Encyclopedia Astronautica
Cape Canaveral LC37B


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.

Longitude: -80.5644 deg.
Latitude: 28.5313 deg.
First Launch: 1964.01.29.
Last Launch: 2007.11.11.
Number: 14 .

More... - Chronology...


Associated Spacecraft
  • Apollo CSM American manned lunar orbiter. 22 launches, 1964.05.28 (Saturn 6) to 1975.07.15 (Apollo (ASTP)). The Apollo Command Service Module was the spacecraft developed by NASA in the 1960's as a standard spacecraft for earth and lunar orbit missions. More...
  • Apollo LM American manned lunar lander. 10 launches, 1968.01.22 (Apollo 5) to 1972.12.07 (Apollo 17). More...
  • Jupiter nose cone American re-entry vehicle technology satellite. One launch, 1964.01.29, Saturn 5. Launch vehicle test. More...
  • Pegasus American earth micrometeoroid satellite. 3 launches, 1965.02.16 (Pegasus 1) to 1965.07.30 (Pegasus 3). Pegasus satellites consisted of vast detector panels deployed from Saturn IV stages on Saturn I test flights. More...
  • DSP American military early warning satellite. 23 launches, 1970.11.06 (IMEWS 1) to 2007.11.11 (USA 176). An evolving series of satellites built by the United States to detect intercontinental ballistic missiles on launch. More...
  • DSCS III American military communications satellite. 15 launches, 1982.10.30 (DSCS III-01) to 2003.08.29 (USA 170). DSCS satellites provided secure voice and data communications for the US military. More...
  • HS 601 American communications satellite bus. First launch 1990.01.09. 3-axis unified ARC 22 N and one Marquardt 490 N bipropellant thrusters, Sun and Barnes Earth sensors and two 61 Nms 2-axis gimbaled momentum bias wheels. More...
  • Advanced Orion American military naval signals intelligence and reconnaisance satellite. Highly classified, operational, first launch 1995.05.14. More...
  • HS 702 American communications satellite bus. Operational, first launched 1999.12.22. More...
  • 3CSat American technology satellite. 2 launched, 2004.12.21. The Three-Corner Sat mission was to obtain stereo images of clouds and test artificial intelligence software. More...

Associated Launch Vehicles
  • Saturn I American orbital launch vehicle. Von Braun launch vehicle known as 'Cluster's Last Stand' - 8 Redstone tanks around a Jupiter tank core,powered by eight Jupiter engines. Originally intended as the launch vehicle for Apollo manned circumlunar flights. However it was developed so early, no payloads were available for it. More...
  • Saturn IB American orbital launch vehicle. Improved Saturn I, with uprated first stage and Saturn IVB second stage (common with Saturn V) replacing Saturn IV. Used for earth orbit flight tests of Apollo CSM and LM. More...
  • Uprated Saturn I American orbital launch vehicle. Initial version of Saturn IB with old-design Saturn IB first stage. More...
  • Delta IV Medium+ (4.2) American orbital launch vehicle. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 4 m diameter payload fairing. More...
  • Delta IV Medium American orbital launch vehicle. Basic Delta-4 vehicle with no strap-ons, the core vehicle, and RL10B-1 upper stage with a 4 m diameter payload fairing. World's first all-cryogenic launch vehicle. More...
  • Delta IV Heavy American orbital launch vehicle. Heavy lift all-cryogenic launch vehicle using two Delta-4 core vehicles as first stage flanking a single core vehicle as second stage. A heavy upper stage is carried with a 5 m diameter payload fairing. More...
  • Delta IV Medium+ (5.4) American orbital launch vehicle. As Delta 4 medium but with 4 x GEM-60 solid rocket boosters and a 5 m diameter payload fairing. More...

Associated Launch Sites
  • Cape Canaveral America's largest launch center, used for all manned launches. Today only six of the 40 launch complexes built here remain in use. Located at or near Cape Canaveral are the Kennedy Space Center on Merritt Island, used by NASA for Saturn V and Space Shuttle launches; Patrick AFB on Cape Canaveral itself, operated the US Department of Defense and handling most other launches; the commercial Spaceport Florida; the air-launched launch vehicle and missile Drop Zone off Mayport, Florida, located at 29.00 N 79.00 W, and an offshore submarine-launched ballistic missile launch area. All of these take advantage of the extensive down-range tracking facilities that once extended from the Cape, through the Caribbean, South Atlantic, and to South Africa and the Indian Ocean. More...

Cape Canaveral LC37B Chronology


1964 January 29 - . 16:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC37B. LV Family: Saturn I. Launch Vehicle: Saturn I. LV Configuration: Saturn I-Blk2 SA-5.
  • 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 vehicle technology satellite. 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. LV Configuration: Saturn I-Blk2 SA-6.
  • 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: Apollo CSM. 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. Summary: 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. LV Configuration: Saturn I-Blk2 SA-7.
  • 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: Apollo CSM. 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. Summary: 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. LV Configuration: Saturn I-Blk2 SA-9.
  • 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: Pegasus. 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. LV Configuration: Saturn I-Blk2 SA-8.
  • 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: Pegasus. 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. LV Configuration: Saturn I-Blk2 SA-10.
  • 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: Pegasus. 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. LV Configuration: Uprated Saturn I SA-203.
  • 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. LV Configuration: Saturn IB SA-204.
  • 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: Apollo LM; LM Descent Propulsion. 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 IV Medium+ (4.2). LV Configuration: Delta 4M+(4,2) D4-1 (293) 4240.
  • Eutelsat W5 - . Payload: W1A. Mass: 3,170 kg (6,980 lb). Nation: Europe. Agency: Eutelsat. Manufacturer: Cannes. Program: Eutelsat. Class: Communications. Type: Civilian communications satellite. 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 IV Medium. LV Configuration: Delta 4M D4-2 (296) 4040.
  • 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: DSCS III. USAF Sat Cat: 27691 . COSPAR: 2003-008A. Summary: 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 IV Medium. LV Configuration: Delta 4M D4-3 (301) 4040.
  • USA 170 - . Payload: DSCS-3-B6. Mass: 1,235 kg (2,722 lb). Nation: USA. Agency: USAF. Class: Communications. Type: Military communications satellite. Spacecraft: DSCS III. USAF Sat Cat: 27875 . COSPAR: 2003-040A. Summary: 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 IV Heavy. LV Configuration: Delta 4H D4-4 (310) 4050H.
  • 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: 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: 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 IV Medium+ (4.2). LV Configuration: Delta 4M+(4,2) D4-5 (315) 4240.
  • GOES-13 - . Mass: 3,199 kg (7,052 lb). Nation: USA. Agency: NOAA. Manufacturer: Boeing. Program: GOES. Class: Earth. Type: Weather satellite. 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 IV Heavy. LV Configuration: Delta 4H D4-8 (329) 4050H.
  • USA 197 - . Payload: DSP-1 Block 18 F23. Mass: 2,270 kg (5,000 lb). Nation: USA. Agency: NSA. Manufacturer: TRW. Class: Military. Type: Early warning satellite. 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 IV Heavy.
  • USA 202 - . Payload: NROL-26. Nation: USA. Agency: NRO. Class: Military. Type: Military naval signals reconnaisance satellite. 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. Summary: 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 IV Medium+ (4.2). LV Configuration: Delta IV Medium+ (4.2) s/n D342.
  • GOES 14 - . Payload: GOES O. Mass: 3,210 kg (7,070 lb). Nation: USA. Agency: Martin. Program: GOES. 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. Summary: 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 IV Medium+ (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: 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. Summary: 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 IV Medium+ (4.2). LV Configuration: Delta IV Medium+ (4.2) s/n D348.
  • GOES 15 - . Mass: 3,240 kg (7,140 lb). Nation: USA. Agency: Martin. Program: GOES. Class: Earth. Type: Weather satellite. 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 IV Medium+ (4.2).
  • USA 213 - . Payload: Navstar 65 / GPS SVN 62 IIF SV-1. Nation: USA. Agency: Martin. Class: Navigation. Type: Navigation satellite. 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. Summary: 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..

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 IV Heavy.
  • USA 223 - . Payload: NROL-32. Nation: USA. Class: Military. Type: Electronic intelligence satellite. 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. Summary: 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 IV Medium+ (4.2).
  • USA 227 - . Payload: NROL-27. Nation: USA. Class: Communications. Type: Military communications satellite. Spacecraft: SDS-3. USAF Sat Cat: 37377 . COSPAR: 2011-011A. Summary: 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. LV Family: Delta IV. Launch Vehicle: Delta IV Medium+ (4.2).
  • USA 232 - . Payload: Navstar 66 / SVN 63 / GPSIIF-2. Nation: USA. Class: Navigation. Type: Navigation satellite. 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.

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