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OSC
American manufacturer of rockets, spacecraft, and rocket engines. Orbital Sciences Corporation, USA.

AKA: Orbital Sciences Corp.. Location: Fairfax, Virginia.



Country: USA. Spacecraft: Orbcomm, APEX, X-38, STEP, CPAC, Orbview-2, Star bus, Early Bird, Celestis, Teledesic, MightySat 1, ACRIMSAT, Orbview, SBD, Galex, Mitex, Dawn, CEV Orbital. Launch Vehicles: Pegasus, Pegasus/HAPS, Storm, Taurus, ARPA Taurus, Pegasus XL, Pegasus H, X-34A, Castor 4B, Storm-2, Pegasus XL/HAPS, Taurus 2210, ait, SR19/SR19, Taurus 2110, Minotaur, Minotaur 1, Taurus 1110, Hyper X, GBI, Coyote, Taurus 3210, Taurus II, Taurus 3110. Projects: Galaxy, Intelsat. Launch Sites: Gando. Stages: X-34, Orion 50SXLG. Agency: BSAT.

1990 January 30 - . 21:22 GMT - . Launch Site: Wallops Island. LV Family: Talos. Launch Vehicle: HPB.
  • TM2-1 test - . Nation: USA. Agency: OSC. Apogee: 422 km (262 mi).

1990 December 18 - . 03:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC20. Launch Vehicle: Starbird.
  • LACE UVPI Target Target mission - . Nation: USA. Agency: OSC. Apogee: 100 km (60 mi).

1991 February 6 - . 07:29 GMT - . Launch Site: Wallops Island. LV Family: Talos. Launch Vehicle: Space Data LCLV.
  • Target / active plasma mission - . Nation: USA. Agency: OSC. Apogee: 510 km (310 mi).

1991 April 12 - . Launch Site: Wallops Island. LV Family: Talos. Launch Vehicle: HPB.
  • Target / decoys mission - . Nation: USA. Agency: OSC. Apogee: 400 km (240 mi).

1991 June 18 - . 11:34 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC20. LV Family: Castor 4A. Launch Vehicle: Prospector sounding rocket. FAILURE: Failure..
  • Microgravity mission - . Nation: USA. Agency: OSC. Apogee: 1.00 km (0.60 mi). Material and biological experiments..

1992 March 29 - . 08:07 GMT - . Launch Site: Poker Flat. LV Family: Talos. Launch Vehicle: HPB.
  • Infrared background mission - . Nation: USA. Agency: OSC. Apogee: 400 km (240 mi).

1992 April 15 - . 09:09 GMT - . Launch Site: Wallops Island. LV Family: Talos. Launch Vehicle: HPB.
  • Target / decoys mission - . Nation: USA. Agency: OSC. Apogee: 450 km (270 mi).

1992 October 16 - . Launch Site: Wake Island. Launch Vehicle: Castor 4A. FAILURE: Failure.
  • Re-entry Vehicle test - . Nation: USA. Agency: OSC. Apogee: 500 km (310 mi).

1993 January 28 - . Launch Site: Wake Island. LV Family: Talos. Launch Vehicle: HPB.
  • Re-entry Vehicle test - . Nation: USA. Agency: OSC. Apogee: 400 km (240 mi).

1993 February 11 - . Launch Site: Wake Island. LV Family: Talos. Launch Vehicle: HPB. FAILURE: Failure.
  • Re-entry Vehicle test - . Nation: USA. Agency: OSC. Apogee: 2.00 km (1.20 mi).

1993 June 22 - . Launch Site: White Sands. Launch Complex: White Sands LC36. LV Family: Minuteman. Launch Vehicle: Aries.
  • Technology mission - . Nation: USA. Agency: BMDO, OSC. Apogee: 300 km (180 mi).

1994 June 27 - . 21:15 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Vandenberg.. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL. FAILURE: Destroyed on launch . Failed Stage: 1.
  • STEP 1 - . Payload: STEP M1 / P90-1. Mass: 180 kg (390 lb). Nation: USA. Agency: OSC. Program: STEP. Class: Military. Type: Strategic defense satellite. Spacecraft: Eagle. Apogee: 38 km (23 mi). Destroyed on launch Air dropped in Point Arguello WADZ..

1996 July 15 - . 18:21 GMT - . Launch Site: Wake Island. LV Family: Castor 4A. Launch Vehicle: Castor 4B.
  • Re-entry Vehicle test - . Nation: USA. Agency: OSC. Apogee: 317 km (196 mi).

1997 February 12 - . 21:00 GMT - . Launch Site: Wallops Island. LV Family: Talos. Launch Vehicle: Space Data LCLV.
  • MDT IV Target mission - . Nation: USA. Agency: OSC. Apogee: 400 km (240 mi).

1997 February 22 - . Launch Site: Wake Island. LV Family: Castor 4A. Launch Vehicle: Castor 4B.
  • Re-entry Vehicle test - . Nation: USA. Agency: OSC. Apogee: 300 km (180 mi).

1997 February 23 - . 10:06 GMT - . Launch Site: Wallops Island. LV Family: Talos. Launch Vehicle: Space Data LCLV.
  • MDT III Target mission - . Nation: USA. Agency: OSC. Apogee: 400 km (240 mi).

1997 March 1 - . Launch Site: Wake Island. LV Family: Castor 4A. Launch Vehicle: Castor 4B.
  • Re-entry Vehicle test - . Nation: USA. Agency: OSC. Apogee: 300 km (180 mi).

1997 April 21 - . 11:59 GMT - . Launch Site: Gando. Launch Complex: Gran Canaria DZ. Launch Pad: 27.0 N x 15.3 W. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL.
  • Celestis - . Payload: CPAC. Nation: USA. Agency: OSC. Manufacturer: Germantown. Program: Celestis. Class: Burial . Type: Burial satellite. Spacecraft: CPAC. Decay Date: 2002-05-21 . USAF Sat Cat: 24780 . COSPAR: 1997-018B. Apogee: 581 km (361 mi). Perigee: 553 km (343 mi). Inclination: 151.0000 deg. Period: 96.00 min. Air dropped in Gran Canaria DZ..

1998 February 10 - . 13:20 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Taurus. Launch Vehicle: Taurus 2210.
  • 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: 108.0000 deg. Period: 101.50 min.

1998 September 24 - . 12:50 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC32. LV Family: Minuteman. Launch Vehicle: Storm-2.
  • MTTV/MTD-3 Target mission - . Nation: USA. Agency: OSC, US Army. Apogee: 180 km (110 mi).

1998 November 6 - . 01:32 GMT - . Launch Site: Kodiak. LV Family: Minuteman. Launch Vehicle: Juno test vehicle.
  • ait-1 test - . Nation: USA. Agency: OSC, USAF. Apogee: 715 km (444 mi).

1999 September 6 - . Launch Site: Wake Island. LV Family: Minuteman. Launch Vehicle: SR19/SR19.
  • TCMP-3A re-entry vehicle test flight - . Nation: USA. Agency: OSC. Apogee: 300 km (180 mi).

1999 December 21 - . 07:13 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Taurus. Launch Vehicle: Taurus 2110.
  • 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: 98.2800 deg. Period: 95.86 min. Burial satellite containing cremated human remains..

2001 June 2 - . 20:43 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Edwards.. Launch Platform: NB-52 008. LV Family: Pegasus. Launch Vehicle: Hyper X. FAILURE: Failure. Failed Stage: 1.
  • X-43A test - . Nation: USA. Agency: OSC. Apogee: 7.00 km (4.30 mi).

    Hypersonic scramjet vehicle test. The X-43A/Pegasus booster combination was air-launched at 7600 m altitude. However the booster disintegrated at Max-Q. The redesign of the launch profile and modifications to the booster would take NASA almost three years. Air dropped in Point Arguello WADZ.


2001 September 21 - . 18:49 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Taurus. Launch Vehicle: Taurus 2110. FAILURE: A problem a few seconds after first stage separation caused the rocket to go off course; it recovered and the remainder of the stages fired, but final cutoff velocity was too low to reach a sustainable orbit.. Failed Stage: G.
  • 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.


2003 January 25 - . 20:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Mayport DZ. Launch Pad: 29.0 N x 78.5 W. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL.
  • SORCE - . Payload: Solstice/SAVE. Mass: 268 kg (590 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Class: Astronomy. Type: Solar satellite. Spacecraft Bus: LEOStar-2. Spacecraft: SORCE. USAF Sat Cat: 27651 . COSPAR: 2003-004A. Apogee: 657 km (408 mi). Perigee: 617 km (384 mi). Inclination: 39.9946 deg. Period: 97.31 min. Solar irradiance monitoring, climatology mission. Launch delayed from December 1 and 13, 2002. Air dropped in Mayport DZ..

2003 February 6 - . 21:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Pegasus. Launch Vehicle: GBI.
  • 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.


2003 April 9 - . 22:52 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G.
  • Galaxy 12 - . Mass: 1,792 kg (3,950 lb). Nation: USA. Agency: PanAmSat. Manufacturer: OSC. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 27715 . COSPAR: 2003-013B. Apogee: 35,791 km (22,239 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. As of 2007 Mar 11 located at 125.09W drifting at 0.001W degrees per day..

2003 April 28 - . 12:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Mayport DZ. Launch Pad: 29.0 N x 78.5 W. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL.
  • Galex - . Mass: 280 kg (610 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Class: Astronomy. Type: Ultraviolet astronomy satellite. Spacecraft Bus: LEOStar-2. Spacecraft: Galex. Duration: 3,710.00 days. USAF Sat Cat: 27783 . COSPAR: 2003-017A. Apogee: 699 km (434 mi). Perigee: 694 km (431 mi). Inclination: 29.0000 deg. Period: 98.70 min.

    Ultraviolet space telescope. Much delayed launch (from January 19, May 19, July 16, 21 and 30, August 14 and October 17, 2002; January 27, March 25 and 30, April 15 and 26 2003). It was finally switched off on 28 June 2013, following an extra tenth year of observing funded by Caltech. Air dropped in Mayport DZ.


2003 June 11 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G.
  • BSAT-2c - . Payload: Star 1. Mass: 1,298 kg (2,861 lb). Nation: Japan. Agency: BSAT. Manufacturer: OSC. Program: BSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 27831 . COSPAR: 2003-028B. Apogee: 35,802 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. As of 2007 Mar 9 located at 155.98E drifting at 0.008W degrees per day..

2003 August 16 - . 18:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF23. Launch Pad: LF23?. LV Family: Pegasus. Launch Vehicle: GBI.
  • BV-6 Missile Defense Interceptor Booster test. - . Nation: USA. Agency: USAF AFSPC. Manufacturer: OSC. Apogee: 1,874 km (1,164 mi).

    The Orbital Sciences Corperation booster was successfully tested with a mock EKV after a one-day launch delay. Shock and vibration environments were measured and compared to previous test levels. Preliminary analyses suggest that the new booster produced lower than expected vibrations at the EKV.


2004 January 27 - . 02:23 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein Meck. LV Family: Pegasus. Launch Vehicle: GBI.
  • IFT-13B [EKV Mock-up] test - . Nation: USA. Agency: OSC. Manufacturer: OSC. Apogee: 272 km (169 mi).

    Launch delayed from October 2003. This system-level test of the Orbital Sciencesí boost vehicle launched the rocket carrying a simulated EKV from Kwajalein Atoll against a simulated target coming from Vandenberg AFB, Calif. IFT-13B was not an intercept attempt. Included in this test was the latest version of the GMD programís fire control software, which was being built by Northrop Grumman and which performed as expected in this test.


2004 March 27 - . 21:59 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Edwards.. Launch Platform: NB-52 008. LV Family: Pegasus. Launch Vehicle: Hyper X.
  • X-43A-2 (Hyper X) - . Nation: USA. Agency: OSC. Apogee: 29 km (18 mi).

    The second X-43 launch incorporated modifications to the first flight vehicle, including an upgraded control system, redesigned autopilot, off-loaded rocket motor, and improved analytical models. The second flight was launched at 12,200 m instead of the 7600 m altitude of the failed first launch to reduce transonic aerodynamic loads and improve structural and control system margins. An offloaded Orion 50S solid rocket motor reduced maximum dynamic pressure during the flight. Air dropped in Point Arguello WADZ.


2004 July 22 - . Launch Site: Fort Greely. Launch Complex: Fort Greely. LV Family: Pegasus. Launch Vehicle: GBI.
  • First GBI Deployment at Fort Greely - . Nation: USA. Agency: MDA. Manufacturer: OSC. The first Ground-Based Interceptor was lowered into a silo at Fort Greely, Alaska. Five additional interceptors were to be deployed in Alaska by the end of September..

2004 November 11 - . Launch Site: Fort Greely. Launch Complex: Fort Greely. LV Family: Pegasus. Launch Vehicle: GBI.
  • GBI Deployment at Fort Greely - . Nation: USA. Agency: MDA. Manufacturer: OSC. The sixth ballistic missile interceptor was installed in its silo at Fort Greely, Alaska, two months behind the mid-year schedule. An additional eight to ten were to be emplaced in 2005, for a total of 14-16..

2004 November 16 - . 22:35 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Edwards.. Launch Platform: NB-52 008. LV Family: Pegasus. Launch Vehicle: Hyper X.
  • X-43A test - . Nation: USA. Agency: OSC. Apogee: 33 km (20 mi).

    Delayed from September, November 9 and 15. Final test of NASA's X-43A-3 Hyper X hypersonic scramjet demonstrated air-frame integrated scramjet performance at speeds approaching Mach 10. Changes to the launch vehicle compared to Flight 2 included high-temperature thermal protection system tiles on the wing and fin leading edge, elimination of all ballast, a full propellant load on the ATK Orion 50S booster, lightweight aluminum structures, and updated control laws and aerodynamics. Air dropped in Point Arguello WADZ.


2004 December 10 - . Launch Site: Vandenberg. Launch Complex: Vandenberg. LV Family: Pegasus. Launch Vehicle: GBI.
  • GBI Deployment at Vandenberg - . Nation: USA. Agency: MDA. Manufacturer: OSC. The first of two operational anti-ballistic missiles to be deployed during 2005 at Vandenberg AFB was lowered into its underground silo. This marked the first installation in the continental United States..

2004 December 15 - . 06:01 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein. LV Family: Pegasus. Launch Vehicle: GBI. FAILURE: Launch abort; anti-ballistic missile never left silo..
  • IFT-13C Launch Abort - . Mass: 55 kg (121 lb). Nation: USA. Agency: MDA. Manufacturer: OSC.

    Launch abort - booster shut down in silo. Missile target, launched from Alaska, impacted in Pacific Ocean. Delayed from January, August, November, December 9 and 12. The failed attempt was later said to be due to a very minor software glitch which created a gap in the flow of electronic messages between the flight computer and the interceptor's thrust vector controller. Five flight tests of the system were scheduled for 2005, including at least two attempted intercepts. The IFT-13c test was expected to be repeated as early as mid-February. IFT-14 was planned for March or April.


2005 February 17 - . Launch Site: Kwajalein. Launch Complex: Kwajalein. LV Family: Pegasus. Launch Vehicle: GBI. FAILURE: Launch abort - booster shut down in silo..
  • IFT-14 launch attempt. - . Mass: 55 kg (121 lb). Nation: USA. Agency: MDA. Manufacturer: OSC.

    Delayed from October 2004. Missile Defense Technology / EKV Prototype planned intercept attempt. The interceptor failed to leave the silo. As in IFT-13C, Orbital Sciencesí booster, carrying Raytheonís production kill vehicle, was supposed to fly from Kwajalein and hit a target coming out of Kodiak, Alaska. The system shut itself down just a few seconds before launch. Arms that held the interceptor in the silo did not fully retract, and the launch software aborted the mission. MDA failure analysis resulted in a redesign of the launch mechanism and improved quality control.


2005 April 8 - . 17:30 GMT - . Launch Pad: Pacific Ocean, 22.0 N x 175.0 W. Launch Platform: C-17. LV Family: Castor 4A. Launch Vehicle: MRT.
  • RRF - . Nation: USA. Agency: OSC. Apogee: 500 km (310 mi).

2005 April 15 - . 17:26 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Vandenberg.. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL/HAPS.
  • DART - . Mass: 360 kg (790 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Class: Technology. Type: Rendezvous technology satellite. Spacecraft: DART. Decay Date: 2016-05-07 . USAF Sat Cat: 28642 . COSPAR: 2005-014A. Apogee: 747 km (464 mi). Perigee: 395 km (245 mi). Inclination: 96.6000 deg. Period: 96.10 min.

    Delayed from April 15; October 18, 19, 26, 28; Nov. 4, 9 and 11; 2004, and March 2, 2005. Autonomous Rendezvous Technology mission, planned to guide itself to within a few metres of a US satellite. On April 16, DART closed within 100 m of the MUBLCOM satellite, then evidently began a series of out-of-control maneuvers resulting in an in-space collission and MUBLCOM being bumped into a 3 to 5 km higher orbit. Remarkably both satellites continued to function. DART then detected that it was running unexpectedly low on nitrogen cold gas used for orientation. Its autonomous software aborted further rendezvous operations and the DART was deorbited shortly thereafter. Air dropped in Point Arguello WADZ.


2005 August 13 - . 23:28 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz-FG.
  • Galaxy 14 - . Mass: 2,087 kg (4,601 lb). Nation: USA. Agency: PanAmSat. Manufacturer: OSC. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 28790 . COSPAR: 2005-030A. Apogee: 35,790 km (22,230 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Payload swapped from Ariane 5. Launch delayed from December 2004; February 25, March 16 and 25, April 25, June 17, July 10 and 28, August 1, 6 and 12, 2005. As of 2007 Mar 9 located at 125.05W drifting at 0.008W degrees per day..

2005 October 13 - . 22:32 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5GS.
  • Galaxy 15 - . Mass: 2,033 kg (4,481 lb). Nation: USA. Agency: PanAmSat. Manufacturer: OSC. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 28884 . COSPAR: 2005-041A. Apogee: 35,796 km (22,242 mi). Perigee: 35,776 km (22,230 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Slated to provide satellite television services to the United States market. As of 2007 Mar 10 located at 132.99W drifting at 0.009W degrees per day..

2005 December 14 - . 03:04 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein Meck. LV Family: Pegasus. Launch Vehicle: GBI.
  • FT-1 EKV Prototype ABM test - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,800 km (1,100 mi). Launch delayed from late 2004. Successful test of hit-to-kill anti-ballistic missile homer, although no target was intercepted..

2006 April 15 - . 01:40 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC8. LV Family: Minuteman. Launch Vehicle: Minotaur 1.
  • Formosat 3A FM6 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft: MicroStar. USAF Sat Cat: 29047 . COSPAR: 2006-011A. Apogee: 538 km (334 mi). Perigee: 496 km (308 mi). Inclination: 72.0000 deg. Period: 95.00 min.

    FORMOSAT-3 consisted of six small 62 kg Orbcomm-type satellites with GPS receivers which were to measure atmospheric conditions by studying the effect of the atmosphere on GPS satellite signals passing through it. The satellites, also known as COSMIC (Constellation Observing System for Meteorology, Ionosphere and Climate), each raised their orbits over several months, all but one reaching operational orbits of around 770 x 840 km by September 2007.

  • Formosat 3B FM1 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft: MicroStar. USAF Sat Cat: 29048 . COSPAR: 2006-011B. Apogee: 541 km (336 mi). Perigee: 500 km (310 mi). Inclination: 72.0000 deg. Period: 95.00 min.
  • Formosat 3C FM5 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft: MicroStar. USAF Sat Cat: 29049 . COSPAR: 2006-011C. Apogee: 681 km (423 mi). Perigee: 567 km (352 mi). Inclination: 72.0000 deg. Period: 97.20 min.
  • Formosat 3D FM3 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft: MicroStar. USAF Sat Cat: 29050 . COSPAR: 2006-011D. Apogee: 538 km (334 mi). Perigee: 496 km (308 mi). Inclination: 72.0000 deg. Period: 95.00 min. Became stuck in intermediate 675 x 750 km due to solar panel failure..
  • Formosat 3E FM4 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft: MicroStar. USAF Sat Cat: 29051 . COSPAR: 2006-011E. Apogee: 538 km (334 mi). Perigee: 496 km (308 mi). Inclination: 72.0000 deg. Period: 95.00 min.
  • Formosat 3F FM2 - . Mass: 70 kg (154 lb). Nation: Taiwan. Agency: NSPO. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft: MicroStar. USAF Sat Cat: 29052 . COSPAR: 2006-011F. Apogee: 542 km (336 mi). Perigee: 497 km (308 mi). Inclination: 72.0000 deg. Period: 95.00 min.

2006 June 21 - . 22:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.
  • USA 187 - . Payload: MiTEx-A. Mass: 225 kg (496 lb). Nation: USA. Agency: DARPA. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: GEOStar-1. Spacecraft: Mitex. USAF Sat Cat: 29240 . COSPAR: 2006-024A. Apogee: 36,222 km (22,507 mi). Perigee: 184 km (114 mi). Inclination: 25.2500 deg. Period: 639.26 min.

    The Microsatellite Technology Experiment was a classified mission, believed to be a test of prototype inspect-and-disable satellites that would control the constellation of geostationary satellites on which the world depends for television reception and communications. Each microsatellite, one built by Orbital Sciences, and the other by Lockheed Martin, had a mass of about 250 kg. They were believed to be solar-powered and equipped with propulsion systems that would allow them to rendezvous with geosynchronous satellites. Once they had reached the satellite, they would presumably be capable of destroying, disabling, or jamming them. To deliver the two satellites to near-synchronous orbit, a Naval Research Laboratory liquid propellant bus equipped with a 400 N main engine and solar panels was used.


2006 September 1 - . 17:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF23. Launch Pad: LF23?. LV Family: Pegasus. Launch Vehicle: GBI.
  • FT-2 - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,000 km (600 mi).

2006 October 13 - . 20:56 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • Optus D1 - . Payload: Star-2. Nation: Australia. Agency: Optus. Manufacturer: OSC. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: Star bus. USAF Sat Cat: 29495 . COSPAR: 2006-043B. Apogee: 35,797 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0400 deg. Period: 1,436.09 min. Direct television broadcast to the Australian market. As of 2007 Mar 7 located at 159.99E drifting at 0.005W degrees per day..

2007 April 25 - . 20:26 GMT - . Launch Site: Point Arguello. Launch Complex: Point Arguello WADZ. Launch Pad: Aircraft from Vandenberg.. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL.
  • AIM - . Mass: 150 kg (330 lb). Nation: USA. Agency: Hampton, NASA. Manufacturer: Ball, OSC. Spacecraft: RS-300. USAF Sat Cat: 31304 . COSPAR: 2007-015A. Apogee: 602 km (374 mi). Perigee: 584 km (362 mi). Inclination: 97.8000 deg. Period: 96.50 min.

    NASA Small Explorer mission, for Aeronomy of Ice in the Mesosphere. AIM carried three scientific instruments to study polar mesospheric clouds: a solar occultation camera, an ultraviolet imager, and a cosmic dust experiment. Air dropped in Point Arguello WADZ.


2007 September 28 - . 20:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF23. Launch Pad: LF23?. LV Family: Pegasus. Launch Vehicle: GBI.
  • FTG-03a - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,000 km (600 mi).

2007 October 5 - . 22:02 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5GS.
  • Optus D-2 - . Mass: 2,400 kg (5,200 lb). Nation: Australia. Agency: Optus. Manufacturer: OSC. Program: Aussat. Class: Communications. Type: Military communications satellite. Spacecraft: Star bus. USAF Sat Cat: 32252 . COSPAR: 2007-044A. Apogee: 35,889 km (22,300 mi). Perigee: 35,862 km (22,283 mi). Inclination: 0.0000 deg. Period: 1,440.70 min.

    Ku-band satellite designed to deliver television, internet, communications, and data services to Australia and New Zealand. After deployment of the two satellites, the EPS third stage made a brief burn at 23:28 GMT to make the first in-flight test the Aestus engine's restart capability. This was to be used in 2008 in the first launch of the ATV ISS resupply spacecraft.

  • Intelsat IS-11 - . Mass: 2,400 kg (5,200 lb). Nation: USA. Agency: Intelsat. Manufacturer: OSC. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 32253 . COSPAR: 2007-044B. Apogee: 35,797 km (22,243 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. C and Ku-band satellite designed to provide Atlantic region communications services..

2007 December 21 - . 21:41 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5GS.
  • Horizons 2 - . Payload: Star-2. Mass: 2,350 kg (5,180 lb). Nation: Bermuda. Agency: Intelsat, JSAT. Manufacturer: OSC. Program: Horizons. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 32388 . COSPAR: 2007-063B. Apogee: 35,816 km (22,254 mi). Perigee: 35,815 km (22,254 mi). Inclination: 0.0000 deg. Period: 1,437.50 min.

    Launched by Horizons Satellite Holdings LLC, a joint venture of Intelsat and the Japanese JSAT company. To be placed at 74 deg W to serve United States, eastern Canada, and the Caribbean with communication services using its 16-transmitter Ku-band communications payload.


2008 October 19 - . 17:47 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein DZ. Launch Pad: RW06/24. Launch Platform: L-1011. LV Family: Pegasus. Launch Vehicle: Pegasus XL.
  • IBEX - . Mass: 107 kg (235 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Microstar. USAF Sat Cat: 33401 . COSPAR: 2008-051A. Apogee: 281,252 km (174,761 mi). Perigee: 69,563 km (43,224 mi). Inclination: 19.2300 deg. Period: 12,855.81 min. Interstellar Boundary Explorer. Mission was to map, from its high earth orbit, the boundary of the heliosphere, the point at the limits of the solar system where the solar wind is overcome by the interstellar medium. Air dropped in Kwajalein DZ..

2008 December 5 - . 20:21 GMT - . Launch Site: Vandenberg. LV Family: Pegasus. Launch Vehicle: GBI.
  • MDA FTG-05 - . Nation: USA. Agency: MDA. Manufacturer: OSC. Class: Military. Type: Anti-satellite system.

2010 January 31 - . 23:45 GMT - . Launch Site: Vandenberg. LV Family: Pegasus. Launch Vehicle: GBI.
  • FTG-06 EKV - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,000 km (600 mi). Interceptor.

2010 June 6 - . 22:25 GMT - . Launch Site: Vandenberg. LV Family: Pegasus. Launch Vehicle: GBI.
  • BVT-1 - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 300 km (180 mi). Test launch.

2010 December 15 - . 20:03 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF23. LV Family: Pegasus. Launch Vehicle: GBI.
  • FTG-06A KV - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,000 km (600 mi). ABM test..
  • GMD FTG-06a - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,000 km (600 mi).

2013 January 26 - . 22:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF23. LV Family: Pegasus. Launch Vehicle: GBI.
  • EKV CTV-01 - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,000 km (600 mi). ABM test of CE-II EKV kill vehicle..

2013 April 21 - . 21:00 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LP0A. LV Family: Antares LV. Launch Vehicle: Antares 110.
  • Cygnus Mass Simulator - . Mass: 4,000 kg (8,800 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus. Decay Date: 2013-04-27 . USAF Sat Cat: 39142 . COSPAR: 2013-016A. Apogee: 161 km (100 mi). Perigee: 153 km (95 mi). Inclination: 51.6100 deg. Period: 87.63 min.

    First launch of the Antares launch vehicle, combining surplus rocket engines from the Soviet N1 moon rocket program with US-built components. The mass simulator carried instrumentation to measure the launch vehicle environment in preparation for future launches of the Cygnus spacecraft designed to carry cargo to the International Space Station. It also released four cubesats into independent orbits.


2013 July 5 - . 18:35 GMT - . Launch Site: Vandenberg. LV Family: Pegasus. Launch Vehicle: GBI.
  • FTG-07 CE-I EKV - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,000 km (600 mi). Anti-ballistic missile. Failure; did not intercept target vehicle..

2013 September 18 - . 14:58 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0A. LV Family: Antares LV. Launch Vehicle: Antares 110.
  • SS G David Low - . Payload: Cygnus OD-1. Mass: 4,127 kg (9,098 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus. Duration: 35.00 days. Decay Date: 2013-10-23 . USAF Sat Cat: 39258 . COSPAR: 2013-051A. Apogee: 414 km (257 mi). Perigee: 411 km (255 mi). Inclination: 51.6500 deg. Period: 92.81 min.

    First Orbital Sciences Cygnus ISS resupply spacecraft. Named SS G. David Low after the late astronaut, son of the former NASA administrator, and Orbital employee. The Cygnus consisted of a pressurized cargo module (PCM) built by Thales Alenia in Torino, and a service module (SM) built by Orbital/Dulles. The craft carried 700 kg of cargo. Intiial orbit was 261 km x 277 km x 51.6 deg; at 20:07 GMT this was raised to 274 km x 384 km. On 22 September the first attempt at rendezvous with the ISS was cancelled due to a software problem in the GPS navigation system; Cygnus passed ISS at a distance of 4 km at 08:45 GMT. On 29 September Cygnus completed its rendezvous with ISS, reaching a 250 m hold point at 09:08 GMT. The SSRMS arm captured Cygnus at 11:00 GMT, and after berthing to the Harmony module of the ISS he astronauts began unloading the ship's cargo. Cygnus unberthed from Harmony at 10:04 GMT on 22 October and was released into a 415 x 419 km orbit by the SSRMS at 11:31 GMT. On 23 October Cygnus conducted its retrofire burn at 17:41 GMT, and burnt up at 18:16 GMT over the South Pacific.


2014 January 9 - . 18:07 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0A. LV Family: Antares LV. Launch Vehicle: Antares 120.
  • SS C Gordon Fullerton - . Payload: Cygnus OA-1. Mass: 4,127 kg (9,098 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus. Duration: 41.00 days. Decay Date: 2014-02-19 . USAF Sat Cat: 39502 . COSPAR: 2014-003A. Apogee: 407 km (252 mi). Perigee: 402 km (249 mi). Inclination: 51.6400 deg. Period: 92.66 min.

    Delivered 1,261 kg of cargo to the ISS. The Cygnus cargo ship SS C. Gordon Fullerton entered an initial 221 x 259 km x 51.6 deg orbit to begin its rendezvous sequence with ISS. Arrived at 250 metres from ISS at 10:01 GMT January 12; moved in to the 10 m capture position; then captured by the Canadarm-2 at 11:08 GMT and berthed on the Harmony module's nadir port at 13:05 GMT. It contained 1465 kg of cargo for ISS, including two bags with a total mas of 152 kg containing a set of 28 Dove 3U Earth-observing cubesats (about 5 kg each) for Planet Labs and five 1U/2U cubesats. Unberthed from the Harmony module and released by the robot arm at 11:42 GMT 18 February. After two orbital maneuvers Cygnus underwent destructive reentry over the Pacific with loss of signal at 18:23 GMT February 19. First launch of Orbital's Antares 120 variant, with a more powerful ATK Castor 30B second stage replacing the Castor 30 used on earlier flights.


2014 June 22 - . 18:55 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF23. Launch Pad: LF23?. LV Family: Pegasus. Launch Vehicle: GBI.
  • GMD FTG-06b CE-II EKV - . Nation: USA. Agency: MDA. Manufacturer: OSC. Apogee: 1,000 km (600 mi).

2014 July 13 - . 16:52 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LP0A. LV Family: Antares LV. Launch Vehicle: Antares 120.
  • SS Janice Voss - . Payload: Cygnus OA-2. Mass: 3,500 kg (7,700 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus. Duration: 35.00 days. Decay Date: 2014-08-17 . USAF Sat Cat: 40084 . COSPAR: 2014-039A. Apogee: 407 km (252 mi). Perigee: 386 km (239 mi). Inclination: 51.6500 deg. Period: 92.48 min.

    Delivered 1,494 kg of cargo to the ISS. After rendezvous with the ISS the station's SSRMS arm grappled it at 10:36 GMT on July 16 and berthed it to the Harmony module at 12:53 GMT. Unberthed at 09:14 GMT on August 15 and released by Canadarm-2 at 10:40 GMT. Deorbited and reentered at 13:15 GMT on 17 August over the South Pacific.


2014 October 28 - . 22:20 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0A. Launch Pad: Wallops MARS 0A. LV Family: Antares LV. Launch Vehicle: Antares 130. FAILURE: Vehicle exploded 14 seconds after launch at an altitude of about 100 metres, and the vehicle and payloads fell back to the pad, resulting in a large explosion. Traced to failure of turbopump in first stage engine; same defect as doomed the N1 moon rocket.. Failed Stage: 1.
  • SS Deke Slayton - . Payload: Cygnus OA-3. Mass: 3,500 kg (7,700 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus.

    The Orbital Cygnus Orb-3 cargo ship; destroyed during launch. As well as ISS cargo, the Orb-3 mission was carrying 26 PlanetLabs Flock-1d 3U cubesats, the JPL/U-Texas RACE 3U cubesat, the Arkyd-3 3U cubesat from Planetary Resources, and also the GOMX-2 ship tracking 2U cubesat from GOMX of Aalborg, Denmark.


2015 December 6 - . 21:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 401.
  • SS Deke Slayton II - . Payload: Cygnus OA-4. Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus. Decay Date: 2016-02-20 . USAF Sat Cat: 41101 . COSPAR: 2015-072A. Apogee: 418 km (259 mi). Perigee: 404 km (251 mi). Inclination: 51.6000 deg.

    United Launch Alliance launched Atlas V flight AV-061 carrying the Cygnus OA-4 cargo ship mission. Following the Antares failure in the prior year, Cygnus payloads were temporarily moved to Atlas. The OA-4 Cygnus, called 'SS Deke Slayton II', was the first Cygnus with the enhanced (stretched) EPCM pressurized cargo module, and the first with a service module carrying the circular UltraFlex solar arrays originally designed for NASA's Orion. This was the first time an Atlas launched a payload towards the ISS. The AV-061 Centaur reached a 234 x 237 km orbit at 2203 UTC, released Cygnus 3 min later, and performed a 10s deorbit burn at 2232 UTC for disposal of the Centaur in the ocean south of Australia at about 132E 49S. The Deke Slayton II reached the ISS on Dec 9, with SSRMS grapple at 1119 UTC and berthing on Harmony at 1426 UTC. Aboard the Cygnus were the small NovaWurks SIMPL satellite, 12 Flock 2e cubesats from Planet Labs, and the CADRE, STMSat-1, MinXSS-1, Nodes 1 and Nodes 2 cubesats. Mass of ISS after the OA-4 arrival was 418 metric tons. The Canadarm-2 unberthed the Cygnus OA-4 cargo ship, SS Deke Slayton II, from the Unity node on Feb 19 at 1040 UTC and released it into orbit at about 1227 UTC. The Cygnus was deorbited over the S Pacific at about 1600 UTC Feb 20.


2016 March 23 - . 03:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 401.
  • SS Rick Husband - . Payload: Cygnus OA-5. Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus. Decay Date: 2016-06-22 . USAF Sat Cat: 41393 . COSPAR: 2016-019A. Apogee: 250 km (150 mi). Perigee: 240 km (140 mi). Inclination: 51.6000 deg.

    Cygnus cargo ship OA-6, "SS Rick Husband", was launched aboard Atlas V flight AV-064. A mixture ratio problem on the Atlas caused an 5-seconds-early first stage cutoff, which required a full extra minute's burn on the Centaur upper stage to make the correct orbit. After deploying Cygnus, the Centaur's second burn was intended to deorbit the stage south of Australia, but because of insufficient remaining propellant the engine cutoff early, and reentry occurred downrange south of New Zealand. SS Rick Husband arrived at the ISS on schedule, and was grappled by the Canadarm-2 at 1051 UTC Mar 26. On Jun 14 the Canadarm-2 unberthed Cygnus OA-6 from the Unity module at 1143 UTC and released it into orbit at 1330 UTC. Cygnus then performed the SAFIRE-1 experiment igniting a significant fire inside an experiment chamber in the Cygnus pressurized PCM module. Mounted on the Cygnus service module was the first NRCSD-E external cubesat deployer carrying 5 Lemur-2 satellites. On Jun 21 two pairs of Lemur-2 cubesats were ejected. A third deployer silo with a single Lemur-2 failed to open, and the cubesat remained inside when then following day Cygnus made its deorbit burn and reentered over the South Pacific at 1329 UTC Jun 22.


2016 October 17 - . 23:45 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA0A. Launch Pad: Wallops MARS 0A. LV Family: Antares LV. Launch Vehicle: Antares 230.
  • SS Alan Poindexter - . Payload: Cygnus OA-6. Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus. Decay Date: 2016-11-28 . USAF Sat Cat: 41818 . COSPAR: 2016-062A. Apogee: 395 km (245 mi). Perigee: 373 km (231 mi). Inclination: 51.6000 deg.

    Orbital ATK Cygnus cargo ship, the SS Alan Poindexter, was launched on mission OA-5. The launch was the first flight of the Antares 230 rocket, featuring a first stage with two Energomash RD-181 engines replacing the Kuznetsov/Aerojet AJ-26 engines used on earlier Antares missions (which were implicated in the Oct 2014 Antares 130 failure), and a second stage with the Castor 30XL solid motor. The Castor 30XL was on the previous Antares launch but didn't get a chance to fire because of the first stage failure, so this was its first real test. In the event the rocket performed above specification and the mission reached a higher-than-planned 209 x 351 km orbit. OA-5 reached the ISS on Oct 23; it was grappled by the SSRMS at 1128 UTC and berthed to the nadir port of the Unity module at 1453 UTC. Cygnus OA-5 carried 2345 kg of pressurized cargo, and the external Nanoracks deployer with four Spire Global Lemur-2 cubesats.Cygnus cargo vehicle SS Alan Poindexter (OA-5) was unberthed from the Unity module at about 1125 UTC Nov 21 and released into space at 1322 UTC. It raised its orbit on Nov 25 to 495 x 504 km and released two pairs of Spire Global cubesats in the Lemur-2 series. Cygnus was deorbited on Nov 27, reentering over the S Pacific at 2336 UTC.


2017 April 18 - . 15:11 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: Cape Canaveral SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 401.
  • SS John Glenn - . Payload: Cygnus OA-7. Mass: 7,221 kg (15,919 lb). Nation: USA. Agency: NASA. Manufacturer: OSC. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Cygnus. USAF Sat Cat: 42681 . COSPAR: 2017-019A. Apogee: 412 km (256 mi). Perigee: 398 km (247 mi). Inclination: 51.6000 deg. Cygnus mission OA-7, the S.S. John Glenn, was launched on ULA Atlas AV-070. The 7221 kg cargo ship carried about 140 kg of small satellites for later deployment and about 3250 kg of other cargo. OA-7 arrived at ISS on Apr 22..


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