1957 January 26 - Launch Vehicle: Delta. Thor DM-18 101 FAILURE: Lox contamination, led to a valve failure. Thrust decayed, the booster settled back through the thrust ring, causing an oxygen fire, followed by booster explosion. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 0 km ( mi). First attempted test flight of USAF Thor IRBM, only 13 months after first production contracts were signed, failed to launch.

1957 April 20 - 04:33 GMT - Launch Vehicle: Delta. Thor DM-18 102 FAILURE: Console wiring error resulted in erroneous tracking indication; destroyed by range safety. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 0 km ( mi). Douglas Thor IRBM (XSM-75) was launched at Cape Canaveral, Fla., destroyed by range safety officer. The missile was actually on course throughout its flight. The console wiring error led the range safety officer to believe it was headed inland rather than out to sea, so he hit the destruct button.

1957 May 22 - 03:00 GMT - Launch Vehicle: Delta. Thor DM-18 103 Research and development Series I (padex) test Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1957 September 20 - Launch Vehicle: Delta. Thor DM-18 105 Series I research and development launch Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). Complete USAF Thor IRBM first successfully launched from Cape Canaveral. Dummy Warhead sent to 1800 km range.

1957 October 11 - 16:33 GMT - Launch Vehicle: Delta. Thor DM-18 108 FAILURE: Turbopump gearbox failure. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). Thor missile launched at Cape Canaveral, the second tested, achieved its designed 1,500-mile range.

1957 December 7 - 22:11 GMT - Launch Vehicle: Delta. Thor DM-18 112 Research and development Series II test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi).

1958 February 28 - 13:08 GMT - Launch Vehicle: Delta. Thor DM-18 120 FAILURE: Failure. Research and development Series II test Agency: USAF 6555 ATW. Apogee: 0 km ( mi). Copper heatsink nose cone

1958 April 19 - 13:30 GMT - Launch Vehicle: Delta. Thor DM-18 121 FAILURE: Failure. Research and development Series II test Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1958 June 13 - 15:06 GMT - Launch Vehicle: Delta. Thor DM-18 122 Research and development Series III test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi).

1958 July 13 - 06:36 GMT - Launch Vehicle: Delta. Thor DM-18 123 Research and development Series III test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi).

1958 July 26 - 06:40 GMT - Launch Vehicle: Delta. Thor DM-18 126 FAILURE: Failure. Research and development Series III test Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1958 November 5 - 08:53 GMT - Launch Vehicle: Delta. Thor DM-18A 138 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1958 November 26 - 09:09 GMT - Launch Vehicle: Delta. Thor DM-18A 140 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi). First operational launch

1958 December 17 - 04:00 GMT - Launch Vehicle: Delta. Thor DM-18A 146 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 January 30 - 23:53 GMT - Launch Vehicle: Delta. Thor DM-18A 154 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 March 27 - 04:02 GMT - Launch Vehicle: Delta. Thor DM-18A 162 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 April 23 - 05:30 GMT - Launch Vehicle: Delta. Thor DM-18A 176 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi). Fourth recovery of a data capsule at AMR, USAF Thor 1,500-mile accuracy test flight.

1959 May 12 - 17:35 GMT - Launch Vehicle: Delta. Thor DM-18A 187 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 June 30 - 02:37 GMT - Launch Vehicle: Delta. Thor DM-18A 194 Series IV Lofted Trajectory research and development mission Agency: USAF. Apogee: 1,000 km (600 mi).

1959 July 21 - 07:33 GMT - Launch Vehicle: Delta. Thor DM-18A 203 FAILURE: Failure. Series IV research and development launch Agency: USAF. Apogee: 1.00 km (0.60 mi).

1959 August 6 - 02:48 GMT - Launch Vehicle: Delta. Thor DM-18A 208 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 August 27 - 12:30 GMT - Launch Vehicle: Delta. Thor DM-18A 216 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 September 22 - 18:00 GMT - Launch Vehicle: Delta. Thor DM-18A 222 Series IV research and development launch/Ionosphere/Meteorites mission Agency: USAF. Apogee: 520 km (320 mi).

1959 October 14 - 04:15 GMT - Launch Vehicle: Delta. Thor DM-18A 221 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 November 3 - Launch Vehicle: Delta. Thor DM-18A 238 Series IV research and development launch/Meteorites mission Agency: USAF. Apogee: 520 km (320 mi).

1959 November 19 - Launch Vehicle: Delta. Thor DM-18A 244 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 December 17 - Launch Vehicle: Delta. Thor DM-18A 255 Series IV research and development launch/Meteorites mission Agency: USAF. Apogee: 520 km (320 mi).

1960 April 13 - 12:02 GMT - Launch Vehicle: Delta. Thor Ablestar 257 AB002? Transit 1B Mass: 121 kg (266 lb). Spacecraft: Transit. Agency: DARPA. Perigee: 363 km (225 mi). Apogee: 644 km (400 mi). Inclination: 51.20 deg. Period: 94.60 min. The Able-Star second stage demonstrated the first engine restart in space and the feasibility of using satellites as navigational aids. The first experimental Transit satellite to achieve orbit operated for 89 days. It transmitted on two frequency pairs to test the technique for refraction correction and to determine if the transmitted frequencies should be close together or far apart. It also tested a magnetic torque device for spacecraft attitude control - the first satellite to do so.

1960 June 22 - 05:54 GMT - Launch Vehicle: Delta. Thor Ablestar 281 AB003? Transit 2A Mass: 101 kg (222 lb). Spacecraft: Transit. Agency: U.S. Navy. Perigee: 604 km (375 mi). Apogee: 988 km (613 mi). Inclination: 66.70 deg. Period: 100.80 min. Also returned geodetic data. Similar to Transit 1B, it transmitted until 26 October 1962. A planned Transit 2B was considered redundant and never built.

1960 August 18 - 19:58 GMT - Launch Vehicle: Delta. Thor Ablestar 262 AB004? FAILURE: Exploded 2.5 minutes after launch. Courier 1A Mass: 225 kg (496 lb). Spacecraft: Courier. Agency: DARPA. Experimental communications sattelite.

1960 October 4 - 17:50 GMT - Launch Vehicle: Delta. Thor Ablestar 293 AB005 Courier 1B Mass: 230 kg (500 lb). Spacecraft: Courier. Agency: U.S. Army. Perigee: 967 km (600 mi). Apogee: 1,214 km (754 mi). Inclination: 28.30 deg. Period: 107.10 min. Experimental communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 November 30 - 19:50 GMT - Launch Vehicle: Delta. Thor Ablestar 283 AB006 FAILURE: Failure. Transit 3A Mass: 91 kg (200 lb). Spacecraft: Transit. Agency: U.S. Navy. Destroyed by range safety; launched with Solrad 2. Thor shut down too early.

1961 February 22 - 03:45 GMT - Launch Vehicle: Delta. Thor Ablestar 313 AB007 Transit 3B Mass: 112 kg (246 lb). Spacecraft: Transit. Agency: U.S. Navy. Lofti 1 piggyback payload did not separate. Nevertheless Transit 3B returned useful data needed for design of the operational satellites. It carried a digital clock driven by the same oscillator that drove the transmitters. It transmitted timing signals governed by the clock and a 384-bit memory. This allowed testing of the techniques for loading the memory from the ground, the ability of the memory to hold a message in orbit, and the ability to encode the memory contents by means of a frequency modulation on one of the main transmitters. It was also shown that ±60° phase modulation could be used to transmit the contents of the satellite memory without degradation of the accuracy of the Doppler signal and Doppler measurements.

1961 June 29 - 04:22 GMT - Launch Vehicle: Delta. Thor Ablestar 315 AB008 Transit 4A Mass: 79 kg (174 lb). Spacecraft: Transit. Agency: U.S. Navy. Perigee: 865 km (537 mi). Apogee: 986 km (612 mi). Inclination: 66.80 deg. Period: 103.50 min. Transits 4A and 4B were drum-shaped instead of spherical to provide more space for solar cells. In addition, operational 150-and 400-MHz frequencies were used for the first time. Carried SNAP-3A nuclear power source.

1961 November 15 - 22:19 GMT - Launch Vehicle: Delta. Thor Ablestar 305 AB009? Transit 4B Mass: 86 kg (189 lb). Spacecraft: Transit. Agency: U.S. Navy. Perigee: 953 km (592 mi). Apogee: 1,104 km (685 mi). Inclination: 32.40 deg. Period: 105.70 min. Together, Transits 4A and 4B allowed the determination of harmonics in the Earth’s gravity field that had not yet been evaluated, and they also allowed firm navigational ties to be established from continent to continent as well as to isolated islands. As a result, it was discovered that the position of Hawaii was incorrect by 1 km. Carried SNAP 3 nuclear power source.

1962 January 24 - 09:30 GMT - Launch Vehicle: Delta. Thor Ablestar 311 AB010 FAILURE: Failure. Lofti 2 Mass: 99 kg (218 lb). Spacecraft: Lofti 2. Agency: U.S. Navy. Carried 5 satellites.

1962 May 10 - 12:07 GMT - Launch Vehicle: Delta. Thor Ablestar 314 AB011 FAILURE: Able-Star failed to ignite. Anna 1A Mass: 160 kg (350 lb). Spacecraft: Anna. Agency: U.S. Army, U.S. Navy, U.S. Air Force, NASA. USN, USAF, US Army, NASA joint program.

1962 July 10 - 08:35 GMT - Launch Vehicle: Delta. Thor Delta 316/D11 Telstar 1 Mass: 77 kg (169 lb). Spacecraft: Telstar. Agency: ATT. Perigee: 945 km (587 mi). Apogee: 5,643 km (3,506 mi). Inclination: 44.80 deg. Period: 157.80 min. First commercial comsat; active repeater. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1962 October 2 - 22:11 GMT - Launch Vehicle: Delta. Thor Delta A 345/D13 Explorer 14 Mass: 40 kg (88 lb). Spacecraft: EPE. Agency: NASA. Perigee: 2,558 km (1,589 mi). Apogee: 96,229 km (59,793 mi). Inclination: 42.30 deg. Period: 2,184.60 min. Magnetosphere studies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1962 October 27 - 23:15 GMT - Launch Vehicle: Delta. Thor Delta A 346/D14 Explorer 15 Mass: 45 kg (99 lb). Spacecraft: EPE. Agency: NASA. Perigee: 306 km (190 mi). Apogee: 17,610 km (10,940 mi). Inclination: 17.90 deg. Period: 314.70 min. Radiation decay data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1963 February 14 - 05:35 GMT - Launch Vehicle: Delta. Thor Delta B 358/D16 Syncom I; Syncom 1 Mass: 39 kg (85 lb). Spacecraft: Syncom. Agency: NASA GSF. Perigee: 34,392 km (21,370 mi). Apogee: 36,739 km (22,828 mi). Inclination: 33.30 deg. Period: 1,425.50 min. Experimental commsat; lost contact following orbital injection. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Four score. Last known longitude (10 March 1987) 172.58 deg E drifting at 2.429 deg E per day.

1963 May 7 - 11:38 GMT - Launch Vehicle: Delta. Thor Delta B 366/D18 Telstar 2 Mass: 79 kg (174 lb). Spacecraft: Telstar. Agency: AT&T. Perigee: 972 km (603 mi). Apogee: 10,802 km (6,712 mi). Inclination: 42.70 deg. Period: 225.30 min. Active repeater. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1963 June 19 - 09:50 GMT - Launch Vehicle: Delta. Thor Delta B 359/D19 Tiros 7 Mass: 135 kg (297 lb). Spacecraft: Tiros. Agency: NASA GSF. Perigee: 338 km (210 mi). Apogee: 349 km (216 mi). Inclination: 58.20 deg. Period: 91.40 min. Returned over 150000 cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1963 September 18 - 09:39 GMT - Launch Vehicle: Delta. Thor DSV-2F 232 ASSET 1 re-entry vehicle test flight Agency: USAF. Apogee: 56 km (34 mi). Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Booster flew to peak altitude of 62 km, then pitched down, driving the spacecraft to separation at 59 km and 4,906 m/s. The spacecraft was sited under its parachute in the recovery zone at Ascension Island, but the flotation bag broke and it sank into the Atlantic.

1963 November 27 - 02:30 GMT - Launch Vehicle: Delta. Thor Delta C 387/D21 Explorer 18 Mass: 62 kg (136 lb). Spacecraft: IMP. Agency: NASA GSF. Perigee: 192 km (119 mi). Apogee: 197,616 km (122,792 mi). Inclination: 33.30 deg. Period: 5,666.20 min. Radiation data; Interplanetary Monitoring Program. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1963 December 21 - 09:30 GMT - Launch Vehicle: Delta. Thor Delta B 371/D22 Tiros 8 Mass: 119 kg (262 lb). Spacecraft: Tiros. Agency: NASA GSF. Perigee: 667 km (414 mi). Apogee: 705 km (438 mi). Inclination: 58.50 deg. Period: 98.50 min. Returned more than 100,000 cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1964 January 21 - 21:14 GMT - Launch Vehicle: Delta. Thor Delta B 373/D23 Relay 2 Mass: 78 kg (171 lb). Spacecraft: Relay. Agency: NASA GSF. Perigee: 1,961 km (1,218 mi). Apogee: 7,540 km (4,680 mi). Inclination: 46.40 deg. Period: 194.70 min. Experimental commsat. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1964 March 24 - 12:15 GMT - Launch Vehicle: Delta. Thor DSV-2G 240 FAILURE: Second stage fired, then shut down, repeating the sequence several times. ASSET 2 re-entry vehicle test flight Agency: USAF. Apogee: 55 km (34 mi). Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Good first stage burn, but the second stage fired, then shut down, repeating the sequence several times. The spacecraft separated, and began to maneuver in a 60 degree bank to recover course, when the self-destruct package blew it apart. The debris impacted the Atlantic 800 km downrange near San Salvador Island.

1964 July 22 - 15:39 GMT - Launch Vehicle: Delta. Thor DSV-2G 250 ASSET 3 re-entry vehicle test flight Agency: USAF. Apogee: 71 km (44 mi). Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Launched after four hours of holds. Tested Dynasoar hardware - tungsten nose cap, molbdenum panels with vapor-deposited disilicide, and liquid-cooled double-walled cockpit bathtub panel. Reached 5,500 m/s and recovered near Ascension Island 12 hours after launch.

1964 October 29 - 03:35 GMT - Launch Vehicle: Delta. Thor DSV-2F 260 ASSET 4 re-entry vehicle test flight Agency: USAF. Apogee: 50 km (31 mi). Suborbital test of small scale spaceplane model to test structural concepts for the X-20 Dynasoar. Aero-environmental test vehicle (AEV) to test aerodynamic properties of flexing outer skin with corrugated columbium panel. Reached 4,000 m/s at 50.6 km altitude before being released from launch vehicle. Telemetry received for 900 seconds until spaceplane had reached Mach 2 1200 km downrange. It then became unstable and crashed into the Atlantic. Recovery was not planned.

1964 December 9 - 02:00 GMT - Launch Vehicle: Delta. Thor DSV-2F 247 ASSET 5 re-entry vehicle test flight Agency: USAF. Apogee: 50 km (31 mi). Suborbital test of small scale spaceplane model to test structural concepts for the X-20 Dynasoar. Aero-environmental test vehicle (AEV) to test aerodynamic properties of flexing outer skin with corrugated columbium panel. Reached 4,000 m/s at 53.2 km altitude before being released from launch vehicle. Telemetry received for 900 seconds until spaceplane had reached Mach 2 1200 km downrange. It then became unstable and crashed into the Atlantic. Recovery was not planned.

1965 February 3 - 16:36 GMT - Launch Vehicle: Delta. Thor Delta C 411/D29 OSO 2 Mass: 247 kg (544 lb). Spacecraft: OSO. Agency: NASA GSF. Perigee: 294 km (182 mi). Apogee: 306 km (190 mi). Inclination: 32.80 deg. Period: 90.50 min. Orbiting Solar Observatory; returned solar X-ray, UV, gamma ray data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1965 February 23 - 14:36 GMT - Launch Vehicle: Delta. Thor DSV-2G 248 ASSET 6 re-entry vehicle test flight Agency: USAF. Apogee: 70 km (43 mi). Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Reached 6,000 m/s and 4,350 km range. Tested twelve different kinds of refractory metals and covered with 2000 dots of heat-sensitive paint to characterize thermal profile on reentry. Telemetry indicated that the spacecraft survived reentry, but it evidently sank upon impacting the ocean and could not be recovered as planned.

1965 May 29 - 12:00 GMT - Launch Vehicle: Delta. Thor Delta C 441/D31 Explorer 28 Mass: 58 kg (127 lb). Spacecraft: IMP. Agency: NASA GSF. Perigee: 229 km (142 mi). Apogee: 261,206 km (162,305 mi). Inclination: 30.50 deg. Period: 8,419.70 min. Magnetic field, radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1965 July 2 - 04:07 GMT - Launch Vehicle: Delta. Thor Delta C 415/D32 Tiros 10 Mass: 127 kg (279 lb). Spacecraft: Tiros. Agency: ESSA. Perigee: 722 km (448 mi). Apogee: 807 km (501 mi). Inclination: 98.80 deg. Period: 100.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1965 August 25 - 15:17 GMT - Launch Vehicle: Delta. Thor Delta C 434/D33 FAILURE: Premature third stage ignition. OSO C Mass: 280 kg (610 lb). Spacecraft: OSO. Agency: NASA.

1966 February 28 - 13:58 GMT - Launch Vehicle: Delta. Thor Delta E 461/D37 ESSA 2 Mass: 132 kg (291 lb). Spacecraft: Tiros. Agency: ESSA. Perigee: 1,355 km (841 mi). Apogee: 1,415 km (879 mi). Inclination: 101.30 deg. Period: 113.50 min. Environmental Survey Satellite; carried APT cameras. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1966 May 25 - 14:00 GMT - Launch Vehicle: Delta. Thor Delta C1 436/D38 Explorer 32 Mass: 225 kg (496 lb). Spacecraft: AE. Agency: NASA GSF. Perigee: 282 km (175 mi). Apogee: 2,723 km (1,691 mi). Inclination: 64.60 deg. Period: 116.00 min. Atmospheric Explorer; aeronomy experiments. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1966 October 26 - 23:05 GMT - Launch Vehicle: Delta. Thor Delta E1 464/D42 FAILURE: Partial Failure. Intelsat 2 F-1 Mass: 140 kg (300 lb). Spacecraft: Intelsat 2. Agency: Intelsat. Perigee: 3,328 km (2,067 mi). Apogee: 37,070 km (23,030 mi). Inclination: 17.30 deg. Period: 718.70 min. Unusable orbit due to AKM failure. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1967 January 11 - 10:55 GMT - Launch Vehicle: Delta. Thor Delta E1 468/D44 Intelsat 2 F-2 Mass: 87 kg (191 lb). Spacecraft: Intelsat 2. Agency: INTELSAT. Perigee: 35,769 km (22,225 mi). Apogee: 35,808 km (22,250 mi). Inclination: 1.60 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 over the Pacific Ocean at 174 deg E in 1967-1969; over the Pacific Ocean 162-170 deg E in 1969-1970; over the Pacific Ocean 150-160 deg E in 1970-1975 As of 7 August 2001 located at 48.66 deg E drifting at 0.413 deg W per day. As of 2007 Mar 8 located at 63.48W drifting at 0.357W degrees per day.

1967 March 23 - 01:30 GMT - Launch Vehicle: Delta. Thor Delta E1 470/D47 Intelsat 2 F-3 Mass: 192 kg (423 lb). Spacecraft: Intelsat 2. Agency: INTELSAT. Perigee: 35,670 km (22,160 mi). Apogee: 35,899 km (22,306 mi). Inclination: 12.50 deg. Period: 1,436.00 min. Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1967-1971; over the Atlantic Ocean at 35 deg W in 1972; over the Atlantic Ocean at 15 deg W in 1973. As of 22 August 2001 was at 6.75 deg W drifting at 0.037 deg W per day. As of 2005 Dec 5 located at 13.34E drifting at 0.188W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1967 July 19 - 14:19 GMT - Launch Vehicle: Delta. Thor Delta E1 488/D50 Explorer 35 Mass: 104 kg (229 lb). Spacecraft: IMP. Agency: NASA GSF. Perigee: 484 km (300 mi). Apogee: 675 km (419 mi). Inclination: 32.40 deg. Period: 96.26 min. Earth magnetic tail measurements. Lunar Orbit (Selenocentric). The Westinghouse Aerospace Division, under contract to National Aeronautics and Space Administration's Goddard Space Flight Center, engaged in the system design, integration, assembly and launch support for Anchored Interplanetary Monitoring Platform Satellite, officially designated Explorer 35 by the National Aeronautics and Space Administration. It was launched on July 19, 1967, with the primary objectives of investigation of interplanetary plasma and the interplanetary magnetic field out to and at the lunar distance, in either a captured lunar orbit or a geocentric orbit of the earth. In the geocentric orbit, the apogee was near or beyond the lunar distance. In a lunar orbit, additional objectives included obtaining data on dust distribution, lunar gravitational field, ionosphere, magnetic field, and radiation environment around the moon. AIMP-E also studied spatial and temporal relationships of geophysical and interplanetary phenomena simultaneously being studied by several other National Aeronautics and Space Administration satellites. The investigation in the vicinity of the moon provided for measurements of the characteristics of the interplanetary dust distribution, solar and galactic cosmic rays, as well as a study of the magnetohydrodynamic wake of the earth in the interplanetary medium at the lunar distances.

1967 September 7 - 22:04 GMT - Launch Vehicle: Delta. Thor Delta G 475/D51 Biosatellite 2 Mass: 507 kg (1,117 lb). Spacecraft: Biosatellite. Agency: NASA ARC. Perigee: 297 km (184 mi). Apogee: 318 km (197 mi). Inclination: 33.50 deg. Period: 90.70 min. Biological capsule recovered. The scientific payload, consisting of 13 select biology and radiation experiments, was exposed to microgravity during 45 hours of Earth-orbital flight. Experimental biology packages on the spacecraft contained a variety of specimens, including insects, frog eggs, microorganisms and plants. The planned three-day mission was recalled early because of the threat of a tropical storm in the recovery area, and because of a communication problem between the spacecraft and the tracking systems. The primary objective of the Biosatellite II mission was to determine if organisms were more, or less, sensitive to ionizing radiation in microgravity than on Earth. To study this question, an artificial source of radiation was supplied to a group of experiments mounted in the forward part of the spacecraft.

1967 September 28 - 00:45 GMT - Launch Vehicle: Delta. Thor Delta E1 442/D52 Intelsat 2 F-4 Mass: 87 kg (191 lb). Spacecraft: Intelsat 2. Agency: INTELSAT. Perigee: 35,729 km (22,200 mi). Apogee: 35,885 km (22,297 mi). Inclination: 13.00 deg. Period: 1,437.10 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 Pacific Ocean at 176 deg E in 1967-1970; over the Pacific Ocean 166 deg W in 1971; over the Atlantic Ocean 30-42 deg W in 1972 As of 1 August 2001 located at 36.36 deg W drifting at 0.096 deg E per day. As of 2007 Mar 7 located at 168.68W drifting at 0.093W degrees per day.

1967 October 18 - 15:58 GMT - Launch Vehicle: Delta. Thor Delta C1 490/D53 OSO 4 Mass: 272 kg (599 lb). Spacecraft: OSO. Agency: NASA GSF. Perigee: 552 km (342 mi). Apogee: 555 km (344 mi). Inclination: 32.90 deg. Period: 95.70 min. Extreme UV solar observations. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1967 December 13 - 14:08 GMT - Launch Vehicle: Delta. Thor Delta E1 489/D55 Pioneer 8 Mass: 63 kg (138 lb). Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA ARC. Solar radiation data. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1968 November 8 - 09:46 GMT - Launch Vehicle: Delta. Thor Delta E1 479/D60 Pioneer 9 Mass: 63 kg (138 lb). Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA ARC. Solar radiation data. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1968 December 5 - 18:55 GMT - Launch Vehicle: Delta. Thor Delta E1 481/D61 HEOS 1 Mass: 108 kg (238 lb). Spacecraft: HEOS. Agency: ESRO. Perigee: 20,020 km (12,430 mi). Apogee: 202,780 km (126,000 mi). Inclination: 60.50 deg. Period: 6,704.30 min. Highly Eccentric Orbiting Satellite; examined magnetic fields outside of Earth's magnetosphere. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1969 January 22 - 16:48 GMT - Launch Vehicle: Delta. Thor Delta C1 487/D64 OSO 5 Mass: 291 kg (641 lb). Spacecraft: OSO. Agency: NASA GSF. Perigee: 538 km (334 mi). Apogee: 559 km (347 mi). Inclination: 33.00 deg. Period: 95.60 min. Orbiting Solar Observatory; solar radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1969 February 26 - 07:47 GMT - Launch Vehicle: Delta. Thor Delta E1 483/D67 ESSA 9 Mass: 145 kg (319 lb). Spacecraft: TOS. Agency: ESSA. Perigee: 1,425 km (885 mi). Apogee: 1,505 km (935 mi). Inclination: 101.80 deg. Period: 115.20 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1972 September 23 - 01:20 GMT - Launch Vehicle: Delta. Delta 1604 579/D90 Explorer 47 Mass: 376 kg (828 lb). Spacecraft: IMP. Agency: NASA GSF. Perigee: 201,100 km (124,900 mi). Apogee: 235,600 km (146,300 mi). Inclination: 17.20 deg. Period: 17,670.00 min. Investigated cislunar radiation, Earth's magnetosphere, interplantary magnetic field. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1972 November 10 - 01:14 GMT - Launch Vehicle: Delta. Delta 1914 580/D92 Anik A1 Mass: 557 kg (1,227 lb). Spacecraft: HS 333. Agency: Telesat. Perigee: 36,145 km (22,459 mi). Apogee: 36,247 km (22,522 mi). Inclination: 11.30 deg. Period: 1,457.10 min. Anik I and Anik II also registered as United States objects. .The satellites, act as space repeaters capable of receiving transmissions from earth stations and retransmitting them to other earth stations in Canada. The antenna coverage of the satellite pr ovides the capability of serving virtually all of Canada. Anik I and II had weights of 1240.59 lb and 1246.48 lb. Each satellite has 12 RF channels each capable of transmitting a color television signal or up to 900 one-way voice channels. Positioned in geosynchronous orbit over the Americas at 114 deg W in 1973-1976; over the Americas at 104 deg W in 1976-1982 As of 1 September 2001 located at 66.14 deg W drifting at 5.205 deg W per day. As of 2007 Mar 9 located at 107.03W drifting at 5.211W degrees per day.

1973 April 20 - 23:47 GMT - Launch Vehicle: Delta. Delta 1914 583/D94 Anik A2 Mass: 272 kg (599 lb). Spacecraft: HS 333. Agency: Telesat. Perigee: 35,886 km (22,298 mi). Apogee: 35,952 km (22,339 mi). Inclination: 13.70 deg. Period: 1,442.90 min. Anik I and Anik II also registered as United States objects. .The satellites, act as space repeaters capable of receiving transmissions from earth stations and retransmitting them to other earth stations in Canada. The antenna coverage of the satellite pr ovides the capability of serving virtually all of Canada. Anik I and II had weights of 1240.59 lb and 1246.48 lb. Each satellite has 12 RF channels each capable of transmitting a color television signal or up to 900 one-way voice channels. Positioned in geosynchronous orbit over the Americas at 109 deg W in 1973-1979; over the Americas at 106 deg W in 1979-1981; over the Americas at 114 deg W in 1981-1982 As of 26 August 2001 located at 0.59 deg E drifting at 1.690 deg W per day. As of 2007 Mar 9 located at 150.94E drifting at 1.684W degrees per day.

1973 June 10 - 14:13 GMT - Launch Vehicle: Delta. Delta 1913 581/D95 Explorer 49 Mass: 328 kg (723 lb). Spacecraft: RAE. Agency: NASA GSF. Radio Astronomy Explorer; measured galactic, stellar radio noise. Lunar Orbit (Selenocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1973 October 26 - 02:26 GMT - Launch Vehicle: Delta. Delta 1604 582/D97 Explorer 50 Mass: 371 kg (817 lb). Spacecraft: IMP. Agency: NASA GSF. Perigee: 190,749 km (118,525 mi). Apogee: 244,361 km (151,838 mi). Inclination: 31.60 deg. Period: 17,576.70 min. Solar flare and radiation monitor. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1974 January 19 - 01:38 GMT - Launch Vehicle: Delta. Delta 2313 587/D100 FAILURE: Partial Failure. Failed to reach planned orbit. Skynet 2A Mass: 129 kg (284 lb). Spacecraft: Skynet. Agency: UK MoD. Perigee: 104 km (64 mi). Apogee: 1,803 km (1,120 mi). Inclination: 37.50 deg. Period: 104.10 min. Partial Failure. Failed to reach planned orbit.

1974 April 13 - 23:33 GMT - Launch Vehicle: Delta. Delta 2914-C 588/D101 Westar 1 Mass: 500 kg (1,100 lb). Spacecraft: HS 333. Agency: WUTC. Perigee: 35,886 km (22,298 mi). Apogee: 35,900 km (22,300 mi). Inclination: 13.40 deg. Period: 1,441.50 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 Americas at 99 deg W in 1974-1982; over the Americas at 100 deg W in 1982; over the Americas at 97 deg W in 1982; over the Americas at 79 deg W in 1982-1983 As of 5 September 2001 located at 85.83 deg W drifting at 1.372 deg W per day. As of 2007 Mar 10 located at 89.54E drifting at 1.381W degrees per day.

1974 May 17 - 09:31 GMT - Launch Vehicle: Delta. Delta 2914 590/D102 SMS 1 Mass: 243 kg (535 lb). Spacecraft: SMS. Agency: NASA GSF. Perigee: 36,216 km (22,503 mi). Apogee: 36,303 km (22,557 mi). Inclination: 15.50 deg. Period: 1,460.30 min. Synchronous Meteorological Satellite. 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 45 deg W in 1974-1975; over the Atlantic Ocean 75 deg W in 1975; over the Americas at 105 deg W in 1976-1978; over the Americas at 91 deg W in1978; over the Atlantic Ocean 75 deg W in 1979; over the Atlantic Ocean 70 deg W in 1979; over the Pacific Ocean 132 deg W in 1980 As of 3 September 2001 located at 84.60 deg W drifting at 5.986 deg W per day. As of 2007 Mar 10 located at 116.51E drifting at 5.981W degrees per day.

1974 October 10 - 22:53 GMT - Launch Vehicle: Delta. Delta 2914-C 589/D103 Westar 2 Mass: 500 kg (1,100 lb). Spacecraft: HS 333. Agency: WUTC. Perigee: 35,895 km (22,304 mi). Apogee: 35,910 km (22,310 mi). Inclination: 9.50 deg. Period: 1,442.00 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 Americas at 123 deg W in 1974-1982; over the Americas at 79 deg W in 1982-1986 As of 2 September 2001 located at 144.45 deg E drifting at 1.482 deg W per day. As of 2007 Mar 8 located at 6.53W drifting at 1.482W degrees per day.

1974 November 23 - 00:28 GMT - Launch Vehicle: Delta. Delta 2313 591/D105 Skynet 2B Mass: 129 kg (284 lb). Spacecraft: Skynet. Agency: UK MoD. Perigee: 35,782 km (22,233 mi). Apogee: 35,822 km (22,258 mi). Inclination: 12.20 deg. Period: 1,436.90 min. Military communications. Positioned in geosynchronous orbit over the Indian Ocean at 50-55 deg E in 1975-1977; drifting As of 3 September 2001 located at 18.23 deg E drifting at 0.206 deg W per day. As of 2007 Feb 27 located at 54.93E drifting at 0.393E degrees per day.

1974 December 19 - 02:39 GMT - Launch Vehicle: Delta. Delta 2914 599/D106 Symphonie 1 Mass: 221 kg (487 lb). Spacecraft: Symphonie. Agency: CNES/DFV. Perigee: 35,853 km (22,277 mi). Apogee: 35,893 km (22,302 mi). Inclination: 14.90 deg. Period: 1,440.50 min. Experimental commsat. Jointly registered by the Federal Republic of Germany (A/AC.105/INF.305) and France (A/AC.105/INF.306). Symphonie flying model no. 1, constructed jointly by France and the Federal Republic of Germany. Description: Experimental teleco mmunications satellite. Orbit: geostationary. Positioned in geosynchronous orbit over the Atlantic Ocean at 11 deg W in 1975-1977; over the Indian Ocean 49 deg E in 1977-1983 As of 25 August 2001 located at 179.98 deg E drifting at 1.086 deg W per day. As of 2007 Mar 11 located at 72.77E drifting at 1.184W degrees per day.

1975 February 6 - 22:04 GMT - Launch Vehicle: Delta. Delta 2914 593/D108 SMS 2 Mass: 627 kg (1,382 lb). Spacecraft: SMS. Agency: NASA GSF. Perigee: 35,941 km (22,332 mi). Apogee: 36,060 km (22,400 mi). Inclination: 12.00 deg. Period: 1,447.10 min. Synchronous Meteorological Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at (GOES W) 115 deg W in 1975-1976; over the Pacific Ocean (GOES W) 135 deg W in 1976-1978; over the Atlantic Ocean (GOES E) 75 deg W in 1979-1981; over the Americas at 106 deg W in 1982 As of 29 August 2001 located at 123.04 deg W drifting at 2.760 deg W per day. As of 2007 Feb 27 located at 127.44E drifting at 2.742W degrees per day.

1975 May 7 - 23:35 GMT - Launch Vehicle: Delta. Delta 2914-C 596/D110 Anik A3 (Telesat 3) Mass: 286 kg (630 lb). Spacecraft: HS 333. Agency: Telesat. Perigee: 35,845 km (22,273 mi). Apogee: 35,851 km (22,276 mi). Inclination: 9.00 deg. Period: 1,439.20 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 Americas at 104 deg W in 1975-1976; over the Americas at 114 deg W in 1976-1984 As of 4 September 2001 located at 32.38 deg E drifting at 0.812 deg W per day. As of 2007 Mar 9 located at 138.81W drifting at 0.829W degrees per day.

1975 June 21 - 11:43 GMT - Launch Vehicle: Delta. Delta 1910 586/D112 OSO 8 Mass: 1,066 kg (2,350 lb). Spacecraft: OSO. Agency: NASA GSF. Perigee: 539 km (334 mi). Apogee: 553 km (343 mi). Inclination: 32.90 deg. Period: 95.60 min. Orbiting Solar Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1975 October 16 - 22:40 GMT - Launch Vehicle: Delta. Delta 2914 597/D116 GOES 1 Mass: 295 kg (650 lb). Spacecraft: GOES. Agency: NOAA. Perigee: 35,787 km (22,236 mi). Apogee: 35,811 km (22,251 mi). Inclination: 14.80 deg. Period: 1,436.70 min. Geostationary Operational Environmental Satellite. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Positioned in geosynchronous orbit over the Atlantic Ocean at 55 deg W in 1975-1976; over the Pacific Ocean 135 deg W in 1976-1978; over the Atlantic Ocean 10 deg W in 1978; over the Indian Ocean 58 deg E in 1978-1979; over the Pacific Ocean 135 deg W in 1979-1980; over the Atlantic Ocean 93 deg W in 1980; over the Pacific Ocean 130 deg W in 1980-1985 As of 3 September 2001 located at 81.97 deg W drifting at 0.051 deg E per day. As of 2007 Mar 9 located at 81.95W drifting at 0.055W degrees per day.

1975 November 20 - 02:06 GMT - Launch Vehicle: Delta. Delta 2910 604/D117 Explorer 55 Mass: 721 kg (1,589 lb). Spacecraft: AE. Agency: NASA GSF. Perigee: 154 km (95 mi). Apogee: 3,002 km (1,865 mi). Inclination: 19.70 deg. Period: 117.70 min. Atmospheric Explorer. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1976 January 17 - 23:27 GMT - Launch Vehicle: Delta. Delta 2914 606/D119 CTS 1 Mass: 500 kg (1,100 lb). Spacecraft: CTS. Agency: CRC. Perigee: 35,704 km (22,185 mi). Apogee: 35,840 km (22,260 mi). Inclination: 12.80 deg. Period: 1,435.40 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 Americas at 116 deg W in 1976-79; over the Pacific Ocean 142 deg W in 1979 As of 5 September 2001 located at 135.36 deg W drifting at 0.161 deg W per day. As of 2007 Mar 10 located at 131.55W drifting at 0.190W degrees per day.

1976 February 19 - 22:32 GMT - Launch Vehicle: Delta. Delta 2914 603/D120 Marisat 1 Mass: 655 kg (1,444 lb). Spacecraft: Marisat. Agency: Comsat. Perigee: 36,033 km (22,389 mi). Apogee: 36,143 km (22,458 mi). Inclination: 13.90 deg. Period: 1,451.50 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 Atlantic Ocean at 15 deg W in 1976-1990; over the Americas at 106 deg W in 1990-1997 As of 2 September 2001 located at 168.03 deg W drifting at 3.834 deg W per day. As of 2007 Mar 10 located at 20.39E drifting at 3.837W degrees per day.

1976 April 22 - 20:46 GMT - Launch Vehicle: Delta. Delta 2914 608/D122 NATO 3A Mass: 310 kg (680 lb). Spacecraft: NATO 3. Agency: NATO. Perigee: 35,801 km (22,245 mi). Apogee: 36,017 km (22,379 mi). Inclination: 13.30 deg. Period: 1,442.40 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 1976-1982; over the Atlantic Ocean 30 deg W in 1982-1984; over the Atlantic Ocean 50 deg W in 1984-1985; over the Atlantic Ocean at 30 deg W in 1985-1989; over the Americas at 125 deg W in 1989-1991 As of 5 September 2001 located at 4.12 deg E drifting at 1.524 deg W per day. As of 2007 Mar 9 located at 142.00E drifting at 1.522W degrees per day.

1977 April 20 - 10:15 GMT - Launch Vehicle: Delta. Delta 2914 617/D130 ESA-Geos 1 Mass: 573 kg (1,263 lb). Spacecraft: ESA-Geos. Agency: ESA. Perigee: 2,939 km (1,826 mi). Apogee: 38,214 km (23,745 mi). Inclination: 26.60 deg. Period: 734.00 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1977 June 16 - 10:51 GMT - Launch Vehicle: Delta. Delta 2914 616/D131 GOES 2 Mass: 627 kg (1,382 lb). Spacecraft: GOES. Agency: NOAA. Perigee: 35,985 km (22,360 mi). Apogee: 36,080 km (22,410 mi). Inclination: 14.10 deg. Period: 1,448.70 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 75 deg W in 1977-1978 over the Americas at 100-110 deg W in 1979-1984 over the Americas at 112-114 deg W in 1984-1990 over the Atlantic Ocean 60 deg W in 1990-1992 over the Pacific Ocean 135 deg W in 1992-1995; over the Pacific Ocean 177 deg W in 1995-on. As of 4 September 2001 located at 147.59 deg W drifting at 3.154 deg W per day. As of 2007 Mar 8 located at 1.58W drifting at 3.141W degrees per day.

1977 July 14 - 10:39 GMT - Launch Vehicle: Delta. Delta 2914 618/D132 Himawari 1 Mass: 670 kg (1,470 lb). Spacecraft: GMS. Agency: NASDA. Perigee: 36,005 km (22,372 mi). Apogee: 36,148 km (22,461 mi). Inclination: 11.10 deg. Period: 1,451.00 min. Geostationary meteorological satellite. Positioned in geosynchronous orbit over the Pacific Ocean at 140 deg E in 1977-1981; over the Pacific Ocean 160 deg E in 1981-1984; over the Pacific Ocean 140 deg E in 1984; over the Pacific Ocean160 deg E in 1984-1989 As of 29 August 2001 located at 10.47 deg W drifting at 3.675 deg W per day. As of 2007 Mar 10 located at 112.63E drifting at 3.690W degrees per day.

1977 August 25 - 23:49 GMT - Launch Vehicle: Delta. Delta 2313 615/D133 Sirio 1 Mass: 220 kg (480 lb). Spacecraft: Sirio. Agency: CNR. Perigee: 35,755 km (22,217 mi). Apogee: 35,869 km (22,287 mi). Inclination: 9.60 deg. Period: 1,437.40 min. Experimental commsat. SIRIO (Satellite Italiano Ricerca Industriale Orientata). Launch time 2350:00 GMT. Geographical longitude of geostationary orbit 15 deg W. SIRIO is a spin stabilized geostationary experimental communications satellite. Characteristics of satellite: Weight at launch 398 kg, in orbit 218 kg. Configuration - cylindrical, height 1.981m, diameter 1.433 m, nominal life two years. Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1977-1981; over the Atlantic Ocean 25 deg W in 1981-1983; over the Indian Ocean 65 deg E in 1983-1985 As of 4 September 2001 located at 86.65 deg E drifting at 0.265 deg E per day. As of 2007 Mar 11 located at 75.38E drifting at 0.003E degrees per day.

1977 October 22 - 13:53 GMT - Launch Vehicle: Delta. Delta 2914 623/D135 ISEE 1 Mass: 340 kg (740 lb). Spacecraft: ISEE. Agency: NASA GSF. Perigee: 436 km (270 mi). Apogee: 137,806 km (85,628 mi). Inclination: 12.70 deg. Period: 3,441.00 min. International Sun-Earth Explorer. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1977 December 15 - 00:47 GMT - Launch Vehicle: Delta. Delta 2914 624/D137 Sakura Mass: 676 kg (1,490 lb). Spacecraft: CS-1. Agency: NASDA. Perigee: 36,169 km (22,474 mi). Apogee: 36,176 km (22,478 mi). Inclination: 10.50 deg. Period: 1,455.90 min. Medium-capacity Communications Satellite for Experimental Purposes . Launch vehicle Delta 2914-137. Launch time 0047 UT. Geographical longitude on geostationary orbit: 135 deg E. CS is a spin stabilized geostationary communications satellite. Characteris tics of satellite: Weight approx 340 kg at an early stage in orbit, configuration: cylindrical, height 3.48 m, diameter 2.18m, Expected life more than three years. Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg E in 1977-1983 over the Pacific Ocean 150 deg E in 1984-1985 As of 25 August 2001 located at 78.79 deg E drifting at 4.904 deg W per day. As of 2007 Mar 10 located at 94.72W drifting at 4.901W degrees per day.

1978 April 7 - 22:01 GMT - Launch Vehicle: Delta. Delta 2914 626/D140 Yuri 1 Mass: 678 kg (1,494 lb). Spacecraft: Yuri. Agency: NASDA. Perigee: 35,736 km (22,205 mi). Apogee: 35,868 km (22,287 mi). Inclination: 11.70 deg. Period: 1,436.90 min. Experimental comsat. Medium-scale broadcasting satellite for experimental purposes (BSE). Launch vehicle Delta 2914-140. Launch time 2201 GMT. Location 110 deg E. Characteristics of satellite: Weight approx 355 kg in an early stage in orbit. Configuration - box shaped satelli te with 2 solar array panels with overall span of 8.95m. Height 3.09m, width 1.32m, length 1.19m. 3-axis stabilized attitude control. Expected life 3 years. Positioned in geosynchronous orbit over the Indian Ocean at 110 deg E in 1978-1982 As of 4 September 2001 located at 44.59 deg E drifting at 0.116 deg E per day. As of 2007 Mar 11 located at 108.19E drifting at 0.031E degrees per day.

1978 June 16 - 10:49 GMT - Launch Vehicle: Delta. Delta 2914 625/D142 GOES 3 Mass: 627 kg (1,382 lb). Spacecraft: GOES. Agency: NOAA. Perigee: 35,767 km (22,224 mi). Apogee: 35,812 km (22,252 mi). Inclination: 9.80 deg. Period: 1,436.30 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 1978-1981 over the Americas at 90 deg W in 1982-1984 over the Pacific Ocean 135 deg W in 1985-1987 over the Americas at129 deg W in 1987-1990 over the Pacific Ocean 175 deg W in 1990-1995 over the Americas at 102-110 deg W in 1996-on. As of 5 September 2001 located at 101.78 deg W drifting at 0.017 deg W per day. As of 2007 Mar 9 located at 105.91W drifting at 0.030W degrees per day.

1978 August 12 - 15:12 GMT - Launch Vehicle: Delta. Delta 2914 633/D144 ISEE 3 Mass: 479 kg (1,056 lb). Spacecraft: ISEE. Agency: NASA GSF. Perigee: 181 km (112 mi). Apogee: 1,089,200 km (676,700 mi). Inclination: 1.00 deg. Period: 67,852.90 min. International Sun-Earth Explorer; later renamed the International Cometary Explorer. Measured interaction between solar wind and Earth; rendezvoused with comet Giacobini-Zinner September 11, 1985. After several passes through the Earth's magnetotail, with gravity assists from lunar flybys in March, April, September and October of 1983, a final close lunar flyby (119.4 km above the moon's surface) on December 22, 1983, ejected the spacecraft out of the Earth-Moon system and into a heliocentric orbit ahead of the Earth, on a trajectory intercepting that of Comet Giacobini-Zinner. A total of fifteen propulsive maneuvers (four of which were planned) and five lunar flybys were needed to carry out the transfer from the halo orbit to an escape trajectory from the earth-moon system into a heliocentric orbit. The primary scientific objective of ICE was to study the interaction between the solar wind and a cometary atmosphere. As planned, the spacecraft traversed the plasma tail of Comet Giacobini-Zinner on September 11, 1985, and made in situ measurements of particles, fields, and waves. It also transited between the Sun and Comet Halley in late March 1986, when other spacecraft (Giotto, Planet-A, MS-T5, VEGA) were also in the vicinity of Comet Halley on their comet rendezvous missions. ICE became the first spacecraft to directly investigate two comets. An update to the ICE mission was approved by NASA headquarters in 1991. It defined a Heliospheric mission for ICE consisting of investigations of coronal mass ejections in coordination with ground-based observations, continued cosmic ray studies, and special period observations such as when ICE and Ulysses are on the same solar radial line. As of January 1990, ICE was in a 355 day heliocentric orbit with an aphelion of 1.03 AU, a perihelion of 0.93 AU and an inclination of 0.1 degree. This will bring it back to the vicinity of the earth-moon system in August, 2014. Termination of operations of ISEE 3 was authorized May 5, 1997. Additional Details: ISEE 3(2324).

1978 November 19 - 00:46 GMT - Launch Vehicle: Delta. Delta 2914 634/D146 NATO 3C Mass: 720 kg (1,580 lb). Spacecraft: NATO 3. Agency: NATO. Perigee: 36,289 km (22,548 mi). Apogee: 36,299 km (22,555 mi). Inclination: 11.80 deg. Period: 1,462.10 min. Positioned in geosynchronous orbit over the Atlantic Ocean at 50 deg W in 1979-1982 over the Atlantic Ocean 21 deg W in 1983-1986 over the Atlantic Ocean 18 deg W in 1987-1991 over the Atlantic Ocean21 deg W in 1991-1992 As of 31 August 2001 located at 122.29 deg E drifting at 6.431 deg W per day. As of 2007 Mar 10 located at 114.22E drifting at 6.438W degrees per day.

1979 January 30 - 21:42 GMT - Launch Vehicle: Delta. Delta 2914 629/D148 SCATHA Mass: 360 kg (790 lb). Spacecraft: SCATHA. Agency: USAF. Perigee: 28,018 km (17,409 mi). Apogee: 42,860 km (26,630 mi). Inclination: 10.20 deg. Period: 1,418.40 min. Spacecraft charging experiments. The SCATHA spacecraft had two charged particle injection systems, one of which was the Satellite Positive-Ion-Beam System (SPIBS). This was a xenon ion source which included some of the technologies used in thrusters: however, the discharge chamber was not performance optimized as was done with ion engines. Maximum operating power was 0.045 kW, and the ion source could produce a thrust of about 0.14 mN at a specific impulse of 350 s. Ions could be ejected at 1 keV or 2 keV. Neutralization was accomplished by a tantalum filament. The specific impulse was low because there was no attempt to optimize the propellant efficiency. The SPIBS system was ground-tested for a period of 600 hours. The SCATHA spacecraft was placed in a near geosynchronous orbit. Ion beam operations were performed intermittently over a 247 day period. The SCATHA flight demonstrated that a charged spacecraft, and the dielectric surfaces on it, could be safely discharged by emitting a very low energy (<50 eV) neutral plasma -- in effect shorting the spacecraft to the ambient plasma before dangerous charging levels could be reached. As of 28 August 2001 located at 153.98 deg W drifting at 4.513 deg E per day. As of 2007 Mar 8 located at 19.65W drifting at 4.513E degrees per day.

1982 August 26 - 23:10 GMT - Launch Vehicle: Delta. Delta 3920/PAM 651/D164 Anik D1 (Telesat 5) Spacecraft: HS 376. Agency: Telesat. Perigee: 35,820 km (22,250 mi). Apogee: 35,846 km (22,273 mi). Inclination: 8.00 deg. Period: 1,438.50 min. Telecommunications. Operating entity Telesat Canada. Longitude 104.5W. Anik D-1 Transmit frequencies (MHz): 3720, 3740, 3760, 3780, 3800, 3820, 3840, 3860, 3880, 3900, 3920, 3940, 3960, 3980, 4000, 4020, 4040, 4060, 4080, 4100, 4120, 4140, 4160, 4180. Power 8.9 watts on each frequency. Positioned in geosynchronous orbit at 104 deg W in 1982-1991 As of 2 September 2001 located at 94.37 deg E drifting at 0.637 deg W per day. As of 2007 Mar 10 located at 52.18E drifting at 0.631W degrees per day.

1982 October 28 - 01:28 GMT - Launch Vehicle: Delta. Delta 3924 652/D165 Satcom 5 Mass: 590 kg (1,300 lb). Spacecraft: AS 3000. Agency: RCA Alas. Perigee: 35,782 km (22,233 mi). Apogee: 35,791 km (22,239 mi). Inclination: 8.10 deg. Period: 1,436.10 min. Positioned in geosynchronous orbit at 143 deg W in 1982-1991; 105 deg W in 1992-2007.

1983 April 11 - 21:39 GMT - Launch Vehicle: Delta. Delta 3924 653/D167 RCA Satcom 6 Mass: 2,385 kg (5,258 lb). Spacecraft: AS 3000. Agency: RCA Amer. Perigee: 35,851 km (22,276 mi). Apogee: 35,953 km (22,340 mi). Inclination: 7.00 deg. Period: 1,442.00 min. Positioned in geosynchronous orbit at 139 deg W in 1983-1991; 131 deg W in 1991-1992 As of 5 September 2001 located at 148.59 deg W drifting at 1.499 deg W per day. As of 2007 Mar 10 located at 90.26E drifting at 1.535W degrees per day.

1983 June 28 - 23:08 GMT - Launch Vehicle: Delta. Delta 3920/PAM D170 Galaxy 1 Mass: 1,218 kg (2,685 lb). Spacecraft: HS 376. Agency: HCI. Perigee: 35,815 km (22,254 mi). Apogee: 35,841 km (22,270 mi). Inclination: 6.30 deg. Period: 1,438.20 min. TV. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 134 deg W in 1983-1991; 133 deg W in 1991-1994 As of 31 August 2001 located at 92.66 deg W drifting at 0.600 deg W per day. As of 2007 Mar 9 located at 46.95W drifting at 0.505W degrees per day.

1983 September 8 - 22:52 GMT - Launch Vehicle: Delta. Delta 3924 D172 RCA Satcom 7 Mass: 1,121 kg (2,471 lb). Spacecraft: AS 3000. Agency: RCA Amer. Perigee: 35,963 km (22,346 mi). Apogee: 36,095 km (22,428 mi). Inclination: 5.70 deg. Period: 1,448.50 min. Positioned in geosynchronous orbit at 72 deg W in 1983-1995 As of 4 September 2001 located at 143.00 deg E drifting at 3.084 deg W per day. As of 2007 Mar 10 located at 40.27E drifting at 3.104W degrees per day.

1984 September 21 - 22:18 GMT - Launch Vehicle: Delta. Delta 3920/PAM D176 Galaxy 3 Mass: 1,218 kg (2,685 lb). Spacecraft: HS 376. Agency: HCI. Perigee: 35,885 km (22,297 mi). Apogee: 35,931 km (22,326 mi). Inclination: 5.70 deg. Period: 1,442.30 min. Geostationary at 3.5 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 94 deg W in 1984-1995 As of 1 September 2001 located at 138.23 deg E drifting at 1.543 deg W per day. As of 2007 Mar 10 located at 125.04W drifting at 1.587W degrees per day.

1986 September 5 - 15:08 GMT - Launch Vehicle: Delta. Delta 3920 D180 USA 19 Spacecraft: SDI. Agency: SDIO. Perigee: 213 km (132 mi). Apogee: 748 km (464 mi). Inclination: 39.10 deg. Period: 94.20 min. SDIO sensor tests. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1987 March 20 - 22:22 GMT - Launch Vehicle: Delta. Delta 3920/PAM D182 Palapa B2P Mass: 1,200 kg (2,600 lb). Spacecraft: HS 376. Agency: Perumtel. Perigee: 35,868 km (22,287 mi). Apogee: 35,906 km (22,310 mi). Inclination: 5.00 deg. Period: 1,441.20 min. Stationed at 113 deg W. Positioned in geosynchronous orbit at 113 deg E in 1987-1996; 144 deg E in 1996-1998 As of 28 August 2001 located at 130.30 deg W drifting at 1.327 deg W per day. As of 2007 Mar 3 located at 141.38E drifting at 1.274W degrees per day.

1988 February 8 - 22:08 GMT - Launch Vehicle: Delta. Delta 3910 D181 USA 30 Mass: 6,000 kg (13,200 lb). Spacecraft: SDI. Agency: SDIO. Perigee: 225 km (139 mi). Apogee: 342 km (212 mi). Inclination: 28.60 deg. Period: 90.20 min. Military tracking exercise; released subsatellites. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1989 March 24 - 21:50 GMT - Launch Vehicle: Delta. Delta 3920-8 D183 USA 36 Spacecraft: SDI. Agency: SDIO. Perigee: 307 km (190 mi). Apogee: 312 km (193 mi). Inclination: 47.70 deg. Period: 90.70 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1989 August 27 - 22:59 GMT - Launch Vehicle: Delta. Delta 4925-8 D187 BSB-1A Mass: 1,233 kg (2,718 lb). Spacecraft: HS 376. Agency: BSB. Perigee: 35,782 km (22,233 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.20 min. British DBS; 31 deg W. Direct broadcasting system. Expected operational life, 10 years. Owner/operator: British Satellite Broadcasting Ltd, The Marcopolo Building, Chelsea Bridge, Queenstown Rd, London SW8 4NQ. Positioned in geosynchronous orbit at 31 deg W in 1989-1993; 5 deg E in 1994-2000; 13 deg W in 2000. As of 31 August 2001 located at 12.98 deg W drifting at 0.008 deg W per day. As of 2007 Mar 9 located at 45.02W drifting at 3.908W degrees per day.

1989 December 11 - 18:10 GMT - Launch Vehicle: Delta. Delta 6925 D190 USA 49 Mass: 1,665 kg (3,670 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 19,992 km (12,422 mi). Apogee: 20,371 km (12,657 mi). Inclination: 55.40 deg. Period: 718.00 min. Global Positioning System. Placed in Plane D Slot 3.

1990 February 14 - 16:15 GMT - Launch Vehicle: Delta. Delta 6920-8 D192 USA 51 Mass: 1,430 kg (3,150 lb). Spacecraft: LACE. Agency: SDIO. Perigee: 463 km (287 mi). Apogee: 480 km (290 mi). Inclination: 43.10 deg. Period: 94.00 min. Low-power Atmospheric Compensation Experiment for SDIO. Research and exploration of the upper atmosphere and outer space. The McDonnell Douglas Corporation has provided the following information for its launch of the Losat spacecraft on 14 Feb 1990: LACE spacecraft (Losat-L), launch time 1615:00.626 GMT, ETR Launch Complex 17. Programmed orbital parameters 95.6 min, apogee 551 km, inc. 43.1 deg. Evaluate laser beam distortion in space.

1990 April 13 - 22:28 GMT - Launch Vehicle: Delta. Delta 6925-8 D194 Palapa B2R Mass: 1,200 kg (2,600 lb). Spacecraft: HS 376. Agency: Perumtel. Perigee: 35,784 km (22,235 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.30 min. Refurbished Palapa B2 retrieved by STS-51A; 107.7 deg E. Communication services for Indonesia, the Association of South-East Asian Nations (ASEAN), and Papua New Guinea. Launch time 2227:59.719 Z. Launch complex 17, ETR. Positioned in geosynchronous orbit at 108 deg E in 1990-1999 As of 29 August 2001 located at 42.49 deg E drifting at 0.002 deg E per day. As of 2007 Mar 9 located at 163.55E drifting at 2.663W degrees per day.

1990 June 12 - 05:52 GMT - Launch Vehicle: Delta. Delta 4925-8 D196 Insat-1D; Insat 1D Mass: 1,190 kg (2,620 lb). Spacecraft: Insat 1. Agency: ISRO. Perigee: 35,729 km (22,200 mi). Apogee: 35,851 km (22,276 mi). Inclination: 3.70 deg. Period: 1,436.30 min. Also performed Indian domestic communications tasks; 83.1 E. Operational multi-purpose satellite for telecommunications, meteorological imaging and data relay, radio and television programme distribution and direct television broadcasting for community reception. Orbital position 83 deg E. Also registered as 1990-5 1A in ST/SG/SER.E/250 by the United States, with category B and orbital parameters 1426.3 min, 35768 x 35811 km x 0.2 deg. Positioned in geosynchronous orbit at 83 deg E in 1990-1999; 74 deg E in 1999-2000 As of 5 September 2001 located at 73.85 deg E drifting at 0.000 deg E per day. As of 2007 Mar 10 located at 71.63E drifting at 0.039E degrees per day.

1990 August 18 - 00:42 GMT - Launch Vehicle: Delta. Delta 6925 D198 Thor 1 / BSB-R2 Mass: 1,220 kg (2,680 lb). Spacecraft: HS 376. Agency: BSB. Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. UK DBS; 31 deg W. Direct broadcasting system. Expected operational life 12.5 yr. Owner/operator: British Sky Broadcasting Ltd, 6 Centaurs Business Park, Grant Way, Isleworth, Middlesex TW7 5QD. Sold on-orbit in 1992 to Telenor Norway and redesignated Thor 1. Positioned in geosynchronous orbit at 50 deg W in 1990; 31 deg W in 1991-1992; 1 deg W in 1992-1999 As of 3 September 2001 located at 0.72 deg W drifting at 0.001 deg E per day. As of 2007 Mar 9 located at 61.51W drifting at 3.830W degrees per day.

1990 October 30 - 23:16 GMT - Launch Vehicle: Delta. Delta 6925 D200 Inmarsat 2 F1 Mass: 1,385 kg (3,053 lb). Spacecraft: Eurostar 1000. Agency: Inmarsat. Perigee: 35,775 km (22,229 mi). Apogee: 35,800 km (22,200 mi). Inclination: 1.70 deg. Period: 1,436.20 min. Mobile communications; 64.5 deg E. Positioned in geosynchronous orbit at 65 deg E in 1990-1996; 179 deg E in 1996-1999 As of 5 September 2001 located at 178.97 deg E drifting at 0.004 deg W per day. As of 2007 Mar 8 located at 143.50E drifting at 0.015W degrees per day.

1991 January 8 - 00:53 GMT - Launch Vehicle: Delta. Delta 7925 D202 NATO 4A Mass: 1,433 kg (3,159 lb). Spacecraft: ECS/OTS. Agency: NATO. Perigee: 35,775 km (22,229 mi). Apogee: 35,800 km (22,200 mi). Inclination: 2.60 deg. Period: 1,436.10 min. NATO communications; 18 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 18 deg W in 1991-1999 As of 5 September 2001 located at 17.81 deg W drifting at 0.007 deg W per day. As of 2007 Mar 10 located at 16.26W drifting at 0.003W degrees per day.

1991 March 8 - 23:03 GMT - Launch Vehicle: Delta. Delta 6925 D203 Inmarsat 2 F2 Mass: 1,385 kg (3,053 lb). Spacecraft: Eurostar 1000. Agency: Inmarsat. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 2.20 deg. Period: 1,436.10 min. Mobile and maritime communications; 15.5 deg W. Positioned in geosynchronous orbit at 15 deg W in 1991-1996; 55 deg W in 1997-1999; DRIFT As of 6 September 2001 located at 97.95 deg W drifting at 0.002 deg W per day. As of 2007 Mar 11 located at 97.96W drifting at 0.006W degrees per day.

1991 April 13 - 00:09 GMT - Launch Vehicle: Delta. Delta 7925 D204 ASC-2 / Spacenet F4 Mass: 1,350 kg (2,970 lb). Spacecraft: ASC. Agency: Contel. Perigee: 35,780 km (22,230 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.20 min. Commercial business communications; stationed at 101 deg W. C, Ku band communications satellite. Positioned in geosynchronous orbit at 101 deg W in 1991-1999; 81 deg W in 2000. As of 6 September 2001 located at 172.04 deg E drifting at 0.007 deg W per day. As of 2007 Mar 9 located at 34.51E drifting at 2.539W degrees per day.

1991 May 29 - 22:55 GMT - Launch Vehicle: Delta. Delta 7925 D205 Aurora 2 Mass: 1,336 kg (2,945 lb). Spacecraft: AS 3000. Agency: GE Alasc. Perigee: 36,125 km (22,446 mi). Apogee: 36,161 km (22,469 mi). Inclination: 1.20 deg. Period: 1,454.40 min. Stationed at 139 deg W. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Positioned in geosynchronous orbit at 139 deg W in 1991-1999 As of 30 August 2001 located at 148.31 deg E drifting at 4.531 deg W per day. As of 2007 Mar 9 located at 2.15E drifting at 4.534W degrees per day.

1992 February 23 - 22:29 GMT - Launch Vehicle: Delta. Delta 7925 D207 USA 79 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,032 km (12,447 mi). Apogee: 20,332 km (12,633 mi). Inclination: 54.20 deg. Period: 718.00 min. Global Positioning System. Placed in Plane A Slot 2.

1992 April 10 - 03:20 GMT - Launch Vehicle: Delta. Delta 7925 D208 USA 80 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,082 km (12,478 mi). Apogee: 20,277 km (12,599 mi). Inclination: 54.50 deg. Period: 717.90 min. Global Positioning System. Retired 15 August 1997.

1992 May 14 - 00:40 GMT - Launch Vehicle: Delta. Delta 7925 D209 Palapa B4 Mass: 1,254 kg (2,764 lb). Spacecraft: HS 376. Agency: PT Telko. Perigee: 35,787 km (22,236 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.20 min. Stationed at 118 deg E. Positioned in geosynchronous orbit at 118 deg E in 1992-1999 As of 2 September 2001 located at 118.02 deg E drifting at 0.020 deg W per day. As of 2007 Mar 9 located at 164.88E drifting at 1.157W degrees per day.

1992 July 7 - 09:20 GMT - Launch Vehicle: Delta. Delta 7925 D211 USA 83 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 19,962 km (12,403 mi). Apogee: 20,400 km (12,600 mi). Inclination: 54.90 deg. Period: 718.00 min. Global Positioning System. Placed in Plane F Slot 2.

1992 August 31 - 10:41 GMT - Launch Vehicle: Delta. Delta 7925 D213 Satcom C4 Mass: 2,000 kg (4,400 lb). Spacecraft: AS 3000. Agency: GE Ameri. Perigee: 35,786 km (22,236 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Stationed at 135 deg W. Positioned in geosynchronous orbit at 135 deg W in 1992-1999 As of 3 September 2001 located at 135.00 deg W drifting at 0.002 deg E per day. As of 2007 Mar 10 located at 164.40W drifting at 4.518W degrees per day.

1992 October 12 - 09:47 GMT - Launch Vehicle: Delta. Delta 7925 D215 DFS 3 Mass: 1,400 kg (3,000 lb). Spacecraft: Spacebus 100. Agency: Bundespo. Perigee: 35,773 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.50 deg. Period: 1,436.10 min. Stationed at 33.5 deg E. Communication satellite. Longitude 33.5 deg E. Delta II flight no 212. Positioned in geosynchronous orbit at 31 deg E in 1992; 23 deg E in 1993-1999 As of 1 September 2001 located at 23.45 deg E drifting at 0.001 deg E per day. As of 2007 Mar 9 located at 29.79E drifting at 1.955W degrees per day.

1992 December 18 - 22:16 GMT - Launch Vehicle: Delta. Delta 7925 D217 USA 87 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,038 km (12,451 mi). Apogee: 20,324 km (12,628 mi). Inclination: 54.70 deg. Period: 718.00 min. Global Positioning System. Placed in Plane F Slot 5.

1993 August 30 - 12:38 GMT - Launch Vehicle: Delta. Delta 7925 D222 USA 94 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,110 km (12,490 mi). Apogee: 20,255 km (12,585 mi). Inclination: 54.90 deg. Period: 718.00 min. Global Positioning System. Placed in Plane B Slot 4.

1993 October 26 - 17:04 GMT - Launch Vehicle: Delta. Delta 7925 D223 USA 96 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,104 km (12,492 mi). Apogee: 20,260 km (12,580 mi). Inclination: 55.10 deg. Period: 718.00 min. Global Positioning System. Placed in Plane D Slot 4.

1994 February 19 - 23:45 GMT - Launch Vehicle: Delta. Delta 7925-8 D225 Galaxy 1R Mass: 1,391 kg (3,066 lb). Spacecraft: HS 376. Agency: HCI. Perigee: 35,774 km (22,228 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Stationed at 133 deg W; replaced Galaxy 1. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit at 133 deg W in 1994-1999 As of 5 September 2001 located at 132.97 deg W drifting at 0.005 deg E per day. As of 2007 Mar 9 located at 88.88W drifting at 3.795W degrees per day.

1994 November 1 - 09:31 GMT - Launch Vehicle: Delta. Delta 7925-10 D227 Wind Mass: 1,195 kg (2,634 lb). Spacecraft: Wind. Agency: NASA GSF. Perigee: 48,840 km (30,340 mi). Apogee: 1,578,658 km (980,930 mi). Inclination: 19.65 deg. Period: 318,240.00 min. Solar wind research in L-1 halo orbit; part of International Solar Terrestrial Physics program. 221 day orbit. NASA's Wind probe made its 32nd lunar flyby on August 19, 2000, with a closest approach of 7600 km to the surface. This placed it on a 2 million km apogee orbit, adjusted on August 26 to an approximately 567000 x 1620000 km x 21.8 deg `Distant Prograde Orbit', reaching apogee on September 29 2000.

1995 August 5 - 11:10 GMT - Launch Vehicle: Delta. Delta 7925 D228 FAILURE: Partial Failure. Mugunghwa 1 Mass: 1,459 kg (3,216 lb). Spacecraft: AS 3000. Agency: Korea Te. Perigee: 35,776 km (22,230 mi). Apogee: 35,796 km (22,242 mi). Inclination: 2.70 deg. Period: 1,436.10 min. 15 Ku-band transponders; boosted into geosynch orbit by satellite thrusters following Delta failure that left satellite in LEO; unplanned use of satellite propellant cut usable satellite lifetime by approx. 50 percent. Stationed at 116.0 deg E. Stage 1 SRM failure Positioned in geosynchronous orbit at 116 deg E in 1995-1999 As of 5 September 2001 located at 47.22 deg E drifting at 0.022 deg E per day. As of 2007 Mar 9 located at 152.88E drifting at 2.155W degrees per day.

1996 January 14 - 11:10 GMT - Launch Vehicle: Delta. Delta 7925 D231 Koreasat 2 Mass: 600 kg (1,320 lb). Spacecraft: AS 3000. Agency: Korea Te. Perigee: 35,782 km (22,233 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.20 min. Geostationary at 116.0E. Positioned in geosynchronous orbit at 116 deg E in 1996-2000 As of 5 September 2001 located at 113.02 deg E drifting at 0.017 deg W per day. As of 2007 Mar 11 located at 116.35E drifting at 0.013W degrees per day.

1996 February 17 - 20:43 GMT - Launch Vehicle: Delta. Delta 7925-8 D232 NEAR Mass: 818 kg (1,803 lb). Spacecraft: NEAR. Agency: NASA GSF. Near Earth Asteroid Rendezvous (NEAR) mission was the first of NASA's Discovery missions, a series of small-scale spacecraft designed to proceed from development to flight in under three years for a cost of less than $150 million. The spacecraft's mission was to rendezvous with and achieve orbit around the asteroid Eros in January 1999, and study the asteroid for one year. However as it flew by the Earth on 23 January 1998, a problem caused an abort of the first encounter burn. The mission had to be rescoped for a later encounter but successfully entered orbit around Eros on Valentine's Day 2000 and ended the mission by gently landing on its surface on 12 February 2001.

1996 March 28 - 00:21 GMT - Launch Vehicle: Delta. Delta 7925 D234 USA 117 Mass: 1,816 kg (4,003 lb). Spacecraft: GPS Block 2 and 2A. Agency: USAF. Perigee: 20,106 km (12,493 mi). Apogee: 20,257 km (12,587 mi). Inclination: 54.60 deg. Period: 718.00 min. Placed in Plane C Slot 2 of the constellation.

1996 May 24 - 01:09 GMT - Launch Vehicle: Delta. Delta 7925 D236 Galaxy 9 Spacecraft: HS 601. Agency: HCI. Perigee: 35,783 km (22,234 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geostationary at 123.0W. Positioned in geosynchronous orbit at 123 deg W in 1996-2000; 127 deg W in 2000.- As of 5 September 2001 located at 126.96 deg W drifting at 0.001 deg W per day. As of 2007 Mar 11 located at 74.14W drifting at 0.004W degrees per day.

1996 December 4 - 06:58 GMT - Launch Vehicle: Delta. Delta 7925 D240 Mars Pathfinder Spacecraft: Mars Pathfinder. Agency: NASA/JPL. En route Mars

1998 January 10 - 00:32 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D252 Skynet 4D Spacecraft: ECS/OTS. Agency: UK MOD. Perigee: 35,776 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 3.90 deg. Period: 1,436.00 min. Geostationary at 52.8 degrees E. Positioned in geosynchronous orbit at 53 deg E in 1998-1999; moving As of 4 September 2001 located at 34.00 deg W drifting at 0.004 deg W per day. As of 2007 Mar 10 located at 34.33W drifting at 0.016W degrees per day.

1998 August 27 - 01:17 GMT - Launch Vehicle: Delta. LV Model: Delta 3 . Delta 8930 D259 FAILURE: Due to guidance system induced oscillation all solid motor gimbal hydraulic fluid exhausted after only 71 seconds of flight. Range safety destroyed booster 75 seconds into flight at 16 km altitude. Galaxy 10 Mass: 3,876 kg (8,545 lb). Spacecraft: HS 601. Agency: Panamsat Inc. Greenwich, Connecticut. Built by Hughes/El Segundo for Panamsat. The satellite carried 24 C-band and 24 Ku-band transponders to provide US/Caribbean coverage, and was to have replaced the ageing SBS-5 satellite at 123 deg West. Replenishing the Galaxy/PAS constellation was a high priority for Panamsat following the loss of Galaxy 4 and problems with Galaxy 7. Galaxy 11 was not scheduled to go up until the first launch of the Sea Launch Zenit-3SL in early 1999, and this booster was in limbo due to legal problems with unauthorised transfer of technical data from Boeing to Russia. In addition there were several PAS satellites awaiting launch over the next year on Proton and Ariane vehicles.

1998 November 22 - 23:54 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D263 BONUM-1 Spacecraft: HS 376. Agency: Telenor. Perigee: 35,785 km (22,235 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.10 deg. BONUM-1 provided domestic Russian television service for Media Most, a Moscow media enterprise, broadcasting 50 channels to western Russia from a geostationary orbit at 36 degrees E. Mass was 1426 kg at launch, 800 kg of that propellant. BONUM-1 carried 8 Ku-band transponders. The Delta upper stage raised the initial 157 km x 189 km at 29.2 degree parking orbit to 159 km x 1304 km and then 1228 km x 1683 km at 26.7 degrees. A Thiokol Star 48B solid third stage boosted BONUM-1 to a 1285 x 36703 km x 19.5 degree geostationary transfer orbit, with the Thiokol Star 30 apogee kick motor placing the satellite in its final geostationary orbit. After separation of the spacecraft, the Delta made a final depletion burn to lower its orbit to 274 km x 1552 km x 25.6 degree to ensure it would quickly decay and burn up in the atmosphere. Geostationary at 35.9 degrees E. From 8 August 2000 position was 56.0 degrees E. Positioned in geosynchronous orbit at 36 deg E in 1998-1999 55 deg E in 2000. As of 5 September 2001 located at 56.03 deg E drifting at 0.016 deg W per day. As of 2007 Mar 10 located at 55.94E drifting at 0.008W degrees per day.

1999 January 3 - 20:21 GMT - Launch Vehicle: Delta. Delta 7425-9.5 D265 Mars Polar Lander Mass: 576 kg (1,269 lb). Spacecraft: Mars Polar Lander. Agency: JPL. The Mars Polar Lander was placed by the first burn of the second stage into a 157 x 245 km x 28.35 deg parking orbit. The second stage restarted at 20:55 GMT and shut down in a 226 x 740 km x 25.8 deg Earth orbit. The solid rocket third stage (a Star 48B with a Nutation Control System and a yo-yo despin device) then ignited and put the spacecraft into solar orbit, separating at 21:02 GMT. Mars Polar Lander was to land near the south pole of Mars on December 3, 1999, and conduct conduct a three month mission, trenching near its landing site and testing for the presense of frozen water and carbon dioxide. Attached were two Deep Space 2 Microprobes, penetrators which would impact the Martian surface separately from the lander and return data on subsurface conditions from widely spaced points.

When the spacecraft reached Mars on December 3, the lander separated from the cruise stage at 19:51 UTC and the two penetrators, Scott and Amundsen, were to separate about 20 seconds later. No further communications were ever received from the spacecraft. Landing had been expected at 20:01 UTC at 76.1S 195.3W, with the penetrators landing a few kilometres from each other at 75.0S 196.5W.

This failure resulted in a review and reassessment of NASA's 'faster, better, cheaper' approach to planetary missions.

1999 May 5 - 01:00 GMT - Launch Vehicle: Delta. LV Model: Delta 3 . Delta 8930 D269 FAILURE: Engine failure at ignition for second burn of Centaur stage. Orion 3 Spacecraft: HS 601. Agency: Loral Or. Perigee: 2,456 km (1,526 mi). Apogee: 2,529 km (1,571 mi). Inclination: 19.80 deg. Period: 138.60 min. The Centaur RL-10B-2 second stage engine's combustion chamber ruptured at the beginning of the second burn. The hot gases already in the chamber vented, putting the stage/spacecraft assembly into an uncontrollable tumble. The Orion 3 communications satellite ended up in a useless parking orbit of 162 km x 1378 km x 29.5 deg. It was to have served the Asia-Pacific region for Loral Orion with 33 Ku-band and 10 C-band transponders.

1999 June 10 - 13:48 GMT - Launch Vehicle: Delta. Delta 7420-10C D270 Globalstar 52 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 July 10 - 08:45 GMT - Launch Vehicle: Delta. Delta 7420-10C D272 Globalstar 32 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 August 17 - 04:37 GMT - Launch Vehicle: Delta. Delta 7420-10C D274 Globalstar 24 Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

2000 February 8 - 21:24 GMT - Launch Vehicle: Delta. Delta 7420-10C D276 Globalstar M060 Mass: 450 kg (990 lb). Spacecraft: Globalstar. Agency: Globalsat. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. Mobile Telephony. These four Globalstar satellites completed the Globalstar initial constellation.

2000 August 23 - 11:05 GMT - Launch Vehicle: Delta. LV Model: Delta 3 . Delta 8930 D280 DM-F3 Mass: 4,348 kg (9,585 lb). Agency: Boeing/H. Perigee: 212 km (131 mi). Apogee: 19,547 km (12,145 mi). Inclination: 27.60 deg. Vehicle Demonstration. Return to flight following earlier failure. The third Boeing Delta III launch was financed by the company and carried a dummy payload in order to bolster customer confidence in the new launch vehicle. The second stage ignited at an altitude of 158 km and the RL-10 shut off as planned in a 157 x 1363 km x 29.5 deg parking orbit. The engine fired again until fuel depletion, to place the vehicle in a geostationary transfer orbit of 190 x 20,655 km x 27.6 deg. This was much lower than that planned (23,400 km plus or minus 3,000 km) due to the fuel temperature and atmospheric conditions on the day of launch. The DM-F3 dummy payload was a mass model of the Orion 3 HS-601 satellite launched on the second Delta 3. The 4348 kg model was a 2.0m diameter, 1.7m high cylinder with two circular end plates, painted with black and white patterns. It was to be used by US Air Force researchers as a calibration target.

2001 May 18 - 17:45 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D285 USA 158 Mass: 93 kg (205 lb). Spacecraft: GeoLITE. Agency: NRO. Perigee: 179 km (111 mi). Apogee: 35,700 km (22,100 mi). Inclination: 19.50 deg. Period: 629.01 min. Military Communications Technology flight. Launch delayed from March 1, April 25, May 2 and 17. GeoLITE, US National Reconnaissance Office spacecraft was into placed by the Delta launch vehicle into a geostationary transfer orbit. GeoLITE was a TRW T-310 class satellite with a mass of about 1800 kg, including a solid apogee motor. The satellite carried an experimental laser communications payload and an operational UHF data relay payload.

2001 June 30 - 19:46 GMT - Launch Vehicle: Delta. Delta 7425-10 D286 MAP Mass: 840 kg (1,850 lb). Spacecraft: MAP. Agency: NASA GSF. Perigee: 4,704 km (2,922 mi). Apogee: 379,553 km (235,842 mi). Inclination: 27.80 deg. Period: 14,669.70 min. NASA's Microwave Anisotropy Probe (MAP) was placed in a 167 x 204 km x 28.8 deg parking orbit at 1958 GMT. At 2104 GMT the second stage ignited again for a 4 second burn, raising the orbit to around 181 x 308 km; the third stage spun up and ignited at 2108 GMT, accelerating MAP to a highly elliptical orbit of 182 x 292,492 km x 28.7 deg. MAP used on-board fuel to tweak the orbit and make a lunar flyby at fourth apogee on July 30, arriving at the L2 Earth-Moon Lagrangian point 1.5 million km from Earth three months later. From L2, MAP was to measure fluctuations in the cosmic 3 Kelvin microwave background with the degree of precision required to answer questions about the big bang and the total mass and fate of the universe. By July 22 the MAP probe was in a 4055 x 355,935 km x 28.0 deg orbit. It flew past the Moon on July 30 at 1639 GMT at an altitude of 5200 km above the lunar surface.

2003 January 29 - Launch Vehicle: Delta. Delta 7925-9.5 D295 USA 166 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,163 km (12,528 mi). Apogee: 20,352 km (12,646 mi). Inclination: 55.06 deg. Period: 720.74 min. Launch delayed from June 11 and August 16, 2001; March 6, April 29, August 11 and November 7, 2002.

2003 July 8 - 04:18 GMT - Launch Vehicle: Delta. Delta 7925H D299 Opportunity (Mars Exploration Rover B, MER-1) Mass: 1,063 kg (2,343 lb). Spacecraft: MER. Agency: JPL. NASA's second Mars Exploration Rover, MER-B (MER-1) 'Opportunity', was launched by a Delta 7925H, which was similar to the standard 7925 model but with larger GEM-46 solid strapon motors previously used only on the Delta III 8930. MER-B separated from the Delta third stage at 0436 UTC and was then on its way to Mars. The launch had been delayed from June 26, 29 and 30, July 3, 6 and 7. Mass included cruise stage, lander and rover. Rover mass was 170 kg, lander 360 kg.

2003 August 25 - 05:35 GMT - Launch Vehicle: Delta. Delta 7920H D300 SIRTF Mass: 923 kg (2,034 lb). Spacecraft: SIRTF. Agency: NASA. Originally to have launched January 9, 2003. Delayed six times. The Space Infrared Telescope Facility (SIRTF) was the last of NASA's 'Great Observatories'. It had a 0.85-meter infrared telescope, with a liquid-helium cooled focal plane carrying the three main instruments. SIRTF was launched by the second Delta II Heavy. The second stage entered a 166 x 167 km x 31.5 deg Earth parking orbit, and after about 33 minutes of coast, passing south of Madagascar, restarted at 0613 UTC to enter a hyperbolic orbit with a perigee of 170 km, an eccentricity of 1.0061, and a velocity of 11.05 km/s. This placed it in a solar orbit of 0.996 x 1.019 AU x 1.14 deg with a year about 4 days longer than Earth's.

2004 March 20 - 17:53 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D303 USA 177 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 20,100 km (12,400 mi). Apogee: 20,268 km (12,593 mi). Inclination: 55.00 deg. Period: 718.00 min. Launch delayed from December 19, 2003, March 8, 2004.

2004 June 23 - 22:54 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D305 USA 178 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: U.S. Air Force. Perigee: 20,090 km (12,480 mi). Apogee: 20,273 km (12,597 mi). Inclination: 55.10 deg. Period: 717.90 min. Delayed from February 17. Delayed from June 5, 11, 13, 14, 16, 18, 19, 20 and 21. Moved up from July 20.

2004 August 3 - 06:15 GMT - Launch Vehicle: Delta. Delta 7925H D307 Messenger Mass: 1,066 kg (2,350 lb). Spacecraft: Messenger. Agency: NASA. The NASA Messenger probe to Mercury was was first placed into a parking orbit. The Delta booster second stage's second burn raised the orbit, then the PAM-D solid motor burned to put the probe on an escape trajectory into a 0.92 x 1.08 AU x 6.4 deg heliocentric orbit. Messenger (Mercury Surface, Space Environment, Geochemistry and Ranging) was to make an Earth flyby on August 1, 2005; Venus flybys in 2006 and 2007; and Mercury encounters in January and October 2008 , September 2009 and March 2011 . On this last encounter the Aerojet 660N engine was to fire to put Messenger into a 200 x 15,193 km x 80 deg orbit around Mercury. Launch delayed from March 10, May 11, August 2

2004 November 6 - 05:39 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D308 USA 180 Mass: 2,032 kg (4,479 lb). Spacecraft: GPS Block 2R. Agency: USAF. Perigee: 19,810 km (12,300 mi). Apogee: 20,413 km (12,684 mi). Inclination: 54.90 deg. Period: 715.10 min. Launch delayed from September 22, October 8, 25 and 30, November 5. Fired its apogee motor at around 02:40 GMT on November 9 to transfer from its initial 159 x 20380 km x 39.1 deg transfer orbit to its operational orbit in the GPS constellation.

2005 January 12 - 18:47 GMT - Launch Vehicle: Delta. Delta 7925-9.5 D311 Deep Impact Mass: 601 kg (1,324 lb). Spacecraft: Deep Impact. Launched into a 0.981 AU x 1.628 AU solar orbit inclined 0.6 deg to the ecliptic. Deep Impact was to fly by Comet 9P/Tempel-1 on 3 July 2005. An impacter it released was to hit the comet on 4 July at 10.2 km/s, producing a crater and ejecta plume that would allow the flyby spacecraft to determine the composition and structure of the comet's nucleus.

2006 October 26 - 00:52 GMT - Launch Vehicle: Delta. Delta 7925-10L D319 Stereo Ahead The booster was used to put the twin spacecraft in a 182 km x 403,810 km x 28.5 deg lunar transfer orbit. They would use a series of lunar flybys to eventually place themselves in two different solar orbits: Stereo Ahead in a 0.95 AU x 0.97 AU x 0.12 Deg / 344 day orbit around the Sun leading the Earth, and Stereo Behind in a 0.99 AU x 1.09 AU x 0.03 deg / 389 day orbit trailing the Earth. The satellites were equipped with optical, ultraviolet, radio, and particle sensors that would allow them to form a three-dimensional image of the sun's corona using identical sensors from two vantage points at the same moment.

2007 February 17 - 23:01 GMT - Launch Vehicle: Delta. Delta 7925-10C D323 Themis P1 Mass: 125 kg (275 lb). Agency: NASA. Perigee: 1,003 km (623 mi). Apogee: 87,254 km (54,217 mi). Inclination: 14.10 deg. Period: 1,882.70 min. The five simultaneously-launched Time History of Events and Macroscale Interactions during Substorms (THEMIS) satellites were the fifth medium-class mission under NASA's Explorer Program. They formed part of a combined ground- and space- based system designed to determine what physical process in near-Earth space initiate the violent eruptions of the aurora that occur during substorms in the Earth's magnetosphere.