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Vandenberg 576E

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First Launch: 1962-08-01. Last Launch: 2011-03-04. Number: 14 . Longitude: -120.62 deg. Latitude: 34.74 deg.

• Research and development test - . Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi). The first Atlas F missile (15F) was launched from Vandenberg on an operational test flight. First successful Atlas F flight at operational site, SMS 576E (15F).

• OT TALL TREE 4 operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 10 km (6 mi).

• Demonstration and shakedown operations launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,400 km (800 mi).

• ST - . Nation: USA. Agency: USAF SAC. Apogee: 1,400 km (800 mi).

• USA 101 - . Payload: STEP-0 / STEP M0. Mass: 502 kg (1,106 lb). Nation: USA. Agency: USAF. Program: STEP. Class: Military. Type: Strategic defense satellite. Spacecraft: TAOS. USAF Sat Cat: 23030 . COSPAR: 1994-017A. Apogee: 561 km (348 mi). Perigee: 555 km (344 mi). Inclination: 105.00 deg. Period: 95.80 min. Space Test Experiment Program; 10 satellite subsystem experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• USA 102 - . Payload: DarpaSat. Mass: 203 kg (447 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Navigation technology satellite. Spacecraft: DARPASAT. USAF Sat Cat: 23031 . COSPAR: 1994-017B. Apogee: 556 km (345 mi). Perigee: 532 km (330 mi). Inclination: 105.00 deg. Period: 95.50 min. GPS receiver and data processor technology tests. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

• GFO - . Nation: USA. Agency: USN. Manufacturer: Ball. Class: Earth. Type: Civilian Radarsat. Spacecraft Bus: BCP-600. Spacecraft: GFO. USAF Sat Cat: 25157 . COSPAR: 1998-007A. Apogee: 788 km (489 mi). Perigee: 786 km (488 mi). Inclination: 108.10 deg. Period: 100.60 min. Altimeter..

• Orbcomm G2 - . Payload: Orbcomm s/n FM4. Mass: 43 kg (94 lb). Nation: USA. Agency: Orbcomm. Manufacturer: Germantown. Program: Orbcomm. Class: Communications. Type: Civilian communications satellite. Spacecraft: Microstar. USAF Sat Cat: 25159 . COSPAR: 1998-007C. Apogee: 871 km (541 mi). Perigee: 783 km (486 mi). Inclination: 107.99 deg. Period: 101.45 min. Plane G. Ascending node 298.1 degrees..

• Celestis-02 - . Payload: Celestis-02/Orion 38. Nation: USA. Agency: OSC. Manufacturer: Germantown. Program: Celestis. Class: Burial . Type: Burial satellite. Spacecraft Bus: Pegasus-3. Spacecraft: Celestis. USAF Sat Cat: 25160 . COSPAR: 1998-007D. Apogee: 876 km (544 mi). Perigee: 780 km (480 mi). Inclination: 108.00 deg. Period: 101.50 min.

• Orbcomm G1 - . Payload: Orbcomm s/n FM3. Mass: 43 kg (94 lb). Nation: USA. Agency: Orbcomm. Manufacturer: Germantown. Program: Orbcomm. Class: Communications. Type: Civilian communications satellite. Spacecraft: Microstar. USAF Sat Cat: 25158 . COSPAR: 1998-007B. Apogee: 874 km (543 mi). Perigee: 781 km (485 mi). Inclination: 107.99 deg. Period: 101.46 min. Plane G. Ascending node 297.9 degrees..

• STEX - . Payload: STEX. Nation: USA. Agency: NRO. Manufacturer: NRL. Class: Technology. Type: Ion engine technology satellite. Spacecraft: STEX. USAF Sat Cat: 25489 . COSPAR: 1998-055A. Apogee: 759 km (472 mi). Perigee: 744 km (462 mi). Inclination: 84.99 deg. Period: 99.77 min.

  Tested TAL-D55 plasma engine and was to be part of the NRO's ATex tether experiment. The ATeX lower end mass was meant to remain attached to the STEX parent spacecraft, but with only 21 m of tether deployed, it appeared the tether was so far off vertical that automatic safety systems jettisoned the base to protect the remainder of the STEX satellite. Thus, the upper and lower ATeX end masses were in orbit as one object connected by a 21 m tether, and designated USA 141 (1998-055C). The main STEX satellite was in orbit as a separate object, 1998-055A.

• USA 141 - . Payload: ATEX. Mass: 54 kg (119 lb). Nation: USA. Agency: NRL, NRO. Class: Technology. Type: Tether technology satellite. Spacecraft: TiPS. USAF Sat Cat: 25615 . COSPAR: 1998-055C. Apogee: 766 km (476 mi). Perigee: 750 km (466 mi). Inclination: 84.99 deg. Period: 99.90 min.

  NRO's ATeX (Advanced Tether eXperiment) reportedly failed on January 16. The ATeX lower end mass was meant to remain attached to the STEX parent spacecraft, but with only 21 m of tether deployed, it appeared the tether was so far off vertical that automatic safety systems jettisoned the base to protect the remainder of the STEX satellite. Thus, the upper and lower ATeX end masses were in orbit as one object connected by a 21 m tether, and designated USA 141 (1998-055C). The main STEX satellite was in orbit as a separate object, 1998-055A.

• Kompsat - . Payload: Arirang. Mass: 470 kg (1,030 lb). Nation: Korea South. Agency: KARI. Manufacturer: KAIST. Class: Earth. Type: Sea satellite. Spacecraft Bus: T200. Spacecraft: KOMPSAT. USAF Sat Cat: 26032 . COSPAR: 1999-070A. Apogee: 677 km (420 mi). Perigee: 670 km (410 mi). Inclination: 97.80 deg. Period: 98.20 min.

  Korean Multipurpose Satellite; carried an ocean color sensor developed by TRW and particle detectors. KOMPSAT was built by the Korean Aerospace Research Institute (KARI) based on a test model built by TRW; it used the TRW STEP Lightsat bus and had a mass of around 500 kg, with 73 kg of hydrazine fuel.

• ACRIMSAT - . Mass: 115 kg (253 lb). Nation: USA. Agency: JPL, NASA. Manufacturer: Germantown. Class: Earth. Type: Seismology satellite. Spacecraft Bus: GemStar. Spacecraft: ACRIMSAT . USAF Sat Cat: 26033 . COSPAR: 1999-070B. Apogee: 711 km (441 mi). Perigee: 671 km (416 mi). Inclination: 97.80 deg. Period: 98.60 min.

  Measured the integrated solar energy output from 0.2 to 2 microns. Carried instrument deleted from Terra spacecraft, studying the total solar output. Failed on 2013 December 14 due to battery problems, months after a review recommended its continued operation. The ACRIM series of experiments, critical data for climate change studies, flew on Solar Max (1980), Spacelab-1 (1983), UARS (1991), and ACRIMSAT. The similar TIM instrument on the SORCE satellite (2003) continued operating, but it was unclear if it would continue in operation until a replacement instrument would be launched on the JPSS satellite in 2017 at the earliest.

• Celestis-03 - . Nation: USA. Agency: OSC. Program: Celestis. Class: Burial . Type: Burial satellite. Spacecraft Bus: Pegasus-3. Spacecraft: Celestis. Decay Date: 1971-03-01 . USAF Sat Cat: 26034 . COSPAR: 1999-070C. Apogee: 571 km (354 mi). Perigee: 550 km (340 mi). Inclination: 98.28 deg. Period: 95.86 min. Burial satellite containing cremated human remains..

• MTI - . Mass: 587 kg (1,294 lb). Nation: USA. Agency: Los Alamos. Manufacturer: Sandia. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: BCP-600. Spacecraft: MTI. USAF Sat Cat: 26102 . COSPAR: 2000-014A. Apogee: 609 km (378 mi). Perigee: 574 km (357 mi). Inclination: 97.40 deg. Period: 96.42 min. Military Technology. Sandia Multispectral Thermal Imager (MTI), aka USAF Space Test Program mission P97-3. The satellite was equipped with a hyperspectral imager for military target recognition / treaty monitoring applications..

• Orbview-4 - . Mass: 368 kg (811 lb). Nation: USA. Agency: Orbimage. Manufacturer: OSC. Program: Orbview. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft Bus: LEOStar. Spacecraft: Orbview. COSPAR: F010921A.

  Launch delayed from June 27, July 18/22, August 12/21 and September1. The Orbital Sciences Taurus 2110 failed to remain in orbit. A problem a few seconds after first stage separation caused the T6 rocket to go off course; the rocket recovered and the remainder of the stages fired, but final cutoff velocity was too low to reach a sustainable orbit. The Castor 120 zero stage was on course but the Orion 50S first stage motor went off course. The satellites separated from the final stage as planned but burned up in the earth's atmosphere northeast of Madagascar before completing the first orbit. The final orbit was about 75-80 km x 425-430 km x 97 deg. The primary payload was the OrbView-4 imaging satellite. OrbView-4, built by Orbital, was a 368 kg box-shaped spacecraft carrying a 1-m resolution panchromatic camera and an 8-m resolution 200-channel hyperspectral imager with a 0.45-meter aperture. It was to be used by the US Air Force.

• SBD - . Mass: 368 kg (811 lb). Nation: USA. Agency: Orbimage. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: Microstar. Spacecraft: SBD. COSPAR: F010921C.

  SBD, the Orbital Sciences' Special Bus Design. The 73 kg satellite was a test version of an enlarged Microstar bus. It would have remained attached to the third stage, together with two Celestis burial canisters containing cremated human remains, and an experimental third stage avionics box.

• Celestis-4 - . Mass: 368 kg (811 lb). Nation: USA. Agency: Orbimage. Manufacturer: OSC. Program: Celestis. Class: Burial . Type: Burial satellite. Spacecraft Bus: Pegasus-3. Spacecraft: Celestis. COSPAR: F010921D. Celestis-4 consisted of two Celestis burial canisters containing cremated human remains. After the launch vehicle failure Celestis guaranteed a relaunch of back-up remains..

• QuikTOMS - . Mass: 368 kg (811 lb). Nation: USA. Agency: Orbimage. Manufacturer: OSC. Class: Earth. Type: Ionosphere satellite. Spacecraft: Microstar. COSPAR: F010921B.

  The QuikTOMS satellite was a NASA-GSFC project carrying the TOMS-5 ozone mapper. QuikTOMS used a 168 kg double Microstar bus and was to have replaced TOMS instruments on a delayed Russian weather satellite and the failed ADEOS. The loss of QuikTOMS put a hole in NASA's attempts to monitor the ozone layer.

• BV-6 Boost Vehicle Test Flight - . Nation: USA. Agency: USAF AFSPC. Manufacturer: OSC. Apogee: 1,810 km (1,120 mi).

  Successful first launch of the prototype of the three-stage version of the Taurus launch vehicle being developed by Orbital Sciences for Boeing for use in the Ground-based Midcourse Defense (GMD) system. The vehicle launched the dummy payload on a trajectory over the Pacific Ocean, reaching an altitude of 2100 km and traveling 6500 km down range.

• ROCSAT 2 - . Payload: LeoStar 500XO. Mass: 760 kg (1,670 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: EADS Astrium. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft Bus: T200. Spacecraft: ROCSAT. USAF Sat Cat: 28254 . COSPAR: 2004-018A. Apogee: 891 km (553 mi). Perigee: 887 km (551 mi). Inclination: 99.10 deg. Period: 102.80 min. Delayed from October, November 25, 2003; January 17, February 26, April 9 and 22, May 17, 2004..

• OCO - . Mass: 407 kg (897 lb). Nation: USA. Agency: McLean. Class: Earth. Type: Climate satellite. Spacecraft: Leostar. Orbiting Carbon Observatory. A single instrument with a three classical grating spectrometers allowed carbon dioxide levels in the atmosphere to be monitored..

• Glory - . Mass: 545 kg (1,201 lb). Nation: USA. Class: Earth. Type: Weather satellite. Spacecraft: Leostar-1. Second failure of this vehicle in a row due to fairing not separating. NASA satellite that would have used an aerosol polarimetry sensor (APS) to provide a global map of aerosol particulates (soot and sulphates) to help calibrate climate change models..

• E1P - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Cubesat. Explorer 1 Prime, Montana State University Cubesat. Was to have duplicated Explorer 1's discovery of the van Allen radiation belts in 1958 using a geiger counter..

• Hermes - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft Bus: Cubesat. Spacecraft: Hermes Cubesat. 1U cubesat for University of Colorado at Boulder..

• KySat-1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. University of Kentucky Cubesat..

• SkySat 13 - . Payload: SkySat C11. Nation: USA. USAF Sat Cat: 42987 . COSPAR: 2017-068A. Apogee: 507 km (315 mi). Perigee: 494 km (306 mi). Inclination: 97.42 deg. Period: 94.63 min. See SkySat 13 (SkySat C11). ..

• SkySat 12 - . Payload: SkySat C10. Nation: USA. USAF Sat Cat: 42988 . COSPAR: 2017-068B. Apogee: 505 km (313 mi). Perigee: 498 km (309 mi). Inclination: 97.42 deg. Period: 94.64 min. See SkySat 12 (SkySat C10). ..

• SkySat 11 - . Payload: SkySat C9. Nation: USA. USAF Sat Cat: 42989 . COSPAR: 2017-068C. Apogee: 502 km (311 mi). Perigee: 500 km (310 mi). Inclination: 97.42 deg. Period: 94.63 min. See SkySat 11 (SkySat C9). ..

• SkySat 10 - . Payload: SkySat C8. Nation: USA. USAF Sat Cat: 42990 . COSPAR: 2017-068D. Apogee: 505 km (313 mi). Perigee: 497 km (308 mi). Inclination: 97.42 deg. Period: 94.64 min. See SkySat 10 (SkySat C8). ..

• SkySat 9 - . Payload: SkySat C7. Nation: USA. USAF Sat Cat: 42991 . COSPAR: 2017-068E. Apogee: 506 km (314 mi). Perigee: 496 km (308 mi). Inclination: 97.42 deg. Period: 94.63 min. See SkySat 9 (SkySat C7). ..

• SkySat 8 - . Payload: SkySat C6. Nation: USA. USAF Sat Cat: 42992 . COSPAR: 2017-068F. Apogee: 510 km (310 mi). Perigee: 492 km (305 mi). Inclination: 97.42 deg. Period: 94.64 min. See SkySat 8 (SkySat C6). ..

• Flock 3m-1 - . Payload: Dove 0F06; FLOCK 3M 1. Nation: USA. Spacecraft: Cubesat. USAF Sat Cat: 42995 . COSPAR: 2017-068J. Apogee: 518 km (321 mi). Perigee: 495 km (307 mi). Inclination: 97.37 deg. Period: 94.75 min. See Flock-3m 1 (Dove 0F06). ..

• Flock 3m-3 (POD-1) - . Payload: Dove 0F13; FLOCK 3M 3. Nation: USA. Spacecraft: Cubesat. USAF Sat Cat: 42996 . COSPAR: 2017-068K. Apogee: 518 km (321 mi). Perigee: 494 km (306 mi). Inclination: 97.36 deg. Period: 94.74 min. See Flock-3m 3 (Dove 0F13). ..

• Flock 3m-4 - . Payload: Dove 0F4C; FLOCK 3M 4. Nation: USA. Spacecraft: Cubesat. USAF Sat Cat: 42997 . COSPAR: 2017-068L. Apogee: 519 km (322 mi). Perigee: 495 km (307 mi). Inclination: 97.39 deg. Period: 94.76 min. See Flock-3m 4 (Dove 0F4C). ..

• Flock 3m-2 - . Payload: Dove 0F02; FLOCK 3M 2. Nation: USA. Spacecraft: Cubesat. USAF Sat Cat: 42998 . COSPAR: 2017-068M. Apogee: 518 km (321 mi). Perigee: 496 km (308 mi). Inclination: 97.38 deg. Period: 94.76 min. See Flock-3m 2 (Dove 0F02). ..