1957 August 30 - Launch Vehicle: Delta. Thor DM-18 104 FAILURE: Failure. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1957 October 3 - 17:13 GMT - Launch Vehicle: Delta. Thor DM-18 107 FAILURE: Failure. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1957 October 24 - 16:32 GMT - Launch Vehicle: Delta. Thor DM-18 109 Series I research and development launch Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). Stripped down Thor long-range flight test successful from AMR, impacting 4400 km downrange.

1957 December 19 - 20:12 GMT - Launch Vehicle: Delta. Thor DM-18 113 Research and development Series II test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). A Thor missile, the eighth tested and the fourth successfully, completed the first fully-guided Thor IRBM flight using an all-inertial guidance system.

1958 January 28 - 20:16 GMT - Launch Vehicle: Delta. Thor DM-18 114 FAILURE: Failure. Research and development Series II test Agency: USAF 6555 ATW. Apogee: 0 km ( mi). Thor IRBM successfully fired from Cape Canaveral, flew prescribed course, and impacted in preselected area.

1958 April 24 - 00:10 GMT - Launch Vehicle: Delta. Thor Able 116 FAILURE: Thor turbopump gearbox failed T+150 sec. Able RTV re-entry vehicle test flight Agency: USAF 6555ATW. Apogee: 0 km ( mi). Mouse 'Mia' not recovered.

1958 July 10 - 02:30 GMT - Launch Vehicle: Delta. Thor Able 118 Able RTV re-entry vehicle test flight Agency: USAF 6555ATW. Apogee: 1,600 km (900 mi). Mouse 'Mia II' reached 1600 km altitude, flew 9600 km range, but re-entry vehicle not recovered.

1958 July 23 - 22:13 GMT - Launch Vehicle: Delta. Thor Able 119 Able RTV re-entry vehicle test flight Agency: USAF 6555ATW. Apogee: 1,600 km (900 mi). Mouse 'Wickie' not recovered; nose cone lost.

1958 August 17 - 12:18 GMT - Launch Vehicle: Delta. Thor Able I 127 FAILURE: Thor exploded after 77 sec. Pioneer (1) Mass: 38 kg (83 lb). Spacecraft: Pioneer 0-1-2. Agency: U.S. Air Force. Apogee: 16 km (9 mi). First US lunar attempt. The first US Air Force lunar probe, using a Thor-Able booster. An explosion ripped it apart 77 seconds after launch.

1958 October 11 - 08:42 GMT - Launch Vehicle: Delta. Thor Able I 130 FAILURE: Third stage produced insufficient thrust. Partial Failure. Pioneer 1 Mass: 38 kg (83 lb). Spacecraft: Pioneer 0-1-2. Agency: NASA. Set distance record; failed to reach moon.

1958 November 8 - 07:30 GMT - Launch Vehicle: Delta. Thor Able I 129 FAILURE: Third stage ignition unsuccessful. Pioneer 2 Mass: 39 kg (85 lb). Spacecraft: Pioneer 0-1-2. Agency: NASA. Apogee: 1,550 km (960 mi). Pioneer 2 was launched from the Atlantic Missile Range, using a Thor-Able booster, the Air Force acting as executive agent to NASA. The 86.3-pound instrumented payload, intended as a lunar probe, failed to reach escape velocity.

1959 January 23 - Launch Vehicle: Delta. Thor Able II 128 FAILURE: Failure. RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 0 km ( mi).

1959 February 28 - 07:58 GMT - Launch Vehicle: Delta. Thor Able II 131 RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 520 km (320 mi).

1959 March 21 - 06:19 GMT - Launch Vehicle: Delta. Thor Able II 132 RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 520 km (320 mi).

1959 April 8 - 06:35 GMT - Launch Vehicle: Delta. Thor Able II 133 RVX-1 Reentry test / particles mission Agency: USAF. Apogee: 1,230 km (760 mi).

1959 May 21 - 06:40 GMT - Launch Vehicle: Delta. Thor Able II 135 RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 520 km (320 mi).

1959 June 11 - 06:44 GMT - Launch Vehicle: Delta. Thor Able II 137 RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 520 km (320 mi).

1959 August 7 - 14:24 GMT - Launch Vehicle: Delta. Thor Able III 134 Explorer 6 Mass: 64 kg (141 lb). Spacecraft: S-2. Agency: NASA. Perigee: 245 km (152 mi). Apogee: 42,400 km (26,300 mi). Inclination: 47.00 deg. Period: 765.00 min. First Earth photo; radiation data.

1959 September 17 - Launch Vehicle: Delta. Thor Able II-M1 136 FAILURE: Third stage failed. Transit 1A Mass: 119 kg (262 lb). Spacecraft: Transit. Agency: DARPA. First Transit test satellite; failed to reach orbit.

1960 March 11 - 13:00 GMT - Launch Vehicle: Delta. Thor Able IV 219 Pioneer 5 Mass: 43 kg (94 lb). Spacecraft: Pioneer 5. Agency: NASA. Solar research. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1960 April 1 - 11:40 GMT - Launch Vehicle: Delta. Thor Able II-M1 148 Tiros 1 Mass: 120 kg (260 lb). Spacecraft: Tiros. Agency: NASA. Perigee: 656 km (407 mi). Apogee: 696 km (432 mi). Inclination: 48.40 deg. Period: 98.30 min. TV and Infrared Observation Satellite; returned 22952 cloud cover photos. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 May 13 - 09:16 GMT - Launch Vehicle: Delta. Thor Delta 144/D1 FAILURE: Second stage attitude control failure. Echo 1 Mass: 56 kg (123 lb). Spacecraft: Echo. Agency: NASA.

1960 August 12 - 09:39 GMT - Launch Vehicle: Delta. Thor Delta 270/D2 Echo 1 Mass: 76 kg (167 lb). Spacecraft: Echo. Agency: NASA. Perigee: 966 km (600 mi). Apogee: 2,157 km (1,340 mi). Inclination: 47.30 deg. Period: 117.30 min. Balloon; passively relayed TV and voice transmissions. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 November 23 - 11:13 GMT - Launch Vehicle: Delta. Thor Delta 245/D3 Tiros 2 Mass: 130 kg (280 lb). Spacecraft: Tiros. Agency: NASA. Perigee: 547 km (339 mi). Apogee: 610 km (370 mi). Inclination: 48.50 deg. Period: 96.30 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1961 March 25 - 15:17 GMT - Launch Vehicle: Delta. Thor Delta 295/D4 Explorer 10 Mass: 35 kg (77 lb). Spacecraft: P-14. Agency: NASA. Perigee: 221 km (137 mi). Apogee: 181,100 km (112,500 mi). Inclination: 33.00 deg. Period: 5,013.90 min. Magnetic field data. Decay date suspect Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1961 July 12 - 10:25 GMT - Launch Vehicle: Delta. Thor Delta 286/D5 Tiros 3 Mass: 129 kg (284 lb). Spacecraft: Tiros. Agency: NASA. Perigee: 723 km (449 mi). Apogee: 790 km (490 mi). Inclination: 47.90 deg. Period: 100.00 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1961 August 16 - 03:21 GMT - Launch Vehicle: Delta. Thor Delta 312/D6 Explorer 12 Mass: 38 kg (83 lb). Spacecraft: EPE. Agency: NASA. Perigee: 790 km (490 mi). Apogee: 76,620 km (47,600 mi). Inclination: 33.40 deg. Period: 1,587.30 min. Radiation and solar wind data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1962 January 15 - 11:07 GMT - Launch Vehicle: Delta. Thor DSV-2D 337 AVT-1 Satellite test Agency: USAF. Apogee: 1,400 km (800 mi).

1962 February 8 - 12:43 GMT - Launch Vehicle: Delta. Thor Delta 317/D7 Tiros 4 Mass: 129 kg (284 lb). Spacecraft: Tiros. Agency: NASA. Perigee: 693 km (430 mi). Apogee: 812 km (504 mi). Inclination: 48.30 deg. Period: 99.90 min. Returned 32593 cloud cover photos. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1962 March 7 - 16:06 GMT - Launch Vehicle: Delta. Thor Delta 301/D8 OSO 1 Mass: 208 kg (458 lb). Spacecraft: OSO. Agency: NASA. Perigee: 522 km (324 mi). Apogee: 553 km (343 mi). Inclination: 32.80 deg. Period: 95.30 min. Orbiting Solar Observatory; solar flare observations. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1962 April 26 - 18:00 GMT - Launch Vehicle: Delta. Thor Delta 320/D9 Ariel 1 Mass: 60 kg (132 lb). Spacecraft: Ariel. Agency: NASA, United Kingdom. Perigee: 398 km (247 mi). Apogee: 1,203 km (747 mi). Inclination: 53.80 deg. Period: 100.80 min. Ionospheric studies; returned X-ray, ionospheric, cosmic ray data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1962 June 19 - 12:19 GMT - Launch Vehicle: Delta. Thor Delta 321/D10 Tiros 5 Mass: 129 kg (284 lb). Spacecraft: Tiros. Agency: NASA. Perigee: 580 km (360 mi). Apogee: 880 km (540 mi). Inclination: 58.10 deg. Period: 99.40 min. Returned 58226 cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1962 July 18 - 09:30 GMT - Launch Vehicle: Delta. Thor DSV-2D 338 AVT 2 Satellite test Agency: USAF. Apogee: 1,484 km (922 mi).

1962 September 18 - 08:53 GMT - Launch Vehicle: Delta. Thor Delta 318/D12 Tiros 6 Mass: 127 kg (279 lb). Spacecraft: Tiros. Agency: NASA. Perigee: 631 km (392 mi). Apogee: 654 km (406 mi). Inclination: 58.30 deg. Period: 97.60 min. Returned 66674 cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1962 October 31 - 08:03 GMT - Launch Vehicle: Delta. Thor Ablestar 319 AB012 Anna 1B Mass: 161 kg (354 lb). Spacecraft: Anna. Agency: U.S. Navy. Perigee: 1,075 km (667 mi). Apogee: 1,181 km (733 mi). Inclination: 50.10 deg. Period: 107.90 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1962 December 13 - 23:30 GMT - Launch Vehicle: Delta. Thor Delta B 355/D15 Relay 1 Mass: 78 kg (171 lb). Spacecraft: Relay. Agency: NASA. Perigee: 1,319 km (819 mi). Apogee: 7,440 km (4,620 mi). Inclination: 47.50 deg. Period: 185.10 min. Communications satellite technology tests. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1963 April 3 - 02:00 GMT - Launch Vehicle: Delta. Thor Delta B 357/D17 Explorer 17 Mass: 185 kg (407 lb). Spacecraft: AE. Agency: NASA GSF. Perigee: 254 km (157 mi). Apogee: 891 km (553 mi). Inclination: 57.60 deg. Period: 96.10 min. Atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1963 July 26 - 14:33 GMT - Launch Vehicle: Delta. Thor Delta B 370/D20 Syncom 2 Mass: 39 kg (85 lb). Spacecraft: Syncom. Agency: NASA GSF. Perigee: 35,891 km (22,301 mi). Apogee: 35,891 km (22,301 mi). Inclination: 32.70 deg. Period: 1,441.50 min. Experimental commsat; 1st geosynchronous satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 55 deg W in 1963; 26 deg W in 1965. Last known longitude (19 July 1995) 68.47 deg E drifting at 0.089 deg W per day.

1964 March 19 - 11:13 GMT - Launch Vehicle: Delta. Thor Delta B 391/D24 FAILURE: Insufficient third stage thrust. Explorer (20) Mass: 54 kg (119 lb). Spacecraft: BE. Agency: NASA. Also known as Explorer S-66.

1964 August 19 - 12:15 GMT - Launch Vehicle: Delta. Thor Delta D 417/D25 Syncom 3 Mass: 39 kg (85 lb). Spacecraft: Syncom. Agency: NASA GSF. Perigee: 35,784 km (22,235 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Experimental commsat; carried Star Flash experiment. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 64 deg W in 1964; 180 deg E in 1964; 25 deg W in 1965; 165 deg E in 1966-1969. Last known longitude (6 December 1974) 6.08 deg W drifting at 0.188 deg W per day.

1964 October 4 - 03:45 GMT - Launch Vehicle: Delta. Thor Delta C 392/D26 Explorer 21 Mass: 62 kg (136 lb). Spacecraft: IMP. Agency: NASA GSF. Perigee: 191 km (118 mi). Apogee: 95,590 km (59,390 mi). Inclination: 33.50 deg. Period: 2,097.00 min. Lower than planned orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1964 December 21 - 09:00 GMT - Launch Vehicle: Delta. Thor Delta C 393/D27 Explorer 26 Mass: 46 kg (101 lb). Spacecraft: EPE. Agency: NASA GSF. Perigee: 284 km (176 mi). Apogee: 10,043 km (6,240 mi). Inclination: 19.80 deg. Period: 205.70 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1965 January 22 - 07:52 GMT - Launch Vehicle: Delta. Thor Delta C 374/D28 Tiros 9 Mass: 138 kg (304 lb). Spacecraft: Tiros. Agency: NASA GSF. Perigee: 705 km (438 mi). Apogee: 2,563 km (1,592 mi). Inclination: 96.40 deg. Period: 119.00 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1965 April 6 - 23:47 GMT - Launch Vehicle: Delta. Thor Delta D 426/D30 Intelsat 1 F-1 Mass: 39 kg (85 lb). Spacecraft: Intelsat 1. Agency: INTELSAT. Perigee: 35,746 km (22,211 mi). Apogee: 35,819 km (22,256 mi). Inclination: 11.70 deg. Period: 1,435.90 min. Over Atlantic. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 28 deg W in 1965; 38 deg W in 1965-1966. As of 27 July 2001 located at 92.54 deg W drifting at 0.324 deg W per day. As of 2007 Jan 13 located at 47.74W drifting at 0.017E degrees per day.

1965 November 6 - 18:38 GMT - Launch Vehicle: Delta. Thor Delta E 457/D34 Explorer 29 Mass: 175 kg (385 lb). Spacecraft: GEOS. Agency: NASA GSF. Perigee: 1,120 km (690 mi). Apogee: 2,269 km (1,409 mi). Inclination: 59.40 deg. Period: 120.30 min. The primary objective of GEOS-A was to provide global geodetic measurements for determining the positions of fiducial control points on the Earth to an accuracy of 10 meters in an Earth centre of mass co-ordinate system, and to determine the structure of the Earth's gravity field to 5 parts in 10 million. Instrumentation included (1) four optical beacons, (2) laser reflectors, (3) a radio range transponder, (4) Doppler beacons, and (5) a range and range rate transponder. These were designed to operate simultaneously to fulfil the objectives of locating observation points (geodetic control stations) in a three dimensional earth centre-of-mass co-ordinate system within 10 m of accuracy, of defining the structure of the earth's irregular gravitational field and refining the locations and magnitudes of the large gravity anomalies, and of comparing results of the various systems onboard the spacecraft to determine the most accurate and reliable system. In January 1967, a failure in the satellite's command system rendered several geodetic systems inoperable. Radio doppler measurements and the passive laser reflector experiment could continue indefinitely, however. Additional Details: Explorer 29(480).

1965 December 16 - 07:31 GMT - Launch Vehicle: Delta. Thor Delta E 460/D35 Pioneer 6 Mass: 63 kg (138 lb). Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA ARC. Measured solar wind, Sun's magnetic field. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1966 February 3 - 07:41 GMT - Launch Vehicle: Delta. Thor Delta C 445/D36 ESSA 1 Mass: 138 kg (304 lb). Spacecraft: Tiros. Agency: ESSA. Perigee: 684 km (425 mi). Apogee: 806 km (500 mi). Inclination: 97.80 deg. Period: 99.70 min. Environmental Survey Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1966 July 1 - 16:02 GMT - Launch Vehicle: Delta. Thor Delta E1 467/D39 Explorer 33 Mass: 93 kg (205 lb). Spacecraft: IMP. Agency: NASA GSF. Perigee: 265,679 km (165,084 mi). Apogee: 480,762 km (298,731 mi). Inclination: 24.10 deg. Period: 38,792.40 min. Intended to enter lunar orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1966 August 17 - 15:20 GMT - Launch Vehicle: Delta. Thor Delta E1 462/D40 Pioneer 7 Mass: 63 kg (138 lb). Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA ARC. Perigee: 246 km (152 mi). Apogee: 993 km (617 mi). Inclination: 33.00 deg. Period: 97.20 min. Monitored solar wind, cosmic rays. SOLAR ORB. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1966 December 14 - 19:20 GMT - Launch Vehicle: Delta. Thor Delta G 471/D43 Biosatellite 1 Mass: 425 kg (936 lb). Spacecraft: Biosatellite. Agency: NASA ARC. Perigee: 295 km (183 mi). Apogee: 309 km (192 mi). Inclination: 33.50 deg. Period: 90.40 min. Reentry into the Earth's atmosphere was not achieved because the retrorocket failed to ignite. The biosatellite was never recovered. Although the scientific objectives of the mission were not accomplished, the Biosatellite I experience provided technical confidence in the program because of excellent performance in most other areas.

1967 March 8 - 16:12 GMT - Launch Vehicle: Delta. Thor Delta C 431/D46 OSO 3 Mass: 281 kg (619 lb). Spacecraft: OSO. Agency: NASA GSF. Perigee: 546 km (339 mi). Apogee: 570 km (350 mi). Inclination: 32.80 deg. Period: 95.80 min. Orbiting Solar Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1968 September 19 - 00:09 GMT - Launch Vehicle: Delta. Thor Delta M 529/D59 FAILURE: Control system failure; destroyed by range safety. Intelsat-3 F-1 Mass: 293 kg (645 lb). Spacecraft: Intelsat 3. Agency: Intelsat.

1968 December 19 - 00:32 GMT - Launch Vehicle: Delta. Thor Delta M 536/D63 Intelsat 3 F-2 Mass: 293 kg (645 lb). Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 35,984 km (22,359 mi). Apogee: 37,111 km (23,059 mi). Inclination: 15.10 deg. Period: 1,475.20 min. Over Brazil. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 24 deg W in 1969-1970. As of 3 September 2001 located at 96.04 deg E drifting at 9.557 deg W per day. As of 2007 Mar 9 located at 48.04W drifting at 9.553W degrees per day.

1969 February 6 - 00:39 GMT - Launch Vehicle: Delta. Thor Delta M 530/D66 Intelsat 3 F-3 Mass: 293 kg (645 lb). Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 35,767 km (22,224 mi). Apogee: 35,803 km (22,246 mi). Inclination: 6.10 deg. Period: 1,436.00 min. Stationed at 63 deg E. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 174 deg E in 1969; over the Indian Ocean 062 deg E in 1969-1975. Last known longitude (24 May 1979) 66.72 deg E drifting at 0.017 deg E per day.

1969 May 22 - 02:00 GMT - Launch Vehicle: Delta. Thor Delta M 533/D68 Intelsat 3 F-4 Mass: 293 kg (645 lb). Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 39,486 km (24,535 mi). Apogee: 39,752 km (24,700 mi). Inclination: 6.10 deg. Period: 1,636.30 min. Positioned in geosynchronous orbit over the Pacific Ocean at 175 deg E in 1969-1972; ? 1972-1977; over the Pacific Ocean 166 deg W in 1977. Last known longitude (20 May 1977) 161.73 deg E drifting at 44.175 deg W per day.Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1969 June 29 - 03:15 GMT - Launch Vehicle: Delta. Thor Delta N 539/D70 Biosatellite 3 Mass: 695 kg (1,532 lb). Spacecraft: Biosatellite. Agency: NASA ARC. Perigee: 363 km (225 mi). Apogee: 374 km (232 mi). Inclination: 33.50 deg. Period: 92.00 min. Biological capsule reentered 7/7/69. The intent had been to fly a 6 kg male pig-tailed monkey (Macaca nemestrina) named Bonnie in Earth-orbit for 30 days. However, after only 8.8 days in orbit, the mission was terminated because of the subject's deteriorating health. High development costs were a strong incentive for maximising the scientific return from the mission. Because of this, the scientific goals had become exceedingly ambitious over time, and a great many measurements were conducted on the single research subject flown. Although the mission was highly successful from a technical standpoint, the science results were apparently compromised. Additional Details: Biosatellite 3(1015).

1969 July 26 - 02:06 GMT - Launch Vehicle: Delta. Thor Delta M 547/D71 FAILURE: Third stage failure; left in unusable orbit. Intelsat 3 F-5 Mass: 269 kg (593 lb). Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 211 km (131 mi). Apogee: 433 km (269 mi). Inclination: 30.20 deg. Period: 91.00 min. Third stage failure; left in unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1969 August 9 - 07:52 GMT - Launch Vehicle: Delta. Thor Delta N 548/D72 OSO 6 Mass: 290 kg (630 lb). Spacecraft: OSO. Agency: NASA GSF. Perigee: 489 km (303 mi). Apogee: 554 km (344 mi). Inclination: 32.90 deg. Period: 95.10 min. Orbiting Solar Observatory; solar physics experiments. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1969 August 27 - 21:59 GMT - Launch Vehicle: Delta. Thor Delta L 540/D73 FAILURE: First stage hydraulics failure. Vehicle destructed at T+383 seconds. Pioneer E Mass: 67 kg (147 lb). Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA.

1969 November 22 - 00:37 GMT - Launch Vehicle: Delta. Thor Delta M 554/D74 Skynet 1A Mass: 243 kg (535 lb). Spacecraft: NATO 1. Agency: UK MoD. Perigee: 35,682 km (22,171 mi). Apogee: 35,894 km (22,303 mi). Inclination: 13.90 deg. Period: 1,436.20 min. Over Indian Ocean. Military communications. Previously registered by the United States in A/AC.105/INF.220: 1969-101A, orbital data 276 x 36716 km x 28.0 deg, category C. Positioned in geosynchronous orbit over the Indian Ocean at 41 deg E in 1969-1972?; ??? 1972-1977; over the Americas at 100-110 deg W in 1977-1998 As of 26 August 2001 located at 104.51 deg W drifting at 0.015 deg W per day. As of 2007 Mar 9 located at 106.94W drifting at 0.015W degrees per day.

1970 January 15 - 00:16 GMT - Launch Vehicle: Delta. Thor Delta M 557/D75 Intelsat 3 F-6 Mass: 293 kg (645 lb). Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 36,079 km (22,418 mi). Apogee: 36,126 km (22,447 mi). Inclination: 14.30 deg. Period: 1,452.30 min. Stationed at 336 deg E. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 25 deg W in 1970; over the Atlantic Ocean 30 deg W in 1970-1971; over the Atlantic Ocean 20 deg W in 1971 Apr-1972 Mar; over the Indian Ocean 64 deg E in 1972-1974; over the Pacific Ocean 177 deg W in 1975 As of 5 September 2001 located at 163.49 deg E drifting at 4.024 deg W per day. As of 2007 Feb 27 located at 47.49E drifting at 4.027W degrees per day.

1970 March 20 - 23:52 GMT - Launch Vehicle: Delta. Thor Delta M 558/D77 NATO 1 Mass: 243 kg (535 lb). Spacecraft: NATO 1. Agency: NATO. Perigee: 35,768 km (22,225 mi). Apogee: 35,801 km (22,245 mi). Inclination: 13.40 deg. Period: 1,436.00 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 18 deg W in 1970-1972; over the Americas at 100-110 deg W in 1977-1998 As of 3 September 2001 located at 101.97 deg W drifting at 0.023 deg E per day. As of 2007 Mar 9 located at 100.55W drifting at 0.016W degrees per day.

1970 April 23 - 00:46 GMT - Launch Vehicle: Delta. Thor Delta M 559/D78 Intelsat 3 F-7 Mass: 293 kg (645 lb). Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 35,775 km (22,229 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.90 deg. Period: 1,435.90 min. Stationed at 341 deg E. Positioned in geosynchronous orbit over the Atlantic Ocean at 19 deg W in 1970-1971 Last known longitude (1 January 1972) L 139.45 deg E drifting at 0.022 deg E per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1970 July 23 - 23:23 GMT - Launch Vehicle: Delta. Thor Delta M 563/D79 Intelsat 3 F-8 Mass: 270 kg (590 lb). Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 33,877 km (21,050 mi). Apogee: 36,599 km (22,741 mi). Inclination: 12.10 deg. Period: 1,408.20 min. Unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). As of 28 August 2001 located at 175.58 deg E drifting at 7.155 deg E per day. As of 2007 Mar 9 located at 110.93W drifting at 7.169E degrees per day.

1970 August 19 - 12:11 GMT - Launch Vehicle: Delta. Thor Delta M 561/D80 Skynet 1B Mass: 243 kg (535 lb). Spacecraft: NATO 1. Agency: UK MoD. Perigee: 278 km (172 mi). Apogee: 37,460 km (23,270 mi). Inclination: 25.90 deg. Period: 665.40 min. AKM failure left in unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1971 February 3 - 01:41 GMT - Launch Vehicle: Delta. Thor Delta M 560/D82 NATO 2 Mass: 243 kg (535 lb). Spacecraft: NATO 1. Agency: NATO. Perigee: 35,772 km (22,227 mi). Apogee: 35,802 km (22,246 mi). Inclination: 13.90 deg. Period: 1,436.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 26 deg W in 1971-1975?; over the Americas at 105 deg W in 1976-1983; over the Americas at 110 deg W in 1983; over the Americas at 105 deg W in 1983-1998 As of 5 September 2001 located at 104.88 deg W drifting at 0.004 deg W per day. As of 2007 Mar 9 located at 105.24W drifting at 0.007W degrees per day.

1971 March 13 - 16:15 GMT - Launch Vehicle: Delta. Thor Delta M6 562/D83 Explorer 43 Mass: 288 kg (634 lb). Spacecraft: IMP. Agency: NASA GSF. Perigee: 1,845 km (1,146 mi). Apogee: 203,130 km (126,210 mi). Inclination: 31.20 deg. Period: 5,957.90 min. Earth magnetosphere research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1971 September 29 - 09:45 GMT - Launch Vehicle: Delta. Thor Delta N 565/D85 OSO 7 Mass: 635 kg (1,399 lb). Spacecraft: OSO. Agency: NASA GSF. Perigee: 326 km (202 mi). Apogee: 572 km (355 mi). Inclination: 33.10 deg. Period: 93.50 min. Orbiting Solar Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1975 August 27 - 01:41 GMT - Launch Vehicle: Delta. Delta 2914 594/D114 Symphonie 2 Mass: 398 kg (877 lb). Spacecraft: Spacebus 100. Agency: CNES/DFV. Perigee: 35,866 km (22,286 mi). Apogee: 35,873 km (22,290 mi). Inclination: 12.70 deg. Period: 1,440.40 min. Jointly registered by the Federal Republic of Germany (A/AC.105/INF.329) and France (A/AC.105/INF.330). Symphonie flying model no II. Experimental telecommunications satellite. Orbit: geostationary. Also registered by the United Stat es in A/AC.105/INF.331 as 1975-77A, category C, with orbit 1427.4 min, 35364 x 35870 km x 0.0 deg Positioned in geosynchronous orbit over the Atlantic Ocean at 11 deg W in 1975-1985 As of 1 September 2001 located at 164.06 deg W drifting at 1.071 deg W per day. As of 2007 Mar 8 located at 167.97E drifting at 1.046W degrees per day.

1975 December 13 - 01:56 GMT - Launch Vehicle: Delta. Delta 3914 607/D118 Satcom 1 Mass: 464 kg (1,022 lb). Spacecraft: AS 1000. Agency: RCA Amer. Perigee: 35,875 km (22,291 mi). Apogee: 36,076 km (22,416 mi). Inclination: 12.80 deg. Period: 1,445.80 min. Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1976-1983; over the Americas at 119 deg W in 1983-1984; over the Pacific Ocean 139 deg W in 1984 As of 5 September 2001 located at 38.03 deg E drifting at 2.422 deg W per day. As of 2007 Mar 9 located at 137.85W drifting at 2.426W degrees per day.

1976 March 26 - 22:47 GMT - Launch Vehicle: Delta. Delta 3914 610/D121 RCA Satcom 2 Mass: 463 kg (1,020 lb). Spacecraft: AS 1000. Agency: RCA Amer. Perigee: 36,016 km (22,379 mi). Apogee: 36,494 km (22,676 mi). Inclination: 8.60 deg. Period: 1,460.10 min. Positioned in geosynchronous orbit over the Americas at 119 deg W in 1976-1984 over the Pacific Ocean 139 deg W in 1984-1985 As of 5 September 2001 located at 72.03 deg W drifting at 5.939 deg W per day. As of 2007 Mar 9 located at 127.82W drifting at 5.942W degrees per day.

1976 June 10 - 00:09 GMT - Launch Vehicle: Delta. Delta 2914 601/D124 Marisat 2 Mass: 362 kg (798 lb). Spacecraft: Marisat. Agency: Comsat. Perigee: 36,513 km (22,688 mi). Apogee: 37,604 km (23,365 mi). Inclination: 14.90 deg. Period: 1,501.60 min. Maritime communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 176 deg E in 1976-1991 over the Pacific Ocean 178 deg W in 1991-1996 As of 5 September 2001 located at 158.48 deg W drifting at 15.761 deg W per day. As of 2007 Mar 10 located at 162.62W drifting at 15.745W degrees per day.

1976 July 8 - 23:31 GMT - Launch Vehicle: Delta. Delta 2914-C 611/D125 Palapa 1 Mass: 300 kg (660 lb). Spacecraft: HS 333. Agency: Perumtel. Perigee: 35,818 km (22,256 mi). Apogee: 35,852 km (22,277 mi). Inclination: 8.60 deg. Period: 1,438.60 min. Palapa A1 and A2 were the initial elements of Indonesia's domestic communications satellite system. The spacecraft were identical to Canada's Anik and Western Union's Westars except for a modified parabolic reflector, enlarged to give maximum illumination of the Indonesian land mass. Operational lives for Palapa A1 and A2 ended June 1985 and January 1988, respectively. Spacecraft: Based on Hughes HS-333 design.1.5 m diameter parabolic reflector with 12 transponders working through 125 Earth stations. Spin stabilised with despun antenna and feeds. Payload: Both satellites carried 12 transponders that provided 4000 voice circuits or 12 simultaneous TV channels to the country's 6000+ inhabited islands. Positioned in geosynchronous orbit over the Indian Ocean at 83 deg E in 1976-1986? As of 28 August 2001 located at 177.38 deg E drifting at 0.588 deg W per day. As of 2007 Mar 10 located at 51.89W drifting at 0.649W degrees per day.

1976 October 14 - 22:44 GMT - Launch Vehicle: Delta. Delta 2914 614/D127 Marisat 3 Mass: 362 kg (798 lb). Spacecraft: Marisat. Agency: Comsat. Perigee: 35,782 km (22,233 mi). Apogee: 35,789 km (22,238 mi). Inclination: 11.60 deg. Period: 1,436.10 min. Maritime communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Indian Ocean at 73 deg E in 1976-on. As of 26 August 2001 located at 33.84 deg W drifting at 0.011 deg W per day. As of 2007 Mar 10 located at 34.60W drifting at 0.007W degrees per day.

1977 January 28 - 00:49 GMT - Launch Vehicle: Delta. Delta 2914 613/D128 NATO 3B Mass: 701 kg (1,545 lb). Spacecraft: NATO 3. Agency: NATO. Perigee: 37,079 km (23,039 mi). Apogee: 37,421 km (23,252 mi). Inclination: 10.50 deg. Period: 1,511.50 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1977-1979 over the Atlantic Ocean 20 deg W in 1979-1982 over the Atlantic Ocean 18 deg W in 1983-1986 over the Atlantic Ocean60 deg W in 1987-1993 As of 5 September 2001 located at 74.61 deg W drifting at 18.018 deg W per day. As of 2007 Mar 10 located at 40.43E drifting at 18.015W degrees per day.

1977 March 10 - 23:16 GMT - Launch Vehicle: Delta. Delta 2914 612/D129 Palapa 2 Mass: 574 kg (1,265 lb). Spacecraft: HS 333. Agency: Perumtel. Perigee: 35,843 km (22,271 mi). Apogee: 35,867 km (22,286 mi). Inclination: 7.60 deg. Period: 1,439.60 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Indian Ocean at 80 deg E in 1977-1986? As of 5 September 2001 located at 64.27 deg W drifting at 0.845 deg W per day. As of 2007 Mar 11 located at 69.73E drifting at 0.893W degrees per day.

1977 September 13 - 23:31 GMT - Launch Vehicle: Delta. Delta 3914 619/D134 FAILURE: Vehicle exploded, probably SRM case. OTS 1 Mass: 865 kg (1,906 lb). Spacecraft: ECS/OTS. Agency: ESA. Orbital Test Satellite; failed to orbit.

1977 November 23 - 01:35 GMT - Launch Vehicle: Delta. Delta 2914 620/D136 Meteosat 1 Mass: 697 kg (1,536 lb). Spacecraft: Meteosat. Agency: ESA. Perigee: 35,777 km (22,230 mi). Apogee: 35,854 km (22,278 mi). Inclination: 11.90 deg. Period: 1,437.60 min. European Space Agency satellite. Launch time 0135 GMT. Reached definitive position, 0 deg longitude over the Gulf of Guinea, on 7 December. Launched by United States Delta rocket. Positioned in geosynchronous orbit over the Atlantic Ocean at E-4 deg W in 1977-1981; 8E-12 deg E in 1981-1984; 2E-6 deg E in 1984-1985 As of 29 August 2001 located at 51.23 deg E drifting at 0.354 deg E per day. As of 2007 Mar 3 located at 11.52E drifting at 0.055W degrees per day.

1978 January 26 - 17:36 GMT - Launch Vehicle: Delta. Delta 2914 628/D138 IUE 1 Mass: 672 kg (1,481 lb). Spacecraft: IUE. Agency: NASA/ESA. Perigee: 30,285 km (18,818 mi). Apogee: 41,296 km (25,660 mi). Inclination: 34.30 deg. Period: 1,436.30 min. International Ultraviolet Explorer. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 30 deg W in-60 deg W in 1978-1996 As of 3 September 2001 located at 35.66 deg E drifting at 0.773 deg W per day. As of 2007 Mar 8 located at 14.14W drifting at 0.700W degrees per day.

1978 May 11 - 22:59 GMT - Launch Vehicle: Delta. Delta 3914 627/D141 OTS 2 Mass: 865 kg (1,906 lb). Spacecraft: ECS/OTS. Agency: ESA. Perigee: 36,085 km (22,422 mi). Apogee: 36,128 km (22,448 mi). Inclination: 13.10 deg. Period: 1,452.50 min. Orbital Test Satellite; replacement for OTS-A; communications experiments. European Space Agency satellite. Launch time 2259 GMT. Reached definitive position, 10 deg east longitude, on May 24 at 0800 GMT. Launch by US Delta rocket. Positioned in geosynchronous orbit over the Atlantic Ocean at 10 deg E in 1978-1982 over the Atlantic Ocean 5 deg E in 1982-1990 As of 30 August 2001 located at 18.51 deg W drifting at 4.070 deg W per day. As of 2007 Mar 9 located at 39.02E drifting at 4.083W degrees per day.

1978 July 14 - 10:43 GMT - Launch Vehicle: Delta. Delta 2914 631/D143 ESA-Geos 2 Mass: 573 kg (1,263 lb). Spacecraft: ESA-Geos. Agency: ESA. Perigee: 36,027 km (22,386 mi). Apogee: 36,049 km (22,399 mi). Inclination: 14.60 deg. Period: 1,449.00 min. Magnetospheric research. European Space Agency satellite. Launch time 1043 GMT. Reached initial operational position of 6 deg East on 26 Jul 1978. During the two years of its mission, it will be maintained in position between longitude 0 and 35 deg east in geosynchronous orbit. Positioned in geosynchronous orbit over the Atlantic Ocean at 36 deg E in 1978-1979 over the Atlantic Ocean 6-36 deg E in 1979-1981; over the Atlantic Ocean 24 deg E in 1981; over the Atlantic Ocean 33-37 deg E in 1981-1984 As of 3 September 2001 located at 177.77 deg W drifting at 3.212 deg W per day. As of 2007 Mar 9 located at 179.12E drifting at 3.212W degrees per day.

1978 December 16 - 00:21 GMT - Launch Vehicle: Delta. Delta 3914 632/D147 Anik B1 (Telesat 4) Mass: 900 kg (1,980 lb). Spacecraft: Anik. Agency: Telesat. Perigee: 35,900 km (22,300 mi). Apogee: 35,927 km (22,323 mi). Inclination: 6.60 deg. Period: 1,442.60 min. Longitude 109.0. Function - telecommunications. Operating entity - Telesat Canada. Positioned in geosynchronous orbit over the Americas at 109 deg W in 1978-1986 As of 29 August 2001 located at 59.48 deg E drifting at 1.672 deg W per day. As of 2007 Mar 9 located at 13.64W drifting at 1.622W degrees per day.

1979 August 10 - 00:20 GMT - Launch Vehicle: Delta. Delta 2914 638/D149 Westar 3 Mass: 572 kg (1,261 lb). Spacecraft: HS 333. Agency: WUTC. Perigee: 35,868 km (22,287 mi). Apogee: 35,883 km (22,296 mi). Inclination: 10.20 deg. Period: 1,440.60 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 91 deg W in 1979-1990 As of 2 September 2001 located at 7.26 deg W drifting at 1.139 deg W per day. As of 2007 Mar 9 located at 158.25E drifting at 1.129W degrees per day.

1979 December 7 - 01:35 GMT - Launch Vehicle: Delta. Delta 3914 622/D150 RCA Satcom 3 Mass: 463 kg (1,020 lb). Spacecraft: AS 1000. Agency: RCA Amer. Perigee: 8,306 km (5,161 mi). Apogee: 35,502 km (22,059 mi). Inclination: 8.10 deg. Period: 788.90 min. Failed before reaching geosynchronous orbit.

1980 February 14 - 15:57 GMT - Launch Vehicle: Delta. Delta 3910 635/D151 SMM Mass: 2,315 kg (5,103 lb). Spacecraft: SMM. Agency: NASA GSF. Perigee: 405 km (251 mi). Apogee: 408 km (253 mi). Inclination: 28.50 deg. Period: 92.70 min. Solar Maximum Mission; solar observatory; repaired 4/9/84 by STS-41C in orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1980 September 9 - 22:27 GMT - Launch Vehicle: Delta. Delta 3914 637/D152 GOES 4 Mass: 627 kg (1,382 lb). Spacecraft: GOES. Agency: NOAA. Perigee: 35,948 km (22,337 mi). Apogee: 36,213 km (22,501 mi). Inclination: 9.40 deg. Period: 1,451.20 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit at 98 deg W in 1980-1981; 135 deg W in 1981-1983; 135-143 deg W in 1983; 139 deg W in 1984-1985; 10 deg W in 1985; 44 deg W in 1985-1988 As of 5 September 2001 located at 37.03 deg E drifting at 3.758 deg W per day. As of 2007 Mar 10 located at 45.89E drifting at 3.763W degrees per day.

1980 November 15 - 22:49 GMT - Launch Vehicle: Delta. Delta 3910/PAM 636/D153 SBS 1 Mass: 550 kg (1,210 lb). Spacecraft: HS 376. Agency: SBS. Perigee: 35,895 km (22,304 mi). Apogee: 35,928 km (22,324 mi). Inclination: 6.10 deg. Period: 1,442.50 min. Satellite Business Systems. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 100 deg W in 1981-1984; 99 deg W in 1984-1990 As of 4 September 2001 located at 115.72 deg E drifting at 1.627 deg W per day. As of 2007 Mar 10 located at 96.16E drifting at 1.647W degrees per day.

1981 May 22 - 22:29 GMT - Launch Vehicle: Delta. Delta 3914 645/D154 GOES 5 Mass: 836 kg (1,843 lb). Spacecraft: GOES. Agency: NOAA. Perigee: 35,775 km (22,229 mi). Apogee: 35,810 km (22,250 mi). Inclination: 6.50 deg. Period: 1,436.40 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 85 deg W in 1981; 75 deg W in 1981-1987; 106 deg W in 1987-1988; 65 deg W in 1988-1989 As of 31 August 2001 located at 107.28 deg W drifting at 0.248 deg W per day. As of 2007 Mar 9 located at 110.88W drifting at 0.246W degrees per day.

1981 September 24 - 23:09 GMT - Launch Vehicle: Delta. Delta 3910/PAM 641/D156 SBS 2 Mass: 550 kg (1,210 lb). Spacecraft: HS 376. Agency: SBS. Perigee: 35,781 km (22,233 mi). Apogee: 35,854 km (22,278 mi). Inclination: 10.10 deg. Period: 1,437.70 min. Positioned in geosynchronous orbit at 97 deg W in 1981-1983; 104 deg W in 1983; 97 deg W in 1983-1988; 99 deg W in 1988-1990; 97 deg W in 1990-1994; 71 deg W in 1994-1996 As of 31 August 2001 located at 125.63 deg E drifting at 0.458 deg W per day. As of 2007 Mar 9 located at 125.97W drifting at 0.561W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1981 November 20 - 01:37 GMT - Launch Vehicle: Delta. Delta 3910/PAM 640/D158 RCA Satcom 4; RCA Satcom 3R Mass: 1,078 kg (2,376 lb). Spacecraft: AS 3000. Agency: RCA Amer. Perigee: 35,824 km (22,259 mi). Apogee: 35,840 km (22,260 mi). Inclination: 8.20 deg. Period: 1,438.40 min. Positioned in geosynchronous orbit at 131 deg W in 1981-1991 As of 3 September 2001 located at 86.96 deg W drifting at 0.634 deg W per day. As of 2007 Mar 11 located at 140.04W drifting at 0.601W degrees per day.

1982 January 16 - 01:55 GMT - Launch Vehicle: Delta. Delta 3910/PAM 643/D159 RCA Satcom 4 Mass: 1,082 kg (2,385 lb). Spacecraft: AS 3000. Agency: RCA Amer. Perigee: 35,964 km (22,346 mi). Apogee: 35,994 km (22,365 mi). Inclination: 1.90 deg. Period: 1,446.00 min. Positioned in geosynchronous orbit at 83 deg W in 1982-1987; 82 deg W in 1987-1991 As of 2 September 2001 located at 171.96 deg E drifting at 2.443 deg W per day. As of 2007 Mar 9 located at 101.04W drifting at 2.479W degrees per day.

1982 February 26 - 00:04 GMT - Launch Vehicle: Delta. Delta 3910/PAM 644/D160 Westar 4 Mass: 1,072 kg (2,363 lb). Spacecraft: HS 376. Agency: WUTC. Perigee: 35,915 km (22,316 mi). Apogee: 35,943 km (22,333 mi). Inclination: 2.00 deg. Period: 1,443.40 min. TV, telephone. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 99 deg W in 1982-1991 As of 2 September 2001 located at 83.31 deg W drifting at 1.825 deg W per day. As of 2007 Mar 8 located at 112.98W drifting at 1.830W degrees per day.

1982 April 10 - 06:47 GMT - Launch Vehicle: Delta. Delta 3910/PAM 647/D161 Insat 1A Mass: 1,152 kg (2,539 lb). Spacecraft: Insat 1. Agency: ISRO. Perigee: 35,734 km (22,204 mi). Apogee: 35,829 km (22,263 mi). Inclination: 13.30 deg. Period: 1,435.80 min. Also carried transponders for domestic communications. Operational multipurpose satellite for telecommunications, meteorological, imaging and data relay, radio and television programme distribution and direct television broadcasting for community reception. Geosynchronous orbit longitude 74 E. A/AC.105/INF.391 was reissued as ST/SG/SER.E/79. Also registered by the United States as 1982-31A in ST/SG/SER.E/67, with category C and orbital parameters 1416.7 min, 35032 x 35783 km x 0.5 deg. Positioned in geosynchronous orbit at 73 deg E in 1982 As of 29 August 2001 located at 82.99 deg E drifting at 0.337 deg W per day. As of 2007 Mar 10 located at 39.55E drifting at 0.205W degrees per day.

1982 June 9 - 00:24 GMT - Launch Vehicle: Delta. Delta 3910/PAM 649/D162 Westar 5 Mass: 1,072 kg (2,363 lb). Spacecraft: HS 376. Agency: WUTC. Perigee: 36,017 km (22,379 mi). Apogee: 36,157 km (22,466 mi). Inclination: 1.40 deg. Period: 1,451.50 min. Voice, TV coverage for Alaska, Hawaii, Puerto Rico, Virgin Islands. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 123 deg W in 1982-1992 As of 5 September 2001 located at 132.07 deg W drifting at 3.816 deg W per day. As of 2007 Mar 10 located at 135.75E drifting at 3.802W degrees per day.

1983 April 28 - 22:26 GMT - Launch Vehicle: Delta. Delta 3914 D168 GOES 6 Mass: 836 kg (1,843 lb). Spacecraft: GOES. Agency: NOAA. Perigee: 35,778 km (22,231 mi). Apogee: 35,820 km (22,250 mi). Inclination: 10.10 deg. Period: 1,436.70 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 135 deg W in 1983-1984; 97 deg W in-108 deg W in 1984-1987; 135 deg W in 1987-1992 As of 5 September 2001 located at 75.78 deg W drifting at 0.054 deg W per day. As of 2007 Mar 10 located at 83.60W drifting at 0.139W degrees per day.

1983 July 28 - 22:49 GMT - Launch Vehicle: Delta. Delta 3920/PAM D171 Telstar 3A Mass: 625 kg (1,377 lb). Spacecraft: HS 376. Agency: AT&T. Perigee: 35,885 km (22,297 mi). Apogee: 36,108 km (22,436 mi). Inclination: 6.50 deg. Period: 1,446.80 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 96 deg W in 1983-1985; 105 deg W in 1985; 96 deg W in 1985-1994; 107 deg W in 1994; 20 deg E in 1995-1996 As of 5 September 2001 located at 143.88 deg W drifting at 2.714 deg W per day. As of 2007 Mar 11 located at 158.94W drifting at 2.690W degrees per day.

1983 September 22 - 22:16 GMT - Launch Vehicle: Delta. Delta 3920/PAM D173 Galaxy 2 Mass: 1,218 kg (2,685 lb). Spacecraft: HS 376. Agency: HCI. Perigee: 35,785 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 74 deg W in 1983-1994 As of 4 September 2001 located at 110.16 deg W drifting at 0.457 deg W per day. As of 2007 Mar 10 located at 57.56E drifting at 0.460W degrees per day.

1984 August 16 - 14:48 GMT - Launch Vehicle: Delta. Delta 3924 D175 CCE-1 Mass: 242 kg (533 lb). Spacecraft: AMPTE. Agency: NASA. Perigee: 1,121 km (696 mi). Apogee: 49,671 km (30,864 mi). Inclination: 4.80 deg. Period: 939.50 min. Charge Composition Explorer; detected tracer ions released into magnetosphere by IRM. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1984 November 14 - 00:34 GMT - Launch Vehicle: Delta. Delta 3914 D177 NATO 3D Mass: 320 kg (700 lb). Spacecraft: NATO 3. Agency: NATO. Perigee: 35,779 km (22,231 mi). Apogee: 35,796 km (22,242 mi). Inclination: 2.20 deg. Period: 1,436.20 min. Stationed at 138 deg W. Positioned in geosynchronous orbit at 30 deg W in 1985; 50 deg W in 1985-1986; 21 deg W in 1986-1991; 30 deg W in 1991-1993; 21 deg W in1993-1997; 18 deg W in 1997-1999 As of 31 August 2001 located at 19.33 deg W drifting at 0.021 deg W per day. As of 2007 Mar 10 located at 120.20W drifting at 19.149W degrees per day.

1986 May 3 - 22:18 GMT - Launch Vehicle: Delta. Delta 3914 D178 FAILURE: Stage one main engine shutdown at T+71 seconds due to electrical failure. GOES G Spacecraft: GOES. Agency: NOAA.

1987 February 26 - 23:05 GMT - Launch Vehicle: Delta. Delta 3914 D179 GOES 7 Mass: 399 kg (879 lb). Spacecraft: GOES. Agency: NOAA. Perigee: 35,777 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 1.20 deg. Period: 1,436.20 min. Stationed at 83 deg W. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 75 deg W in 1987-1988; 108 deg W in-98 deg W in 1989-1992; 111 deg W in 1992; 112 deg W in 1993-1994; 135 deg W in 1995; 98 deg W in 1996-1998 As of 5 September 2001 located at 179.83 deg E drifting at 0.023 deg W per day. As of 2007 Mar 9 located at 176.12W drifting at 0.061W degrees per day.

1989 February 14 - 18:30 GMT - Launch Vehicle: Delta. Delta 6925 D184 USA 35 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 21,480 km (13,340 mi). Apogee: 21,758 km (13,519 mi). Inclination: 56.60 deg. Period: 777.00 min. First launch of second generation / operational Global Positioning System. Placed in Plane E Slot 1 of the constellation. Suffered a shutdown of its onboard reaction wheels on March 26, 2000. Decommissioned on April 14, 2000 and replaced by GPS 2R-4.

1989 June 10 - 22:19 GMT - Launch Vehicle: Delta. Delta 6925 D185 USA 38 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 19,849 km (12,333 mi). Apogee: 20,514 km (12,746 mi). Inclination: 54.80 deg. Period: 718.00 min. Global Positioning System. Placed in Plane B Slot 3.

1989 August 18 - 05:58 GMT - Launch Vehicle: Delta. Delta 6925 D186 USA 42 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 21,509 km (13,365 mi). Apogee: 21,576 km (13,406 mi). Inclination: 56.40 deg. Period: 773.80 min. Global Positioning System. Retired.

1989 October 21 - 09:31 GMT - Launch Vehicle: Delta. Delta 6925 D188 USA 47 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 21,190 km (13,160 mi). Apogee: 21,236 km (13,195 mi). Inclination: 53.30 deg. Period: 760.20 min. Global Positioning System. Placed in Plane A Slot 5.

1990 January 24 - 22:55 GMT - Launch Vehicle: Delta. Delta 6925 D191 USA 50 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 21,168 km (13,153 mi). Apogee: 21,226 km (13,189 mi). Inclination: 55.00 deg. Period: 759.50 min. Global Positioning System. Retired.

1990 March 26 - 02:45 GMT - Launch Vehicle: Delta. Delta 6925 D193 USA 54 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,960 km (13,020 mi). Apogee: 21,156 km (13,145 mi). Inclination: 53.70 deg. Period: 753.80 min. Global Positioning System. Declared unusable on 21 May 1996 at 22:42 following two uncommanded changes in frequency standards.

1990 June 1 - 21:48 GMT - Launch Vehicle: Delta. Delta 6920-10 D195 ROSAT Mass: 2,426 kg (5,348 lb). Spacecraft: ROSAT. Agency: DLR. Perigee: 539 km (334 mi). Apogee: 554 km (344 mi). Inclination: 53.00 deg. Period: 95.60 min. West German extreme UV, X-ray telescope; all-sky survey.

1990 August 2 - 05:39 GMT - Launch Vehicle: Delta. Delta 6925 D197 USA 63 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 19,896 km (12,362 mi). Apogee: 20,468 km (12,718 mi). Inclination: 54.70 deg. Period: 718.00 min. Global Positioning System. Placed in Plane E Slot 2.

1990 October 1 - 21:56 GMT - Launch Vehicle: Delta. Delta 6925 D199 USA 64 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,002 km (12,428 mi). Apogee: 20,363 km (12,652 mi). Inclination: 55.40 deg. Period: 718.00 min. Global Positioning System. Placed in Plane D Slot 5.

1990 November 26 - 21:39 GMT - Launch Vehicle: Delta. Delta 7925 D201 USA 66 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 19,978 km (12,413 mi). Apogee: 20,384 km (12,666 mi). Inclination: 54.90 deg. Period: 717.90 min. Global Positioning System. Placed in Plane E Slot 5.

1991 July 4 - 02:32 GMT - Launch Vehicle: Delta. Delta 7925 D206 USA 71 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,043 km (12,454 mi). Apogee: 20,319 km (12,625 mi). Inclination: 55.60 deg. Period: 717.90 min. Global Positioning System. Placed in Plane D Slot 1.

1992 June 7 - 16:40 GMT - Launch Vehicle: Delta. Delta 6920-10 D210 EUVE Mass: 3,275 kg (7,220 lb). Spacecraft: EUVE. Agency: NASA GSF. Perigee: 510 km (310 mi). Apogee: 524 km (325 mi). Inclination: 28.40 deg. Period: 95.00 min. Extreme Ultra-Violet Explorer; mapped galactic EUV sources. The Extreme Ultraviolet Explorer was switched off on February 2, 2001. NASA decided to terminate funding for the mission, even though the spacecraft was still operating well. The sky survey was completed in January 1993 and after that the EUVE was used by guest astronomers for observations of specific targets. The final observations were made on January 26, 2001. After end-of-life tests of the never-used backup high voltage supplies and checking the remaining battery capacity, EUVE was stabilized pointing away from the Sun and sent into safehold at 2359 GMT on January 31. The transmitters were commanded off on February 2.

1992 July 24 - 14:26 GMT - Launch Vehicle: Delta. Delta 6925 D212 Geotail Mass: 1,008 kg (2,222 lb). Spacecraft: Geotail. Agency: ISAS. Perigee: 57,448 km (35,696 mi). Apogee: 399,941 km (248,511 mi). Inclination: 18.00 deg. Period: 18,904.40 min. Measured magnetosphere and Earth's geomagnetic tail. To investigate the structure and dynamics of the geomagnetic tail that extends on the nightside of the Earth. Launch time 1426 GMT. Launching states Japan and the United States of America. Launching organization NASA.

1992 September 9 - 08:57 GMT - Launch Vehicle: Delta. Delta 7925 D214 USA 84 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 19,909 km (12,370 mi). Apogee: 20,453 km (12,708 mi). Inclination: 54.50 deg. Period: 718.00 min. Global Positioning System. Placed in Plane A Slot 4.

1992 November 22 - 23:54 GMT - Launch Vehicle: Delta. Delta 7925 D216 USA 85 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,038 km (12,451 mi). Apogee: 20,325 km (12,629 mi). Inclination: 55.50 deg. Period: 718.00 min. Global Positioning System. Placed in Plane F Slot 4.

1993 February 3 - 02:55 GMT - Launch Vehicle: Delta. Delta 7925 D218 USA 88 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,006 km (12,431 mi). Apogee: 20,359 km (12,650 mi). Inclination: 54.80 deg. Period: 718.00 min. Global Positioning System. Placed in Plane Plane B Slot 1.

1993 March 30 - 03:09 GMT - Launch Vehicle: Delta. Delta 7925 D219 USA 90 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,072 km (12,472 mi). Apogee: 20,293 km (12,609 mi). Inclination: 55.00 deg. Period: 718.00 min. Global Positioning System. Placed in Plane C Slot 3.

1993 May 13 - 00:07 GMT - Launch Vehicle: Delta. Delta 7925 D220 USA 91 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,017 km (12,437 mi). Apogee: 20,345 km (12,641 mi). Inclination: 55.10 deg. Period: 718.00 min. Global Positioning System. Placed in Plane C Slot 4.

1993 June 26 - 13:27 GMT - Launch Vehicle: Delta. Delta 7925 D221 USA 92 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,112 km (12,496 mi). Apogee: 20,250 km (12,580 mi). Inclination: 54.60 deg. Period: 717.90 min. Global Positioning System. Placed in Plane A Slot 1.

1993 December 8 - 00:48 GMT - Launch Vehicle: Delta. Delta 7925 D224 USA 98 Mass: 1,430 kg (3,150 lb). Spacecraft: ECS/OTS. Agency: NATO. Perigee: 35,767 km (22,224 mi). Apogee: 35,805 km (22,248 mi). Inclination: 2.20 deg. Period: 1,436.10 min. NATO encrypted communications relay. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 6 deg E in 1994-1998; 20 deg W in 1998-1999 As of 2 September 2001 located at 20.16 deg W drifting at 0.009 deg W per day. As of 2007 Mar 10 located at 35.47E drifting at 0.007E degrees per day.

1994 March 10 - 03:40 GMT - Launch Vehicle: Delta. Delta 7925 D226 USA 100 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,000 km (12,000 mi). Apogee: 20,366 km (12,654 mi). Inclination: 53.90 deg. Period: 718.00 min. Final element of initial GPS constellation. Placed in Plane C Slot 1.

1995 December 30 - 13:48 GMT - Launch Vehicle: Delta. Delta 7920-10 D230 XTE Mass: 3,000 kg (6,600 lb). Spacecraft: XTE. Agency: NASA GSF. Perigee: 565 km (351 mi). Apogee: 583 km (362 mi). Inclination: 23.00 deg. Period: 96.10 min. X-ray Timing Explorer; X-ray astronomy.

1996 July 16 - 00:50 GMT - Launch Vehicle: Delta. Delta 7925 D237 USA 126 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,127 km (12,506 mi). Apogee: 20,237 km (12,574 mi). Inclination: 55.10 deg. Period: 717.90 min. Placed in Plane E Slot 3 of the constellation.

1996 September 12 - 08:49 GMT - Launch Vehicle: Delta. Delta 7925 D238 USA 128 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,042 km (12,453 mi). Apogee: 20,320 km (12,620 mi). Inclination: 54.70 deg. Period: 718.00 min. Placed in Plane B Slot 2 of the constellation.

1996 November 7 - 17:00 GMT - Launch Vehicle: Delta. Delta 7925 D239 Mars Global Surveyor Spacecraft: Mars Global Surveyor. Agency: NASA/JPL. Mars Global Surveyor entered a 258 x 54021 km x 93.3 deg polar orbit around Mars on 12 September 1997 after a 22 minute burn of its main engine. After a long aerobraking phase to a lower circular orbit, the spacecraft began its primary mission of photographing and observing changes on the Martian surface in March 1999. After nearly ten years of service, the last signals from MGS were received on 3 November 2006. The spacecraft went silent after an incorrect software upload caused its solar arrays to lose power.

1997 January 17 - 16:28 GMT - Launch Vehicle: Delta. Delta 7925 D241 FAILURE: T+12 sec GEM strap-on number 2 structural failure. GPS 42 Mass: 2,030 kg (4,470 lb). Spacecraft: GPS Block 2R. Agency: MDSSC. Destroyed in launch vehicle failure.

1997 May 20 - 22:39 GMT - Launch Vehicle: Delta. Delta 7925 D243 Thor 2 Spacecraft: HS 376. Agency: Telenor. 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 0.8W Positioned in geosynchronous orbit at 1 deg W in 1997-1999 As of 5 September 2001 located at 0.73 deg W drifting at 0.000 deg E per day. As of 2007 Mar 9 located at 0.76W drifting at 0.002W degrees per day.

1997 July 23 - 03:43 GMT - Launch Vehicle: Delta. Delta 7925 D245 USA 132 Mass: 2,030 kg (4,470 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,132 km (12,509 mi). Apogee: 20,235 km (12,573 mi). Inclination: 55.80 deg. Period: 718.00 min. Placed in Plane F Slot 3 of the constellation.

1997 August 25 - 14:39 GMT - Launch Vehicle: Delta. Delta 7920-8 D247 ACE Spacecraft: ACE. Agency: NASA GSF. Perigee: 176 km (109 mi). Apogee: 128,196 km (79,657 mi). Period: 86,411.37 min. Earth-Sun L1 point

1997 November 6 - 00:30 GMT - Launch Vehicle: Delta. Delta 7925 D249 USA 134 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 19,970 km (12,400 mi). Apogee: 20,394 km (12,672 mi). Inclination: 55.00 deg. Period: 718.00 min. Final GPS Block 2A satellite. Placed in Plane A Slot 3.

1998 February 14 - 14:34 GMT - Launch Vehicle: Delta. Delta 7420-10C D253 Globalstar FM1 Mass: 222 kg (489 lb). Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. Plane 1. Ascending node 43.9 degrees.

1998 April 24 - 22:38 GMT - Launch Vehicle: Delta. Delta 7420-10C D256 Globalstar FM6 Mass: 222 kg (489 lb). Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,503 km (933 mi). Apogee: 1,523 km (946 mi). Inclination: 52.00 deg. Period: 116.30 min. Plane 2. Ascending node 90.4 degrees.

1998 June 10 - 00:35 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D258 Thor 3 Spacecraft: HS 376. Agency: Telenor. Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.10 deg. Period: 1,436.10 min. The spacecraft was delivered to its final orbit in a complex series of five engine burns by three rocket stages. The Delta's second stage demonstrated its restart capability in 4 burns: Burn 1 placed the rocket and payload into a low circular orbit; Burn 2 raised the apogee to 1400 km; Burn 3 circularised the orbit at 1400 km. The second stage then separated, and Burn 4 lowered the spent stage's perigee to a low altitude to ensure the stage would decay quickly and not add to the space junk already on orbit. Stage 3 burned once to place the payload and its kick motor into a high 1400 km perigee geosynchronous transfer orbit. The Stage 4 Star 30 apogee kick motor circularised the spacecraft's orbit at geostationary altitude. Geostationary at 0.8 degrees W. Positioned in geosynchronous orbit at 1 deg W in 1998-1999 As of 4 September 2001 located at 0.83 deg W drifting at 0.000 deg E per day. As of 2007 Mar 9 located at 0.85W drifting at 0.002W degrees per day.

1998 October 24 - 12:08 GMT - Launch Vehicle: Delta. Delta 7326-9.5 D261 Deep Space 1 Mass: 486 kg (1,071 lb). Spacecraft: Deep Space 1. Agency: NASA/JPL. The primary mission of Deep Space 1 probe was to test new technology for future interplanetary spacecraft, the main experiment being an ion propulsion engine using xenon propellant. It had an initial mass of 486.3 kg, including 81.5 kg of Xenon and 31.1 kg of hydrazine propellants. The Delta 7326 used three Alliant GEM-40 solid strap-on motors, the standard Delta II core vehicle, and a Thiokol Star 37FM solid motor as the third stage. The Delta second stage entered a 185 km parking orbit, then fired again to enter a 174 km x 2744 km x 28.5 degree orbit. The Star 37FM then separated and accelerated to place Deep Space 1 to escape velocity. Deep Space 1 successfully started its ion engine on November 24 after an initial attempt failed after four minutes on November 10. From its initial solar orbit of 0.99 AU x 1.32 AU x 0.4 degree, Deep Space 1 was to fly past the 3 km diameter asteroid 1992 KD at its perihelion of 1.33 AU. The spacecraft then flew past the nucleus of comet 19P/Borrelly at a distance of 2200 km at 2230 GMT on Sep 22 2001. It survived the encounter in good shape, sending back photos of the comet. At the encounter DS1 was in a 1.3 x 1.5 AU x 0 deg (ecliptic) solar orbit; Borrelly's orbit was 1.3 x 5.9 AU.

1998 December 11 - 18:45 GMT - Launch Vehicle: Delta. Delta 7425-9.5 D264 Mars Climate Orbiter Mass: 629 kg (1,386 lb). Spacecraft: MCO. Agency: JPL. The Mars Climate Orbiter was the second flight of the Mars Surveyor Program. The probe was to enter a 160 km x 38600 km polar orbit around Mars on September 23,1999, and use aerobraking to reach a 373 km x 437 km x 92.9 degree sun-synchronous mapping orbit by November 23 1999. While the Mars Orbit Insertion burn began as planned on September 23, 1999 at 08:50 GMT, no signal was received after the spacecraft went behind the planet. Subsequent investigation showed that the spacecraft had plunged deep into the Martian atmosphere, with its closest approach to Mars being 57 km. It was concluded that the spacecraft burnt up in the atmosphere. It was later found that cutbacks in tracking, combined with incorrect values in a look-up table imbedded deep in the spacecraft software (use of pounds force instead of newtons) were to blame. This failure led to a shake-up of NASA's 'faster, better, cheaper' approach to unmanned spaceflight. Additional Details: Mars Climate Orbiter(12378).

1999 February 7 - 21:04 GMT - Launch Vehicle: Delta. Delta 7426-9.5 D266 Stardust Mass: 370 kg (810 lb). Spacecraft: Stardust. Agency: JPL. Stardust was to fly within 100 km of comet 81P/Wild-2 in January 2004 and recover cometary material using an aerogel substance. A return capsule would land on a lake bed in Utah in January 2006, returning the material to earth. The launch went as planned. The second stage ignited at 21:08 GMT and its first burn put the vehicle into a 185 km x 185 km x 28 degree parking orbit at 21:14 GMT. The second stage second burn at 21:25 changed the orbit to planned values of 178 km x 7184 km x 28.5 degrees. The Star 37FM solid third stage ignited at 21:29 GMT and placed the spacecraft into a 2 year period solar orbit. The spacecraft separated at 21:31 GMT. Meanwhile, the Delta 266 second stage burned a third time on its own, until its propellants were depleted, entering a final orbit of 294 km x 6818 km x 22.5 degrees. The Stardust probe flew past Earth at a distance of 3706 km at 1115 GMT on January 15, 2001, and flew near the Moon at a distance of 98000 km at around 0200 GMT on January 16. The gravity assist flyby changed Stardust's heliocentric orbit from 0.956 x 2.216 AU x 0.0 deg to 0.983 x 2.285 AU x 3.7 deg.

1999 June 24 - 15:44 GMT - Launch Vehicle: Delta. Delta 7320-10 D271 FUSE Spacecraft: FUSE. Agency: NASA GSF. Perigee: 753 km (467 mi). Apogee: 769 km (477 mi). Inclination: 25.00 deg. The Delta 3-m payload fairing was successfully jettisoned and the Far Ultraviolet Spectroscopic Explorer was placed in a 754 km x 769 km x 25.0 degree initial orbit. After separation the Delta second stage then a depletion burn and was left in a 182 x 915 km x 19.1 degree orbit from which it would quickly decay out of orbit. Checkout of FUSE in orbit was proceeding well as of July 1.

1999 July 25 - 07:46 GMT - Launch Vehicle: Delta. Delta 7420-10C D273 Globalstar 26 Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

1999 October 7 - 12:51 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D275 USA 145 Mass: 2,030 kg (4,470 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,163 km (12,528 mi). Apogee: 20,202 km (12,552 mi). Inclination: 52.60 deg. Period: 718.00 min. Third GPS Block 2R satellite. SVN 46 replaced SVN 50 which had been damaged by rain on Pad 17 earlier while being prepared for launch earlier in the year. Placed in Plane D Slot 2.

2000 May 11 - 01:48 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D278 USA 150 Mass: 2,030 kg (4,470 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,127 km (12,506 mi). Apogee: 20,235 km (12,573 mi). Inclination: 55.20 deg. Period: 717.90 min. Placed into an elliptical transfer orbit. The satellite's Thiokol Star 37 apogee motor was used to circularise the orbit at 20,000 km in Plane E Slot 1 of the constellation, replacing GPS GPS 2-1.

2000 July 16 - 09:17 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D279 USA 151 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,054 km (12,460 mi). Apogee: 20,309 km (12,619 mi). Inclination: 55.20 deg. Global Positioning satellite, placed in Plane B Slot 5. Launch delayed from June 15 and the June 21.

2000 November 10 - Launch Vehicle: Delta. Delta 7925-9.5 D281 USA 154 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,118 km (12,500 mi). Apogee: 20,244 km (12,579 mi). Inclination: 55.50 deg. Period: 717.90 min. The Delta stage 2 entered a 153 x 418 km x 37 deg parking orbit followed by a 172 x 1144 km second orbit; the PAM-D solid upper stage then fired to give SVN 41 a 20457 km apogee. The Thiokol Star 37FM solid kick motor was fired prior to November 13 to place the spacecraft in its final circular 20,000 km orbit. Placed in Plane F Slot 1 of the GPS constellation.

2001 January 30 - 07:55 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D283 USA 156 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,157 km (12,524 mi). Apogee: 20,208 km (12,556 mi). Inclination: 55.20 deg. Period: 718.00 min. GPS Block IIR production no. SV 14. Placed in Plane E Slot 4 of the constellation.

2001 April 7 - Launch Vehicle: Delta. Delta 7925-9.5 D284 2001 Mars Odyssey Mass: 725 kg (1,598 lb). Spacecraft: Mars Odyssey. Agency: JPL. The 2001 Mars Odyssey probe (formerly the Mars Surveyor 2001 Orbiter) was the first spacecraft in the revamped NASA Mars Exploration Program. Built by Lockheed Martin Astronautics (Denver) and JPL, the satellite was similar to Mars Climate Orbiter. It carried a 6-meter boom with a gamma ray spectrometer for remote sensing of Martian surface mineralogy, as well as an infrared imager and a radiation environment monitor. The probe had a dry mass of 376 kg and carried 349 kg of propellant. 2001 Mars Odyssey entered a 195 x 215 km x 52 deg parking orbit 10 minutes after launch. After a 12 minute coast the Delta second stage fired again and separated from the third stage, which placed the probe on an Earth escape trajectory into a 0.982 x 1.384 AU x 3.05 deg solar orbit. It escaped Earth's nominal gravitational sphere of influence at around 19:00 GMT on April 10.

The 2001 Mars Odyssey probe entered Mars orbit on October 24, 2001. The orbit insertion burn with the main 640 N bipropellant N2O4/hydrazine engine began at 0218 GMT lasted 20 min 19 sec. Mass of the spacecraft was then 456 kg, including 79 kg of fuel left. Initial orbit was was 272 x 26818 km x 93.42 deg with periapsis near the Martian north pole. 76 days of aerobraking began on October 26 to slowly circularise the orbit to its 400 km altitude, 2 hour period sun synchronous operational orbit. The solar panels reached 180 deg C as Odyssey skimmed through upper atmosphere of Mars on each orbit.

After reaching the operational orbit, the probe was to conduct a 917 day mapping program. It was to also serve as a communications relay for American and international landers expected to arrive in 2003/2004. In the Martian orbit, it was to map the distribution of elements and minerals on the surface, the distribution of hydrogen (embedded in water ice) and the radiation environment. The second was to assess the likelyhood of past or present life, and the third was to assess the radiation hazard to manned missions. The three major instruments on board were THEMIS (Thermal Emission Imaging System at the visible and infrared light) for the distribution, at 100 meter resolution, of minerals that form only in the presence of water, GRS (Gamma Ray Spectrometer) for determining hydrogen and other elements, and MARIE (presumably, MArs RadIation Environment) for determining the radiation hazard. THEMIS was to also enable site selection for a future manned landing. THEMIS was expected to provide 15,000 images, each covering 20 x 20 km. GRS carried two neutron monitors also. The gamma rays and neutrons come out of the surface in distinct, element-specific energies, released by cosmic ray bombardment.

2001 August 8 - 16:13 GMT - Launch Vehicle: Delta. Delta 7326-9.5 D287 Genesis Mass: 636 kg (1,402 lb). Agency: NASA/JPL. Perigee: 213,681 km (132,774 mi). Apogee: 1,175,513 km (730,428 mi). Inclination: 28.00 deg. Period: 97,345.15 min. Launch delayed from February 10 and July 30. The Genesis probe flew to the Earth-Sun L1 Lagrangian point and spend two years collecting samples of the solar wind. The collected samples were to be physically returned to Earth in a sample return capsule (air-snatch recovery was planned over Utah) and analysed in ground-based laboratories. The first burn of the Delta second stage put Genesis in a 185 x 197 km x 28.5 deg parking orbit at 1624 GMT. At 1712 GMT a second burn raised the orbit to 182 x 3811 km, and at 1713 GMT the third stage fired to put Genesis on its trajectory to L1 with a nominal apogee of around 1.2 million km. By the first week of November 2001 Genesis arrived at the Earth-Sun L1 point. A malfunctioning thermal radiator caused some concern for the health of the sample return capsule's critical battery, which was overheating, but Genesis began collecting solar wind samples on schedule.

On September 8, 2004, the Genesis space probe became the first spacecraft to return from beyond lunar orbit to the Earth's surface. The Genesis Sample Return Capsule separated from the spacecraft on September 8, 66,000 km above the Earth. The capsule successfully re-entered the atmosphere over Oregon at 11 km/s, but a wiring error resulted in the drogue parachute release mortar failing to fire at 33 km altitude. The capsule crashed to earth at 90 m/s in the Dugway Proving Ground at 40 07 40 N 113 30 29 W. Although the vehicle was smashed, some of the samples could be retrieved.

2002 July 3 - 06:47 GMT - Launch Vehicle: Delta. Delta 7425-9.5 D292 / Star 30 Contour Mass: 1,005 kg (2,215 lb). Spacecraft: Contour. Agency: NASA (U.S.), Cornell University (U.S.). Perigee: 212 km (131 mi). Apogee: 108,614 km (67,489 mi). Inclination: 30.60 deg. Period: 2,486.10 min. Launch delayed from July 1st. The latest NASA Discovery mission was successfully launched on Jul 3. The CONTOUR (Comet Nucleus Tour) probe, built and operated by the Johns Hopkins University's Applied Physics Laboratory (APL), began its five year mission to explore three comets, using repeated encounters with the earth to modify its orbit in order to reach each target. The first burn of the second stage completed at 0659 UTC putting the spacecraft in a 185 x 197 km x 29.7 deg parking orbit. At 0746 UTC the second stage restarted for a short 4s burn to 185 x 309 km x 29.7 deg, and then separated once the PAM-D (ATK Star 48B) solid third stage was spun up. The 1.5 minute burn of the third stage motor at 0748 UTC put it and CONTOUR in a 90 x 106689 km x 30.5 deg phasing orbit. By July 8 CONTOUR's orbit was 214 x 106686 km x 29.8 deg. CONTOUR stayed in this phasing orbit until August 15, when it was injected into solar orbit using its internal ATK Star 30 solid motor. Flyby of the first target, comet 2P/Encke, was scheduled for Nov 2003.

2003 March 31 - 22:09 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D297 USA 168 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 19,985 km (12,418 mi). Apogee: 20,376 km (12,661 mi). Inclination: 55.00 deg. Period: 717.90 min. Delayed from May 16, July 25, November 14, 2002, and February 6, 2003. Timely replenishment of GPS constellation.

2003 June 10 - Launch Vehicle: Delta. Delta 7925-9.5 D298 / Star 48 Spirit (Mars Exploration Rover A, MER-2) Mass: 1,063 kg (2,343 lb). Spacecraft: MER. Agency: NASA. Mars rover, placed in a 1.014 AU x 1.531 AU x 0.2 deg solar orbit. Anticipated landing on Mars on Launch delayed from May 30, June 6, 8 and 9. Payload included 530 kg Mars lander total mass, 170 kg Mars Rover mass..

2003 December 21 - 08:05 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D302 USA 175 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 19,963 km (12,404 mi). Apogee: 20,328 km (12,631 mi). Inclination: 55.10 deg. Period: 716.50 min. Tenth Navstar Block IIR (R = replenishment) launch.

2004 November 20 - 17:16 GMT - Launch Vehicle: Delta. Delta 7320-10C D309 Swift Mass: 1,331 kg (2,934 lb). Spacecraft: Swift. Agency: NASA. Perigee: 584 km (362 mi). Apogee: 604 km (375 mi). Inclination: 20.60 deg. Period: 96.60 min. NASA Medium-class Explorer satellite dedicated to study of gamma ray bursts, the third after the IMAGE and WMAP satellites. Delayed from December 5 and 29, 2003, January 14, April 29, July 15, September 1, October 7 and 26, November 8, 11, 17, 18 and 19.

2005 September 26 - 03:37 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D313 USA 183 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,006 km (12,431 mi). Apogee: 20,187 km (12,543 mi). Inclination: 55.00 deg. Period: 714.50 min. Delayed from December 2004; February 1, March 17, 2005. Moved up from May 20 2005. Then delayed from May 4, July 29, August 26, September 22, 2005. Became operational at 23:30 GMT on 16 December. First GPS Block IIR-M version, which added extra navigation signals for both civil and military users. The NASA-funded L2C tracking demonstration was managed by JPL and explored the use of a new Civilian code signal (L2C). The data was collected with Trimble NetRS receivers L2C-enabled firmware. The sites were globally distributed: South Africa, Norway, Antarctica, Hawaii, and Alaska.

2006 June 21 - 22:15 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D316 USA 187 Mass: 225 kg (496 lb). Spacecraft: Mitex. Agency: DARPA. Perigee: 184 km (114 mi). Apogee: 36,222 km (22,507 mi). Inclination: 25.25 deg. Period: 639.26 min. The Microsatellite Technology Experiment was a classified mission, believed to be a test of prototype inspect-and-disable satellites that would control the constellation of geostationary satellites on which the world depends for television reception and communications. Each microsatellite, one built by Orbital Sciences, and the other by Lockheed Martin, had a mass of about 250 kg. They were believed to be solar-powered and equipped with propulsion systems that would allow them to rendezvous with geosynchronous satellites. Once they had reached the satellite, they would presumably be capable of destroying, disabling, or jamming them. To deliver the two satellites to near-synchronous orbit, a Naval Research Laboratory liquid propellant bus equipped with a 400 N main engine and solar panels was used.

2006 September 25 - 18:50 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D318 USA 190 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Perigee: 20,020 km (12,430 mi). Apogee: 20,342 km (12,639 mi). Inclination: 54.90 deg. Period: 717.90 min. Second GPS Block IIR-M version, which added extra navigation signals for both civil and military users.

2006 November 17 - 19:12 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D321 USA 192 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: U.S. Air Force. Perigee: 20,206 km (12,555 mi). Apogee: 20,367 km (12,655 mi). Inclination: 54.90 deg. Period: 722.20 min. Set operational at 03:07 GMT on 12 December.

2007 August 4 - 09:26 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D325 Phoenix Mass: 680 kg (1,490 lb). Spacecraft: Phoenix. Agency: NASA. Mars lander based on surplus hardware from the cancelled Mars Surveyor 2001 and the failed Mars Polar Lander (whence the Phoenix designation). The planned landing location was in the north of Mars, at Vastitas Borealis. The spacecraft consisted of a cruise stage, aeroshell for re-entry, backshell for protection of the lander, parachute system for braking the lander after re-entry, and liquid propellant rocket system for a soft touchdown on the surface. The lander was equipped with a robotic arm, soil analysis instruments, meteorology instruments, and cameras.

2007 October 17 - 12:23 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D328 USA 196 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: U.S. Air Force. Perigee: 20,149 km (12,519 mi). Apogee: 20,213 km (12,559 mi). Inclination: 54.90 deg. Period: 717.90 min. Set operational at 22:46 GMT on 31 October.