1965 December 21 - 14:00 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-8 OV2-03 Mass: 193 kg (425 lb). Spacecraft: OV2. Agency: USAF. Perigee: 321 km (199 mi). Apogee: 22,846 km (14,195 mi). Inclination: 26.80 deg. Period: 399.30 min. Upper stage separation failed. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1966 June 16 - 14:00 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-11 GGTS 1 Mass: 47 kg (103 lb). Spacecraft: GGTS. Agency: USAF. Perigee: 33,663 km (20,917 mi). Apogee: 33,858 km (21,038 mi). Inclination: 4.20 deg. Period: 1,334.00 min. Gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1966 August 26 - 13:59 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-12 FAILURE: Payload fairing broke up 78 seconds after launch. IDCSP (8) ... IDCSP (14) Spacecraft: IDCSP. Agency: U.S. Air Force. 8 satellites, each weighing 45 kg.

1967 January 18 - 14:19 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-13 IDCSP 2-1 Mass: 45 kg (99 lb). Spacecraft: IDCSP. Agency: USAF. Perigee: 33,518 km (20,827 mi). Apogee: 33,829 km (21,020 mi). Inclination: 8.70 deg. Period: 1,329.50 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1967 April 28 - 10:01 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-10 Vela 7 Mass: 317 kg (698 lb). Spacecraft: Advanced Vela. Agency: USAF. Perigee: 108,948 km (67,697 mi). Apogee: 112,627 km (69,983 mi). Inclination: 32.10 deg. Period: 6,652.10 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1967 July 1 - 13:15 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-14 IDCSP 3-1 Mass: 45 kg (99 lb). Spacecraft: IDCSP. Agency: USAF. Perigee: 33,030 km (20,520 mi). Apogee: 33,515 km (20,825 mi). Inclination: 11.90 deg. Period: 1,309.60 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1968 June 13 - 14:03 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-16 IDCSP 4-1 Mass: 45 kg (99 lb). Spacecraft: IDCSP. Agency: USAF. Perigee: 33,725 km (20,955 mi). Apogee: 33,850 km (21,030 mi). Inclination: 11.90 deg. Period: 1,335.20 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1968 September 26 - 07:37 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-5 OV2-05 Mass: 204 kg (449 lb). Spacecraft: OV2. Agency: USAF. Perigee: 35,113 km (21,818 mi). Apogee: 35,745 km (22,210 mi). Inclination: 12.30 deg. Period: 1,417.90 min. Environmental research. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). As of 22 August 2001 located at 128.37 deg E drifting at 4.618 deg E per day. As of 2007 Feb 27 located at 91.48E drifting at 4.631E degrees per day.

1969 February 9 - 21:09 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-17 Tacsat 1 Mass: 730 kg (1,600 lb). Spacecraft: Tacsat. Agency: USAF. Perigee: 35,939 km (22,331 mi). Apogee: 36,044 km (22,396 mi). Inclination: 1.00 deg. Period: 1,446.60 min. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit over the Americas at 107 deg W in 1969?-1970; over the Pacific Ocean 173 deg W in 1970; over the Pacific Ocean 179 deg W in 1971-1972; over the Pacific Ocean170 deg E in 1972 Last known longitude (9 June 1995) 176.44 deg E drifting at 0.150 deg E per day.

1969 May 23 - 07:57 GMT - Launch Vehicle: Titan. LV Model: Titan 3C . Titan IIIC 3C-15 OV5-05 Mass: 259 kg (570 lb). Spacecraft: OV5. Agency: USAF. Perigee: 59,630 km (37,050 mi). Apogee: 69,130 km (42,950 mi). Inclination: 33.00 deg. Period: 3,121.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1974 February 11 - 13:48 GMT - Launch Vehicle: Titan. LV Model: Titan 3E . Titan IIIE 23E-1 / Centaur D-1T E-1 FAILURE: Centaur LOX pump failure. Sphinx Spacecraft: Sphinx. Agency: USAF. Space Plasma High Voltage Interaction Experiment. Payload carried on test flight of Titan 3E booster.

1974 December 10 - 07:11 GMT - Launch Vehicle: Titan. LV Model: Titan 3E . Titan IIIE 23E-2 / Centaur D-1T E-2 Helios 1 Mass: 370 kg (810 lb). Spacecraft: Helios. Agency: DFVLR. Solar probe. Solar Orbit (Heliocentric). Launched by the United States and the Federal Republic of Germany. Helios A (Helios I). Heliocentric orbit 190 days, 0.309 x 0.985 AU x 0 deg. Exploration of the interplanetary space between the earth and the sun and study of solar influences on that area.

1975 August 20 - 21:22 GMT - Launch Vehicle: Titan. LV Model: Titan 3E . Titan IIIE 23E-4 / Centaur D-1T E-4 Viking 1 Orbiter Mass: 3,399 kg (7,493 lb). Spacecraft: Viking. Agency: NASA JPL. Combined Mars orbiter and lander mission; orbiter inserted in Mars orbit 6/19/76; lander soft landed on Martian surface 7/20/76Mars. Mars Orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1975 September 9 - 18:39 GMT - Launch Vehicle: Titan. LV Model: Titan 3E . Titan IIIE 23E-3 / Centaur D-1T E-3 Viking 2 Orbiter Mass: 3,399 kg (7,493 lb). Spacecraft: Viking. Agency: NASA JPL. Combined Mars orbiter and lander mission; orbiter inserted in Mars orbit 8/7/76; lander soft landed on Martian surface 9/3/76Mars. Mars Orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1976 January 15 - 05:34 GMT - Launch Vehicle: Titan. LV Model: Titan 3E . Titan IIIE 23E-5 / Centaur D-1T E-5 Helios 2 Mass: 376 kg (828 lb). Spacecraft: Helios. Agency: DFVLR. Solar probe. Solar Orbit (Heliocentric). Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1977 August 20 - 14:29 GMT - Launch Vehicle: Titan. LV Model: Titan 3E . Titan IIIE 23E-7 / Centaur D-1T E-7 Voyager 2 Mass: 800 kg (1,760 lb). Spacecraft: Voyager. Agency: NASA JPL. Jupiter flyby 7/9/79, Saturn flyby 8/26/81, Uranus flyby 1/24/86, Neptune flyby 8/25/89. Solar system escape trajectory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1977 September 5 - 12:56 GMT - Launch Vehicle: Titan. LV Model: Titan 3E . Titan IIIE 23E-6 / Centaur D-1T E-6 Voyager 1 Mass: 800 kg (1,760 lb). Spacecraft: Voyager. Agency: NASA JPL. Jupiter flyby 3/5/79, Saturn flyby 11/12/80. Solar system escape trajectory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1989 June 14 - 13:18 GMT - Launch Vehicle: Titan. Titan 402A/IUS K-1 (45D-1) USA 39 Mass: 2,360 kg (5,200 lb). Spacecraft: DSP. Agency: USAF. Perigee: 35,699 km (22,182 mi). Apogee: 35,614 km (22,129 mi). Inclination: 3.10 deg. Period: 1,421.80 min. First DSP-1 Block 14 ballistic missile launch detection satellite; first Titan 4 launch. Positioned in geosynchronous orbit at 165 deg W in 1990-1994; 145 deg W in 1999; 166 deg W in 2000.. Still in service as of March 2007. As of 2007 Feb 5 located at 145.23W drifting at 0.014W degrees per day.

1990 June 8 - 05:22 GMT - Launch Vehicle: Titan. Titan 405A K-4 (45H-4) USA 59 Spacecraft: NOSS-2. Agency: NRO/NRL. Perigee: 268 km (166 mi). Apogee: 284 km (176 mi). Inclination: 61.00 deg. Period: 90.00 min. First launch by Titan 4 of new generation of NOSS naval reconnaissance satellites. However earlier NOSS weighed only 2,000 kg; Titan 4 booster has seven times this capacity. What else was launched?

1990 November 13 - 00:37 GMT - Launch Vehicle: Titan. Titan 402A/IUS K-6 (45D-2) USA 65 Mass: 2,360 kg (5,200 lb). Spacecraft: DSP. Agency: USAF. Perigee: 35,614 km (22,129 mi). Apogee: 35,699 km (22,182 mi). Inclination: 3.10 deg. Period: 1,421.80 min. DSP-1 Block 14 ballistic missile launch detection satellite. Positioned in geosynchronous orbit at 105 deg E in 1991; 70 deg E in 1991-1992; 5 deg E in 1992-1993; 35 deg W in 1993; 38 deg W in 1999-2004. Believed to have been taken out of service in 2006.

1994 May 3 - 15:55 GMT - Launch Vehicle: Titan. Titan 401A/Centaur K-7/TC-10 (45E-1) USA 103 Mass: 5,200 kg (11,400 lb). Spacecraft: Trumpet. Agency: NRO/USAF. Perigee: 518 km (321 mi). Apogee: 537 km (333 mi). Inclination: 55.10 deg. Period: 95.20 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1994 August 27 - 08:58 GMT - Launch Vehicle: Titan. Titan 401A/Centaur K-9/TC-11 (45E-2) USA 105 Spacecraft: Mercury ELINT. Agency: NRO/USAF. Perigee: 35,780 km (22,230 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. First launch of Mercury ELINT satellite.

1995 July 10 - 12:38 GMT - Launch Vehicle: Titan. Titan 401A/Centaur K-19/TC-8 (45E-5) USA 112 Mass: 5,200 kg (11,400 lb). Spacecraft: Trumpet. Agency: NRO/USAF. Perigee: 1,000 km (600 mi). Apogee: 39,000 km (24,000 mi). Inclination: 64.00 deg.

1996 April 24 - 23:37 GMT - Launch Vehicle: Titan. Titan 401A/Centaur K-16/TC-15 (45E-4) USA 118 Spacecraft: Mercury ELINT. Agency: NRO/USAF. Perigee: 30,000 km (18,000 mi). Second launch of Mercury ELINT satellite.

1997 November 8 - 02:05 GMT - Launch Vehicle: Titan. Titan 401A/Centaur 4A-17/TC-16 (45E-?) USA 136 Mass: 5,200 kg (11,400 lb). Spacecraft: Trumpet. Agency: NRO/USAF. Perigee: 1,100 km (600 mi). Apogee: 39,059 km (24,270 mi). Inclination: 63.60 deg.

1998 August 12 - 11:30 GMT - Launch Vehicle: Titan. Titan 401A/Centaur 4A-20/TC-9 (K-17) FAILURE: Due to guidance system loss of heading after power interrupt, booster pitched over 40 seconds after launch, and was destroyed by range safety. Mercury ELINT Spacecraft: Mercury ELINT. Agency: NRO/NSA. Third launch of Mercury ELINT satellite.

1999 April 9 - 17:01 GMT - Launch Vehicle: Titan. LV Model: Titan 402B/IUS . Titan 402B 4B-27 / IUS K-32 FAILURE: IUS first and second stages failed to separate. USA 142 Mass: 2,380 kg (5,240 lb). Spacecraft: DSP. Agency: USAF. Perigee: 720 km (440 mi). Apogee: 35,800 km (22,200 mi). Inclination: 28.00 deg. The Titan 4B placed the IUS upper stages and DSP-1 Block 14 ballistic missile launch detection satellite. payload into a 188 km x 718 km x 28.6 deg parking orbit. The first stage of the IUS burned at 18:14 GMT and put the second stage and payload into a geosynchronous transfer orbit. The IUS second stage fired at 23:34 GMT in order to place the spacecraft in geosynchronous orbit. However, at least one connector remained attached between the stages, and the second stage motor nozzle did not extend properly. When the stage fired, the vehicle tumbled wildly during the burn. Separation of the DSP was achieved. Although it could not perform its primary mission, it did provide a good test case in that the effects of radiation on its systems could be monitored as they underwent twice-daily passages of the Van Allen Radiation Belts. However after some weeks the hydrazine propellant aboard the satellite vented into space due to a broken fuel line. It was believed this had been induced by the wild ride aboard the IUS-2 stage.

2002 August 21 - 22:05 GMT - Launch Vehicle: Atlas V. Atlas V 401 AV-001 Hot Bird 6 Mass: 3,905 kg (8,609 lb). Spacecraft: Spacebus 3000. Agency: Eutelsat. Perigee: 35,757 km (22,218 mi). Apogee: 35,814 km (22,253 mi). Inclination: 0.00 deg. Period: 1,436.10 min. This was the maiden flight of the Atlas 5 EELV. Launch delayed from May 9, July 8 and 29, August 6 and 12 due to both payload and booster delays. Hot Bird 6 was a European (EUTELSAT) geostationary communications spacecraft. The 4.9-ton Hot Bird 6 (a Spacebus 3000B3) was to provide digital radio and television coverage to Europe, North Africa, and the Middle East through its 28 Ku-band and four Ka-band transponders after being parked over 13° E longitude. As of 2007 Mar 4 located at 12.95E drifting at 0.012E degrees per day.

2003 May 13 - Launch Vehicle: Atlas V. Atlas V 401 AV-002 Hellas Sat 2 Mass: 3,440 kg (7,580 lb). Spacecraft: Eurostar 2000. Agency: Hellas Sat Consortium. Perigee: 35,775 km (22,229 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Launch delayed from January 30, March 11 and 14, May 10 and 12, 2003. Spacecraft former Intelsat KTV, NSS-KTV, NSS-6, Intelsat APR-3. As of 2007 Mar 8 located at 38.95E drifting at 0.006E degrees per day.

2003 July 17 - 23:45 GMT - Launch Vehicle: Atlas V. Atlas V 521 AV-003 Rainbow 1 (Cablevision 1) Mass: 4,328 kg (9,541 lb). Spacecraft: AS 2100. Agency: Cablevision. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Delayed from May 8 As of 2007 Mar 10 located at 61.68W drifting at 0.011W degrees per day.

2004 December 17 - 12:07 GMT - Launch Vehicle: Atlas V. Atlas V 521 AV-005 AMC-16 (GE-16) Mass: 4,200 kg (9,200 lb). Spacecraft: AS 2100. Agency: SES Americom. Perigee: 35,781 km (22,233 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.10 deg. Period: 1,436.10 min. AMC-16, like AMC-15, was a hybrid Ku/Ka-band satellite built by Lockheed Martin and based on the A2100 spacecraft platform. The spacecraft was to become operational in early 2005 from 85º West with a 15 year design life. The satellite carried 24 x 36 MHz/140 W Ku-band transponders and 12 x 125MHz/75 W spot beams. Coverage included the continental United States, Alaska, and Hawaii. Launch was delayed from December 6 and 16. As of 2007 Mar 9 located at 118.75W drifting at 0.002W degrees per day.

2005 March 11 - 21:42 GMT - Launch Vehicle: Atlas V. Atlas V 431 AV-004 Inmarsat 4-F1 Mass: 5,959 kg (13,137 lb). Spacecraft: Eurostar 3000. Agency: Inmarsat. Perigee: 35,562 km (22,097 mi). Apogee: 36,011 km (22,376 mi). Inclination: 3.00 deg. Period: 1,436.10 min. Heaviest single payload to geosynchronous transfer orbit to that date. Delayed from October 2004, February 27, March 10, 2005. The satellite was to provide L-band mobile communications and wideband data transmission for Inmarsat's global network. As of 2007 Mar 11 located at 63.82E drifting at 0.000E degrees per day.

2005 August 12 - 11:43 GMT - Launch Vehicle: Atlas V. Atlas V 401 AV-007 Mars Reconnaissance Orbiter Mass: 2,180 kg (4,800 lb). Spacecraft: Mars Reconnaissance Orbiter. Agency: NASA/JPL. Transferred from Atlas 3B. Delayed from August 10 and 11, 2005.

2006 January 19 - 19:00 GMT - Launch Vehicle: Atlas V. Atlas V 551 AV-010 / Star-48 New Horizons Mass: 478 kg (1,053 lb). Spacecraft: New Horizons. Agency: NASA/JPL. Last robotic mission to an unexplored planet in our solar system. New Horizons was due to receive a gravity boost from Jupiter in February 2007, then fly by Pluto in 2015. During launch toward Jupiter it reached a higher velocity than any manmade object, and was the first to be boosted directly to solar escape velocity. The trajectory had a perihelion of 0.98 AU, an inclination of 0.87 deg and an eccentricity of 1.03. After the Jupiter encounter it was to have a perihelion of 2.2 AU, an inclination of 2.3 deg and an eccentricity of 1.40. At encounter with Pluto on July 14, 2015, the spacecraft would be 1.1 AU above the ecliptic plane and 32.9 AU from the Sun, leaving the solar system toward the star Xi Sgr.

2006 April 20 - 20:27 GMT - Launch Vehicle: Atlas V. Atlas V 411 AV-008 Astra 1KR Mass: 4,332 kg (9,550 lb). Spacecraft: AS 2100. Agency: SES Astra. Perigee: 35,631 km (22,140 mi). Apogee: 35,696 km (22,180 mi). Inclination: 0.10 deg. Period: 1,429.80 min. The first Centaur upper stage burn placed the stack into a 167 km x 22442 km x 24.8 deg transfer orbit. After a second burn the Centaur released the satellite into a 6470 km x 36240 km x 23.8 deg orbit, from which it would use its own engine to achieve final geosynchronous orbit. As of 2007 Mar 10 located at 19.18E drifting at 0.022W degrees per day.

2007 March 9 - 03:10 GMT - Launch Vehicle: Atlas V. Atlas V 401 AV-013 STPSat-1 Mass: 170 kg (370 lb). Agency: USAFRL. Perigee: 558 km (346 mi). Apogee: 560 km (340 mi). Inclination: 35.40 deg. Period: 95.80 min. STPSat carried experiments to study the Earth's atmosphere, ionosphere and radiation environment. It also released the two MEPSI picosatellites.

2007 June 15 - 15:11 GMT - Launch Vehicle: Atlas V. Atlas V 401 AV-009 USA 194 Spacecraft: NOSS-3. Agency: NRO. Perigee: 776 km (482 mi). Apogee: 1,246 km (774 mi). Inclination: 63.00 deg. Classified National Reconnaissance Office mission. There appeared to be problem in the second burn of the Centaur upper stage. Amateur observors believed that two satellites were to be have been deployed in 1150 km altitude, 63 deg inclination, but that only a 776 km x 1246 km was achieved. However it was believed that the payloads could reach the final intended orbits using on-board propulsion

2007 October 11 - 00:22 GMT - Launch Vehicle: Atlas V. Atlas V 421 AV-011 USA 195 Spacecraft: HS 702. Perigee: 32,586 km (20,247 mi). Apogee: 39,016 km (24,243 mi). Inclination: 0.20 deg. Period: 1,436.80 min. First USAF Wideband Global Satcom satellite, designed to replace the DSCS series, was placed by the Atlas booster in an initial 477 km x 66,847 km x 20.1 deg geosynchronous transfer orbit. The satellite carried X-band and Ka-band communications payloads.