1964 January 29 - 16:25 GMT - Launch Vehicle: Saturn I. Saturn I-Blk2 SA-5 Saturn 5 Mass: 17,100 kg (37,600 lb). Spacecraft: Jupiter nose cone. Agency: NASA MSF. Perigee: 274 km (170 mi). Apogee: 740 km (450 mi). Inclination: 31.40 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 Vehicle: Saturn I. Saturn I-Blk2 SA-6 Saturn 6 Mass: 16,900 kg (37,200 lb). Spacecraft: Apollo CSM. Agency: NASA MSC. Perigee: 179 km (111 mi). Apogee: 204 km (126 mi). Inclination: 31.70 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 Vehicle: Saturn I. Saturn I-Blk2 SA-7 Saturn 7 Mass: 16,700 kg (36,800 lb). Spacecraft: Apollo CSM. Agency: NASA MSC. Perigee: 181 km (112 mi). Apogee: 215 km (133 mi). Inclination: 31.70 deg. Period: 88.50 min. Apollo systems test. Third orbital test. First closed-loop guidance test.

1965 February 16 - 14:37 GMT - Launch Vehicle: Saturn I. Saturn I-Blk2 SA-9 Pegasus 1 Mass: 10,400 kg (22,900 lb). Spacecraft: Pegasus. Agency: NASA MSF. Perigee: 510 km (310 mi). Apogee: 726 km (451 mi). Inclination: 31.70 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.

1965 May 25 - 07:35 GMT - Launch Vehicle: Saturn I. Saturn I-Blk2 SA-8 Pegasus 2 Mass: 10,464 kg (23,069 lb). Spacecraft: Pegasus. Agency: NASA MSF. Perigee: 502 km (311 mi). Apogee: 740 km (450 mi). Inclination: 31.70 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.

1965 July 30 - 13:00 GMT - Launch Vehicle: Saturn I. Saturn I-Blk2 SA-10 Pegasus 3 Mass: 10,500 kg (23,100 lb). Spacecraft: Pegasus. Agency: NASA MSF. Perigee: 441 km (274 mi). Apogee: 449 km (278 mi). Inclination: 28.90 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.

1966 July 5 - 14:53 GMT - Launch Vehicle: Saturn I. Uprated Saturn I SA-203 Apollo 203 Mass: 26,500 kg (58,400 lb). Agency: NASA MSF. Perigee: 183 km (113 mi). Apogee: 212 km (131 mi). Inclination: 31.90 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 Vehicle: Saturn I. Saturn IB SA-204 Apollo 5 Mass: 14,360 kg (31,650 lb). Spacecraft: Apollo LM. Agency: NASA MSC. Perigee: 169 km (105 mi). Apogee: 374 km (232 mi). Inclination: 31.60 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 Vehicle: Delta IV. LV Model: Delta IV Medium+ (4.2) . Delta 4M+(4,2) D4-1 (293) 4240 Eutelsat W5 Mass: 3,170 kg (6,980 lb). Spacecraft: Spacebus 3000. Agency: Eutelsat. Perigee: 35,788 km (22,237 mi). Apogee: 35,801 km (22,245 mi). Inclination: 0.10 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 Vehicle: Delta IV. LV Model: Delta IV Medium . Delta 4M D4-2 (296) 4040 USA 167 Mass: 1,235 kg (2,722 lb). Spacecraft: DSCS III. Agency: USAF. 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 Vehicle: Delta IV. LV Model: Delta IV Medium . Delta 4M D4-3 (301) 4040 USA 170 Mass: 1,235 kg (2,722 lb). Spacecraft: DSCS III. Agency: US Air Force. Delayed from July 1, 11 and 23, then August 3 and 28.

2004 December 21 - 21:50 GMT - Launch Vehicle: Delta IV. LV Model: Delta IV Heavy . Delta 4H D4-4 (310) 4050H USA 181 Mass: 5,993 kg (13,212 lb). Agency: USAF. Perigee: 19,035 km (11,827 mi). Apogee: 36,413 km (22,625 mi). Inclination: 13.48 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.

2006 May 24 - 22:11 GMT - Launch Vehicle: Delta IV. LV Model: Delta IV Medium+ (4.2) . Delta 4M+(4,2) D4-5 (315) 4240 GOES-13 Mass: 3,199 kg (7,052 lb). Spacecraft: HS 601. Agency: NOAA. Perigee: 35,779 km (22,231 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.50 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.