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Cape Canaveral LC37B
Part of Cape Canaveral Family
Saturn I, Delta IV launch complex. Complexes 34 and 37 were designed to support NASA's Saturn I and Saturn IB program. Complex 37 was built in 1962, and it was occupied by NASA in January 1963. Complex 37 supported eight Saturn I and Saturn IB missions, including the first flight of an unmanned Apollo lunar module, between 29 January 1964 and 23 January 1968. Complexes 34 and 37 were mothballed in November 1971, and their service structures were scrapped in April 1972. NASA retained control of both complexes, and both sites became NASA tour stops.

First Launch: 1964-01-29. Last Launch: 2014-07-28. Number: 30 . Longitude: -80.5644 deg. Latitude: 28.5313 deg.

Spacecraft: ANGELS, GSSAP, Quasar, Apollo LM, Apollo CSM, Jupiter nose cone, Pegasus satellite, DSP, DSCS III, HS 601, Advanced Orion, Spacebus 3000, HS 702, 3CSat, GPS Block 2F, Orion. Launch Vehicles: Saturn I, Saturn IB, Uprated Saturn I, Delta 4M+(4,2), Delta 4M, Delta 4H, Delta 4M+(5,4). Launch Sites: Cape Canaveral.



1964 January 29 - . 16:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn I.
  • Saturn 5 - . Payload: Saturn-SA 5. Mass: 17,100 kg (37,600 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Technology. Type: Re-entry test vehicle. Spacecraft Bus: Jupiter nose cone. Spacecraft: Jupiter nose cone. Decay Date: 1966-04-30 . USAF Sat Cat: 744 . COSPAR: 1964-005A. Apogee: 740 km (450 mi). Perigee: 274 km (170 mi). Inclination: 31.4000 deg. Period: 94.80 min.

    First first mission of Block II Saturn with two live stages. SA-5, a vehicle development flight, was launched from Cape Kennedy Complex 37B at 11:25:01.41, e.s.t. This was the first flight of the Saturn I Block II configuration (i.e., lengthened fuel tanks in the S-1 and stabilizing tail fins), as well as the first flight of a live (powered) S-IV upper stage. The S-1, powered by eight H-1 engines, reached a full thrust of over 680,400 kilograms (1.5 million pounds) the first time in flight. The S-IV's 41,000 kilogram (90,000-pound-thrust cluster of six liquid-hydrogen RL-10 engines performed as expected. The Block II SA-5 was also the first flight test of the Saturn I guidance system.


1964 May 28 - . 17:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn I.
  • Saturn 6 - . Payload: Apollo CSM Boilerplate 13. Mass: 16,900 kg (37,200 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft Bus: Apollo. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1964-06-01 . USAF Sat Cat: 800 . COSPAR: 1964-025A. Apogee: 204 km (126 mi). Perigee: 179 km (111 mi). Inclination: 31.7000 deg. Period: 88.20 min. Apollo Saturn Mission A-101, using CM BP-13 atop SA-6 Saturn I launch vehicle, launched at Cape Kennedy, Fla., to prove spacecraft/launch vehicle compatibility. Boilerplate CSM, LM adapter, LES. LES jettison demonstrated..

1964 September 18 - . 16:22 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn I.
  • Saturn 7 - . Payload: Apollo CSM Boilerplate 15. Mass: 16,700 kg (36,800 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft Bus: Apollo. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1964-09-22 . USAF Sat Cat: 883 . COSPAR: 1964-057A. Apogee: 215 km (133 mi). Perigee: 181 km (112 mi). Inclination: 31.7000 deg. Period: 88.50 min. Apollo systems test. Third orbital test. First closed-loop guidance test..

1965 February 16 - . 14:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn I.
  • Pegasus 1 - . Payload: Pegasus 1. Mass: 10,400 kg (22,900 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Earth. Type: Micrometeoroid satellite. Spacecraft Bus: Pegasus satellite. Spacecraft: Pegasus satellite. Decay Date: 1978-09-17 . USAF Sat Cat: 1085 . COSPAR: 1965-009A. Apogee: 726 km (451 mi). Perigee: 510 km (310 mi). Inclination: 31.7000 deg. Period: 97.00 min.

    A Saturn I vehicle SA-9 launched a multiple payload into a high 744 by 496 km (462 by 308 mi) earth orbit. The rocket carried a boilerplate (BP) CSM (BP-16) and, fitted inside the SM, the Pegasus I meteoroid detection satellite. This was the eighth successful Saturn flight in a row, and the first to carry an active payload. BP-16's launch escape tower was jettisoned following second-stage S-IV ignition. After attaining orbit, the spacecraft were separated from the S-IV. Thereupon the Pegasus I's panels were deployed and were ready to perform their task, i.e., registering meteoroid impact and relaying the information to the ground.

  • Apollo-Model 3 - . Payload: Apollo CSM Boilerplate 16. Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1985-07-10 . USAF Sat Cat: 1088 . COSPAR: 1965-009B. Apogee: 736 km (457 mi). Perigee: 500 km (310 mi). Inclination: 31.7000 deg. Period: 97.06 min.

1965 May 25 - . 07:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn I.
  • Pegasus 2 - . Payload: Pegasus 2. Mass: 10,464 kg (23,069 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Earth. Type: Micrometeoroid satellite. Spacecraft Bus: Pegasus satellite. Spacecraft: Pegasus satellite. Decay Date: 1979-11-03 . USAF Sat Cat: 1381 . COSPAR: 1965-039A. Apogee: 740 km (450 mi). Perigee: 502 km (311 mi). Inclination: 31.7000 deg. Period: 97.00 min.

    Pegasus 2 was a meteoroid detection satellite. The Saturn I launch vehicle (SA-8) placed the spacecraft, protected by a boilerplate CSM (BP-26), into a 740-by-509-km (460-by-316-mi) orbit. Once in orbit, the dummy CSM was jettisoned. Pegasus 2, still attached to the second stage of the launch vehicle, then deployed its 29-m (96-ft) winglike panels. Within several hours, the device began registering meteoroid hits.

  • Apollo-Model 4 - . Payload: Apollo CSM Boilerplate 26. Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1989-07-08 . USAF Sat Cat: 1385 . COSPAR: 1965-039B. Apogee: 739 km (459 mi). Perigee: 511 km (317 mi). Inclination: 31.7000 deg. Period: 97.21 min.

1965 July 30 - . 13:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn I.
  • Pegasus 3 - . Payload: Pegasus 3. Mass: 10,500 kg (23,100 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Earth. Type: Micrometeoroid satellite. Spacecraft Bus: Pegasus satellite. Spacecraft: Pegasus satellite. Decay Date: 1969-08-04 . USAF Sat Cat: 1467 . COSPAR: 1965-060A. Apogee: 449 km (278 mi). Perigee: 441 km (274 mi). Inclination: 28.9000 deg. Period: 93.40 min.

    NASA launched Pegasus 3, third of the meteoroid detection satellites, as scheduled at 8:00 a.m. EST, from Cape Kennedy. As earlier, an Apollo spacecraft (boilerplate 9) served as the payload's shroud. This flight (SA-10) marked the end of the Saturn I program, which during its seven-year lifetime had achieved 10 straight successful launches and had contributed immeasurably to American rocket technology.

  • Apollo-Model 5 - . Payload: Apollo CSM Boilerplate 9A. Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1975-11-22 . USAF Sat Cat: 1468 . COSPAR: 1965-060B. Apogee: 536 km (333 mi). Perigee: 521 km (323 mi). Inclination: 28.8000 deg. Period: 95.21 min.

1966 July 5 - . 14:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Uprated Saturn I.
  • Apollo 203 - . Payload: Saturn S-IVB-203. Mass: 26,500 kg (58,400 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Decay Date: 1966-07-05 . USAF Sat Cat: 2289 . COSPAR: 1966-059A. Apogee: 212 km (131 mi). Perigee: 183 km (113 mi). Inclination: 31.9000 deg. Period: 88.50 min.

    First orbital test Saturn IB; no spacecraft. AS-203 lifted off from Launch Complex 37, Eastern Test Range, at 10:53 a.m. EDT in the second of three Apollo-Saturn missions scheduled before manned flight in the Apollo program. All objectives - to acquire flight data on the S-IVB stage and instrument unit - were achieved.

    The uprated Saturn I - consisting of an S-IB stage, S-IVB stage, and an instrument unit - boosted an unmanned payload into an original orbit of 185 by 189 kilometers. The inboard engine cutoff of the first stage occurred after 2 minutes 18 seconds of flight and the outboard engine cutoff was 4 seconds later. The S-IVB engine burned 4 minutes 50 seconds. No recovery was planned and the payload was expected to enter the earth's atmosphere after about four days.


1968 January 22 - . 22:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn IB.
  • Apollo 5 - . Payload: Apollo LM-1. Mass: 14,360 kg (31,650 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar lander. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LM. Decay Date: 1968-02-12 . USAF Sat Cat: 3107 . COSPAR: 1968-007B. Apogee: 374 km (232 mi). Perigee: 169 km (105 mi). Inclination: 31.6000 deg. Period: 89.90 min.

    NASA launched Apollo 5 - the first, unmanned LM flight - on a Saturn IB from KSC Launch Complex 37B at 5:48:08 p.m. EST. Mission objectives included verifying operation of the LM structure itself and its two primary propulsion systems, to evaluate LM staging, and to evaluate orbital performances of the S-IVB stage and instrument unit. Flight of the AS-204 launch vehicle went as planned, with nosecone (replacing the CSM) jettisoned and LM separating. Flight of LM-1 also went as planned up to the first descent propulsion engine firing. Because velocity increase did not build up as quickly as predicted, the LM guidance system shut the engine down after only four seconds of operation, boosting the LM only to a 171 x 222 km orbit. Mission control personnel in Houston and supporting groups quickly analyzed the problem. They determined that the difficulty was one of guidance software only (and not a fault in hardware design) and pursued an alternate mission plan that ensured meeting the minimum requirements necessary to achieve the primary objectives of the mission. The ascent stage separated and boosted itself into a 172 x 961 km orbit. After mission completion at 2:45 a.m. EST January 23, LM stages were left in orbit to reenter the atmosphere later and disintegrate. Apollo program directors attributed success of the mission to careful preplanning of alternate ways to accomplish flight objectives in the face of unforeseen events.


2002 November 20 - . 22:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • Eutelsat W5 - . Payload: Spacebus 3000B2. Mass: 3,170 kg (6,980 lb). Nation: Europe. Agency: Eutelsat. Manufacturer: Cannes. Program: Eutelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: Spacebus 3000. Spacecraft: Spacebus 3000. USAF Sat Cat: 27554 . COSPAR: 2002-051A. Apogee: 35,801 km (22,245 mi). Perigee: 35,788 km (22,237 mi). Inclination: 0.1000 deg. Period: 1,436.50 min.

    Maiden flight of the Delta 4 EELV booster, delayed due to development problems from January and November 2001, April 30, July 15, August 31, October 9, November 3, 16 and 19. EUTELSAT W5 was a European (EUTELSAT Consortium) geostationary communication spacecraft. EUTELSAT W5 was to provide voice, video, and Internet services to all countries in western Europe, central Asia, and the Indian subcontinent through its 24 Ku-band transponders after being parked over 70.5 E longitude. As of 2007 Mar 10 located at 70.55E drifting at 0.004W degrees per day.


2003 March 11 - . 00:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M.
  • USA 167 - . Payload: DSCS III A-3. Mass: 1,235 kg (2,722 lb). Nation: USA. Agency: USAF. Program: DSCS. Class: Communications. Type: Military communications satellite. Spacecraft Bus: DSCS III. Spacecraft: DSCS III. USAF Sat Cat: 27691 . COSPAR: 2003-008A. First flight of a fully cryogenic orbital launch vehicle. Delayed from December 2001, February 2, 6, 8, 11, 12 and March 8 2003. Satellite mas 2,733 kg with kick stage..

2003 August 29 - . 23:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M.
  • USA 170 - . Payload: DSCS-3-B6. Mass: 1,235 kg (2,722 lb). Nation: USA. Agency: USAF. Class: Communications. Type: Military communications satellite. Spacecraft Bus: DSCS III. Spacecraft: DSCS III. USAF Sat Cat: 27875 . COSPAR: 2003-040A. Delayed from July 1, 11 and 23, then August 3 and 28..

2004 December 21 - . 21:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4H.
  • USA 181 - . Payload: Demosat / HLVOLSDP. Mass: 5,993 kg (13,212 lb). Nation: USA. Agency: USAF. USAF Sat Cat: 28500 . COSPAR: 2004-050A. Apogee: 36,413 km (22,625 mi). Perigee: 19,035 km (11,827 mi). Inclination: 13.4790 deg. Period: 1,044.23 min.

    Mass model payload. First launch of a heavy EELV. The demonstration satellite was supposed to have been inserted into a sub-geosynchronous 36,350 km circular orbit but was instead deployed in a 19,035 km x 36,413 km orbit following a 5-hour and 50-minute flight. A shorter than expected first burn of the Centaur upper stage led to an orbit well below that planned. The Air Force EELV program office claimed that the primary flight objectives were accomplished. These included the heavy boost phase, flight of the new five-meter diameter Centaur upper stage and five-meter payload fairing, extended coast, upper stage third burn and payload separation, and activation and usage of Space Launch Complex 37B. Delayed from September 2003, July 3, September 10, November 18, December 10, 11 and 12.

  • 3CSat 1 Sparkie - . Payload: Nanosat 2. Mass: 15 kg (33 lb). Nation: USA. Agency: USAF. Manufacturer: New Mexico. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: 3CSat. Spacecraft: 3CSat. COSPAR: 2004-050x.

    One of a pair of student-built nanosats for stero cloud imagery. The satellites did not contact the ground after separation from the booster in a lower-than-planned orbit and their fate was unclear. It was believed that they separated but re-entered rapidly from the 105 km perigee orbit.

  • 3CSat 2 Ralphie - . Payload: Nanosat 2. Mass: 15 kg (33 lb). Nation: USA. Agency: USAF. Manufacturer: Colorado. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: 3CSat. Spacecraft: 3CSat. COSPAR: 2004-050x.

2006 May 24 - . 22:11 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • GOES 13 - . Mass: 3,199 kg (7,052 lb). Nation: USA. Agency: NOAA. Manufacturer: Boeing. Program: GOES. Class: Earth. Type: Weather satellite. Spacecraft Bus: HS 601. Spacecraft: HS 601. USAF Sat Cat: 29155 . COSPAR: 2006-018A. Apogee: 35,791 km (22,239 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.5000 deg. Period: 1,436.00 min.

    GOES-13 carried weather imager and sounder instruments, a space environment monitor, and a soft X-ray solar imaging telescope. Mass was 1543 kg empty. It joined GOES 10 (operating as GOES-WEST), GOES 12 (operating as GOES-EAST) and GOES 11 (on standby, set to replace GOES-10 on June 27). As of 2007 Mar 11 located at 105.26W drifting at 0.008W degrees per day.


2007 November 11 - . 01:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4H.
  • USA 197 - . Payload: DSP-1 Block 18 F23. Mass: 2,270 kg (5,000 lb). Nation: USA. Agency: NSA. Manufacturer: TRW. Class: Surveillance. Type: Early warning satellite. Spacecraft Bus: DSP. Spacecraft: DSP. USAF Sat Cat: 32287 . COSPAR: 2007-054A. Apogee: 36,325 km (22,571 mi). Perigee: 35,800 km (22,200 mi). Inclination: 0.0000 deg. Period: 1,436.00 min.

    Final DSP launch. The series was to be replaced by SBIRS, which was in the middle of a troubled development program. The Delta 4H performed well after problems on its first launch. The RL10-powered upper stage made three burns before releasing the early-warning satellite in its final geosynchronous orbit. Total cost of the flight was $700 million, with the DSP worth $400 million. The DSP carried a special 25 kg supplementary payload designed to detect extremely small nuclear tests in space. The payload was required by a secret White House/National Security Council directive to detect any attempted covert nuclear tests by Iran or North Korea.


2009 January 18 - . 02:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4H.
  • USA 202 - . Payload: Orion 6 / NROL-26. Mass: 5,400 kg (11,900 lb). Nation: USA. Agency: NRO. Class: Surveillance. Type: ELINT. Spacecraft Bus: Advanced Orion. Spacecraft: Advanced Orion. USAF Sat Cat: 33490 . COSPAR: 2009-001A. Apogee: 38,077 km (23,659 mi). Perigee: 35,943 km (22,333 mi). Inclination: 3.0000 deg. Period: 1,440.00 min. Classified signals intelligence satellite. It was speculated that it was a large-antenna spacecraft with the same mission as earlier Rhyolite, Aquacade, Magnum, and Orion missions..

2009 June 27 - . 22:51 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • GOES 14 - . Payload: HS 601HP. Mass: 3,210 kg (7,070 lb). Nation: USA. Agency: Martin. Program: GOES. Class: Earth. Type: Weather satellite. Spacecraft Bus: HS 601. Spacecraft: HS 601. USAF Sat Cat: 35491 . COSPAR: 2009-033A. Apogee: 35,788 km (22,237 mi). Perigee: 35,786 km (22,236 mi). Inclination: 0.5000 deg. Period: 1,436.10 min. Geostationary Operational Environmental Satellite..

2009 December 6 - . 01:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(5,4).
  • USA 211 - . Payload: WGS 3. Mass: 5,990 kg (13,200 lb). Nation: USA. Agency: Martin. Class: Communications. Type: Military communications satellite. Spacecraft Bus: HS 702. Spacecraft: HS 702. USAF Sat Cat: 36108 . COSPAR: 2009-068A. Apogee: 64,827 km (40,281 mi). Perigee: 31,268 km (19,428 mi). Inclination: 0.6000 deg. Period: 2,106.00 min. US Army Wideband Global Satcom, carried X-band and Ka-band communications payloads..

2010 March 4 - . 23:57 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • GOES 15 - . Mass: 3,240 kg (7,140 lb). Nation: USA. Agency: Martin. Program: GOES. Class: Earth. Type: Weather satellite. Spacecraft Bus: HS 601. Spacecraft: HS 601. USAF Sat Cat: 36411 . COSPAR: 2010-008A. Apogee: 35,803 km (22,246 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.3000 deg. Period: 1,436.10 min.

2010 May 28 - . 03:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • USA 213 - . Payload: Navstar 65 / GPS SVN 62 / IIF-1 / Polaris. Mass: 1,630 kg (3,590 lb). Nation: USA. Agency: Boeing. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2F. USAF Sat Cat: 36585 . COSPAR: 2010-022A. Apogee: 20,225 km (12,567 mi). Perigee: 20,188 km (12,544 mi). Inclination: 55.0000 deg. Period: 719.00 min.

    First Block IIF Global Positioning System satellite. Supported the L1M and L2M military GPS channels, the L2C civilian channel and a new L5 civilian channel. Also included a nuclear explosion detection system. The IIF system replaces earlier Block I, Block II, and IIA series built by Rockwell/Seal Beach (now part of Boeing) and Block IIR satellites built by Lockheed Martin/Valley Forge.


2010 November 21 - . 22:58 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4H.
  • USA 223 - . Payload: Orion 7 / NROL-32. Mass: 5,400 kg (11,900 lb). Nation: USA. Class: Surveillance. Type: ELINT. Spacecraft Bus: Advanced Orion. Spacecraft: Advanced Orion. USAF Sat Cat: 37232 . COSPAR: 2010-063A. Apogee: 35,800 km (22,200 mi). Perigee: 35,800 km (22,200 mi). Inclination: 0.0000 deg. Period: 1,436.00 min. Probable geosynchronous signals intelligence satellite..

2011 March 11 - . 23:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • USA 227 - . Payload: NROL-27. Nation: USA. Class: Communications. Type: Military communications satellite. Spacecraft Bus: Quasar. Spacecraft: Quasar. USAF Sat Cat: 37377 . COSPAR: 2011-011A. Apogee: 35,800 km (22,200 mi). Perigee: 35,800 km (22,200 mi). Inclination: 0.0000 deg. Period: 1,440.00 min. Probable classified Satellite Data System communications satellite inserted into geostationary orbit..

2011 July 16 - . 06:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • USA 232 - . Payload: Navstar 66 / GPS SVN 63 / IIF-2 / Sirius. Mass: 1,630 kg (3,590 lb). Nation: USA. Agency: Boeing. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2F. USAF Sat Cat: 37753 . COSPAR: 2011-036A. Apogee: 20,188 km (12,544 mi). Perigee: 20,177 km (12,537 mi). Inclination: 55.0000 deg. Period: 718.00 min. Second Block IIF Global Positioning System satellite..

2012 January 20 - . 00:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(5,4).
  • USA 233 - . Payload: WGS 4. Mass: 6,000 kg (13,200 lb). Nation: USA. Class: Communications. Type: Military communications satellite. Spacecraft Bus: HS 702. Spacecraft: HS 702. USAF Sat Cat: 38070 . COSPAR: 2012-003A. Apogee: 66,872 km (41,552 mi). Perigee: 27,959 km (17,372 mi). Inclination: 1.1000 deg. Period: 2,069.50 min. Fourth Wideband Global Satcom satellite, providing high bandwidth communications for the US military. Operated by US Army Space Command, placed in an initial supersynchronous geostationary transfer orbit..

2012 June 29 - . 13:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4H.
  • USA 237 - . Payload: Orion 8 / NROL-15. Mass: 5,400 kg (11,900 lb). Nation: USA. Class: Surveillance. Type: ELINT. Spacecraft Bus: Advanced Orion. Spacecraft: Advanced Orion. USAF Sat Cat: 38528 . COSPAR: 2012-034A. Apogee: 35,800 km (22,200 mi). Perigee: 35,800 km (22,200 mi). Inclination: 0.0000 deg. Period: 1,440.00 min. Probable geosynchronous signals intelligence satellite..

2012 October 4 - . 00:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • USA 239 - . Payload: Navstar 67 / GPS SVN 65 /IIF-3 / SV-1 Arcturus. Mass: 1,630 kg (3,590 lb). Nation: USA. Agency: Boeing. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2F. USAF Sat Cat: 38833 . COSPAR: 2012-053A. Apogee: 20,192 km (12,546 mi). Perigee: 20,174 km (12,535 mi). Inclination: 55.0000 deg. Period: 718.00 min.

    Third GPS Block IIF satellite, spacecraft 65; replaced SVN 39 in the Navstar constellation. The upper stage and payload first entered a 163 km x 394 km x 41.6 deg parking orbit, followed by a 254 km x 20448 km x 43.3 deg transfer orbit and then a third burn into the final 20426 km x 20481 km x 55.0 deg circular orbit where the satellite was deployed. The RL-10 second stage engine operated at lower than planned thrust during the first two burns, but onboard software compensated by increasing the duration of the engine firings.


2013 May 25 - . 00:27 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(5,4).
  • USA 243 - . Payload: WGS 5. Mass: 5,987 kg (13,199 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft Bus: HS 702. Spacecraft: HS 702. USAF Sat Cat: 39168 . COSPAR: 2013-024A. Apogee: 40,362 km (25,079 mi). Perigee: 31,171 km (19,368 mi). Inclination: 0.2300 deg. Period: 1,435.07 min. Wideband Gapfiller Satellite; provided communications for the US military from geosynchronous orbit..

2014 July 28 - . 23:28 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • USA 253 - . Payload: GSSAP-1. Mass: 2,500 kg (5,500 lb). Nation: USA. Agency: ULAB. Spacecraft Bus: GSSAP. Spacecraft: GSSAP. USAF Sat Cat: 40099 . COSPAR: 2014-043A. Apogee: 35,500 km (22,000 mi). Perigee: 35,500 km (22,000 mi). Inclination: 0.0000 deg. Designed to catalog satellites and space debris in geostationary orbit. Built by Orbital for US Air Force Space Command. Orbit and mass classified; figures shown are speculative..
  • USA 254 - . Payload: GSSAP-2. Mass: 2,500 kg (5,500 lb). Nation: USA. Agency: ULAB. Spacecraft Bus: GSSAP. Spacecraft: GSSAP. USAF Sat Cat: 40100 . COSPAR: 2014-043B. Apogee: 35,500 km (22,000 mi). Perigee: 35,500 km (22,000 mi). Inclination: 0.0000 deg. Designed to catalog satellites and space debris in geostationary orbit. Built by Orbital for US Air Force Space Command. Orbit and mass classified; figures shown are speculative..
  • USA 255 - . Payload: ANGELS. Mass: 70 kg (154 lb). Nation: USA. Agency: ULAB. Spacecraft Bus: ANGELS. Spacecraft: ANGELS. USAF Sat Cat: 40101 . COSPAR: 2014-043C. Apogee: 35,500 km (22,000 mi). Perigee: 15,000 km (9,000 mi). Inclination: 25.0000 deg.

    Small satellite for the Air Force Research Lab which made observations of the Delta rocket's second stage at ranges from 50 kilometers down to a few kilometers, for further development of satellite inspection technology. Orbit and mass classified; figures shown are speculative.


2014 December 5 - . 12:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: Cape Canaveral SLC37B. LV Family: Delta IV. Launch Vehicle: Delta 4H.
  • Orion EFT-1 - . Mass: 9,400 kg (20,700 lb). Nation: USA. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Orion CEV. Spacecraft: Orion. Decay Date: 2014-12-05 . USAF Sat Cat: 40329 . COSPAR: 2014-077A. Apogee: 5,809 km (3,609 mi). Perigee: -37 km (-37 mi). Inclination: 28.8000 deg.

    Exploration Flight Test 1 used an Orion Crew Module (probably around 9400 kg) with an LAS launch escape tower, atop a dummy Service Module with jettisonable side panels, which in turn was fixed to the OSA (Orion-to-Stage-Adapter). This vehicle was mounted on the second stage of a Delta IV Heavy vehicle 369. Delta 369's second stage was inserted into a 185 km x 888 km x 28.8 deg orbit at 12:22 GMT, 17 minutes after launch. The stage made a second burn at 14:00, entering a -37 km x 5.807 km orbit; apogee was at 1510. At 15:28 the Orion CM separated from the stage. The Orion CM made a small RCS adjust burn at 16:02 and entered the atmosphere at 8.9 km/s at 16:18, landing at 16:29 off Baja California at 23.60 deg N x 116.46 deg W. It was recovered by the USS Anchorage.


2015 March 25 - . 18:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. Launch Pad: Cape Canaveral SLC37. LV Family: Delta IV. Launch Vehicle: Delta 4M+(4,2).
  • USA 260 - . Payload: Navstar 73 / GPS SVN 71 / IIF-9 / Deneb. Mass: 1,630 kg (3,590 lb). Nation: USA. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2F. USAF Sat Cat: 40534 . COSPAR: 2015-013A. Apogee: 20,195 km (12,548 mi). Perigee: 20,169 km (12,532 mi). Inclination: 55.0400 deg. Period: 717.97 min. Nicknamed Deneb; launched into a 12-hour-period orbit to join the navigation constellation..

2015 July 24 - . 00:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Delta IV. Launch Vehicle: Delta 4M+(5,4).
  • USA 263 - . Payload: WGS 7. Mass: 6,200 kg (13,600 lb). Nation: USA. Class: Communications. Type: Communications satellite. Spacecraft Bus: HS 702. Spacecraft: HS 702. USAF Sat Cat: 40746 . COSPAR: 2015-036A. Apogee: 66,798 km (41,506 mi). Perigee: 494 km (306 mi). Inclination: 24.1000 deg.

    Wideband Global Satcom military communications satellite launched initially into a supersynchronous geotransfer orbit. WGS satellites were managed by the USAF Space and Missile Center and replaced the older DSCS system with X-band and Ka-band communications systems. Second Delta 4 launch to use the uprated RS-68A main engine.



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