing attempt failed. Surveyor II was launched from Cape Kennedy at 8:32 a.m. EDT. The Atlas-Centaur launch vehicle placed the spacecraft on a nearly perfect lunar intercept trajectory that would have missed the aim point by about 130 kilometers. Following injection, the spacecraft successfully accomplished all required sequences up to the midcourse thrust phase. This phase was not successful because of the failure of one of the three vernier engines to ignite, causing eventual loss of the mission. Contact with the spacecraft was lost at 5:35 a.m. EDT, September 22, and impact on the lunar surface was predicted at 11:18 p.m. on that day.

• Surveyor 4 - . Payload: Surveyor SC-4. Mass: 283 kg (623 lb). Nation: USA. Agency: JPL, NASA. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. Decay Date: 1967-07-17 . USAF Sat Cat: 2875 . COSPAR: 1967-068A. Soft lunar landing attempt failed..

• Surveyor 7 - . Payload: Surveyor SC-7. Mass: 1,036 kg (2,283 lb). Nation: USA. Agency: JPL, NASA. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. Decay Date: 1968-01-10 . USAF Sat Cat: 3091 . COSPAR: 1968-001A. Soft landed on lunar Moon; photographed lunar surface; sampled lunar soil..

• ATS 4 - . Payload: ATS D. Mass: 391 kg (862 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: HS 306. Spacecraft: ATS-4. Decay Date: 1968-08-10 . USAF Sat Cat: 3344 . COSPAR: 1968-068A. Apogee: 769 km (477 mi). Perigee: 220 km (130 mi). Inclination: 29.10 deg. Period: 94.50 min.

  Applications Technology Satellite that was to have been put into a geosynchronous transfer orbit, instead was left in a nearly-useless LEO orbit. ATS-4 included two cesium contact ion engines. Flight test objectives were to measure thrust and to examine electromagnetic compatibility with other spacecraft subsystems. The 5 cm diameter thrusters were designed to operate at 0.02 kW and provide about 89 microN thrust at about 6700 s specific impulse. The thrusters had the capability to operate at 5 setpoints from 18 to 89 microN. Thrusters were configured so they could be used for East-West station-keeping. Prior to launch, a 5 cm cesium thruster was life tested for 2245 hours at the 67 microN thrust level. However the Centaur upper stage did not achieve a second burn and the spacecraft remained attached to the Centaur in a 218 km by 760 km orbit. It was estimated that the pressure at these altitudes was between 10^-6 and 10^-8 Torr. Each of the two engines was tested on at least two occasions each over the throttling range. Combined test time of the two engines was about 10 hours over a 55 day period. The spacecraft re-entered the atmosphere on October 17, 1968. TheATS-4 flight was the first successful orbital test of an ion engine. There was no evidence of IPS electromagnetic interference related to spacecraft subsystems. Measured values of neutralizer emission current were much less than the ion beam current, implying inadequate neutralization. The spacecraft potential was about -132V which was much different than the anticipated value of about -40V.

• Mariner 7 - . Payload: Mariner 69-2. Mass: 412 kg (908 lb). Nation: USA. Agency: JPL, NASA. Program: Mariner. Class: Mars. Type: Mars probe. Spacecraft Bus: Mariner. Spacecraft: Mariner 6-7. USAF Sat Cat: 3837 . COSPAR: 1969-030A.

  Mars flyby 5 August 1969; returned 126 images of Martian surface. Mariner 7 was launched on a direct-ascent trajectory to Mars 31 days after Mariner 6. On 8 April 1969 a midcourse correction was made by firing the hydrazine moter for 7.6 seconds. On 8 May Mariner 7 was put on gyro control to avoid attitude control problems which were affecting Mariner 6. On 31 July telemetry from Mariner 7 was suddenly lost and the spacecraft was commanded to switch to the low-gain antenna. It was later successfully switched back to the high-gain antenna. It was thought that leaking gases, perhaps from the battery which later failed a few days before encounter, had caused the anomaly.

  At 09:32:33 GMT on 2 August 1969 Mariner 7 bagan the far-encounter sequence involving imaging of Mars with the narrow angle camera. Over the next 57 hours, ending about 5 hours before closest approach, 93 images of Mars were taken and transmitted. The spacecraft was reprogrammed as a result of analysis of Mariner 6 images. The new sequence called for the spacecraft to go further south than originally planned, take more near-encounter pictures, and collect more scientific data on the lighted side of Mars. Data from the dark side of Mars were to be transmitted directly back to Earth but there would be no room on the digital recorder for backup due to the added dayside data. At closest approach, 05:00:49 GMT on 5 August, Mariner 7 was 3430 km above the martian surface. Over this period, 33 near-encounter images were taken. About 19 minutes after the flyby, the spacecraft went behind Mars and emerged roughly 30 minutes later. X-band occultation data were taken during the entrance and exit phases. Science and imaging data were played back and transmitted over the next few days. The spacecraft was then returned to cruise mode which included engineering and communications tests, star photography TV tests, and UV scans of the Milky Way and an area containing comet 1969-B. Periodic tracking of the spacecraft in its heliocentric orbit was also done.

  Science Results

  The total data return for Mariners 6 and 7 was 800 million bits. Mariner 7 returned 93 far and 33 near encounter images. Close-ups from the near encounter phases covered 20% of the surface. The spacecraft instruments measured UV and IR emissions and radio refractivity of the Martian atmosphere. Images showed the surface of Mars to be very different from that of the Moon, in some contrast to the results from Mariner 4. The south polar cap was identified as being composed predominantly of carbon dioxide. Atmospheric surface pressure was estimated at between 6 and 7 mb. Radio science refined estimates of the mass, radius and shape of Mars.

• ATS 5 - . Payload: ATS E. Mass: 821 kg (1,809 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-5. Completed Operations Date: 1984-01-01 . USAF Sat Cat: 4068 . COSPAR: 1969-069A. Apogee: 36,024 km (22,384 mi). Perigee: 35,992 km (22,364 mi). Inclination: 14.50 deg. Period: 1,447.40 min.

  Applications Technology Satellite; communications tests. Launch vehicle successfully put the payload into a geosynchronous transfer orbit. The spacecraft maneuvered into geostationary orbit at 108 degrees W. The purpose of this flight was to demonstrate North-South Stationkeeping of a geosynchronous satellite. ATS-5 was equipped with an ion engine package identical to that on ATS-4. Once in geosynchronous orbit the spacecraft could not be despun as planned, and thus the spacecraft gravity gradient stabilization could not be implemented. The spacecraft spin rate was about 76 revolutions per minute, and this caused an effective 4g acceleration on the cesium feed system. The high g-loading on the cesium feed system caused flooding of the discharge chamber, and normal operation of the thruster with ion beam extraction could not be performed. The IPS was instead be operated as a neutral plasma source, without high-voltage ion extraction, along with the wire neutralizer to examine spacecraft charging effects. The neutralizer was also operated by itself to provide electron injection for the spacecraft charging experiments. Positioned in geosynchronous orbit over the Americas at 105 deg W in 1969-1977; over the Americas at 70 deg W in 1977-1983. As of 1 September 2001 located at 15.48 deg E drifting at 2.807 deg W per day. As of 2007 Mar 10 located at 111.70E drifting at 2.819W degrees per day.

• Intelsat 4 F-2 - . Mass: 706 kg (1,556 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4. Completed Operations Date: 1983-05-11 . USAF Sat Cat: 4881 . COSPAR: 1971-006A. Apogee: 36,236 km (22,515 mi). Perigee: 36,151 km (22,463 mi). Inclination: 15.30 deg. Period: 1,457.00 min.

  Launch vehicle put payload into geosynchronous transfer orbit; the satellite performed the apogee burn and positioned itself in geosynchronous orbit over the Atlantic Ocean at 24.5 deg W. Subsequently at 23 deg W in 1971-1975; over the Atlantic Ocean 1-6 deg W in 1976-1980; over the Atlantic Ocean 0-5 deg E in 1980-1983. As of 3 September 2001 at 31.91 deg E drifting at 5.168 deg W per day. As of 2006 Dec 18 located at 133.93E drifting at 5.166W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• Mariner H - . Payload: Mariner 71H. Mass: 996 kg (2,195 lb). Nation: USA. Agency: NASA. Program: Mariner. Class: Mars. Type: Mars probe. Spacecraft Bus: Mariner. Spacecraft: Mariner 8-9. Decay Date: 1971-05-08 . Intended Mars flyby..

• Intelsat 4 F-3 - . Mass: 1,410 kg (3,100 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4. Completed Operations Date: 1984-02-23 . USAF Sat Cat: 5709 . COSPAR: 1971-116A. Apogee: 36,009 km (22,374 mi). Perigee: 35,930 km (22,320 mi). Inclination: 11.10 deg. Period: 1,445.50 min.

  Over Atlantic. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Atlantic Ocean at 20-25 deg W in 1972-1976; over the Atlantic Ocean 34 deg W in 1976-1977; over the Atlantic Ocean 18-22 deg W in 1977-1980; over the Atlantic Ocean 53 deg W in 1981-1982; over the Atlantic Ocean 38-44 deg W in 1982-1983 As of 4 September 2001 located at 90.58 deg E drifting at 2.365 deg W per day. As of 2007 Mar 10 located at 54.69E drifting at 2.365W degrees per day.

• Pioneer 10 - . Payload: Pioneer F. Mass: 259 kg (570 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Outer planets. Type: Outer planets probe. Spacecraft: Pioneer 10-11. USAF Sat Cat: 5860 . COSPAR: 1972-012A.

  Jupiter flyby December 1973; first man-made object to leave solar system. The spacecraft achieved its closest approach to Jupiter on December 3, 1973, when it reached approximately 2.8 Jovian radii (about 200,000 km). As of Jan. 1, 1997 Pioneer 10 was at about 67 AU from the Sun near the ecliptic plane and heading outward from the Sun at 2.6 AU/year and downstream through the heliomagnetosphere towards the tail region and interstellar space. Additional Details: here....

• Intelsat 4 F-7 - . Mass: 1,410 kg (3,100 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4. Completed Operations Date: 1984-02-23 . USAF Sat Cat: 6796 . COSPAR: 1973-058A. Apogee: 36,132 km (22,451 mi). Perigee: 36,080 km (22,410 mi). Inclination: 10.40 deg. Period: 1,452.50 min.

  Over Atlantic Ocean. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Atlantic Ocean at 30 deg W in 1973-1976 over the Atlantic Ocean 1 deg W in 1976-1980; over the Indian Ocean 56 deg E in 1980-1981; over the Pacific Ocean179 deg E in 1981-1982; over the Atlantic Ocean 53 deg W in 1982-1983 As of 31 August 2001 located at 74.52 deg W drifting at 4.067 deg W per day. As of 2007 Mar 10 located at 19.61E drifting at 4.058W degrees per day.

• Intelsat 4 F-6 - . Mass: 1,410 kg (3,100 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4. Decay Date: 1975-02-20 . Staging electrical disconnect. Launch vehicle was to have put payload into geosynchronous transfer orbit.

• Intelsat 4 F-1 - . Mass: 727 kg (1,602 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4. Completed Operations Date: 1987-10-27 . USAF Sat Cat: 7815 . COSPAR: 1975-042A. Apogee: 36,128 km (22,448 mi). Perigee: 36,016 km (22,379 mi). Inclination: 8.90 deg. Period: 1,450.70 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Indian Ocean at 63 deg E in 1976-1978; over the Atlantic Ocean 17.0 deg W in 1978; over the Atlantic Ocean 18.5 deg W in 1979-1981; over the Pacific Ocean 174 deg E in 1982; over the Atlantic Ocean 53 deg W in 1983-1984; over the Atlantic Ocean 50 deg W in 1984-1987 As of 30 August 2001 located at 111.08 deg W drifting at 3.657 deg W per day. As of 2007 Mar 11 located at 95.13E drifting at 3.657W degrees per day.

• Comstar 1 - . Payload: Comstar 1A. Mass: 792 kg (1,746 lb). Nation: USA. Agency: Comsat. Program: Comstar. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4A. Completed Operations Date: 1984-10-26 . USAF Sat Cat: 8838 . COSPAR: 1976-042A. Apogee: 35,925 km (22,322 mi). Perigee: 35,903 km (22,309 mi). Inclination: 12.70 deg. Period: 1,442.60 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Americas at 128 deg W in 1976-1981 over the Americas at 95 deg W in 1981-1983 over the Atlantic Ocean 76 deg W in 1983-1984 As of 4 September 2001 located at 48.64 deg E drifting at 1.641 deg W per day. As of 2007 Mar 10 located at 31.21E drifting at 1.624W degrees per day.

• Intelsat 4A F-4 - . Mass: 1,500 kg (3,300 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4A. Completed Operations Date: 1989-08-10 . USAF Sat Cat: 10024 . COSPAR: 1977-041A. Apogee: 36,075 km (22,415 mi). Perigee: 35,969 km (22,350 mi). Inclination: 7.80 deg. Period: 1,448.20 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Atlantic Ocean at 34.5 deg W in 1977-1983 over the Atlantic Ocean 21.5 deg W in 1983-1989 As of 28 August 2001 located at 153.30 deg E drifting at 2.976 deg W per day. As of 2007 Mar 10 located at 121.69W drifting at 3.003W degrees per day.

• Intelsat IVA F-5 - . Mass: 1,500 kg (3,300 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4A. Decay Date: 1977-09-29 .

• Fltsatcom 1 - . Mass: 1,884 kg (4,153 lb). Nation: USA. Agency: USN. Class: Communications. Type: Military communications satellite. Spacecraft: Fltsatcom. USAF Sat Cat: 10669 . COSPAR: 1978-016A. Apogee: 36,170 km (22,470 mi). Perigee: 36,119 km (22,443 mi). Inclination: 14.60 deg. Period: 1,454.40 min.

  An Atlas booster was launched from Cape Canaveral carrying the first FLTSATCOM satellite. The launch was successful, and the satellite functioned normally once in orbit. It was declared operational on 4 April. Fleet Satellite Communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Americas at 100 deg W in 1978-1987; over the Pacific Ocean 177 deg W in 1987-1992; over the Atlantic Ocean 15 deg W in 1992-1996;over the Indian Ocean 72 deg E in 1996-2001. Last known longitude (26 July 1999) 71.17 deg E drifting at 0.004 deg W per day.

• Pioneer Venus Orbiter - . Payload: Pioneer-Venus 1. Mass: 582 kg (1,283 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Venus. Type: Venus probe. Spacecraft: Pioneer 12. Decay Date: 1992-10-22 . USAF Sat Cat: 10911 . COSPAR: 1978-051A.

  The Pioneer Venus Orbiter was inserted into an elliptical orbit around Venus on December 4, 1978. After entering orbit around Venus in 1978, the spacecraft returned global maps of the planet's clouds, atmosphere and ionosphere, measurements of the atmosphere-solar wind interaction, and radar maps of 93 percent of the planet's surface. Additionally, the vehicle made use of several opportunities to make systematic UV observations of several comets. From Venus orbit insertion to July 1980, periapsis was held between 142 and 253 km (at 17 degrees north latitude) to facilitate radar and ionospheric measurements. The spacecraft was in a 24 hour orbit with an apoapsis of 66,900 km. Thereafter, the periapsis was allowed to rise (to 2290 km at maximum) and then fall, to conserve fuel. In 1991 the Radar Mapper was reactivated to investigate previously inaccessible southern portions of the planet. In May 1992 Pioneer Venus began the final phase of its mission, in which the periapsis was held between 150 and 250 km until the fuel ran out and atmospheric entry destroyed the spacecraft. With a planned primary mission duration of only eight months, the spacecraft remained in operation until October 8, 1992 when it finally burned up in Venus' atmosphere after running out of propellant.

• Pioneer Venus 2 - . Payload: Pioneer-Venus 2. Mass: 904 kg (1,992 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Venus. Type: Venus probe. Spacecraft: Pioneer 13. Decay Date: 1978-12-09 . USAF Sat Cat: 11001 . COSPAR: 1978-078A.

  The Pioneer Venus Multiprobe consisted of a bus which carried one large and three small `atmospheric probes. The large probe was released on November 16, 1978 and the three small probes on November 20. All four probes entered the Venus atmosphere on December 9, followed by the bus. The small probes were each targeted at different parts of the planet and were named accordingly. The North probe entered the atmosphere at about 60 degrees north latitude on the day side. The night probe entered on the night side. The day probe entered well into the day side, and was the only one of the four probes which continued to send radio signals back after impact, for over an hour. With no heat shield or parachute, the bus survived and made measurements only to about 110 km altitude before burning up. It afforded the only direct view of the upper Venus atmosphere, as the probes did not begin making direct measurements until they had decelerated lower in the atmosphere.

• Pioneer Venus Probe 1 - . Payload: Pioneer-Venus 2. Mass: 315 kg (694 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Venus. Type: Venus probe. Spacecraft: Pioneer 13. Decay Date: 1978-12-09 . USAF Sat Cat: 12103 . COSPAR: 1978-078D.

• Pioneer Venus Probe 4 - . Payload: Pioneer-Venus 2. Mass: 90 kg (198 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Venus. Type: Venus probe. Spacecraft: Pioneer 13. Decay Date: 1978-12-09 . USAF Sat Cat: 12106 . COSPAR: 1978-078G.

• Pioneer Venus Probe 2 - . Payload: Pioneer-Venus 2. Mass: 90 kg (198 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Venus. Type: Venus probe. Spacecraft: Pioneer 13. Decay Date: 1978-12-09 . USAF Sat Cat: 12104 . COSPAR: 1978-078E.

• Pioneer Venus Probe 3 - . Payload: Pioneer-Venus 2. Mass: 90 kg (198 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Venus. Type: Venus probe. Spacecraft: Pioneer 13. Decay Date: 1978-12-09 . USAF Sat Cat: 12105 . COSPAR: 1978-078F.

• Fltsatcom 2 - . Mass: 1,884 kg (4,153 lb). Nation: USA. Agency: USN. Class: Communications. Type: Military communications satellite. Spacecraft: Fltsatcom. Completed Operations Date: 1992-02-12 . USAF Sat Cat: 11353 . COSPAR: 1979-038A. Apogee: 36,331 km (22,574 mi). Perigee: 36,227 km (22,510 mi). Inclination: 13.50 deg. Period: 1,461.30 min.

  The second FLTSATCOM satellite was successfully launched from Cape Canaveral, Florida, on board an Atlas/Centaur booster. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 23 deg W in 1979-1980; 72 deg E in 1980-1992 As of 5 September 2001 located at 90.48 deg W drifting at 6.234 deg W per day. As of 2007 Mar 9 located at 12.01W drifting at 6.223W degrees per day.

• Fltsatcom 3 - . Mass: 1,884 kg (4,153 lb). Nation: USA. Agency: USN. Class: Communications. Type: Military communications satellite. Spacecraft: Fltsatcom. Completed Operations Date: 1991-01-01 . USAF Sat Cat: 11669 . COSPAR: 1980-004A. Apogee: 35,851 km (22,276 mi). Perigee: 35,669 km (22,163 mi). Inclination: 9.10 deg. Period: 1,434.80 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 22 deg W in 1980-1990 As of 28 August 2001 located at 174.83 deg W drifting at 0.082 deg W per day. As of 2007 Mar 10 located at 84.20W drifting at 0.376E degrees per day.

• Fltsatcom 4 - . Mass: 1,800 kg (3,900 lb). Nation: USA. Agency: USN. Class: Communications. Type: Military communications satellite. Spacecraft: Fltsatcom. USAF Sat Cat: 12046 . COSPAR: 1980-087A. Apogee: 35,803 km (22,246 mi). Perigee: 35,769 km (22,225 mi). Inclination: 9.20 deg. Period: 1,436.10 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 171 deg E from 1981. Last known longitude (25 July 1999) 172.61 deg E drifting at 0.001 deg W per day.

• Comstar 4 - . Payload: Comstar 1D. Mass: 1,520 kg (3,350 lb). Nation: USA. Agency: Comsat. Program: Comstar. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 312 / HS 351 / HS 353. Spacecraft: Intelsat 4A. USAF Sat Cat: 12309 . COSPAR: 1981-018A. Apogee: 35,792 km (22,240 mi). Perigee: 35,783 km (22,234 mi). Inclination: 7.20 deg. Period: 1,436.20 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 142 deg W in 1981; 127 deg W in 1981-1985; 76 deg W in 1985-on. As of 31 August 2001 located at 25.65 deg W drifting at 1.067 deg E per day. As of 2007 Mar 11 located at 78.95E drifting at 0.039W degrees per day.

• Fltsatcom 5 - . Mass: 1,884 kg (4,153 lb). Nation: USA. Agency: USN. Class: Communications. Type: Military communications satellite. Spacecraft: Fltsatcom. Completed Operations Date: 1986-07-12 . USAF Sat Cat: 12635 . COSPAR: 1981-073A. Apogee: 36,300 km (22,500 mi). Perigee: 36,221 km (22,506 mi). Inclination: 8.90 deg. Period: 1,460.40 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit. The Atlas G Centaur delivered a badly damaged but operating FLTSATCOM spacecraft to its correct orbit. Investigation showed that the most likely cause was failure of the fiberglass fairing during ascent. Positioned in geosynchronous orbit at 90 deg W in 1981; 90-114 deg W in 1982; 44 deg W in 1982-1986 As of 5 September 2001 located at 140.32 deg W drifting at 6.003 deg W per day. As of 2007 Mar 10 located at 31.85E drifting at 6.002W degrees per day.

• Intelsat 5 F-4 - . Mass: 1,928 kg (4,250 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 5. Completed Operations Date: 1995-11-28 . USAF Sat Cat: 13083 . COSPAR: 1982-017A. Apogee: 36,243 km (22,520 mi). Perigee: 35,920 km (22,310 mi). Inclination: 9.40 deg. Period: 1,451.20 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 32 deg E in 1982; 63 deg E in 1982; 27 deg W in 1983-1985; 34 deg W in 1985-1992; 40 deg W in 1992; 31 deg W in 1993-1995; 29 deg W in 1995 As of 1 September 2001 located at 4.64 deg W drifting at 3.747 deg W per day. As of 2007 Mar 7 located at 4.34W drifting at 3.748W degrees per day.

• Intelsat 5 F-6 - . Mass: 1,928 kg (4,250 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 5. Completed Operations Date: 1998-07-06 . USAF Sat Cat: 14077 . COSPAR: 1983-047A. Apogee: 36,125 km (22,446 mi). Perigee: 36,076 km (22,416 mi). Inclination: 8.30 deg. Period: 1,452.10 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 29 deg E in 1983; 18 deg W in 1983-1992; 34 deg W in 1992; 50 deg W in 1992-1995; 31 deg W in 1995-1998 As of 4 September 2001 located at 47.96 deg E drifting at 3.999 deg W per day. As of 2007 Mar 10 located at 62.15W drifting at 3.995W degrees per day.

• USA 78 - . Payload: DSCS III B-14. 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: 21873 . COSPAR: 1992-006A. Apogee: 35,503 km (22,060 mi). Perigee: 30,675 km (19,060 mi). Inclination: 0.90 deg. Period: 1,300.50 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit; at 135 deg W in 1995..

• USA 82 - . Payload: DSCS III B-12. 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: 22009 . COSPAR: 1992-037A. Apogee: 35,800 km (22,200 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.20 deg. Period: 1,436.20 min.

  Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 12 deg W in 1995-1996. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• USA 93 - . Payload: DSCS III B-9. Mass: 2,615 kg (5,765 lb). Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 22719 . COSPAR: 1993-046A. Apogee: 35,764 km (22,222 mi). Perigee: 183 km (113 mi). Inclination: 26.10 deg. Period: 625.80 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 175 deg E in 1995-1997.

• USA 97 - . Payload: DSCS III B-10. Mass: 2,615 kg (5,765 lb). Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 22915 . COSPAR: 1993-074A. Apogee: 35,501 km (22,059 mi). Perigee: 195 km (121 mi). Inclination: 26.40 deg. Period: 625.40 min.

  Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 52 deg W in 1995; 60 deg E in 1997. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

• DBS 2 - . Mass: 2,860 kg (6,300 lb). Nation: USA. Agency: DirecTV. Program: DirecTV. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23192 . COSPAR: 1994-047A. Apogee: 35,797 km (22,243 mi). Perigee: 35,776 km (22,230 mi). Inclination: 0.0100 deg. Period: 1,436.11 min.

  Commercial TV broadcast. Stationed at 100.79 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 101 deg W in 1994-1999 As of 5 September 2001 located at 100.81 deg W drifting at 0.010 deg W per day. As of 2007 Mar 11 located at 91.17W drifting at 0.006W degrees per day.

• Orion 1 - . Mass: 2,358 kg (5,198 lb). Nation: USA. Manufacturer: Toulouse. Program: Orion. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 2000. USAF Sat Cat: 23413 . COSPAR: 1994-079A. Apogee: 35,792 km (22,240 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  34 Ku-band transponders for TV. Stationed at 37.48 deg W. Launch vehicle put payload into supersynchronous earth orbit with IFR trajectory option. Positioned in geosynchronous orbit at 37 deg W in 1994-1999 As of 5 September 2001 located at 37.54 deg W drifting at 0.010 deg W per day. As of 2007 Mar 11 located at 37.60W drifting at 0.015W degrees per day.

• USA 108 - . Payload: UHF F/O F4. Mass: 3,023 kg (6,664 lb). Nation: USA. Agency: HCI. Program: UHF. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23467 . COSPAR: 1995-003A. Apogee: 35,799 km (22,244 mi). Perigee: 35,775 km (22,229 mi). Inclination: 2.20 deg. Period: 1,436.10 min. UHF Follow-On #4; US Navy communications . Stationed at 177.0 deg W. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 177 deg W in 1995-1999..

• AMSC-1 - . Mass: 2,700 kg (5,900 lb). Nation: USA. Agency: AMSC. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23553 . COSPAR: 1995-019A. Apogee: 35,796 km (22,242 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Mobile communicaitons. Stationed at 101.1 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 101 deg W in 1995-1999 As of 5 September 2001 located at 101.01 deg W drifting at 0.024 deg W per day. As of 2007 Mar 11 located at 100.99W drifting at 0.003W degrees per day.

• USA 111 - . Payload: UHF F/O F5-EHF. Mass: 3,015 kg (6,646 lb). Nation: USA. Agency: USN. Program: UHF. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23589 . COSPAR: 1995-027A. Apogee: 35,796 km (22,242 mi). Perigee: 35,774 km (22,228 mi). Inclination: 4.80 deg. Period: 1,436.10 min. UHF Follow-On #5; US Navy communications . Stationed at 72.3 deg E. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 72 deg E in 1995-1999..

• USA 113 - . Payload: DSCS III B-7. Mass: 2,610 kg (5,750 lb). Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 23628 . COSPAR: 1995-038A. Apogee: 35,787 km (22,236 mi). Perigee: 35,787 km (22,236 mi). Inclination: 0.00 deg. Positioned in geosynchronous orbit; located at 53 deg W in 1997..

• USA 114 - . Payload: UHF F/O F6-EHF. Mass: 3,015 kg (6,646 lb). Nation: USA. Agency: USN. Program: UHF. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23696 . COSPAR: 1995-057A. Apogee: 35,797 km (22,243 mi). Perigee: 35,776 km (22,230 mi). Inclination: 5.00 deg. Period: 1,436.10 min. UHF Follow-On #6; US Navy communications. Stationed at 105.3 deg W. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 105 deg W in 1995-1999..

• Galaxy 3R - . Payload: HS 376. Mass: 2,980 kg (6,560 lb). Nation: USA. Agency: HCI. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23741 . COSPAR: 1995-069A. Apogee: 35,799 km (22,244 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Stationed at 95 deg W; 24 C-band, 24 Ku-band transponders; TV for Caribbean and Central America. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 95 deg W in 1996-1999 As of 3 September 2001 located at 95.05 deg W drifting at 0.008 deg W per day. As of 2007 Mar 9 located at 132.80W drifting at 0.084W degrees per day.

• Inmarsat 3 F1 - . Mass: 2,068 kg (4,559 lb). Nation: International. Agency: Inmarsat. Manufacturer: Lockheed. Program: Inmarsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 4000. USAF Sat Cat: 23839 . COSPAR: 1996-020A. Apogee: 35,806 km (22,248 mi). Perigee: 35,767 km (22,224 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Geostationary at 64.1E. Launch vehicle put payload into geosynchronous transfer orbit with RAAN Cntl trajectory option. Positioned in geosynchronous orbit at 64 deg E in 1996-1999 As of 5 September 2001 located at 63.98 deg E drifting at 0.003 deg E per day. As of 2007 Mar 10 located at 64.52E drifting at 0.006W degrees per day.

• USA 127 - . Payload: UHF F/O F7-EHF. Mass: 3,015 kg (6,646 lb). Nation: USA. Agency: HCI. Program: UHF. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23967 . COSPAR: 1996-042A. Apogee: 35,791 km (22,239 mi). Perigee: 35,784 km (22,235 mi). Inclination: 4.90 deg. Period: 1,436.20 min. Positioned in geosynchronous orbit at 170 deg W in 1996; 23 deg W in 1996-1999; 100 deg W in 1999. As of 29 July 1999) 99.21 deg W drifting at 0.011 deg W per day. As of 2007 Feb 22 located at 21.85W drifting at 0.014W degrees per day..

• Hot Bird 2 - . Payload: Eurostar 2000+. Mass: 2,900 kg (6,300 lb). Nation: France. Agency: Eutelsat. Manufacturer: Toulouse. Program: Eutelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 2000. USAF Sat Cat: 24665 . COSPAR: 1996-067A. Apogee: 35,803 km (22,246 mi). Perigee: 35,768 km (22,225 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Geostationary at 13.0E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 13 deg E in 1997-1999 As of 3 September 2001 located at 12.95 deg E drifting at 0.024 deg E per day. As of 2007 Mar 4 located at 13.07E drifting at 0.011E degrees per day.

• Tempo 2 - . Mass: 3,640 kg (8,020 lb). Nation: USA. Agency: TCI. Manufacturer: Palo Alto. Program: Tempo. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 24748 . COSPAR: 1997-011A. Apogee: 35,792 km (22,240 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Geosynchronous. Stationed over 118.7W Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 119 deg W in 1997-1999 As of 5 September 2001 located at 118.82 deg W drifting at 0.001 deg W per day. As of 2007 Mar 10 located at 42.64E drifting at 4.479W degrees per day.

• GE 3 - . Payload: A2100A. Mass: 2,845 kg (6,272 lb). Nation: USA. Agency: GE Americom. Manufacturer: RCA. Program: Americom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 24936 . COSPAR: 1997-050A. Apogee: 35,795 km (22,241 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Geosynchronous. Stationed over 87.1W Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 87 deg W in 1997-1999 As of 3 September 2001 located at 87.12 deg W drifting at 0.002 deg W per day. As of 2007 Mar 11 located at 86.99W drifting at 0.010W degrees per day.

• USA 135 - . Payload: DSCS III B-13. Mass: 2,613 kg (5,760 lb). Nation: USA. Agency: USAF. Manufacturer: Valley Forge. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 25019 . COSPAR: 1997-065A. Apogee: 35,800 km (22,200 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.00 deg. Geosynchronous. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option..

• Falcon Gold - . Nation: USA. Agency: Lockheed. Manufacturer: USAF Colorado Springs. Class: Technology. Type: Navigation technology satellite. Spacecraft: Falcon Gold. Decay Date: 1998-09-27 . USAF Sat Cat: 25020 . COSPAR: 1997-065B. Apogee: 34,457 km (21,410 mi). Perigee: 151 km (93 mi). Inclination: 26.20 deg. Period: 185.80 min. US Air Force Academy experiment to demonstrate use of GPS navigation in geosynchronous orbit..

• USA 137 - . Payload: CAPRICORN?. Nation: USA. Agency: NRO. Manufacturer: El Segundo. Class: Communications. Type: Military communications satellite. Spacecraft: Quasar. USAF Sat Cat: 25148 . COSPAR: 1998-005A. Apogee: 35,800 km (22,200 mi). Perigee: 35,800 km (22,200 mi). Inclination: 0.00 deg. Period: 1,440.00 min.

  Classified satellite for the National Reconnaissance Office. It was likely that it was a technology test satellite combining equipment for several future projects, including a prototype COBRA BRASS infrared early warning satellite sensor. The project seemed to have been several years behind schedule (based on the launch vehicle serial number.

• USA 138 - . Payload: UHF F/O F8-EHF. Mass: 3,206 kg (7,068 lb). Nation: USA. Agency: USN. Manufacturer: El Segundo. Program: UHF. Class: Communications. Type: Military communications satellite. Spacecraft: HS 601. USAF Sat Cat: 25258 . COSPAR: 1998-016A. Apogee: 35,803 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 3.30 deg. Period: 1,436.10 min.

  UHF Follow-On F8 was the first Block III UHF Follow-On satellite, replacing the old FLTSATCOM satellites. It carried UHF, EHF and Ka-band transponders, including a video broadcast payload. This was the last Atlas II launch; future Atlas launches would use the Atlas IIA, IIAS and III models. Positioned in geosynchronous orbit at 172 deg E in 1998-1999.

• Intelsat 805 - . Mass: 3,520 kg (7,760 lb). Nation: International. Agency: Intelsat. Manufacturer: RCA. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 7000. USAF Sat Cat: 25371 . COSPAR: 1998-037A. Apogee: 35,800 km (22,200 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Satellite had 28 C-band and 3 Ku-band transponders, and initially served the Atlantic Ocean region for INTELSAT. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Geostationary at 55.5 degrees W. Positioned in geosynchronous orbit at 55 deg W in 1998-1999 As of 5 September 2001 located at 55.52 deg W drifting at 0.009 deg W per day. As of 2007 Mar 11 located at 55.54W drifting at 0.012W degrees per day.

• USA 140 - . Payload: UHF F/O F9. Mass: 3,200 kg (7,000 lb). Nation: USA. Agency: USN. Manufacturer: El Segundo. Program: UHF. Class: Technology. Type: Navigation technology satellite. Spacecraft: HS 601. USAF Sat Cat: 25501 . COSPAR: 1998-058A. Apogee: 35,806 km (22,248 mi). Perigee: 35,773 km (22,228 mi). Inclination: 3.80 deg. Period: 1,436.20 min.

  The orbit at burnout of the Centaur was 286 km x 25866 km x 27.0 degree. Modification of the orbit to a geostationary 38,300 km circular x 0.0 degree inclination was accomplished by the Marquardt R-4D liquid propellant motor on the HS-601 spacecraft. The satellite carried UHF and EHF transponders for naval communications, and a Ka-band Global Broadcast Service video relay package. Launch mass of 3200 kg dropped to 1550 kg once geostationary orbit was reached. UHF F/O F9 was placed over the Atlantic Ocean in geosynchronous orbit at 174 deg W in 1998; 22 deg W in 1999. Additional Details: here....

• JCSAT-6 - . Mass: 2,900 kg (6,300 lb). Nation: Japan. Agency: JSAT. Manufacturer: El Segundo. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 25630 . COSPAR: 1999-006A. Apogee: 35,791 km (22,239 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  JCSAT-6 carried a Ku-band relay system. It was operated by Japan Satellite Systems, Inc., Tokyo, provided communications and data relay for Japan and the Pacific Rim. Two burns of the Centaur upper stage placed it into a supersynchronous transfer orbit of 258 km x 96736 km x 24.1 degrees. JCSAT-6's on-board R-4D engine would maneuver it into its final geostationary location. Dry mass of the spacecraft was 1230 kg. Stationed at 124 deg E Positioned in geosynchronous orbit at 123 deg E in 1999. As of 5 September 2001 located at 124.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 10 located at 124.01E drifting at 0.011W degrees per day.

• Eutelsat W3 - . Payload: Spacebus 3000B2. Mass: 3,183 kg (7,017 lb). Nation: Europe. Agency: Eutelsat. Manufacturer: Cannes. Program: Eutelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 3000. USAF Sat Cat: 25673 . COSPAR: 1999-018A. Apogee: 35,803 km (22,246 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.10 deg. Period: 1,436.10 min.

  Communications satellite is for the European Telecommunications Satellite Organization. The vehicle entered a 153 km x 385 km x 27.4 deg parking orbit nine minutes after launch. The second Centaur stage burn delivered the satellite to a 166 km x 46,076 km x 19.7 deg super-synchronous transfer orbit. The satellite was stationed at 7 deg E and carried 24 Ku-band transponders with a wide beam covering Europe, North Africa and Asia, and a spot beam for digital TV to Turkey. Positioned in geosynchronous orbit at 7 deg E in 1999. As of 26 August 2001 located at 7.01 deg E drifting at 0.004 deg W per day. As of 2007 Mar 7 located at 21.59E drifting at 0.003E degrees per day.

• Echostar 5 - . Mass: 3,602 kg (7,941 lb). Nation: USA. Agency: PanAmSat. Manufacturer: Palo Alto. Program: Echostar. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 25913 . COSPAR: 1999-050A. Apogee: 35,795 km (22,241 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  The Centaur second stage put Echostar 5 into a supersynchronous transfer orbit of 131 km x 45526 km x 26.6 degrees. The satellite's own engine put it into the final geosynchronous orbit. Echostar 5 was a Ku-band satellite, part of the Dish Network. Stationed at 110 deg W. Positioned in geosynchronous orbit at 110 deg W in 1999. As of 5 September 2001 located at 110.01 deg W drifting at 0.003 deg W per day. As of 2007 Mar 11 located at 128.86W drifting at 0.001E degrees per day.

• USA 148 - . Payload: DSCS III B-8. Mass: 1,232 kg (2,716 lb). Nation: USA. Agency: USAF. Manufacturer: Valley Forge. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 26052 . COSPAR: 2000-001A. Apogee: 35,790 km (22,230 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.00 deg. Part of the US Air Force Defense Satellite Communications System. To be stationed in geosynchronous orbit over the Pacific Ocean..

• GOES 11 - . Payload: GOES L. Mass: 2,217 kg (4,887 lb). Nation: USA. Agency: NOAA. Manufacturer: Palo Alto. Program: GOES. Class: Earth. Type: Weather satellite. Spacecraft: FS-1300. USAF Sat Cat: 26352 . COSPAR: 2000-022A. Apogee: 35,796 km (22,242 mi). Perigee: 35,786 km (22,236 mi). Inclination: 0.40 deg. Period: 1,436.30 min.

  US civilian geostationary weather satellite in the Geostationary Operational Environmental Satellite series. It was the first GOES launch on the Atlas II launch vehicle (the Atlas I having been phased out). Built by SS/Loral, based on the FS-1300 bus. It was equipped with one solar panel array and a counter-boom with a solar sail. The satellite carried well as an imaging radiometer and an X-ray detector to monitor solar activity. Stationed at 106 deg W. Positioned in geosynchronous orbit at 104 deg W in 2000. As of 5 September 2001 located at 108.58 deg W drifting at 0.018 deg E per day. As of 2007 Mar 11 located at 135.52W drifting at 0.001E degrees per day.

• TDRS 8 - . Payload: TDRS-H. Mass: 3,180 kg (7,010 lb). Nation: USA. Agency: NASA Greenbelt. Manufacturer: El Segundo. Program: STS. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 26388 . COSPAR: 2000-034A. Apogee: 35,800 km (22,200 mi). Perigee: 35,773 km (22,228 mi). Inclination: 5.40 deg. Period: 1,436.10 min.

  Launch delayed from June 29. First Advanced Tracking and Data Relay Satellite, using a Hughes HS 601 satellite bus. It included an S-band phased array antenna and two Ku/Ka band reflectors 4.6 meters in diameter. The satellite was launched into a a 167 x 577 km x 28.3 deg parking orbit at 13:05 GMT. The Centaur upper stage made a second burn at 13:21 GMT, releasing the satellite into a subsynchronous transfer orbit of 237 x 27,666 km x 27.0 deg. The satellite's own Primex/Marquardt R4D liquid apogee engine would be used to maneuver the satellite into its final geosynchronous orbit. Stationed at 151 deg W. Positioned in geosynchronous orbit at 150 deg W in 2000. As of 5 September 2001 located at 149.99 deg W drifting at 0.014 deg E per day. As of 2007 Mar 11 located at 145.38E drifting at 3.007W degrees per day.

• USA 153 - . Payload: DSCS III B-11. Mass: 1,235 kg (2,722 lb). Nation: USA. Agency: USAF. Manufacturer: Valley Forge. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 26575 . COSPAR: 2000-065A. Apogee: 35,790 km (22,230 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.00 deg.

  Military Communications satellite. Launch delayed from October 12 by spacecraft problem. The US Air Force Defense Satellite Communications System satellite was placed by the Centaur upper stage into a 148 km x 898 km x 29.3 deg parking orbit. A second burn put it into a 218 km x 35,232 km x 26.0 deg transfer orbit. The DSCS III B-11 IABS-8 apogee stage, with two Primex R4D liquid apogee engines, circularised the orbit at geostationary altitude on October 21 and then separated from the DSCS.

• USA 155 - . Payload: Capricorn 2? / MLV-11 'Great Bear'. Mass: 3,600 kg (7,900 lb). Nation: USA. Agency: NRO. Manufacturer: El Segundo. Class: Communications. Type: Military communications satellite. Spacecraft: Quasar. USAF Sat Cat: 26635 . COSPAR: 2000-080A. Apogee: 35,790 km (22,230 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.00 deg. Period: 1,440.00 min.

  Classified satellite. Launch delayed 24 hours by RL10 engine problem in upper stage. USA 155 was a classified National Reconnaissance Office satellite. The Centaur placed the payload in a 176 x 831 km parking orbit and then in a 270 x 37490 km x 26.5 deg geostationary transfer orbit. The spacecraft was probably either a data relay satellite (to relay spy satellite imagery and data to the ground) and/or a signals intelligence satellite.

• GOES 12 - . Payload: GOES-M. Mass: 2,105 kg (4,640 lb). Nation: USA. Agency: NOAA. Manufacturer: Palo Alto. Program: GOES. Class: Earth. Type: Weather satellite. Spacecraft: FS-1300. USAF Sat Cat: 26871 . COSPAR: 2001-031A. Apogee: 35,813 km (22,253 mi). Perigee: 35,769 km (22,225 mi). Inclination: 0.00 deg. Period: 1,436.30 min.

  Launch delayed from July 12, 15 and 22. The GOES-M weather satellite was placed by the Atlas AC-142 Centaur stage into a 164 x 505 km parking orbit and then a super synchronous transfer orbit of 274 x 42275 km x 20 deg. GOES-M was a Loral 1300-series satellite with a single solar array and a solar attitude control sail. Launch mass was 2279 kg and dry mass 1042 kg. The Geostationary Operational Environmental Satellites were developed by NASA-Goddard and were transferred to the NOAA weather agency when operational. In addition to the usual weather imager/sounder, GOES-M carried a new solar soft X-ray imager. Earlier GOES satellites carried simple X-ray collimator detectors, but the new SXI was a full-fledged grazing incidence telescope similar to the SXT on Japan's Yohkoh satellite. The GOES-M satellite was redesignated GOES 12 once in orbit.

  GOES 12 was a 980 kg, 973 W spacecraft that carried an IR imager, a "sounder", and an X-ray imager. The IR imager was a Cassegrain telescope covering five wavelength channels, 0.55-0.75, 3.80-4.00, 6.50-7.00, 10.20-11.20, and 11.50-12.50 microns. It provided images covering 3,000 km x 3,000 km every 41 seconds, by scanning the area in 16 square kilometer sections. The "sounder" provided vertical distribution of temperature, moisture and ozone, by passive monitoring in 18 depth-dependent wavelengths. (Long wave IR: 14.71, 14.37, 14.06, 13.64, 13.37, 12.66, and 12.02 microns. Medium wave IR: 11.03, 9.71, 7.43, 7.02, and 6.51 microns. Short wave IR: 4.57, 4.52, 4.45, 4.13, 3.98, and 3.74 microns. There was also another band at visible wavelength 0.7 microns, to provide pictures of cloud tops.) The sounder covered an area of 3,000 km x 3,000 km in about 42 minutes. Another instrument package named SEM (Space Environment Monitor) monitored the energetic electrons and protons in the magnetosphere and the X-rays from the Sun. The above three had been carried on the earlier GOES missions, but GOES 12 carried also an X-ray imager providing an X-ray (about 0.1-1.0 nm wavelength) picture of the solar disk. For some months, the spacecraft was to be on standby, to be activated and moved to a desired longitude. As of 5 September 2001 located at 89.93 deg W drifting at 0.001 deg W per day. As of 2007 Mar 11 located at 74.73W drifting at 0.014E degrees per day.

• TDRS 9 - . Payload: TDRS-I. Mass: 3,192 kg (7,037 lb). Nation: USA. Agency: NASA Greenbelt. Manufacturer: El Segundo. Program: STS. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 27389 . COSPAR: 2002-011A. Apogee: 35,811 km (22,251 mi). Perigee: 35,758 km (22,218 mi). Inclination: 8.30 deg. Period: 1,436.00 min.

  Launch delayed from October 31, November 13 and 26, 2001 and February 6 due to contract dispute with Boeing over performance of earlier satellites of the series. The Centaur upper stage entered a 167 x 578 km parking orbit and then placed the payload into a 247 x 29135 km x 27.1 deg subsynchronous transfer orbit. NASA's TDRS-I (TDRS-9) data relay satellite used a Boeing BSS-601 bus and was to provide S, Ku and Ka band communications for the Shuttle and International Space Station. After launch a problem developed with the fuel supply from one of the satellite's four propellant tanks. The tanks were paired, so losing one tank cuts the propellant supply in half. A test burn of the General Dynamics R-4D apogee motor raised the orbit to 433 x 29146 km x 26.4 deg on March 11 and a larger perigee burn raised the apogee to geostationary altitude, 429 x 35800 km, on March 13. A further burn on March 19, raised the orbit to 3521 x 35789 km and lowered the inclination to 21.4 deg. A burn on March 25 raised the orbit further to 8383 x 35811 km and lowered inclination to 17.4 deg. As of 2007 Mar 11 located at 62.04W drifting at 0.008W degrees per day.

• Hispasat 1D - . Payload: Spacebus 3000B2. Mass: 3,250 kg (7,160 lb). Nation: Spain. Agency: Hispasat. Manufacturer: Cannes. Program: Hispasat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 3000. USAF Sat Cat: 27528 . COSPAR: 2002-044A. Apogee: 35,802 km (22,246 mi). Perigee: 35,772 km (22,227 mi). Inclination: 0.00 deg. Period: 1,436.10 min.

  Launch delayed from May 28, August 14. Hispasat 1D was a Spanish geostationary communications spacecraft. The 3.3-ton, 7.0-kW satellite carried three antennae looking in different directions to provide video, data, and Internet services to Europe, North America, and North Africa via 28 Ku-band transponders after being parked over 30° W longitude alongside Hispasat 1A, 1B, and 1C. As of 2007 Mar 9 located at 29.97W drifting at 0.014W degrees per day.

• TDRS 10 - . Payload: TDRS-J. Mass: 3,190 kg (7,030 lb). Nation: USA. Agency: NASA Greenbelt. Manufacturer: El Segundo. Program: STS. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 27566 . COSPAR: 2002-055A. Apogee: 35,804 km (22,247 mi). Perigee: 35,765 km (22,223 mi). Inclination: 7.00 deg. Period: 1,436.00 min.

  Delayed from October 29, November 21 and 23. The third and final Advanced Tracking and Data Relay Satellite satellite separated from the Centaur upper stage 30 minutes after launch. This completed the $800 million, three satellite contract. Last launch of the Atlas 2A booster. Flight delayed from October 29, November 21 and 23. As of 2007 Mar 10 located at 40.92W drifting at 0.012E degrees per day.

• AMC-10 (GE-10) - . Payload: A2100A. Mass: 2,340 kg (5,150 lb). Nation: USA. Agency: SES Americom. Manufacturer: Lockheed. Program: Americom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 28154 . COSPAR: 2004-003A. Apogee: 35,798 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0100 deg. Period: 1,436.09 min.

  Americom 10 (AMC-10) was a replacement satellite for Satcom C3. It was to be located at 135 deg W. The C-band satellite, to be accompanied by AMC-11 later in 2004, were designed to support SES Americom's cable network in the United States, Canada, the Caribbean, and Mexico. The satellite had a design life of 15 years and carried 24 x 36 MHz C-band transponders. As of 2007 Mar 10 located at 134.97W drifting at 0.005E degrees per day.

• Superbird 6 - . Mass: 3,100 kg (6,800 lb). Nation: Japan. Agency: JSCC. Program: Superbird. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 28218 . COSPAR: 2004-011A. Apogee: 35,797 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.00 deg. Period: 1,436.10 min. The satellite was to provide Ka and Ku band communications for Japan's Space Communications Corporation..

• USA 179 - . Payload: Nemesis / NROL-1). Mass: 3,600 kg (7,900 lb). Nation: USA. Agency: NRO. Class: Communications. Type: Military communications satellite. Spacecraft: Quasar. USAF Sat Cat: 28384 . COSPAR: 2004-034A. Apogee: 35,800 km (22,200 mi). Perigee: 35,800 km (22,200 mi). Inclination: 0.00 deg. Period: 1,440.00 min.

  63rd and last flight of Atlas IIAS. 576th and final launch of Rocketdyne-powered Atlas rockets. Final launch from LC36A after 42 years of use. Launch delayed from June 24 and 25, July 1 and 27, August 27, 28, 29 and 30. The payload was probably a communications satellite used to relay data from imaging spy satellites.