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Falcon

Falcon 1

Falcon 1

Falcons are a family of two stage, reusable, liquid oxygen and kerosene powered launch vehicles, designed for cost-efficient and reliable transport of satellites and manned spacecraft to low Earth orbit. The Falcon 1 satellite launcher began launches in 2006, with the Falcon 9 - as large as a Saturn I - flying in 2010. The Falcon series was the only successful project among many attempts to privately develop a low cost launch system since the 1960's.

AKA: AIM-4.

Falcon I was a two stage, reusable, liquid oxygen and kerosene powered launch vehicle. A single engine powered the first stage. It was designed for cost-efficient and reliable transport of satellites to low Earth orbit. First launch of the Falcon I was scheduled for mid-2004 from Vandenberg, carrying a US Defense Department communications satellite. Development delays and problems with USAF clearances for launch from Vandenberg resulted in the first launch attempt being made in 2006 from a private facility at Omelek near Kwajalein atoll in the Pacific. Success was achieved on the fourth launch in 2008. The Falcon 1 was to be superseded by the Falcon 1e, with an extended-tank first stage, from 2010.

The first stage primary structure was made of a space grade aluminum alloy in a patent pending, graduated monocoque, common bulkhead, flight pressure stabilized architecture developed by SpaceX. The design was a blend between a fully pressure stabilized design, such as Atlas II, and a heavier isogrid design, such as Delta II. As a result, SpaceX claimed to have captured the mass efficiency of pressure stabilization, but avoided the ground handling difficulties of a structure unable to support its own weight. A single SpaceX Merlin engine powered the Falcon I first stage. After engine start, Falcon would be held down until all vehicle systems were verified to be functioning normally before release for lift-off. Helium tank pressurization was provided by composite over-wrapped Inconel tanks from Arde Corporation, the same model used in Boeing's Delta IV rocket. Stage separation occurred via dual initiated separation bolts and a pneumatic pusher system. All components were space qualified and had flown before on other launch vehicles.

The first stage returned by parachute to a water landing, where it was picked up by ship in a procedure similar to that of the Space Shuttle solid rocket boosters. The parachute recovery system was built for SpaceX by Irvin Parachute Corporation, who also builds the Shuttle booster recovery system.

The second stage tank structure was made of aluminum-lithium alloy. SpaceX found this to be the lowest total system mass in this application of any material examined, including liquid oxygen compatible super-alloys and composites. A single SpaceX Kestrel pressure-fed engine powered the Falcon I upper stage. For added reliability of restart, the engine had dual redundant torch igniters. Helium pressurization was again provided by composite over wrapped Inconel tanks from Arde. The helium was also used in cold gas thrusters for attitude control and propellant settling when a restart was needed.



Subtopics

Falcon 5 American low cost orbital launch vehicle. Falcon V was a two stage, reusable, liquid oxygen and kerosene powered launch vehicle. The maiden flight was targeted for mid-2005 as of early 2004. It used of the same engines, structural materials and concepts, and avionics and launch system as the Falcon I, differing in having five first-stage engines instead of 1 and a larger diameter. This meant that all the critical components would have a flight proven history even before first launch. By 2006 it had been superseded by the slightly larger Falcon 9.

Falcon 1 American two stage, liquid oxygen and kerosene powered, low cost launch vehicle. A single engine powered the first stage. It was designed for cost-efficient and reliable transport of satellites to low Earth orbit. First launch of the Falcon I was scheduled for mid-2004 from Vandenberg, carrying a US Defense Department communications satellite. Development delays and problems with USAF clearances for launch from Vandenberg resulted in the first launch attempt being made in 2006 from a private facility at Omelek near Kwajalein atoll in the Pacific. Success was achieved on the fourth launch in 2008. The Falcon 1 was to be superseded by the Falcon 1e, with an extended-tank first stage, from 2010.

Falcon-1 (Development Version) American orbital launch vehicle variant, development version of Falcon 1.

Falcon 9 Heavy American low cost orbital launch vehicle. The Falcon 9 Heavy would consist of a standard Falcon 9 v1.1 with two additional Falcon 9 first stages as liquid strap-on boosters.

Falcon 9 v1.1 Falcon 9 v1.1 represented a 50% increase in lift-off mass, with correspondingly upgraded engines with a 5% improvement in specific impulse.

Falcon 9 American low cost orbital launch vehicle. In September 2006 SpaceX was named as one of two winners of the NASA Commercial Orbital Transportation Services competition. The SpaceX award was $278 million for three flight demonstrations of the Falcon 9 booster carrying the Dragon space capsule. On 23 December 2008 NASA announced that the Falcon 9 / Dragon had been selected for launch of a guaranteed minimum of 20,000 kg of payload to the International Space Station in 2010-2014. The firm contract was worth $1.6 billion, with another $1.5 billion of options.

Grasshopper Test version of recoverable Falcon 9 first stage, used for landing tests.

Falcon 9R Version of Falcon 9 with capability to recover first stage on a floating platform downrange or at the launch site, depending on the payload margins.

Falcon 9 v1.2 American orbital launch vehicle. Upgraded version of Falcon 9 v1.1 with greater thrust, improved structure, 30% greater payload performance.

Falcon-9 v1.2(ex) American orbital launch vehicle. Expendable first stage for maximum payload as opposed to standard recoverable first stage variant.

Falcon-9 Family American orbital launch vehicle family.

Country: USA. Spacecraft: Celestis, FalconSat, Nanosail, PreSat, Trailblazer. Launch Sites: Kwajalein.
Photo Gallery

FalconFalcon
Credit: via Andreas Parsch



2006 March 24 - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1. FAILURE: Fuel leak at T+25 seconds caused a fire in the first stage engine area. Failed Stage: 1.
  • Falconsat-2 - . Mass: 20 kg (44 lb). Nation: USA. Agency: USAF Colorado Springs. Manufacturer: USAFA. Class: Technology. Type: Navigation technology satellite. Spacecraft: Falconsat. The satellite fell through the roof of SpaceX's machine shop on the atoll..

2007 March 21 - . 01:10 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1. FAILURE: Liquid oxygen slosh in the second stage created an oscillation, putting the stage in an uncontrollable roll, starving the engine from propellant.. Failed Stage: 2.
  • DemoFlight 2 - . Nation: USA. Agency: DARPA. Class: Technology. Type: Navigation technology satellite.

    An oscillation appeared in the upper stage control system 90 seconds into the burn. This instability grew and after 30 seconds induced a roll torque that exceeded the control capability of the second stage roll control thrusters. The propellants were centrifuged away from the outlets, causing flame-out of the Kestrel engine. LOX slosh was believed to be the primary contributor to this instability. Second stage slosh baffles would be included in future boosters to prevent reoccurence of the problem.


2008 August 3 - . 03:34 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1. FAILURE: The new Merlin 1C first stage engine completed its burn, but the thrust took longer to decay than expected. It was still thrusting when stage 2 tried to separate, and the two stages collided, setting the second stage tumbling..
  • Nanosail-D - . Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: SpaceX. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. 3U cubesat for NASA. Technology mission..
  • PreSat - . Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: SpaceX. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. 3U cubesat for NASA. Technology mission..

2008 September 28 - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1.
  • Ratsat - . Nation: USA. Agency: SpaceX. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ratsat. USAF Sat Cat: 33393 . COSPAR: 2008-048A. Apogee: 643 km (399 mi). Perigee: 622 km (386 mi). Inclination: 9.3000 deg. Period: 97.40 min. First successful launch of low-cost Falcon launch vehicle. The second stage demonstrated restart. The payload was a dummy mass which remained attached to the stage..

2009 July 14 - . 03:36 GMT - . Launch Site: Kwajalein. Launch Complex: Kwajalein OM. LV Family: Falcon. Launch Vehicle: Falcon 1.
  • Razaksat - . Mass: 180 kg (390 lb). Nation: Malaysia. Agency: SpaceX. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft: Satrec. USAF Sat Cat: 35578 . COSPAR: 2009-037A. Apogee: 690 km (420 mi). Perigee: 665 km (413 mi). Inclination: 9.0000 deg. Period: 98.30 min. Malaysian imaging satellite..

2010 June 4 - . 18:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Dragon/Falcon 9 - . Mass: 4,000 kg (8,800 lb). Nation: USA. Agency: SpaceX. Class: Manned. Type: Manned spacecraft. Spacecraft: Dragon. Duration: 23.00 days. Decay Date: 2010-06-27 . USAF Sat Cat: 36595 . COSPAR: 2010-026A. Apogee: 140 km (80 mi). Perigee: 138 km (85 mi). Inclination: 34.5000 deg. Period: 87.30 min. First launch of the commercial Falcon 9 launch vehicle. Structural model of Dragon reusable spacecraft. Remained attached to final stage..

2010 December 8 - . 15:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Dragon C1 - . Mass: 6,650 kg (14,660 lb). Nation: USA. Class: Manned. Type: Manned spacecraft. Spacecraft: Dragon. Duration: 0.14 days. Decay Date: 2010-01-12 . USAF Sat Cat: 37244 . COSPAR: 2010-066A. Apogee: 306 km (190 mi). Perigee: 281 km (174 mi). Inclination: 34.5000 deg. Period: 90.40 min. First test of the Dragon recoverable spacecraft. Splashed down and successfully recovered in the Pacific Ocean 800 km west of Mexico after a 3 hour 20 minute mission..
  • QBX2 - . Payload: QbX-2. Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2011-12-31 . USAF Sat Cat: 37245 . COSPAR: 2010-066B. Apogee: 187 km (116 mi). Perigee: 173 km (107 mi). Inclination: 34.5000 deg. Period: 88.10 min. 3U cubesat built by Pumpkin Inc of San Francisco for the National Reconaissance Office's Colony-1 technology development project. Successful..
  • SMDC One - . Payload: SMDC-One. Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2011-12-31 . USAF Sat Cat: 37246 . COSPAR: 2010-066C. Apogee: 184 km (114 mi). Perigee: 173 km (107 mi). Inclination: 34.5000 deg. Period: 88.10 min. Operational Nanosatellite Experiment for the US Army Space and Missile Defense Center.
  • Perseus 003 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2010-01-06 . USAF Sat Cat: 37247 . COSPAR: 2010-066D. Apogee: 190 km (110 mi). Perigee: 179 km (111 mi). Inclination: 34.5000 deg. Period: 88.20 min. Los Alamos National Laboratory cubesat, perhaps for ionospheric monitoring..
  • Perseus 001 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2010-12-30 . USAF Sat Cat: 37248 . COSPAR: 2010-066E. Apogee: 183 km (113 mi). Perigee: 176 km (109 mi). Inclination: 34.5000 deg. Period: 88.10 min. Los Alamos National Laboratory cubesat, perhaps for ionospheric monitoring..
  • QBX1 - . Payload: QbX-1. Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2011-12-30 . USAF Sat Cat: 37249 . COSPAR: 2010-066F. Apogee: 197 km (122 mi). Perigee: 185 km (114 mi). Inclination: 34.5000 deg. Period: 88.30 min. 3U cubesat satellite built by Pumpkin Inc of San Francisco for the National Reconaissance Office's Colony-1 technology development project. Successful..
  • Perseus 002 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2010-12-22 . USAF Sat Cat: 37250 . COSPAR: 2010-066G. Apogee: 193 km (119 mi). Perigee: 183 km (113 mi). Inclination: 34.5000 deg. Period: 88.20 min. Los Alamos National Laboratory cubesat, perhaps for ionospheric monitoring..
  • Perseus 000 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2010-12-30 . USAF Sat Cat: 37251 . COSPAR: 2010-066H. Apogee: 190 km (110 mi). Perigee: 180 km (110 mi). Inclination: 34.5000 deg. Period: 88.20 min. Los Alamos National Laboratory cubesat, perhaps for ionospheric monitoring..
  • Mayflower - . Payload: Caerus/Mayflower. Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2010-12-22 . USAF Sat Cat: 37252 . COSPAR: 2010-066J. Apogee: 194 km (120 mi). Perigee: 179 km (111 mi). Inclination: 34.5000 deg. Period: 88.20 min.

    Experiment for Northrop Grumman NovaWorks and the University of Southern California. 3U cubesat with deployable solar panels composed of a Northrop Grumman's 2-unit Mayflower Next Generation Technology Nanosat and University of Southern California's 1-unit cubesat.


2012 May 22 - . 07:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Dragon C2 - . Mass: 6,650 kg (14,660 lb). Nation: USA. Program: ISS. Class: Manned. Type: Manned spacecraft. Spacecraft: Dragon. Duration: 9.00 days. Decay Date: 2012-05-31 . USAF Sat Cat: 38348 . COSPAR: 2012-027A. Apogee: 406 km (252 mi). Perigee: 392 km (243 mi). Inclination: 51.6000 deg. Period: 92.50 min. First commercial delivery of cargo to a space station. After rendezvous with the International Space Station, it was captured by the station's SSRMS robot arm on 25 May at 13:56 GMT. Berthed at the nadir CBM port of the Harmony module at 16:02 GMT..
  • Celestis 11 - . Mass: 7.00 kg (15.40 lb). Nation: USA. Class: Burial. Type: Burial satellite. Spacecraft Bus: Pegasus-3. Spacecraft: Celestis. Decay Date: 2012-06-27 . USAF Sat Cat: 38349 . COSPAR: 2012-027B. Apogee: 298 km (185 mi). Perigee: 253 km (157 mi). Inclination: 51.7000 deg. Period: 90.00 min. Released from the Dragon spacecraft. Carried some of the ashes of Star Trek actor James Doohan, among others..

2012 September 21 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Grasshopper.
  • Nation: USA. Agency: SPX. Apogee: 0 km (0 mi). 2m hop.

2012 October 8 - . 00:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Dragon CRS-1 - . Mass: 9,500 kg (20,900 lb). Nation: USA. Program: ISS. Class: Manned. Type: Manned spacecraft. Spacecraft: Dragon. Duration: 20.00 days. Decay Date: 2012-10-28 . USAF Sat Cat: 38846 . COSPAR: 2012-054A. Apogee: 425 km (264 mi). Perigee: 402 km (249 mi). Inclination: 51.6000 deg. Period: 92.80 min.

    One first stage engine had an anomaly at max Q (T+1:20) with some debris observed falling away; the engine was shut down but the remaining engines and the second stage compensated to reach the initial orbit. However, extra propellant was used and stage two did not restart as planned. Nevertheless Dragon reached the ISS on 10 October and was captured by the station's SSRMS arm at 10:56 GMT and berthed to the Harmony module at 13:03 GMT. Following unloading of the cargo delivered to the ISS and loading of experimental results and failed equipment for return to earth, the SSRMS unberthed Dragon at 11:19 GMT on 28 October and released it at 13:29 GMT. At 14:22 GMT the Dragon made a burn to lower its orbit and at 18:28 GMT came the 10 minute 40 second long deorbit burn. The Dragon trunk was jettisoned at 18:41 GMT and the capsule reached entry interface at 19:02 GMT. Splashdown in the Pacific Ocean was at around 123 deg W 28 deg N at 19:22

  • Orbcomm OG2-1 - . Mass: 172 kg (379 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. Decay Date: 2012-10-10 . USAF Sat Cat: 38847 . COSPAR: 2012-054B. Apogee: 204 km (126 mi). Perigee: 145 km (90 mi). Inclination: 51.6000 deg. Period: 88.00 min.

    The mission's secondary payload, the first Orbcomm Second Generation communications satellite, was sacrificed in order to allow the Dragon cargo ship to reach the ISS after a rocket engine failure in the booster during ascent to orbit. The OG2 was ejected at 01:37 GMT into a 203 km x 323 km orbit instead of its planned 350 km x 750 km insertion orbit. Orbcomm was not be able to get to the operational 750 km x 750 km orbit. Instead the satellite reentered at 06:19 GMT on 10 October after two days in space, probably over the Pacific west of Vancouver, Canada. An Orbcomm press release stated that they were able to test out the satellite's systems before the reentry.


2012 November 1 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Grasshopper.
  • Nation: USA. Agency: SPX. Apogee: 0 km (0 mi). 5m hop.

2012 December 17 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Grasshopper.
  • Nation: USA. Agency: SPX. Apogee: 0 km (0 mi). 40m hop.

2013 March 1 - . 15:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Dragon CRS-2 - . Mass: 9,500 kg (20,900 lb). Nation: USA. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Duration: 25.00 days. Decay Date: 2013-03-26 . USAF Sat Cat: 39115 . COSPAR: 2013-010A. Apogee: 409 km (254 mi). Perigee: 380 km (230 mi). Inclination: 51.6500 deg. Period: 92.44 min.

    Initial issues with thrusters and solar panel deployment were solved, but delayed rendezvous with the ISS by one day. Captured by the ISS SSRMS robot arm at 10:31 GMT on 3 March. Delivered 677 kg of cargo in the pressurized section. Externally, two 119 kg grapple fixtures for the ISS Heat Rejection System were delivered. Undocked and released by the SSRMS at 10:56 GMT on 26 March. Retrofire at 15:42 GMT followed by splashdown in the Pacific at 30.52 deg N / 120.04 deg W at 16:35 GMT.


2013 March 7 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Grasshopper.
  • Nation: USA. Agency: SPX. Apogee: 0 km (0 mi). 80m.

2013 April 19 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Grasshopper.
  • Nation: USA. Agency: SPX. Apogee: 0 km (0 mi). 250m.

2013 June 14 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Grasshopper.
  • Nation: USA. Agency: SPX. Apogee: 0 km (0 mi). 325m.

2013 August 13 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Grasshopper.
  • Nation: USA. Agency: SPX. Apogee: 0 km (0 mi). 250m.

2013 September 29 - . 16:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Cassiope - . Mass: 500 kg (1,100 lb). Nation: Canada. Class: Communications. Type: Communications satellite. Spacecraft: MAC-200. USAF Sat Cat: 39265 . COSPAR: 2013-055A. Apogee: 1,437 km (892 mi). Perigee: 324 km (201 mi). Inclination: 80.9900 deg. Period: 102.57 min.

    Canadian Space Agency satellite with two payloads: the CASCADE high bandwith Ka-band communications relay package and the ePOP suite of instruments to study the polar ionosphere. The satellite was built by MacDonald, Dettwiler and Associates (MDA Ltd.) using a Bristol Aerospace spacecraft bus. First launch of the Falcon 9 v1.1 upgrade of the Falcon 9 rocket.

  • CUSat - . Mass: 23 kg (50 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: CUSat. USAF Sat Cat: 39266 . COSPAR: 2013-055B. Apogee: 1,426 km (886 mi). Perigee: 323 km (200 mi). Inclination: 80.9900 deg. Period: 102.45 min.

    Cornell University satellite; carried a differential GPS navigation system and pulsed plasma thrusters. The defunct-before-launch CUSAT 2/Top satellite remained attached to the Falcon 9 second stage. CUSAT (formerly CUSAT 1/Bottom) was launched attached to CUSAT 2 and separated from it after orbit insertion.

  • DANDE - . Mass: 38 kg (83 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: DANDE. USAF Sat Cat: 39267 . COSPAR: 2013-055C. Apogee: 1,448 km (899 mi). Perigee: 324 km (201 mi). Inclination: 80.9900 deg. Period: 102.69 min.

    Drag and Atmospheric Neutral Density Explorer from the University of Colorado. The sphere carried a particle spectrometer to measure the outer atmosphere wind speed and direction, and a drag measurement system. It was attached to an 8 kg Lightband adapter which was jettisoned on October 30 (cataloged as 2013-055AC) and DANDE then began its atmospheric density studies.

  • POPACS 1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: Cubesat. USAF Sat Cat: 39268 . COSPAR: 2013-055D. Apogee: 1,419 km (881 mi). Perigee: 323 km (200 mi). Inclination: 81.0000 deg. Period: 102.37 min. 3U cubesat which split after deployment into four spacer sections that released three 0.10 m diameter aluminium spheres used as passive atmospheric density calibration probes..
  • POPACS 2 - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: Cubesat. USAF Sat Cat: 39269 . COSPAR: 2013-055E. Apogee: 1,440 km (890 mi). Perigee: 323 km (200 mi). Inclination: 81.0000 deg. Period: 102.60 min.
  • POPACS 3 - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: Cubesat. USAF Sat Cat: 39270 . COSPAR: 2013-055F. Apogee: 1,451 km (901 mi). Perigee: 324 km (201 mi). Inclination: 81.0000 deg. Period: 102.73 min.

2013 October 7 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Grasshopper.
  • Nation: USA. Agency: SPX. Apogee: 1.00 km (0.60 mi). 325m.

2013 December 3 - . 22:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • SES-8 - . Payload: GeoStar-2.4 Bus. Mass: 3,170 kg (6,980 lb). Nation: SES. Class: Communications. Type: Communications satellite. Spacecraft: Star bus. USAF Sat Cat: 39460 . COSPAR: 2013-071A. Apogee: 35,801 km (22,245 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.0200 deg. Period: 1,436.13 min.

    Communications satellite for SES World Skies. First geostationary launch for Falcon 9 launch vehicle. After reaching parking orbit the second stage reignited at 2308 GMT and placed SES-8 in a 423 x 79,977 km x 20.47 deg supersynchronous transfer orbit. SES-8 used its engine to move into its final geosynchronous orbit.


2014 January 6 - . 22:06 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Thaicom 6 - . Mass: 3,016 kg (6,649 lb). Nation: Thailand. Class: Communications. Type: Communications satellite. Spacecraft: Orbital star. USAF Sat Cat: 39500 . COSPAR: 2014-002A. Apogee: 35,806 km (22,248 mi). Perigee: 35,767 km (22,224 mi). Inclination: 0.0700 deg. Period: 1,436.09 min.

    Thaicom Plc of Bangkok communications satellite with Ku and C-band payloads for coverage of southeast Asia, Africa and the Middle East. The initial burn of the Falcon 9 second stage reached a 197 x 497 km parking orbit, and a second burn sent the Thaicom 6 payload to a 375 x 90,039 km x 22.5 deg supersync transfer orbit. By February 3 the satellite had manuevered to a 35,784 x 35,789 km x 0.1 deg geostationary orbit over 78.4 deg East.


2014 April 17 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Falcon 9R.
  • F9R Dev1 F001 - . Nation: USA. Agency: SPX. Apogee: 0 km (0 mi). 250m.

2014 April 18 - . 19:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Dragon CRS-3 - . Mass: 9,500 kg (20,900 lb). Nation: USA. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Duration: 30.00 days. Decay Date: 2014-05-18 . USAF Sat Cat: 39680 . COSPAR: 2014-022A. Apogee: 410 km (250 mi). Perigee: 398 km (247 mi). Inclination: 51.6500 deg. Period: 92.65 min.

    Placed in an initial 313 x 322 km orbit. The first flight of a Falcon 9 with experimental landing legs on the first stage. Falcon 9 stage 1 reignited during descent after reaching around 120 km, and touched down vertically on the ocean after demonstrating that it could maintain its orientation during the return from space. The Falcon 9 second stage carried five cubesats; after ejecting them, the stage was deorbited over the Indian Ocean and destroyed during reentry. The Dragon trunk carried the OPALS and HDEV experiments for laser communications and Earth imaging respectively. They would be installed on the ISS - JSC's HDEV on the Columbus module EPF, and JPL's OPALS for the ELC-1 platform. Spacesuit EMU 3003 was also aboard Dragon. Following unloading of cargo and reloading with items to be returned to earth, the hatch to Dragon CRS-3 was closed on May 17. Dragon was unberthed by the SSRMS Canadarm-2 at about 12:00 GMT May 18 and released at 13:26 GMT. The deorbit burn at 18:12 to 18:22 GMT was followed by trunk separation at about 18:24 GMT, atmosphere entry at 18:45 GMT and splashdown west of Baja California at 19:05 GMT. It was reported that some water leaked into the Dragon cabin after splashdown, but NASA said the cargo was not damaged.

  • SporeSat - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Biology. Type: Biology satellite. Spacecraft: Cubesat. Decay Date: 2014-06-04 . USAF Sat Cat: 39681 . COSPAR: 2014-022B. Apogee: 153 km (95 mi). Perigee: 151 km (93 mi). Inclination: 51.6200 deg. Period: 87.54 min. Cubesat for NASA Ames. Released from Falcon second stage..
  • TSat - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2014-05-28 . USAF Sat Cat: 39682 . COSPAR: 2014-022C. Apogee: 167 km (103 mi). Perigee: 153 km (95 mi). Inclination: 51.6100 deg. Period: 87.68 min. Cubesat for Taylor University. Released from Falcon second stage..
  • All-Star - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Science. Type: Science satellite. Spacecraft: Cubesat. Decay Date: 2014-05-26 . USAF Sat Cat: 39683 . COSPAR: 2014-022D. Apogee: 156 km (96 mi). Perigee: 154 km (95 mi). Inclination: 51.6400 deg. Period: 87.59 min. Cubesat for the Colorado Space Grant consortium. Released from Falcon second stage..
  • PhoneSat-2.5 - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2014-05-15 . USAF Sat Cat: 39684 . COSPAR: 2014-022E. Apogee: 119 km (73 mi). Perigee: 109 km (67 mi). Inclination: 51.5400 deg. Period: 86.76 min. Cubesat for NASA Ames. Released from Falcon second stage..
  • Kicksat - . Mass: 3.00 kg (6.60 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2014-05-14 . USAF Sat Cat: 39685 . COSPAR: 2014-022F. Apogee: 175 km (108 mi). Perigee: 160 km (90 mi). Inclination: 51.6500 deg. Period: 87.83 min.

    Cubesat for Cornell University's Space Systems Design Stuido. The satellite had a mass of 2.68 kg, of which 0.52 kg was to have been ejected on May 4 in the form of 104 tiny 5-gram Sprites, circuit boards which acted as independent satellites with small transmitters able to send a simple message to ground stations. A timer problem on Kicksat meant that the deployment of the Sprite subsatellites was reset to May 16. However, Kicksat, and its undeployed Sprites, were destroyed when it reentered on May 14.


2014 May 1 - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Falcon 9R.
  • F9R Dev1 F002 - . Nation: USA. Agency: SPX. Apogee: 1.00 km (0.60 mi).

2014 June 17 - . 22:04 GMT - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Falcon 9R.
  • F9R Dev1 F003 Fin - . Nation: USA. Agency: SPX. Apogee: 1.00 km (0.60 mi).

2014 July 14 - . 15:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Orbcomm FM 109 - . Mass: 172 kg (379 lb). Nation: USA. Agency: SPX. Spacecraft: SN-100. USAF Sat Cat: 40086 . COSPAR: 2014-040A. Apogee: 738 km (458 mi). Perigee: 619 km (384 mi). Inclination: 47.0000 deg. Period: 98.32 min.

    The second stage of the booster deployed a set of six VHF messaging relay satellites for Orbcomm. The second stage carried two ESPA rings (developed for EELV auxilary payloads) each carrying four slots for the 172 kg satellites; the two extra slots were filled with mass dummies which remained attached. The Falcon 9 first stage made a flyback maneuver and deployed landing legs as part of engineering tests for future recovery; the stage was destroyed as it landed on the ocean.

  • Orbcomm FM 107 - . Mass: 172 kg (379 lb). Nation: USA. Agency: SPX. Spacecraft: SN-100. USAF Sat Cat: 40087 . COSPAR: 2014-040B. Apogee: 738 km (458 mi). Perigee: 619 km (384 mi). Inclination: 47.0100 deg. Period: 98.32 min.
  • Orbcomm FM 106 - . Mass: 172 kg (379 lb). Nation: USA. Agency: SPX. Spacecraft: SN-100. USAF Sat Cat: 40088 . COSPAR: 2014-040C. Apogee: 739 km (459 mi). Perigee: 619 km (384 mi). Inclination: 47.0100 deg. Period: 98.33 min.
  • Orbcomm FM 111 - . Mass: 172 kg (379 lb). Nation: USA. Agency: SPX. Spacecraft: SN-100. USAF Sat Cat: 40089 . COSPAR: 2014-040D. Apogee: 740 km (450 mi). Perigee: 619 km (384 mi). Inclination: 47.0100 deg. Period: 98.35 min.
  • Orbcomm FM 104 - . Mass: 172 kg (379 lb). Nation: USA. Agency: SPX. Spacecraft: SN-100. USAF Sat Cat: 40090 . COSPAR: 2014-040E. Apogee: 740 km (450 mi). Perigee: 619 km (384 mi). Inclination: 47.0100 deg. Period: 98.35 min.
  • Orbcomm FM 103 - . Mass: 172 kg (379 lb). Nation: USA. Agency: SPX. Spacecraft: SN-100. USAF Sat Cat: 40091 . COSPAR: 2014-040F. Apogee: 741 km (460 mi). Perigee: 620 km (380 mi). Inclination: 47.0100 deg. Period: 98.37 min.

2014 August 5 - . 08:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9.
  • Asiasat 8 - . Payload: LS-1300LL. Mass: 4,535 kg (9,997 lb). Nation: China. Agency: SPX. Spacecraft: FS-1300. USAF Sat Cat: 40107 . COSPAR: 2014-046A. Apogee: 35,791 km (22,239 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.0500 deg. Period: 1,436.14 min.

    Used an R-4D bipropellant thruster to reach GEO. The first R-4D burn on August 6 raised the orbit from 180 km x 35,762 km x 24.3 deg to 7,137 x 35,751 km x 10.7 deg. By August 11 the satellite was in a 35,725 x 35,732 km x 0.1 deg orbit drifting east over 104 deg E.


2014 August 22 - . 22:45 GMT - . Launch Site: McGregor. LV Family: Falcon. Launch Vehicle: Falcon 9R.
  • F9R Dev1 F004 3 engine test - . Nation: USA. Agency: SPX. Apogee: 1.00 km (0.60 mi). FTS.

2014 September 7 - . 05:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • Asiasat 6 - . Mass: 4,428 kg (9,762 lb). Nation: China. Class: Communications. Type: Communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 40141 . COSPAR: 2014-052A. Apogee: 35,788 km (22,237 mi). Perigee: 35,785 km (22,235 mi). Inclination: 0.0200 deg. Period: 1,436.09 min.

    Communications satellite for Asiasat, a Hong Kong based telecom company. The satellite had C and Ku band communications payloads and an additional C-band payload for the Thai operator Thaicom; this payload was marketed as Thaicom 7. Stationed over 119.8 deg E.


2014 September 21 - . 05:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • Dragon CRS-4 - . Mass: 9,500 kg (20,900 lb). Nation: USA. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Duration: 34.00 days. Decay Date: 2014-10-25 . USAF Sat Cat: 40210 . COSPAR: 2014-056A. Apogee: 412 km (256 mi). Perigee: 403 km (250 mi). Inclination: 51.6400 deg. Period: 92.71 min.

    ISS resupply mission. The Dragon Trunk carried two packages, the ISS RapidScat radar scatterometer science instrument and the RapidScat Nadir Adapter, which was to be installed on the SDX nadir attach point of the Columbus module's external payload facility. The Dragon cabin carried SpinSat, an 0.56m spherical NRL satellite to be deployed by the Kibo JEM-RMS, and the NASA-Ames Rodent Research 1 life sciences payload with 20 mice. The SSRMS Canadarm-2 grappled the Dragon at 10:52 GMT on September 23 and berthed it to the Harmony node at 13:21 GMT. Unberthed and released by the SSRMS at 13:57 GMT on 25 October. It made its deorbit burn at 18:43 GMT and splashed down in the Pacific Ocean at 19:38 GMT off Baja California near 34 deg N x 123.5 deg W.


2015 January 10 - . 09:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • Dragon CRS-5 - . Mass: 9,500 kg (20,900 lb). Nation: USA. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Duration: 32.00 days. Decay Date: 2015-02-11 . USAF Sat Cat: 40370 . COSPAR: 2015-001A. Apogee: 408 km (253 mi). Perigee: 400 km (240 mi). Inclination: 51.7000 deg.

    Launched into a 206 km x 353 km x 51.6 deg orbit. The 9700 kg spacecraft carried 1823 kg of internal cargo and the 494 kg CATS lidar experiment from NASA-GSFC in the trunk. Inside Dragon were two PlanetLabs Flock-1d' cubesats and the AESP-14 1U cubesat from Brazil's space agency AEB and the ITA technical institute. On January 12 Dragon was grappled by the SSRMS arm at 10:54 GMT and berthed on the Harmony module at 13:54 GMT. The cubesats were transferred internally to the Kibo module and were to be deployed from the Kibo airlock. CATS was grappled by the Dextre robot on 2015 Jan 22 and unberthed from Dragon around 07:00 GMT; it was then handed off to the JEM-RMS at around 10:30 and installed on the Kibo Exposed Facility at location EFU3 at about 14:00. The Falcon 9 first stage performed a flyback attempt to land around 360 km downrange at 78 deg W / 31 deg N. The stage made a 'hard' landing on the ASDS (Autonomous Spaceport Drone Ship). The first stage was destroyed when hydraulic fluid depletion made it tip over ahd hit the deck sideways, but the incident did not cause serious damage to the ship. The ASDS has now been renamed "Just Read The Instructions" after the name of an AI spaceship in the book 'The Player of Games' by the late science fiction writer Iain M. Banks.

    Dragon CRS-5 was unberthed from the ISS Harmony module on February 10 by the SSRMS arm, which released it at 19:10 GMT. The Dragon made its deorbit burn at 23:49 GMT, with trunk separation at 00:05 GMT February 11 and splashdown at about 00:44 GMT. Six of the PlanetLabs Flock-1b cubesats (Nos. 3, 4, 13, 14, 19, 20) were returned to Earth aboard CRS-5 without having been deployed, after 212 days in space.


2015 February 11 - . 23:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • DSCOVR - . Mass: 570 kg (1,250 lb). Nation: USA. Class: Science. Type: Space science. Spacecraft: DSCOVR. USAF Sat Cat: 40390 . COSPAR: 2015-007A. Apogee: 1,371,156 km (851,995 mi). Perigee: 187 km (116 mi). Inclination: 33.1000 deg.

    The Deep Space Climate Observatory, DSCOVR, was launched after many years of gestation. Originally a NASA mission called Triana and centered around its Earth observation camera, it had at one point been scheduled for launch on the fatal STS-107 flight of Columbia, but was cancelled amid political controversy (it grew out of an idea by Vice-President Gore for whole-Earth imaging to raise eco-awareness) and placed in storage. The mission was reactivated as part of a NOAA (US National Oceanic and Atmospheric Administration) effort to monitor 'space weather', the flux of particles and radiation in the solar wind and its interaction with the Earth's outer atmosphere. DSCOVR 145 kg of hydrazine propellant, and was stationed at the Earth-Sun L1 point, 1.5 million km noonward from Earth. It carried a Faraday cup instrument to measure solar wind speed, an electron spectrometer and a magnetometer to measure local plasma and fields, a broad band (0.2 to 100 microns) radiometer to measure the Earth's total energy output, and the Earth Polychomatic Imaging Camera to return images of the full Earth disk. DSCOVR was launched into a 184 km x 186 km x 37 deg parking orbit; 30 minutes after launch the Falcon 9 second stage restarted to boost DSCOVR into a 187 km x 1,371,156 km x 37 deg transfer orbit. When the probe reached the L1 point it entered a Lissajous orbit, tracing out a complex pattern around the gravitationally stable balance point. Radius of this pattern was initially around 250,000 km.


2015 March 2 - . 03:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • ABS-3A - . Payload: BSS-702SP. Mass: 2,000 kg (4,400 lb). Nation: China. Class: Communications. Type: Communications satellite. Spacecraft: HS 702. USAF Sat Cat: 40424 . COSPAR: 2015-010A. Apogee: 35,795 km (22,241 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.0100 deg. Period: 1,436.12 min.

    Dual communications satellite payload placed initially in a supersynchronous transfer orbit. Falcon 9 reached a 174 km x 953 km parking orbit 9 minutes after launch, and then made a second burn over the equator to a 391 km x 63452 km x 24.8 deg orbit. The two payloads were 2000 kg Boeing BSS-702SP models with XIPS-25 ion thrusters as their main propulsion system. ABS-3A, for Asia Broadcast Satellite of Hong Kong, was launched directly attached to the lower satellite, Eutelsat 115 West B, until it separated from the stack following stage 2 second cutoff.

  • Eutel.115 West B - . Payload: BSS-702SP. Mass: 2,000 kg (4,400 lb). Nation: Mexico. Class: Communications. Type: Communications satellite. Spacecraft: HS 702. USAF Sat Cat: 40425 . COSPAR: 2015-010B. Apogee: 35,787 km (22,236 mi). Perigee: 35,786 km (22,236 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Eutelsat 115 West B was owned by Eutelsat Americas (Mexico City), and was called Satmex 7. Satmex was taken over by Europe's Eutelsat and renamed Eutelsat Americas in March 2014..

2015 April 14 - . 20:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • Dragon CRS-6 - . Mass: 9,500 kg (20,900 lb). Nation: USA. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Duration: 37.00 days. Decay Date: 2015-05-21 . USAF Sat Cat: 40588 . COSPAR: 2015-021A. Apogee: 360 km (220 mi). Perigee: 205 km (127 mi). Inclination: 51.6000 deg.

    ISS resupply mission. Delivered into a 206 x 357 km orbit. Attempted recovery of the Falcon 9's first stage failed. It was flown down to the barge 'Just Read The Instructions' in the Atlantic but a stuck valve caused control problems in the final burn and the stage crash-landed. The Dragon itself arrived at ISS on April 17. The SSRMS arm grappled CRS-6 at 10:55 GMT and berthed it on the Harmony module at 13:29 GMT. After unloading and packing with materials to be returned to earth, the cargo ship was unberthed again around 09:29 GMT May 21, released at 11:04 GMT, and splashed down in the Pacific at 16:42 GMT.

    CRS-6 carried 16 cubesats: 14 3U-size Flock-1e for Planet Labs, one Arkyd-3R for Planetary Resources (also a 3U) and a 1U cubesat, Centennial-1, for Booz Allen Hamilton carrying an Air Force Research Lab imaging experiment. The cubesats were transferred to the Kibo module after Dragon docking and later ejected into orbit via the NanoRacks deployers and the Kibo robot arm. CRS-6 also carried a number of mice aboard the Rodent Research 2 package, and a 20 kg microgravity-qualified Lavazza espresso machine.


2015 April 27 - . 23:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • TurkmenAlem52E/Monacosat - . Payload: Spacebus 4000C2. Mass: 4,700 kg (10,300 lb). Nation: Turkmenistan. Class: Communications. Type: Communications satellite. Spacecraft: Spacebus 4000. USAF Sat Cat: 40617 . COSPAR: 2015-023A. Apogee: 35,798 km (22,243 mi). Perigee: 35,776 km (22,230 mi). Inclination: 0.0200 deg. Period: 1,436.10 min.

    Communications satellite owned by the Turkmenistan National Space Agency and the Turkmen Ministry of Communications, which operated 26 Ku-band transponders. The GEO orbital slot was assigned to Monaco and its GEO telecom operator Space Systems International; Monaco had a further 12 Ku-band transponders on the satellite for the MonacoSat portion of the payload, operated by the SES company on its behalf. Stationed in geosynchronous orbit at 52.0 deg east.


2015 June 28 - . 14:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1. FAILURE: Failed close to the end of stage 1 burn. A strut holding an internal helium pressurization tank broke during second stage initialization at T+139 sec at 45 km altitude. The resulting overpressure caused the second stage to blow apart.. Failed Stage: 2.
  • Dragon CRS-7 - . Mass: 9,500 kg (20,900 lb). Nation: USA. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Apogee: 45 km (27 mi). Perigee: -6,250 km (-6,250 mi). Inclination: 51.6000 deg. Dragon capsule CRS-7 was lost in the Atlantic, with its cargo which included 8 Flock 1f cubesats, the IDA-1 docking adapter, spacesuit EMU 3017, and the second NORS oyxgen recharge tank (the first one was lost on the Orb-3 failure in 2014)..

2015 December 22 - . 01:29 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • Orbcomm FM105 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41181 . COSPAR: 2015-081C. Apogee: 657 km (408 mi). Perigee: 613 km (380 mi). Inclination: 47.0000 deg.
  • Orbcomm FM108 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41187 . COSPAR: 2015-081J. Apogee: 658 km (408 mi). Perigee: 614 km (381 mi). Inclination: 47.0000 deg.
  • Orbcomm FM110 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41182 . COSPAR: 2015-081D. Apogee: 657 km (408 mi). Perigee: 614 km (381 mi). Inclination: 47.0000 deg.
  • Orbcomm FM112 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41184 . COSPAR: 2015-081F. Apogee: 657 km (408 mi). Perigee: 614 km (381 mi). Inclination: 47.0000 deg.
  • Orbcomm FM113 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41185 . COSPAR: 2015-081G. Apogee: 657 km (408 mi). Perigee: 613 km (380 mi). Inclination: 47.0000 deg.
  • Orbcomm FM114 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41179 . COSPAR: 2015-081A. Apogee: 655 km (406 mi). Perigee: 613 km (380 mi). Inclination: 47.0000 deg.

    SpaceX launched their first Falcon 9 since the CRS-7 failure. Core F9-021 was also the first 'full thrust' Falcon 9 with improved performance. The primary payload was a cluster of Orbcomm OG2 comm satellites. The 11 OG2s and one non-separating mass simulator were mounted on the circumference of a dispenser consisting of three ESPA rings attached to the second stage. After the satellites were deployed, the second stage was deorbited. The first stage shut down at an altitude of around 80 km and a velocity of 1.65 km/s (Earth-relative), just before stages 1 and 2 separated. The stage reached an apogee of around 200 km before beginning a boostback burn to kill its eastward velocity and send it back towards Florida. Following a third reentry burn the stage landed back at Cape Canaveral's Landing Zone 1 (former pad 13). The fully controlled vertical landing came at 0139 UTC Dec 22.

  • Orbcomm FM115 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41186 . COSPAR: 2015-081H. Apogee: 654 km (406 mi). Perigee: 612 km (380 mi). Inclination: 47.0000 deg.
  • Orbcomm FM116 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41189 . COSPAR: 2015-081L. Apogee: 656 km (407 mi). Perigee: 613 km (380 mi). Inclination: 47.0000 deg.
  • Orbcomm FM117 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41188 . COSPAR: 2015-081K. Apogee: 656 km (407 mi). Perigee: 614 km (381 mi). Inclination: 47.0000 deg.
  • Orbcomm FM118 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41183 . COSPAR: 2015-081E. Apogee: 654 km (406 mi). Perigee: 613 km (380 mi). Inclination: 47.0000 deg.
  • Orbcomm FM119 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: SN-100. USAF Sat Cat: 41180 . COSPAR: 2015-081B. Apogee: 654 km (406 mi). Perigee: 613 km (380 mi). Inclination: 47.0000 deg.

2016 January 17 - . 18:42 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.1.
  • Jason-3 - . Nation: USA. Class: Earth. Type: Climate satellite. USAF Sat Cat: 41240 . COSPAR: 2016-002A. Apogee: 1,320 km (820 mi). Perigee: 1,295 km (804 mi). Inclination: 66.0000 deg.

    Falcon 9 F9-019 was the last version 1.1 core. It took off soutbound from Space Launch Complex 4-East at Vandenberg AFB at 1842 UTC, entered a 175 x 1321 km x 66 deg transfer orbit at 1851 UTC, and circularized the orbit at apogee with spacecraft separation at 1938 UTC. The second stage was then deorbited with a burn at around 1945 UTC lowering perigee into the atmosphere, leading to a reentry around 2030 UTC over the northeastern Pacific. Meanwhile the first stage completed a boostback burn and flew down to the center of the target on the ASDS ship "Just Read The Instructions" in the Pacific at about 1852 UTC. However, on landing one of the deployed legs failed to lock in place and the vehicle toppled and was destroyed. Jason-3 was the fourth in a series of French/US satellites carrying the Poseidon altimeter to measure sea surface height across the world, an important parameter in climate change studies. The satellites also carry microwave radiometers. The first Poseidon satellite was the TOPEX/Poseidon research experiment which operated from 1992 to 2006. This was followed on by the progressively more operational Jason series; Jason-1 in 2001-2013, and the still operational Jason-2 launched in 2008. The 550 kg satellite was built by Thales Alenia (Cannes) using the Proteus bus and owned by the French space agency CNES. Lead agencies for the overall Jason-3 program are the US weather agency NOAA and the European weather satellite group EUMETSAT, taking over from CNES and JPL who led the earlier missions.


2016 March 4 - . 23:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • SES-9 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: Eurostar 3000. USAF Sat Cat: 41380 . COSPAR: 2016-013A. Apogee: 41,649 km (25,879 mi). Perigee: 28,569 km (17,751 mi). Inclination: 0.5000 deg.

    Falcon 9 rocket F9-022 first stage flew to an apogee of around 160 km and descended 660 km downrange to crash on the droneship "Of Course I Still Love You" at about 73.8W 28.3N, in a technology test to develop experience for future landing attempts. The second stage accelerated to reach a 160 x 531 km x 28.5 deg parking orbit at 2344 UTC and then reignited at 0002 UTC Mar 5 to reach a 334 x 40648 km x 28.0 deg transfer orbit. The SES-9 payload separated at 0006 UTC. It was a Boeing 702HP satellite with a mass of about 5270 kg and a Ku-band communications payload for delivery of services to Asia and the Indian Ocean from 108.2E. By Mar 14, SES-9 was in a 28569 x 41649 km x 0.5 deg orbit.


2016 April 8 - . 20:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • Dragon CRS-8 - . Nation: USA. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Decay Date: 2016-05-11 . USAF Sat Cat: 41452 . COSPAR: 2016-024A. Apogee: 353 km (219 mi). Perigee: 209 km (129 mi). Inclination: 51.7000 deg.

    Falcon 9 F9-023 launched a Dragon with the Bigelow BEAM inflatable module experiment in its trunk. CRS-8 was scheduled to arrive at ISS on Apr 10. The F9-023 first stage performed boostback and reentry burns to successfully land on the ship "Of Course I Still Love You" at 78.50W 30.50N in the Atlantic. This was the second succesful reentry and landing of a Falcon 9 first stage, following the Dec 2015 landing of F9-021 at Cape Canaveral. Dragon CRS-8 arrived at the capture point 10m from the Harmony module at 1115 UTC Apr 10. The Canadarm-2 grappled it at 1123 UTC and berthed it on Harmony's nadir CBM port at 1357 UTC. At about 0600 UTC on Apr 16 the BEAM module was extracted from Dragon's trunk; BEAM was installed on the Tranquility module's aft port at 0937 UTC Apr 16. CRS-8 was unberthed at 1102 UTC May 11 and released into space at 1319 UTC. After a deorbit burn at 1801 UTC it splashed down around 120.1W 31.4N, off the coast of California, at 1851 UTC. The CRS-8 Dragon brought back to Earth the EMU 3011 spacesuit implicated in the Parmitano and Kopra water leaks. EMU 3011 was launched into space on mission STS-132 in 2010. Also brought back aboard CRS-8 were the Flock-2b 11 and 12 cubesats which failed to deploy from the ISS last October. Nanoracks deployers NRCSD-5 and NRCSD-6 were also returned to Earth on CRS-8. The Bigelow Expansion Activity Module (BEAM) remains attached to Node 3. On May 28 the module expansion was successfuly carried out; the process of expanding and pressurizing the module took from 1305 to 2044 UTC. The diameter of the module was 3.2metres; its length was increased by 1.8m to about 3.7m.


2016 May 6 - . 05:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • JCSAT 14 - . Payload: JCSAT 2B. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 41471 . COSPAR: 2016-028A. Apogee: 35,864 km (22,284 mi). Perigee: 35,758 km (22,218 mi). Inclination: 0.0000 deg.

    Placed in geosynchronous orbit at 176 deg E. SSL-1300 comms platform built by SSL-MDA, launched by into geotransfer orbit. The Falcon 9 first stage landed downrange on the SpaceX droneship Of Course I Still Love You. Each of the JCSAT series satellites has two names - essentially, a name that identifies the physical satellite and a name that marks the service it was providing at a specific orbital slot.


2016 May 27 - . 21:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • Thaicom 8 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: GEOStar-2. USAF Sat Cat: 41552 . COSPAR: 2016-031A. Apogee: 90,190 km (56,040 mi). Perigee: 347 km (215 mi). Inclination: 21.2000 deg. SpaceX launched the Thaicom-8 satellite to a high apogee supersynchronous transfer orbit. The Falcon 9 first stage landed safely on the 'Of Course I Still Love You' in the Atlantic. Orbital Star-2.3 bus..

2016 June 15 - . 14:29 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • Eutelsat 117 West B - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: HS 702. USAF Sat Cat: 41589 . COSPAR: 2016-038B. Apogee: 62,761 km (38,997 mi). Perigee: 399 km (247 mi). Inclination: 24.7000 deg. Eutelsat 117 West B (the former Satmex 9) to provide service for Eutelsat Americas, supplementing Satmex 8 (now renamed Eutelsat 117 West A). Boeing BSS-702SP satellite with all-electric-propulsion, which use ion engines to complete the trip to GEO..
  • ABS-2A - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: HS 702. USAF Sat Cat: 41588 . COSPAR: 2016-038A. Apogee: 62,649 km (38,928 mi). Perigee: 395 km (245 mi). Inclination: 24.6000 deg.

    The Falcon 9 vehicle 26 second stage made two burns to deliver a pair of Boeing BSS-702SP satellites to supersynchronous transfer orbits. This was the second matched pair of all-electric-propulsion payloads, which use ion engines to complete the trip to GEO. ABS-2A will supplement Asia Broadcast Satellite's ABS-2


2016 July 18 - . 04:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • Dragon CRS-9 - . Nation: USA. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Decay Date: 2016-08-26 . USAF Sat Cat: 41672 . COSPAR: 2016-046A. Apogee: 355 km (220 mi). Perigee: 204 km (126 mi). Inclination: 51.6000 deg.

    SpaceX's Dragon CRS-9 cargo ship carried the IDA-2 docking adapter and spacesuit EMU 3006. The Falcon 9 first stage returned to Cape Canaveral for a landing at Landing Complex 1. The second stage was deorbited south of Australia. CRS-9 arrived at the ISS on Jul 20; it was grappled by the SSRMS at 1056 UTC and berthed at Harmony nadir at 1403 UTC. The IDA-2 docking adapter will be installed on the end of the old PMA-2 Shuttle docking port to conver On Aug 25 at about 2100 UTC the SSRMS (Canadarm-2) unberthed Dragon CRS-9 from the Harmony module. At 1011 UTC the Dragon was released into orbit; at 1456 UTC Dragon fired its Draco thrusters in a deorbit burn which sent it plunging into the atmosphere at about 1520 UTC. The empty trunk was jettisoned at 1513 UTC. Dragon splashed down off the coast of Baja at 1547 UTC. Spacesuit EMU 3005 was returned to Earth aboard CRS-9.


2016 August 14 - . 05:26 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. Launch Pad: Cape Canaveral SLC40. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • JCSAT-16 - . Nation: Japan. Class: Communications. Type: Communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 41729 . COSPAR: 2016-050A. Apogee: 36,183 km (22,483 mi). Perigee: 151 km (93 mi). Inclination: 20.9000 deg.

    JCSAT-16 satellite for Sky Perfect JSAT, a Japanese satellite broadcasting company. The second stage put JCSAT-16 in geostationary transfer orbit, while the first stage completed a ballistic trajectory and landed on the droneship 'Of Course I Still Love You' in the Atlantic. After its first orbit raising burn, JCSAT-16 was in a 5581 x 35905 km x 10.8 deg orbit. The Falcon 9 second stage was in an 82 x 34111 km geotransfer orbit, ensuring quick orbital decay.


2017 January 14 - . 17:54 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • Iridium Next SV01 - . Payload: Iridium 106. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41917 . COSPAR: 2017-003A. Apogee: 626 km (388 mi). Perigee: 617 km (383 mi). Inclination: 86.7000 deg.

    The first cluster of second generation communications satellites for Iridium Communications was launched, aboard the first SpaceX Falcon 9 to fly since the Amos-6 pad accident the previous year. The Falcon 9 placed all ten satellites in the correct orbit, and the first stage landed on the barge 'Just Read The Instructions'. The Falcon 9 second stage was expected to be deorbited over Antarctica. However, JSpOC was tracking 11 objects in orbit rather than the expected The Iridium satellites carry communications payloads for global mobile communications coverage as well as Aireon ADS-B airplane data relay payloads and, on four of the 10 satellites, AIS ship tracking payloads for the Canadian company ExactEarth.

  • Iridium Next SV02 - . Payload: Iridium 103. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41918 . COSPAR: 2017-003B. Apogee: 622 km (386 mi). Perigee: 610 km (370 mi). Inclination: 86.7000 deg.
  • Iridium Next SV03 - . Payload: Iridium 109. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41919 . COSPAR: 2017-003C. Apogee: 621 km (385 mi). Perigee: 608 km (377 mi). Inclination: 86.7000 deg.
  • Iridium Next SV04 - . Payload: Iridium 102. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41920 . COSPAR: 2017-003D. Apogee: 621 km (385 mi). Perigee: 608 km (377 mi). Inclination: 86.7000 deg.
  • Iridium Next SV05 - . Payload: Iridium 105. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41921 . COSPAR: 2017-003E. Apogee: 619 km (384 mi). Perigee: 605 km (375 mi). Inclination: 86.7000 deg.
  • Iridium Next SV06 - . Payload: Iridium 104. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41922 . COSPAR: 2017-003F. Apogee: 621 km (385 mi). Perigee: 610 km (370 mi). Inclination: 86.7000 deg.
  • Iridium Next SV07 - . Payload: Iridium 114. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41923 . COSPAR: 2017-003G. Apogee: 617 km (383 mi). Perigee: 610 km (370 mi). Inclination: 86.7000 deg.
  • Iridium Next SV08 - . Payload: Iridium 108. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41924 . COSPAR: 2017-003H. Apogee: 622 km (386 mi). Perigee: 607 km (377 mi). Inclination: 86.7000 deg.
  • Iridium Next SV09 - . Payload: Iridium 112. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41925 . COSPAR: 2017-003J. Apogee: 621 km (385 mi). Perigee: 604 km (375 mi). Inclination: 86.7000 deg.
  • Iridium Next SV10 - . Payload: Iridium 111. Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 41926 . COSPAR: 2017-003K. Apogee: 622 km (386 mi). Perigee: 609 km (378 mi). Inclination: 86.7000 deg.

2017 February 19 - . 14:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • Dragon CRS-10 - . Nation: USA. Class: Manned. Type: Manned logistics spacecraft. Spacecraft: Dragon. Decay Date: 2017-03-19 . USAF Sat Cat: 42053 . COSPAR: 2017-009A. Apogee: 359 km (223 mi). Perigee: 204 km (126 mi). Inclination: 51.6000 deg.

    Dragon CRS-10 was launched from Kennedy Space Center LC39A aboard a SpaceX Falcon 9; the first non-NASA launch operation ever from KSC and the first launch from KSC since 2011. NASA KSC abuts USAF Cape Canaveral Air Force Station on its northern side; previous Falcon 9 east coast launches were from SLC40 at Cape Canaveral. On this flight the Falcon 9 first stage, B1031, landed at Cape Canaveral's LZ1. CRS-10 carried three packages in its trunk for installation on ISS. The USAF Space Test Program's STP-H5 experiment suite includes a NASA lightning sensor and NRL ionosphere-study experiments. SAGE-III IP continued a long series of NASA ozone monitoring studies. SAGE-III NVP (Nadir Viewing Platform) was an adapter which will allow the IP to be installed sideways on the ISS ELC platform. On Feb 22 Dragon aborted its approach to the ISS at a distance of 1.2 km due to a navigation system error. Rendezvous was rescheduled for Feb 23 when Dragon was grappled by the SSRMS at 1044 UTC, then berthed on the Harmony module. he Dextre and Canadarm-2 robot arms were used to unload the experiments in the Dragon external cargo trunk on Feb 25-Mar 7 in a rather complicated sequence involving Dextre's two main arms and its EOTP (Enhanced ORU Temp Platform, a storage position). The experiments were installed on the Express Logistics Carriers ELC-1 and ELC-4 on the station truss. Older experiments from ELC-1, ELC-2 and ELC-4 were removed for disposal. These incuded the These included the OPALS laser comm payload launched in 2014; the RRM Robotic Refuelling Mission experiment of 2011, and the MISSE FSE adapter that mounted the MISSE 7 and 8 materials exposure experiments of 2009. These packages, with a total mass of 811 kg, were destroyed on reentry when the Dragon trunk was jettisoned following Dragon's deorbit burn. Dragon was unberthed from the Harmony module at 2145 UTC Mar 18 and released by Canadarm-2 at 0911 UTC Mar 19. After a deorbit burn at 1355 UTC it splashed down in the Pacific near 31 44N 121 15W at 1446 UTC, carrying 1652 kg of ISS return cargo. This return cargo includd 104 kg of unspecified EVA equipment.


2017 March 16 - . 06:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • Echostar 23 - . Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 42070 . COSPAR: 2017-014A. Apogee: 35,903 km (22,309 mi). Perigee: 179 km (111 mi). Inclination: 22.4000 deg. Echostar 23 communications sat to provide television services to Brazil and Latin America for Echostar Corp. It was launched by Falcon 9 F31; the first stage on this mission did not have landing legs and no recovery was attempted..

2017 March 30 - . 22:27 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Falcon. Launch Vehicle: Falcon 9 v1.2.
  • SES-10 - . Nation: Europe. Class: Communications. Type: Communications satellite. USAF Sat Cat: 42432 . COSPAR: 2017-017A. Apogee: 35,673 km (22,166 mi). Perigee: 246 km (152 mi). Inclination: 26.2000 deg.

    SpaceX launched the 5300 kg SES-10 communications satellite into a 246 x 35673 km x 26.2 deg geotransfer orbit. After several orbit raising burns SES-10 reached a 35775 x 35796 km x 0.1 deg geostationary orbit at 68.5W on Apr 11. The Falcon 9 F9-033 second stage reduced its apogee slightly, ending up in a 235 x 33407 km orbit. The first stage was Falcon 9 core B1021, which had previously flown on the F9-023/CRS-8 mission in Apr 2016. The reused stage performed successfully and landed for a second time on the ASDS drone ship 'Of Course I Still Love You' in the Atlantic.



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