1965 August 11 - 14:31 GMT - Launch Vehicle: Atlas. Atlas Centaur D AC-6 / Centaur D 151D Surveyor; Atlas Centaur 6 Mass: 950 kg (2,090 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Centaur AC-6 launched dummy Surveyor payload into a barycentric / translunar orbit.

1966 April 8 - 01:00 GMT - Launch Vehicle: Atlas. Atlas Centaur D AC-8 / Centaur D 184D FAILURE: Centaur propellant leak. Surveyor Model Mass: 784 kg (1,728 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Perigee: 182 km (113 mi). Apogee: 336 km (208 mi). Inclination: 30.70 deg. Period: 89.70 min. Launch vehicle test. Payload was dummy Surveyor spacecraft.

1966 October 26 - 11:12 GMT - Launch Vehicle: Atlas. Atlas Centaur D AC-9 / Centaur D 174D Surveyor SD-4 Mass: 951 kg (2,096 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Perigee: 166 km (103 mi). Apogee: 406,200 km (252,400 mi). Inclination: 29.60 deg. Period: 15,912.00 min. Launch vehicle test. Centaur D AC-9 put Surveyor spacecraft payload into geosynchronous transfer orbit

1967 April 17 - 07:05 GMT - Launch Vehicle: Atlas. Atlas Centaur D AC-12 / Centaur D 292D Surveyor 3 Mass: 283 kg (623 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft landed on Moon; perrformed soil sample tests and imaged lunar surface.

1967 September 8 - 07:57 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-13 / Centaur D-1A 5901C Surveyor 5 Mass: 279 kg (615 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft lunar landing; returned 19,000 photos, soil data.

1967 November 7 - 07:39 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-14 / Centaur D-1A 5902C Surveyor 6 Mass: 280 kg (610 lb). Spacecraft: Surveyor. Agency: NASA/JPL. Soft landed on lunar Moon; photographed lunar surface; sampled lunar soil; used propulsion system to briefly lift off of lunar surface.

1968 December 7 - 08:40 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-16 / Centaur D-1A 5002C OAO 2 Mass: 2,012 kg (4,435 lb). Spacecraft: OAO. Agency: NASA GSF. Perigee: 749 km (465 mi). Apogee: 758 km (470 mi). Inclination: 35.00 deg. Period: 99.90 min. Orbiting Astronomical Observatory; carried 11 telescopes; performed X-ray, UV, IR observations of stars. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Launch vehicle put payload into geosynchronous transfer orbit

1969 February 25 - 01:29 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-20 / Centaur D-1A 5403C Mariner 6 Mass: 412 kg (908 lb). Spacecraft: Mariner 6-7. Agency: NASA/JPL. Mars flyby 31 July 1969; returned 75 images of Martian surface. Ten days before the scheduled launch, a faulty switch opened the main valves on the Atlas stage. This released the pressure which supported the Atlas structure, and as the booster deflated it began to crumple. Two ground crewman started pressurizing pumps, saving the structure from further collapse. The two ground crewman, who had acted at risk of the 12-story rocket collapsing on them, were awarded Exceptional Bravery Medals from NASA.

The Mariner 6 spacecraft was removed, put on another Atlas/Centaur, and launched on schedule. The main booster was jettisoned 4 min. 38 sec. after launch, followed by a 7.5 minute Centaur burn to inject the spacecraft into Mars direct trajectory. After Mariner 6 separated from the Centaur the solar panels were deployed. A midcourse correction involving a 5.35 second burn of the hydrazine rocket occurred on 1 March 1969. A few days later explosive valves were deployed to unlatch the scan platform. Some bright particles released during the explosion distracted the Canopus sensor, and attitude lock was lost temporarily. It was decided to place the spacecraft on inertial guidance for the Mars flyby to prevent a similar occurrence.

On 29 July, 50 hours before closest approach, the scan platform was pointed to Mars and the scientific instruments turned on. Imaging of Mars began 2 hours later. For the next 41 hours, 49 approach images (plus a 50th fractional image) of Mars were taken through the narrow-angle camera. At 05:03 UT on 31 July the near-encounter phase began, including collection of 26 close-up images. Due to a cooling system failure, channel 1 of the IR spectrometer did not cool sufficiently to allow measurements from 6 to 14 micrometers so no infrared data were obtained over this range. Closest approach occurred at 05:19:07 UT at a distance of 3431 km from the martian surface. Eleven minutes later Mariner 6 passed behind Mars and reappeared after 25 minutes. 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

Mariner 6 returned 49 far encounter and 26 near encounter images of Mars. 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.

1970 November 30 - 22:40 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-21 / Centaur D-1A 5003C FAILURE: Shroud failed to separate. OAO-B Mass: 2,121 kg (4,676 lb). Spacecraft: OAO. Agency: NASA. Orbiting Astronomical Observatory. Launch vehicle was to have put payload into geosynchronous transfer orbit

1971 May 30 - 22:23 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-23 / Centaur D-1A 5404C Mariner 9 Mass: 974 kg (2,147 lb). Spacecraft: Mariner 8-9. Agency: NASA/JPL. The first spacecraft to orbit another planet. The Mariner Mars 71 mission was planned to consist of two spacecraft on complementary missions. Mariner 8 was to map 70 % of the Martian surface and Mariner 9 was to study temporal changes in the Martian atmosphere and on the Martian surface. The launch failure of Mariner 8 forced Mariner 9 to combine the mission objectives of both. For the survey portion of the mission, the planetary surface was to be mapped with the same resolution as planned for the original mission, although the resolution of pictures of the polar regions would be decreased due to the increased slant range. The variable features experiments were changed from studies of six given areas every 5 days to studies of smaller regions every 17 days. Mariner 9 was launched on a direct trajectory to Mars. Separation from the booster occurred at 22:36 GMT. The four solar panels were deployed at 22:40 GMT. The sensors locked onto the Sun at 23:16, shortly after the spacecraft left the Earth's shadow and Canopus acquisition was achieved at 02:26 GMT 31 May. A planned midcourse maneuver was executed on 5 June. Mariner 9 arrived at Mars on 14 November 1971 after a 167 day flight. A 15 minute 23 second rocket burn put the spacecraft into Mars orbit. The insertion orbit had a periapsis of 1398 km and a period of 12 hr, 34 min. Two days later a 6 second rocket burn changed the orbital period to just under 12 hours with a periapsis of 1387 km. A correction trim maneuver was made on 30 December on the 94th orbit which raised the periapsis to 1650 km and changed the orbital period to 11:59:28 so that synchronous data transmissions could be made to the Goldstone 64-m DSN antenna.

Imaging of the surface of Mars by Mariner 9 was delayed by a dust storm which started on 22 September 1971 in the Noachis region. The storm quickly grew into one of the largest global storms ever observed on Mars. By the time the spacecraft arrived at Mars no surface details could be seen except the summits of Olympus Mons and the three Tharsis volcanoes. The storm abated through November and December and normal mapping operations began. The spacecraft gathered data on the atmospheric composition, density, pressure, and temperature and also the surface composition, temperature, gravity, and topography of Mars. A total of 54 billion bits of scientific data were returned, including 7329 images covering the entire planet. After depleting its supply of attitude control gas, the spacecraft was turned off on 27 October 1972. Mariner 9 was left in an orbit which should not decay for at least 50 years, after which the spacecraft will enter the Martian atmosphere.

The Mariner 9 mission resulted in a global mapping of the surface of Mars, including the first detailed views of the martian volcanoes, Valles Marineris, the polar caps, and the satellites Phobos and Deimos. It also provided information on global dust storms, the gravity field as well as evidence for surface aeolian activity.

1972 January 23 - 00:12 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-28 / Centaur D-1A 5008C Intelsat 4 F-4 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 35,905 km (22,310 mi). Apogee: 35,917 km (22,317 mi). Inclination: 10.50 deg. Period: 1,442.50 min. Over Pacific. 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 Pacific Ocean at 174 deg E in 1972-1974; over the Pacific Ocean 179 deg E in 1975-1982; over the Atlantic Ocean 1 deg W in 1982-1983 As of 28 August 2001 located at 178.00 deg E drifting at 1.569 deg W per day. As of 2007 Mar 7 located at 155.84W drifting at 1.593W degrees per day.

1972 June 13 - 21:53 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-29 / Centaur D-1A 5009C Intelsat 4 F-5 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 35,811 km (22,251 mi). Apogee: 35,847 km (22,274 mi). Inclination: 11.30 deg. Period: 1,438.30 min. Over Indian 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 Indian Ocean at 61 deg E in 1972-1975; over the Indian Ocean 60 deg E in 1976-1980; over the Pacific Ocean 179 deg E in 1980-1981 As of 2 September 2001 located at 8.61 deg E drifting at 0.536 deg W per day. As of 2007 Mar 9 located at 73.10W drifting at 0.625W degrees per day.

1972 August 21 - 10:28 GMT - Launch Vehicle: Atlas. SLV-3C Centaur AC-22 / Centaur D-1A 5004C OAO 3 Mass: 2,204 kg (4,858 lb). Spacecraft: OAO. Agency: NASA GSF. Perigee: 713 km (443 mi). Apogee: 724 km (449 mi). Inclination: 35.00 deg. Period: 99.20 min. UV observations of stellar objects. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Launch vehicle put payload into geosynchronous transfer orbit

1973 April 6 - 02:11 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-30 / Centaur D-1AR 5011D Pioneer 11 Mass: 259 kg (570 lb). Spacecraft: Pioneer 10-11. Agency: NASA ARC. Jupiter flyby December 1974; Saturn flyby September 1979. Solar system escape trajectory. Pioneer 11 was the second mission to investigate Jupiter and the outer solar system and the first to explore the planet Saturn and its main rings. Pioneer 11, like Pioneer 10, used Jupiter's gravitational field to alter its trajectory radically. It passed close to Saturn and then it followed an escape trajectory from the solar system. During its closest approach, December 4, 1974, Pioneer 11 passed to within 34,000 km of Jupiter's cloud tops. It passed by Saturn on September 1, 1979, at a distance of 21,000 km from Saturn's cloud tops. The spacecraft has operated on a backup transmitter since launch. Instrument power sharing began in February 1985 due to declining RTG power output. Science operations and daily telemetry ceased on September 30, 1995 when the RTG power level was insufficient to operate any experiments. As of the end of 1995 the spacecraft was located at 44.7 AU from the Sun at a nearly asymptotic latitude of 17.4 degrees above the solar equatorial plane and was heading outward at 2.5 AU/year. Routine tracking and project data processing operations were terminated on March 31, 1997 for budget reasons.

1973 November 3 - 05:45 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-34 / Centaur D-1AR 5014D Mariner 10 Mass: 526 kg (1,159 lb). Spacecraft: Mariner 10. Agency: NASA/JPL. Mariner 10 was the first spacecraft to reach Mercury. Mariner 10 was placed in a parking orbit for 25 minutes after launch, then accelerated to a trans-Venus escape trajectory. The television and ultraviolet experiments were trained on the comet Kohoutek while the spacecraft was en route to its destination. The vehicle's first planetary encounter was with Venus on February 5, 1974, at a distance of 4200 km. Mariner 10 took 4,000 photos of Venus, which revealed a nearly round planet enveloped in smooth cloud layers. The gravity of Venus bent the orbit of the spacecraft and sent it towards Mercury. It crossed the orbit of Mercury on March 29, 1974, at 20:46 GMT, at a distance of 704 km from the surface. Photographs taken during the pass revealed an intensely cratered, Moon-like surface and a faint atmosphere of mostly helium. After the first flyby, Mariner 10 entered solar orbit, which permitted two more rendezvous with Mercury. On September 21, 1974, the second Mercury rendezvous, at an altitude of about 47,000 km, provided another opportunity to photograph the sunlit side of the planet and the south polar region. The third and final Mercury encounter on March 16, 1975, at an altitude of 327 km, yielded 300 photographs and magnetic field measurements. The vehicle was turned off March 24, 1975 when the supply of attitude-control gas was depleted.

1974 November 21 - 23:43 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-32 / Centaur D-1AR 5012D Intelsat 4 F-8 Mass: 1,410 kg (3,100 lb). Spacecraft: Intelsat 4. Agency: Intelsat. Perigee: 35,907 km (22,311 mi). Apogee: 35,944 km (22,334 mi). Inclination: 8.80 deg. Period: 1,443.20 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 Pacific Ocean at 174 deg E in 1974-1982; over the Pacific Ocean 179 deg E in 1982; over the Atlantic Ocean 1 deg W in 1983-1985 As of 1 September 2001 located at 139.80 deg W drifting at 1.762 deg W per day. As of 2007 Mar 9 located at 61.11W drifting at 1.754W degrees per day.

1975 September 26 - 00:17 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-36 / Centaur D-1AR 5016 Intelsat 4A F-1 Mass: 1,500 kg (3,300 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,860 km (22,280 mi). Apogee: 35,910 km (22,310 mi). Inclination: 8.90 deg. Period: 1,441.10 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 over the Atlantic Ocean at 25 deg W in 1975-1981; over the Atlantic Ocean 18.5 deg W in 1982-1983; over the Atlantic Ocean 30 deg W in 1983-1986 As of 30 August 2001 located at 4.05 deg E drifting at 1.213 deg W per day. As of 2007 Mar 10 located at 28.51E drifting at 1.239W degrees per day.

1976 January 29 - 23:56 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-37 / Centaur D-1AR 501 Intelsat 4A F-2 Mass: 1,500 kg (3,300 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,924 km (22,322 mi). Apogee: 35,981 km (22,357 mi). Inclination: 9.00 deg. Period: 1,444.60 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 Atlantic Ocean at 29.5 deg W in 1976-79; over the Atlantic Ocean 27.5 deg W in 1979-1980; over the Atlantic Ocean 21.5 deg W in 1980-1983; over the Indian Ocean 57 deg E in 1983-1984; over the Atlantic Ocean 2-4 deg W in 1984-1985 As of 3 September 2001 located at 151.88 deg E drifting at 2.088 deg W per day. As of 2007 Mar 10 located at 130.98W drifting at 2.123W degrees per day.

1976 July 22 - 22:04 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-40 / Centaur D-1AR 5022 Comstar 2 Mass: 792 kg (1,746 lb). Spacecraft: Intelsat 4A. Agency: Comsat. Perigee: 35,855 km (22,279 mi). Apogee: 35,887 km (22,299 mi). Inclination: 12.60 deg. Period: 1,440.40 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 Positioned in geosynchronous orbit over the Americas at 95 deg W in 1976-1983 over the Americas at 76 deg W in 1983-1993 As of 28 August 2001 located at 172.63 deg W drifting at 1.031 deg W per day. As of 2007 Mar 10 located at 150.18W drifting at 1.064W degrees per day.

1977 August 12 - 06:29 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-45 / Centaur D-1AR 5025 HEAO 1 Mass: 2,720 kg (5,990 lb). Spacecraft: HEAO. Agency: NASA MSF. Perigee: 429 km (266 mi). Apogee: 447 km (277 mi). Inclination: 22.70 deg. Period: 93.40 min. High Energy Astronomical Observatory; surveyed sky in X-ray band. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1978 January 7 - 00:15 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-46 / Centaur-D1AR AC-46 Intelsat 4A F-3 Mass: 1,511 kg (3,331 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,874 km (22,291 mi). Apogee: 35,909 km (22,312 mi). Inclination: 7.20 deg. Period: 1,441.50 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 60 deg E in 1978-1982 over the Pacific Ocean 179 deg E in 1982-1986 over the Pacific Ocean 177 deg E in 1986-1988 As of 2 September 2001 located at 156.51 deg W drifting at 1.304 deg W per day. As of 2007 Feb 27 located at 107.90E drifting at 1.326W degrees per day.

1978 March 31 - 23:36 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-48 / Centaur D-1AR 5028 Intelsat 4A F-6 Mass: 826 kg (1,821 lb). Spacecraft: Intelsat 4A. Agency: Intelsat. Perigee: 35,758 km (22,218 mi). Apogee: 35,823 km (22,259 mi). Inclination: 11.60 deg. Period: 1,436.30 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 1978-1982; over the Pacific Ocean 174 deg E in 1982-1986; over the Pacific Ocean 170 deg E in 1986 As of 26 August 2001 located at 92.43 deg E drifting at 0.407 deg E per day. As of 2007 Mar 11 located at 75.50E drifting at 0.437W degrees per day.

1978 June 29 - 22:24 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-41 / Centaur D-1AR 5021 Comstar 3 Mass: 1,520 kg (3,350 lb). Spacecraft: Intelsat 4A. Agency: Comsat. Perigee: 36,007 km (22,373 mi). Apogee: 36,172 km (22,476 mi). Inclination: 11.50 deg. Period: 1,451.60 min. US domestic telephone service. 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 87 deg W in 1978-1984 over the Americas at 76 deg W in 1984-1986 As of 1 September 2001 located at 101.79 deg W drifting at 3.884 deg W per day. As of 2007 Mar 4 located at 39.19E drifting at 3.878W degrees per day.

1978 November 13 - 05:24 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-52 / Centaur D-1AR 5032 HEAO 2 Mass: 3,150 kg (6,940 lb). Spacecraft: HEAO. Agency: NASA MSF. Perigee: 526 km (326 mi). Apogee: 548 km (340 mi). Inclination: 23.50 deg. Period: 95.40 min. High Energy Astronomy Observatory. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1979 September 20 - 05:28 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-53 / Centaur D-1AR 5033 HEAO 3 Mass: 3,150 kg (6,940 lb). Spacecraft: HEAO. Agency: NASA. Perigee: 487 km (302 mi). Apogee: 503 km (312 mi). Inclination: 43.60 deg. Period: 94.50 min. High Energy Astronomy Observatory; cosmic, gamma ray measurements. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1980 December 6 - 23:31 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-54 / Centaur D-1AR 5034 Intelsat 5 F-2 Mass: 2,000 kg (4,400 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 36,118 km (22,442 mi). Apogee: 36,242 km (22,519 mi). Inclination: 9.70 deg. Period: 1,456.20 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 21 deg W in 1981; 27 deg W in 1981-1983; 34 deg W in 1983-1985; 27 deg W in 1985; 1 deg W in 1985-1989; 21 deg W in 1989-1994; 40 deg W in 1994-1998 As of 2 September 2001 located at 103.82 deg W drifting at 5.004 deg W per day. As of 2007 Mar 10 located at 81.84W drifting at 5.000W degrees per day.

1981 May 23 - 22:42 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-56 / Centaur D-1AR 5036 Intelsat 5 F-1 Mass: 1,928 kg (4,250 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 36,151 km (22,463 mi). Apogee: 36,224 km (22,508 mi). Inclination: 10.10 deg. Period: 1,456.60 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 at 24 deg W in 1981; 60 deg E in 1982-1984; 57 deg E in 1984-1986; 174 deg E in 1986-1988; 177 deg E in 1988-1990; 177 deg W in 1990-1992; 91 deg E in 1993-1996; 72 deg E in 1996-1997 As of 4 September 2001 located at 169.69 deg W drifting at 5.095 deg W per day. As of 2007 Mar 10 located at 13.28E drifting at 5.096W degrees per day.

1981 December 15 - 23:35 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-55 / Centaur D-1AR 5035 Intelsat 5 F-3 Mass: 1,870 kg (4,120 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 35,894 km (22,303 mi). Apogee: 36,129 km (22,449 mi). Inclination: 9.40 deg. Period: 1,447.60 min. Positioned in geosynchronous orbit at 24 deg W in 1982-1985; 27 deg W in 1985; 53 deg W in 1985-1988; 174 deg E in 1988-1990; 177 deg E in 1990-1992; 177 deg W in 1992-1995; 157 deg E in 1995-1998 As of 5 September 2001 located at 57.52 deg W drifting at 2.890 deg W per day. As of 2007 Mar 9 located at 101.94W drifting at 2.904W degrees per day.

1982 September 28 - 23:17 GMT - Launch Vehicle: Atlas. SLV-3D Centaur AC-60 / Centaur D-1AR 5040 Intelsat 5 F-5 Mass: 2,000 kg (4,400 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 36,228 km (22,510 mi). Apogee: 36,404 km (22,620 mi). Inclination: 9.00 deg. Period: 1,463.30 min. Positioned in geosynchronous orbit at 63 deg E in 1982-1990; 66 deg E in 1991-1996; 33 deg E in 1996; 72 deg E in 1997-on. As of 3 September 2001 located at 16.28 deg E drifting at 6.707 deg W per day. As of 2007 Mar 9 located at 163.88W drifting at 6.709W degrees per day.

1984 June 9 - 23:03 GMT - Launch Vehicle: Atlas. Atlas G Centaur AC-62 / Centaur D-1AR 5042G FAILURE: Centaur structural failure. Intelsat 5 F-9 Mass: 1,091 kg (2,405 lb). Spacecraft: Intelsat 5. Agency: Intelsat. Perigee: 180 km (110 mi). Apogee: 1,227 km (762 mi). Inclination: 29.20 deg. Period: 98.90 min. Failure of Centaur upper stage left stranded in useless orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle was to have put payload into geosynchronous transfer orbit

1985 March 22 - 23:58 GMT - Launch Vehicle: Atlas. Atlas G Centaur AC-63 / Centaur D-1AR 5043G Intelsat 5A F-10 Mass: 2,013 kg (4,437 lb). Spacecraft: Intelsat 5A. Agency: Intelsat. Perigee: 36,237 km (22,516 mi). Apogee: 36,468 km (22,660 mi). Inclination: 7.20 deg. Period: 1,465.10 min. Positioned in geosynchronous orbit at 24 deg W in 1985-1990; 174 deg E in 1990-1994; 66 deg E in 1994-1995; 57 deg E in 1995-1996; 33 deg E in 1996-1999 As of 5 September 2001 located at 135.23 deg W drifting at 7.152 deg W per day. As of 2007 Mar 9 located at 107.21W drifting at 7.157W degrees per day.

1985 June 30 - 00:44 GMT - Launch Vehicle: Atlas. Atlas G Centaur AC-64 / Centaur D-1AR 5044G Intelsat 5A F-11 Mass: 1,098 kg (2,420 lb). Spacecraft: Intelsat 5A. Agency: Intelsat. Perigee: 35,773 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.70 deg. Period: 1,436.10 min. Positioned in geosynchronous orbit at 27 deg W in 1985-1990; 63 deg E in 1990-1992; 177 deg E in 1992-1994; 180 deg E in 1994-1997; 29 deg W in 1998-1999 As of 4 September 2001 located at 29.54 deg W drifting at 0.005 deg W per day. As of 2007 Mar 9 located at 113.07W drifting at 0.696W degrees per day.

1985 September 28 - 23:36 GMT - Launch Vehicle: Atlas. Atlas G Centaur AC-65 / Centaur D-1AR 5045G Intelsat 5A F-12 Mass: 1,096 kg (2,416 lb). Spacecraft: Intelsat 5A. Agency: Intelsat. Perigee: 36,086 km (22,422 mi). Apogee: 36,140 km (22,450 mi). Inclination: 6.20 deg. Period: 1,452.80 min. Telephone communications; 31 deg E. Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 60 deg E in 1985-1989; 1 deg W in 1989-1994; 21 deg W in 1994-1996; 56 deg W in 1996-1998 As of 28 August 2001 located at 145.57 deg E drifting at 4.159 deg W per day. As of 2007 Mar 10 located at 19.14E drifting at 4.163W degrees per day.

1986 December 5 - 02:30 GMT - Launch Vehicle: Atlas. Atlas G Centaur AC-66 / Centaur D-1AR 5046G USA 20 Mass: 2,310 kg (5,090 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 35,740 km (22,200 mi). Apogee: 35,832 km (22,264 mi). Inclination: 0.90 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 100 deg W in 1987-1999 Last known longitude (27 July 1999) 100.33 deg W drifting at 0.027 deg W per day.

1987 March 26 - 21:22 GMT - Launch Vehicle: Atlas. Atlas G Centaur AC-67 / Centaur D-1AR 5048G FAILURE: Lightning strike zapped guidance at T+51 seconds. Fault was directly attributed to a random memory upset that forced rocket to veer off course. Destroyed by range safety. Fltsatcom 6 Mass: 2,300 kg (5,000 lb). Spacecraft: Fltsatcom. Agency: U.S. Navy.

1989 September 25 - 08:41 GMT - Launch Vehicle: Atlas. Atlas G Centaur AC-68 / Centaur D-1AR 5047G USA 46 Mass: 2,310 kg (5,090 lb). Spacecraft: Fltsatcom. Agency: USN. Perigee: 35,777 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 4.10 deg. Period: 1,436.10 min. Last in series of 8. 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 1989-1999.

1990 July 25 - 19:21 GMT - Launch Vehicle: Atlas. Atlas I AC-69 / Centaur I 5049 CRRES Mass: 1,629 kg (3,591 lb). Spacecraft: CRRES. Agency: USAF/NAS. Perigee: 335 km (208 mi). Apogee: 34,739 km (21,585 mi). Inclination: 18.00 deg. Period: 613.40 min. Combined Release and Radiation Effects Satellite. First launch of commercial Atlas-Centaur. Spacecraft engaged in research and exploration of the upper atmosphere or outer space. Elliptical orbit; MRS trajectory.

1991 April 18 - 23:30 GMT - Launch Vehicle: Atlas. Atlas I AC-70 FAILURE: RL-10 Centaur engine turbopump failed at T+361 seconds; destroyed by range safety. Yuri 3H Mass: 600 kg (1,320 lb). Spacecraft: AS 3000. Agency: TSCJ. Apogee: 175 km (108 mi).

1991 December 7 - 22:47 GMT - Launch Vehicle: Atlas. Atlas II AC-102 / Centaur II 8102 Eutelsat II F3 Mass: 1,874 kg (4,131 lb). Spacecraft: Spacebus 100. Agency: Eutelsat. Perigee: 35,769 km (22,225 mi). Apogee: 35,802 km (22,246 mi). Inclination: 2.00 deg. Period: 1,436.10 min. Stationed at 16 deg E. Telecommunications satellite. French registration 1991-8. Transfer orbit was 663 min, 200 x 36000 km x 7.0 deg. Registered by France in ST/SG/SER.E/249 until EUTELSAT can register the satellite. EUTELSAT is the European Telecommunications Satellite Organi zation. Launch vehicle put payload into supersynchronous earth orbit with IFR trajectory option. Positioned in geosynchronous orbit at 16 deg E in 1992-1998; 36 deg E in 1999. As of 1 September 2001 located at 21.51 deg E drifting at 0.017 deg E per day. As of 2007 Mar 11 located at 74.40E drifting at 3.531W degrees per day.

1992 March 14 - 00:00 GMT - Launch Vehicle: Atlas. Atlas I AC-72 / Centaur I 5052 Galaxy 5 Mass: 1,412 kg (3,112 lb). Spacecraft: HS 376. Agency: HCI. Perigee: 35,782 km (22,233 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geostationary at 125 deg W. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 125 deg W in 1992-2001. As of 2007 Mar 8 located at 7.46E drifting at 3.538W degrees per day.

1992 June 10 - 00:00 GMT - Launch Vehicle: Atlas. Atlas IIA AC-105 / Centaur II 8105 Intelsat K Mass: 2,928 kg (6,455 lb). Spacecraft: AS 5000. Agency: Intelsat. Perigee: 35,781 km (22,233 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Stationed at 21.5 deg W. Intelsat K is a single spacecraft purchased to meet critical requirements for Ku-band capacity over the Atlantic region, driven primarily by international broadcasters. The satellite was purchased from GE Americom while under construction (as Satcom K4) and required extensive payload modifications. Spacecraft: Based on GE 5000 series bus.3-axis stabilised using magnetotorquers. Hydrazine propulsion system. Two large solar panels with 1-axis articulation provide 4800 W BOL.4 50 Ahr NiH batteries. Payload: 16 Ku-band transponders which can be configured into 32 high quality television channels. Permits access from ground antennas 1.2 meters dia. and smaller. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 21 deg W in 1992-1999 As of 6 September 2001 located at 21.54 deg W drifting at 0.011 deg W per day. As of 2007 Mar 10 located at 160.51W drifting at 11.137W degrees per day.

1992 August 22 - 22:40 GMT - Launch Vehicle: Atlas. Atlas I AC-71 / Centaur I 5051 FAILURE: Destroyed by range safety. Centaur engine turbopump did not start. Identical to the 18 April 1991 failure. Galaxy 1R Spacecraft: HS 376. Agency: Hughes Communications Inc.

1993 March 25 - 21:38 GMT - Launch Vehicle: Atlas. Atlas I AC-74 / Centaur I 5054 FAILURE: Atlas engine failure. Loss of booster engine thrust resulted in a lower-than planned 1560 km x 1900 km orbit. UHF F1 Mass: 2,866 kg (6,318 lb). Spacecraft: HS 601. Agency: HCI. Perigee: 36,053 km (22,402 mi). Apogee: 36,098 km (22,430 mi). Inclination: 21.10 deg. Period: 1,450.90 min. US Navy communications; Ultra High Frequency Follow On; unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle was to have put payload into subsynchronous earth orbit with MRS trajectory option. As of 28 August 2001 located at 45.55 deg W drifting at 3.676 deg W per day. As of 2007 Mar 10 located at 95.89E drifting at 3.687W degrees per day.

1993 September 3 - 11:17 GMT - Launch Vehicle: Atlas. Atlas I AC-75 / Centaur I 5055 USA 95 Mass: 2,844 kg (6,269 lb). Spacecraft: HS 601. Agency: HCI. Perigee: 35,767 km (22,224 mi). Apogee: 35,805 km (22,248 mi). Inclination: 5.00 deg. Period: 1,436.10 min. US Navy communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 72 deg E in 1993-1999.

1993 December 16 - 00:38 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-108 / Centaur II 8201 Telstar 401 Mass: 3,375 kg (7,440 lb). Spacecraft: AS 7000. Agency: AT&T. Perigee: 35,759 km (22,219 mi). Apogee: 35,821 km (22,258 mi). Inclination: 4.30 deg. Period: 1,436.30 min. Stationed at 97 deg W. 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 IFR trajectory option. Positioned in geosynchronous orbit at 97 deg W in 1994-1997 As of 5 September 2001 located at 100.42 deg W drifting at 0.039 deg E per day. As of 2007 Mar 10 located at 97.36W drifting at 0.024W degrees per day.

1994 April 13 - 06:04 GMT - Launch Vehicle: Atlas. Atlas I AC-73 / Centaur I 5053 GOES 8 Mass: 2,105 kg (4,640 lb). Spacecraft: GOES-Next. Agency: NOAA. Perigee: 35,770 km (22,220 mi). Apogee: 35,807 km (22,249 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Geostationary Environmental Satellite. Stationed at 75 deg W. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 90 deg W in 1994-1995; 75 deg W in 1995-1999 As of 5 September 2001 located at 74.78 deg W drifting at 0.019 deg E per day. NASA announced that GOES-8 was "de-orbited" (presumably moved to a sub-synchronous orbit) on May 5, 2004 after 10 years of service. As of 2007 Mar 11 located at 87.46E drifting at 4.935W degrees per day.

1994 June 24 - 13:50 GMT - Launch Vehicle: Atlas. Atlas I AC-76 / Centaur I 5056 USA 104 Mass: 2,847 kg (6,276 lb). Spacecraft: HS 601. Agency: HCI. Perigee: 35,776 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 4.81 deg. Period: 1,436.05 min. US Navy communications . Stationed at 14.38 deg W 1995-1999. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option.

1994 October 6 - 06:35 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-111 / Centaur II 8202 Intelsat 703 Mass: 3,656 kg (8,060 lb). Spacecraft: FS-1300. Agency: Intelsat. Perigee: 35,779 km (22,231 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.0400 deg. Period: 1,436.07 min. 38 C-band and 20 Ku-band transponders. Initially positioned in geosynchronous orbit at 177 deg E in 1994-1996. Then reassigned to Intelsat subsidiary New Skies, redesignated NSS 703, and moved to 57 deg E after 1996. At the crossroads of three continents, NSS-703 provided cross-connectivity for Europe, Africa and Asia. NSS-703 was used for video contribution from Europe to India and Africa, and was capable of bringing signals from London to India and Australia in one hop. NSS-703's coverage included a global beam, and two C-band hemispheric beams, which covered Africa and the triangle from Eastern Iran to Japan and Australia, including all of India and China. Three steerable Ku-band spot beams targeted Europe and Iran, Central Asia and Afghanistan-Pakistan-North India. Expected end of life March 2009. As of 2007 Mar 9 located at 56.96E drifting at 0.001E degrees per day.

1995 January 10 - 06:18 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-113 / Centaur II 8203 Intelsat 704 Mass: 3,656 kg (8,060 lb). Spacecraft: FS-1300. Agency: Intelsat. Perigee: 35,776 km (22,230 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.10 deg. Stationed at 66.0 deg E. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 66 deg E in 1995-1999 As of 29 August 2001 located at 66.03 deg E drifting at 0.005 deg W per day. As of 2007 Mar 10 located at 66.03E drifting at 0.002W degrees per day.

1995 March 22 - 06:18 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-115 Intelsat 705 Mass: 3,669 kg (8,088 lb). Spacecraft: FS-1300. Agency: Intelsat. Perigee: 35,776 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Stationed at 50.1 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 50 deg W in 1995-1996; 18 deg W in 1996-1999 As of 5 September 2001 located at 17.97 deg W drifting at 0.006 deg W per day. As of 2007 Mar 11 located at 50.01W drifting at 0.007W degrees per day.

1995 May 23 - 05:52 GMT - Launch Vehicle: Atlas. Atlas I AC-77 / Centaur I 5057 GOES 9 Mass: 2,105 kg (4,640 lb). Spacecraft: GOES-Next. Agency: NOAA. Perigee: 35,809 km (22,250 mi). Apogee: 35,911 km (22,314 mi). Inclination: 0.20 deg. Period: 1,435.90 min. Stationed at 135 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 90 deg W in 1995; 135 deg W in 1996-1998; 98-105 deg W in 1998-1999 As of 5 September 2001 located at 103.62 deg W drifting at 0.009 deg W per day. As of 2007 Mar 10 located at 159.81E drifting at 0.002W degrees per day.

1995 August 29 - 00:53 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-117 JCSAT 3 Mass: 1,841 kg (4,058 lb). Spacecraft: HS 601. Agency: JSAT. Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.20 min. 8 transponders for digital TV. Stationed at 128.1 deg E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 128 deg E in 1995-1999 As of 5 September 2001 located at 128.05 deg E drifting at 0.005 deg E per day. As of 2007 Feb 20 located at 126.99E drifting at 0.144W degrees per day.

1995 December 2 - 08:08 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-121 SOHO Mass: 1,850 kg (4,070 lb). Spacecraft: SOHO. Agency: ESA. Perigee: 8,973 km (5,575 mi). Apogee: 671,400 km (417,100 mi). Inclination: 29.60 deg. Period: 29,196.30 min. Solar and Heliospheric Observatory; orbiting at L1 Lagrange point; solar physics. En route Earth-Sun L1 point Earth-Sun L1 libration point transfer trajectory. Inertial trajectory option.

1996 February 1 - 01:15 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-126 Palapa C-1 Spacecraft: HS 601. Agency: Satelind. Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. 30 C-band, 6 Ku-band transponders. Geostationary at 150.4E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 113 deg E in 1996; 150 deg E in 1996-1999 As of 5 September 2001 located at 50.03 deg E drifting at 0.006 deg E per day. As of 2007 Mar 11 located at 38.04E drifting at 0.007E degrees per day.

1996 April 30 - 04:31 GMT - Launch Vehicle: Atlas. Atlas I AC-78 / Centaur I 5058 Beppo SAX Spacecraft: SAX. Agency: ASI. Perigee: 584 km (362 mi). Apogee: 601 km (373 mi). Inclination: 4.00 deg. Period: 96.50 min. LEO. Satellite per Astronomia a raggi X; X-ray celestial observatory Launch vehicle put payload into low earth orbit with IFR trajectory option. 100th Atlas-Centaur flight.

1996 September 8 - 21:49 GMT - Launch Vehicle: Atlas. Atlas IIA AC-123 GE 1 Spacecraft: AS 2100. Agency: GE Americom. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geostationary at 103.0W. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 103 deg W in 1996-1999 As of 4 September 2001 located at 103.06 deg W drifting at 0.009 deg W per day. As of 2007 Mar 11 located at 103.03W drifting at 0.006W degrees per day.

1996 December 18 - 01:57 GMT - Launch Vehicle: Atlas. Atlas IIA AC-129 Inmarsat 3 F3 Mass: 1,021 kg (2,250 lb). Spacecraft: AS 4000. Agency: Inmarsat. Perigee: 35,764 km (22,222 mi). Apogee: 35,807 km (22,249 mi). Inclination: 0.00 deg. Period: 1,436.00 min. Geostationary at 157.6E. Launch vehicle put payload into geosynchronous transfer orbit with RAAN Cntl trajectory option. Positioned in geosynchronous orbit at 178 deg E in 1997-1999 As of 5 September 2001 located at 178.02 deg E drifting at 0.006 deg W per day. As of 2007 Mar 10 located at 178.19E drifting at 0.002E degrees per day.

1997 February 17 - 01:42 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-127 JCSAT 4 Spacecraft: HS 601. Agency: JSAT. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 150.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 150 deg E in 1997-1998; 124 deg E in 1998-1999; 127 deg E in 1999. As of 5 September 2001 located at 127.02 deg E drifting at 0.015 deg W per day. As of 2007 Mar 7 located at 150.01E drifting at 0.008W degrees per day.

1997 April 25 - 05:49 GMT - Launch Vehicle: Atlas. Atlas I AC-79 GOES 10 Spacecraft: GOES-Next. Agency: NOAA. Perigee: 35,780 km (22,230 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.40 deg. Period: 1,436.30 min. Geosynchronous. Stationed over 105.7W Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 105 deg W in 1997-1998; 135 deg W in 1998-1999 As of 6 September 2001 located at 135.09 deg W drifting at 0.037 deg W per day. As of 2007 Mar 11 located at 59.64W drifting at 0.009W degrees per day.

1997 July 28 - 01:15 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-133 Superbird C Spacecraft: HS 601. Agency: SCC. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 144.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 144 deg E in 1997-1999 As of 5 September 2001 located at 144.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 9 located at 143.94E drifting at 0.009W degrees per day.

1997 October 5 - 21:01 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-135 Echostar 3 Spacecraft: AS 7000. Agency: Echostar. Perigee: 35,777 km (22,230 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 61.4W Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 61 deg W in 1997-1999 As of 5 September 2001 located at 61.53 deg W drifting at 0.017 deg W per day. As of 2007 Mar 11 located at 61.50W drifting at 0.007W degrees per day.

1997 December 8 - 23:52 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-149 Galaxy 8i Spacecraft: HS 601. Agency: Panamsat. Perigee: 35,781 km (22,233 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 79.2W Launch vehicle put payload into geosynchronous transfer orbit with MRS trajectory option. Used HS-601 XIPS ion engine for station keeping. Positioned in geosynchronous orbit at 95 deg W in 1998-1999 As of 3 September 2001 located at 94.92 deg W drifting at 0.000 deg W per day. As of 2007 Mar 10 located at 37.58W drifting at 2.053W degrees per day.

1998 February 28 - 00:21 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-151 Intelsat 806 Spacecraft: AS 7000. Agency: Intelsat. Perigee: 35,775 km (22,229 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Initially positioned in geosynchronous orbit at 40 deg W in 1998-2001. 36 C-band and 6 Ku-band transponders. Later assigned to Intelsat spin-off New Skies, redesignated NSS-806, and moved to 319.5º East, giving it an optimum view of Latin American markets while also reaching the Iberian peninsula, the Canary Islands, Western Europe and much of Eastern Europe. Its tailored, high-powered hemispheric beam provided simultaneous coverage of both Europe and the Americas, with virtually complete coverage of North, Central and South America, therefore ensuring the maximum reach throughout Spanish and Portuguese speaking markets. Expected end of life July 2016. As of 2007 Mar 10 located at 40.47W drifting at 0.007W degrees per day.

1998 October 9 - 22:50 GMT - Launch Vehicle: Atlas. Atlas IIA AC-134 Hot Bird 5 Mass: 3,000 kg (6,600 lb). Spacecraft: Eurostar 2000. Agency: Eutelsat. Perigee: 35,766 km (22,223 mi). Apogee: 35,805 km (22,248 mi). Inclination: 0.00 deg. Geostationary at 10.0 degrees E. Positioned in geosynchronous orbit at 13 deg E in 1998-1999 As of 3 September 2001 located at 12.97 deg E drifting at 0.010 deg E per day. As of 2007 Mar 11 located at 25.56E drifting at 0.014W degrees per day.

1999 November 23 - 04:06 GMT - Launch Vehicle: Atlas. Atlas IIA AC-136 USA 146 Spacecraft: HS 601. Agency: USN. Perigee: 35,945 km (22,335 mi). Apogee: 36,626 km (22,758 mi). Inclination: 6.00 deg. UHF Follow-on satellite providing UHF and EHF communications, and Global Broadcast Service television for the US Navy. Positioned in geosynchronous orbit at 173 deg W in 1999; 72 deg E in 2000-2003.

2000 February 3 - 23:30 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-158 Hispasat 1C Mass: 3,112 kg (6,860 lb). Spacecraft: Spacebus 3000. Agency: Hispasat. Perigee: 35,778 km (22,231 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Spanish domestic geosynchronous communications satellite. Stationed at 30 deg W. Positioned in geosynchronous orbit at 30 deg W in 2000. As of 3 September 2001 located at 30.14 deg W drifting at 0.013 deg W per day. As of 2007 Mar 9 located at 30.01W drifting at 0.005W degrees per day.

2000 May 24 - 23:10 GMT - Launch Vehicle: Atlas V. LV Model: Atlas IIIA . Atlas 3A AC-201 Eutelsat W4 Mass: 3,190 kg (7,030 lb). Spacecraft: Spacebus 3000. Agency: Eutelsat. Perigee: 35,775 km (22,229 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Communications satellite. Maiden flight of Atlas IIIA with Russian RD-180 main engine; scrubbed four times. European Telecommunications Satellite Organization (Eutelsat) satellite equipped with 32 Ku-band transponders, and antennae covering Russia and Africa. It will be stationed at 36 deg E. This was the third of the high power Eutelsat W series to be launched (W1 was destroyed in a ground accident). Stationed at 36 deg E. Positioned in geosynchronous orbit at 32 deg E in 2000. As of 4 September 2001 located at 35.98 deg E drifting at 0.003 deg E per day. As of 2007 Mar 9 located at 36.08E drifting at 0.005E degrees per day.

2000 July 14 - 05:21 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-161 Echostar 6 Mass: 3,700 kg (8,100 lb). Spacecraft: FS-1300. Agency: Echostar. Perigee: 35,779 km (22,231 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Communications satellite, positioned in geosynchronous orbit at 149 deg W. By 5 September 2001 located at 119.07 deg W drifting at 0.002 deg W per day. As of 2007 Mar 10 located at 110.39W drifting at 0.006W degrees per day.

2001 June 19 - 04:41 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-156 ICO F-2 Mass: 2,750 kg (6,060 lb). Spacecraft: HS 601. Agency: ICO. Perigee: 10,385 km (6,452 mi). Apogee: 10,389 km (6,455 mi). Inclination: 45.00 deg. Period: 360.10 min. Launch delayed from June 5. The ICO-2 satellite was launched by British New ICO (formerly ICO Global Communications) to provide mobile communications and data/Internet services at S-band, supporting 4500 simultaneous calls. The Boeing BSS-601M satellite was similar to the standard geostationary 601 model except that it omitted the R-4D apogee engine and associated fuel, and had a larger payload section. Launch mass was 2700 kg; dry mass was around 2200-2400 kg with the remainder being station-keeping fuel. The AC-156 launch vehicle's Centaur stage reached a 167 x 10099 km x 44.6 deg transfer orbit 10 minutes after launch. A second burn 1.5 hours later put ICO-2 into a circular 10,100 km orbit. The first ICO satellite was launched in March 2000 but failed to reach orbit. ICO-2 was used for testing of the ICO system before the remaining satellites would be launched. Unlike the Iridium and Globalstar constellations, ICO proposed to use a small number of large satellites. The ICO fleet, anticipated to consist of 10 satellites, was to enable relay in S- and C-bands of voice and internet communications from/to land and ocean based mobile telephones. With a total power of 5 kW, ICO F2 was to enable a simultaneous capacity in 4,500 channels.

2001 October 11 - 02:32 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-162 USA 162 Mass: 3,600 kg (7,900 lb). Spacecraft: SDS-3. Agency: U.S. Air Force (U.S.). The Atlas AC-162 Centaur entered a 176 x 907 km x 28.2 deg parking orbit at 0242 GMT and then made a second burn to deploy its payload in a 274 x 37538 km x 26.5 deg geostationary transfer orbit at 0301 GMT. USA 162 was rumoured to be a data relay satellite used to return data from imaging satellites similar to the one launched on October 5 2001. It was also possible that the satellite is a signals intelligence payload. The satellite is owned and operated by the National Reconnaissance Office (NRO).

2002 February 21 - 12:43 GMT - Launch Vehicle: Atlas V. LV Model: Atlas 3B DEC . Atlas 3B-DEC AC-204 Echostar 7 Mass: 690 kg (1,520 lb). Spacecraft: LM 700. Agency: Echostar. Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Direct Broasdcasting satellite. The first launch of the Atlas 3B, with the Common Centaur stretched two-engine upper stage. Launch delayed from December 19, 2001 and January 22. The Echostar 7 communications satellite was placed into geostationary transfer orbit. The first burn of the Centaur put the stack into a 185 x 193 km x 28.1 deg parking orbit. At 1305 UTC the Centaur burned again to achieve the final 245 x 57060 km x 22.6 deg transfer orbit and separated from Echostar. As of 2007 Mar 11 located at 118.92W drifting at 0.006W degrees per day.

2003 April 12 - 00:47 GMT - Launch Vehicle: Atlas V. LV Model: Atlas 3B SEC . Atlas 3B-SEC AC-205 AsiaSat 4 Mass: 4,042 kg (8,911 lb). Spacecraft: HS 601. Agency: AsiaSat. Perigee: 35,772 km (22,227 mi). Apogee: 35,805 km (22,248 mi). Inclination: 0.00 deg. Period: 1,436.20 min. Delayed from May 28, 2002, and January 13, February 5, and April 11, 2003. AsiaSat 4 was designed to provide broadcast, telecommunications and broadband multimedia services to the Asia Pacific region, and direct-to-home broadcast servic-es to Hong Kong, from its orbital position of 122 deg É East longitude.The satellite generated up to 9,600 watts using two sun-tracking four-panel solar wings covered with triple-junction gallium arsenide solar cells. AsiaSat 4 was to operate in C-band and Ku-band. The satellite carried 28 active transponders with six spares in C-band, powered by 55-watt traveling-wave tube amplifiers (TWTAs), and 20 active transponders with four spares in Ku-band, powered by 140-watt TWTAs. The C-band payload was designed to offer pan-Asian coverage, similar to AsiaSat 3S, also a 601HP model. The Ku-band payload provided high power, and spot beams for selected areas in either the Fixed Satellite Service frequency band or in the Broadcast Satellite Service frequency band. As of 2007 Mar 10 located at 122.23E drifting at 0.011W degrees per day.

2003 December 18 - 02:30 GMT - Launch Vehicle: Atlas V. LV Model: Atlas 3B SEC . Atlas 3B-SEC AC-203 USA 174 Spacecraft: HS 601. Agency: USN. Perigee: 35,781 km (22,233 mi). Apogee: 35,798 km (22,243 mi). Inclination: 4.20 deg. Period: 1,436.20 min. The last UHF Follow-On communications satellite for the US Navy. The satellite provided fleet communications from geostationary orbit.

2004 March 13 - 05:40 GMT - Launch Vehicle: Atlas V. LV Model: Atlas IIIA . Atlas 3A AC-202 MBSAT Mass: 4,143 kg (9,133 lb). Spacecraft: FS-1300. Agency: Mobile Broadcasting Corp. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Mobile S-band digital broadcasting services for home and automobile users in Japan. As of 2007 Mar 9 located at 144.03E drifting at 0.009W degrees per day.

2004 May 19 - 22:22 GMT - Launch Vehicle: Atlas. Atlas IIAS AC-166 AMC-11 (GE-11) Mass: 2,316 kg (5,105 lb). Spacecraft: AS 2100. Agency: SES Americom. Perigee: 35,778 km (22,231 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.00 min. Delayed from May 17. As of 2007 Mar 11 located at 131.04W drifting at 0.000E degrees per day.