Delta IV Credit - (c) Mark Wade

Orbital launch vehicle. Country: USA. Status: Active.

The Delta IV was the world's first all-Lox/LH2 launch vehicle and represented the only all-new-technology launch vehicle developed in the United States since the 1970's. It was the winner of the bulk of the USAF EELV orders and was based on the all-new RS-68-powered Lox/LH2 cryogenic Common Booster Core (CBC). This could be used with new Delta cryogenic upper stages powered by the RL10 engine but unrelated to previous Centaur upper stages. It could be flown without augmentation, or use 2-4 large GEM-60 solid rocket boosters. The heavy lift version used two core vehicles as a first stage, flanking the single core vehicle second stage.

The configuration of Delta IV vehicles was encoded as follows:

• First digit: basic vehicle configuration: 4 = Delta-4 Lox/LH2 core
• Second digit: Number of GEM-60 solid propellant strap-ons (0, 2, or 4).
• Third digit: Second stage
  • 4 = Delta-4 Lox/LH2 cryogenic upper stage with 4 m diameter
  • 5 = Delta-4 Lox/LH2 cryogenic upper stage with 5 m diameter
• Fourth digit: Third stage
  • 0 = No third stage
  • 3 = Star 37D / TE-364-3 solid propellant kick stage
  • 4 = Star 37E / TE-364-4 solid propellant kick stage
  • 5 = Star-48B / PAM-D solid propellant kick stage (often listed as '0' upper stage with a PAM-D due to the modular nature of the PAM configuration).
  • 6 = Star 37FM solid propellant kick stage
• Optional letter after fourth digit: An 'H' here indicates a 'Heavy' configuration, indicating use of two strap-on Common Booster Cores (CBC) to supplement the CBC on the core stage.
• Dash number: Payload fairing. For Delta II, this indicates the diameter of the fairing in feet. For Delta III or Delta IV, it indicates the length of the fairing in meters.

Manufacturer: Douglas. Launches: 8. Success Rate: 100.00%. First Launch Date: 2002-11-20. Last Launch Date: 2007-11-11. Launch data is: continuing. Version:

Delta IV Medium.

Delta IV Medium Credit - © Mark Wade

Status: Active.

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.

Launches: 3. First Launch Date: 2003-03-11. Last Launch Date: 2006-11-04. LEO Payload: 8,600 kg (18,900 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 3,900 kg (8,500 lb). to a: Geosynchronous transfer, 27deg inclination trajectory. Associated Spacecraft: DSCS III. Liftoff Thrust: 2,890.000 kN (649,690 lbf). Total Mass: 249,500 kg (550,000 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 63.00 m (206.00 ft). Launch Price $: 133.000 million. in: 2004 price dollars. Cost comments: The originally estimated launch price in 1999 was $90 million.

• Stage1: 1 x Delta RS-68. Gross Mass: 226,400 kg (499,100 lb). Empty Mass: 26,760 kg (58,990 lb). Motor: 1 x RS-68. Thrust (vac): 3,312.755 kN (744,737 lbf). Isp: 420 sec. Burn time: 249 sec. Length: 40.80 m (133.80 ft). Diameter: 5.10 m (16.70 ft). Propellants: Lox/LH2.

• Stage2: 1 x Delta 4 - 2. Gross Mass: 24,170 kg (53,280 lb). Empty Mass: 2,850 kg (6,280 lb). Motor: 1 x RL-10B-2. Thrust (vac): 110.050 kN (24,740 lbf). Isp: 462 sec. Burn time: 850 sec. Length: 12.00 m (39.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/LH2.

Launches: 3. First Launch Date: 2002-11-20. Last Launch Date: 2006-06-25. LEO Payload: 11,700 kg (25,700 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 5,300 kg (11,600 lb). to a: Geosynchronous transfer, 27deg inclination trajectory. Associated Spacecraft: Spacebus 3000. Liftoff Thrust: 4,183.200 kN (940,421 lbf). Total Mass: 292,732 kg (645,363 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 66.20 m (217.10 ft). Launch Price $: 138.000 million. in: 2004 price dollars. Development cost is USAF portion only in cost-sharing arrangement for all Delta IV models. The original USAF order was for 19 Delta IV launches at a total price of $ 1.38 billion ($72 million each). The estimated launch price in 1999 was $95 million. Due to the collapse of the commercial launch market, this was revised by the USAF in November 2004 to $ 138 million.

• Stage0: 2 x GEM 60. Gross Mass: 33,798 kg (74,511 lb). Empty Mass: 3,849 kg (8,485 lb). Motor: 1 x GEM 60. Thrust (vac): 826.553 kN (185,817 lbf). Isp: 275 sec. Burn time: 90 sec. Length: 16.20 m (53.10 ft). Diameter: 1.52 m (4.98 ft). Propellants: Solid.

• Stage1: 1 x Delta RS-68. Gross Mass: 226,400 kg (499,100 lb). Empty Mass: 26,760 kg (58,990 lb). Motor: 1 x RS-68. Thrust (vac): 3,312.755 kN (744,737 lbf). Isp: 420 sec. Burn time: 249 sec. Length: 40.80 m (133.80 ft). Diameter: 5.10 m (16.70 ft). Propellants: Lox/LH2.

• Stage2: 1 x Delta 4 - 2. Gross Mass: 24,170 kg (53,280 lb). Empty Mass: 2,850 kg (6,280 lb). Motor: 1 x RL-10B-2. Thrust (vac): 110.050 kN (24,740 lbf). Isp: 462 sec. Burn time: 850 sec. Length: 12.00 m (39.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/LH2.

• Stage0: 2 x GEM 60. Gross Mass: 33,798 kg (74,511 lb). Empty Mass: 3,849 kg (8,485 lb). Motor: 1 x GEM 60. Thrust (vac): 826.553 kN (185,817 lbf). Isp: 275 sec. Burn time: 90 sec. Length: 16.20 m (53.10 ft). Diameter: 1.52 m (4.98 ft). Propellants: Solid.

• Stage1: 1 x Delta RS-68. Gross Mass: 226,400 kg (499,100 lb). Empty Mass: 26,760 kg (58,990 lb). Motor: 1 x RS-68. Thrust (vac): 3,312.755 kN (744,737 lbf). Isp: 420 sec. Burn time: 249 sec. Length: 40.80 m (133.80 ft). Diameter: 5.10 m (16.70 ft). Propellants: Lox/LH2.

• Stage2: 1 x Delta 4 - 2. Gross Mass: 24,170 kg (53,280 lb). Empty Mass: 2,850 kg (6,280 lb). Motor: 1 x RL-10B-2. Thrust (vac): 110.050 kN (24,740 lbf). Isp: 462 sec. Burn time: 850 sec. Length: 12.00 m (39.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/LH2.

• Stage0: 4 x GEM 60. Gross Mass: 33,798 kg (74,511 lb). Empty Mass: 3,849 kg (8,485 lb). Motor: 1 x GEM 60. Thrust (vac): 826.553 kN (185,817 lbf). Isp: 275 sec. Burn time: 90 sec. Length: 16.20 m (53.10 ft). Diameter: 1.52 m (4.98 ft). Propellants: Solid.

• Stage1: 1 x Delta RS-68. Gross Mass: 226,400 kg (499,100 lb). Empty Mass: 26,760 kg (58,990 lb). Motor: 1 x RS-68. Thrust (vac): 3,312.755 kN (744,737 lbf). Isp: 420 sec. Burn time: 249 sec. Length: 40.80 m (133.80 ft). Diameter: 5.10 m (16.70 ft). Propellants: Lox/LH2.

• Stage2: 1 x Delta 4 - 2. Gross Mass: 24,170 kg (53,280 lb). Empty Mass: 2,850 kg (6,280 lb). Motor: 1 x RL-10B-2. Thrust (vac): 110.050 kN (24,740 lbf). Isp: 462 sec. Burn time: 850 sec. Length: 12.00 m (39.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/LH2.

• Stage0: 2 x Delta RS-68. Gross Mass: 226,400 kg (499,100 lb). Empty Mass: 26,760 kg (58,990 lb). Motor: 1 x RS-68. Thrust (vac): 3,312.755 kN (744,737 lbf). Isp: 420 sec. Burn time: 249 sec. Length: 40.80 m (133.80 ft). Diameter: 5.10 m (16.70 ft). Propellants: Lox/LH2.

• Stage1: 1 x Delta RS-68. Gross Mass: 226,400 kg (499,100 lb). Empty Mass: 26,760 kg (58,990 lb). Motor: 1 x RS-68. Thrust (vac): 3,312.755 kN (744,737 lbf). Isp: 420 sec. Burn time: 249 sec. Length: 40.80 m (133.80 ft). Diameter: 5.10 m (16.70 ft). Propellants: Lox/LH2.

• Stage2: 1 x Delta 4H - 2. Gross Mass: 30,710 kg (67,700 lb). Empty Mass: 3,490 kg (7,690 lb). Motor: 1 x RL-10B-2. Thrust (vac): 110.050 kN (24,740 lbf). Isp: 462 sec. Burn time: 1,125 sec. Length: 12.00 m (39.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/LH2.

• Stage1: 1 x Delta RS-68. Gross Mass: 226,400 kg (499,100 lb). Empty Mass: 26,760 kg (58,990 lb). Motor: 1 x RS-68. Thrust (vac): 3,312.755 kN (744,737 lbf). Isp: 420 sec. Burn time: 249 sec. Length: 40.80 m (133.80 ft). Diameter: 5.10 m (16.70 ft). Propellants: Lox/LH2.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

LEO Payload: 27,000 kg (59,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 10,000 kg (22,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 35 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by adding RS-68B upgraded engines to the core vehicles and an AUS-60 upper stage powered by 2 MB-45 or RL-45 20 tonne thrust Lox/LH2 engines. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.

LEO Payload: 32,000 kg (70,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 12,500 kg (27,500 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 40 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, and cryogenic propellant densification. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.

LEO Payload: 36,000 kg (79,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 14,000 kg (30,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 42 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by adding new RS-800 engines to the core vehicles, an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.

LEO Payload: 38,000 kg (83,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 14,000 kg (30,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 43 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, cryogenic propellant densification, and an AUS-60 upper stage powered by 1 MB-60 or RL-60 27 tonne thrust Lox/LH2 engine. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.

LEO Payload: 39,000 kg (85,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 14,500 kg (31,900 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 45 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by adding 6 GEM-60 solid rocket boosters, RS-68B upgraded engines to the core vehicles, and an AUS-60 upper stage powered by 1 MB-60 or RL-60 27 tonne thrust Lox/LH2 engine. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.

LEO Payload: 41,000 kg (90,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 15,000 kg (33,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 48 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, cryogenic propellant densification, and cryogenic propellant cross-feed between the strap-ons and core. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.

LEO Payload: 43,000 kg (94,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 15,800 kg (34,800 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 53 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by clustering five common booster modules, using an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.

LEO Payload: 48,000 kg (105,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 18,000 kg (39,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 67 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, and using an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines. A payload fairing over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.

LEO Payload: 61,000 kg (134,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 22,500 kg (49,600 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 70 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using an AUS-60 upper stage powered by 3 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines. A payload fairing over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.

LEO Payload: 63,000 kg (138,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 24,000 kg (52,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 71.00 m (232.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 76 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using an AUS-60 upper stage powered by 3 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.

LEO Payload: 69,000 kg (152,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 26,000 kg (57,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 67.00 m (219.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 87 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using a new RS-800K engine in the booster stages, and an AUS-60 27 tonne thrust Lox/LH2 upper stage. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.

LEO Payload: 79,000 kg (174,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 30,000 kg (66,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 67.00 m (219.00 ft). Span: 15.00 m (49.00 ft). Version:

Delta IV Heavy Upgrade 94 t. Status: Study 2004.

Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using a new RS-800K engine in the booster stages, an AUS-60 upper stage powered by 4 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.

LEO Payload: 85,000 kg (187,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 32,000 kg (70,000 lb). to a: earth escape trajectory. Core Diameter: 5.00 m (16.40 ft). Total Length: 67.00 m (219.00 ft). Span: 15.00 m (49.00 ft). Version:

Next Genertion Delta 100 t. Status: Study 2004.

Conceptual next generation Delta booster beyond Delta IV Heavy, equalling Saturn V of the 1960's in payload capability. The booster would use two parallel 7-m-diameter booster stages, a notional RS-XXX Lox/LH2 rocket motor, and a 7 m diameter upper stage and fairing. Payload fairings of 7 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure, and a new factory to handle the larger-diameter tooling.

LEO Payload: 91,000 kg (200,000 lb). to: 407 km Orbit. at: 28.50 degrees. Payload: 35,000 kg (77,000 lb). to a: earth escape trajectory. Core Diameter: 7.00 m (22.90 ft). Total Length: 64.00 m (209.00 ft). Span: 21.00 m (68.00 ft).

2002 November 20 - 22:39 GMT - Cape Canaveral LC37B. 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.

2002 December 13 - USAF to subsidise EELV's The US Air Force asked the Congress to provide $1 billion of subsidies in 2004-2009 for the Atlas V and Delta 4 EELV launch vehicles. The collapse of the commercial satellite market invalidated the cost model on which the manufacturers invested their own funds in development. Lack of adequate sales could have meant the closure of the production line of one or both of the launch vehicles on which the US government would rely for future space missions. The US Air Force asked for a $200-million first tranche n FY2004.

2003 March 11 - 00:59 GMT - Cape Canaveral LC37B. 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 - Cape Canaveral LC37B. 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 - Cape Canaveral LC37B. 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 - Cape Canaveral LC37B. 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.

2006 June 25 - Vandenberg SLC6. LV Model: Delta IV Medium+ (4.2) . Delta 4M+(4,2) D4-6 (317) 4240 USA 184 Mass: 4,500 kg (9,900 lb). Spacecraft: Jumpseat-2. Agency: NRO. Secret payload for the National Reconnaissance Office. The intended orbit was thought to be a "Molniya" elliptical 12-hour orbit with an inclination of 63 degrees. American data relay and signals intelligence satellites have used this orbit in the past, notably the Jumpseat series of 1971-1983. A secondary payload was later confirmed to be the first SBIRS-HEO (Space-based Infrared System) sensor. SBIRS was the successor to the DSP (Defence Support Program), which provided early warning of missile launches. Also carried the NASA/Los Alamos TWINS-A magnetospheric research payload

2006 November 4 - 13:53 GMT - Vandenberg SLC6. LV Model: Delta IV Medium . Delta 4M D4-7 (320) 4040 DMSP-5D3-F17 Mass: 1,154 kg (2,544 lb). Spacecraft: DMSP Block 5D-3. Agency: U.S. Air Force. Perigee: 841 km (522 mi). Apogee: 855 km (531 mi). Inclination: 98.80 deg. Period: 101.90 min. Defense Meteorological Satellite Program satellite with the Operational Linescan System camera, a microwave imager-sounder, ultraviolet spectrometers, particle detectors, a magnetometer, and a laser threat warning sensor. Reportedly went for a time into safe mode due to software problems after launch. The booster upper stage was conducted a maneuver to deorbit itself after placing the satellite in orbit. After the burn an explosion evidently occurred aboard the stage - dozens of objects were tracked in various orbits with perigees down to 670 km and apogees up to 851 km.

2007 November 11 - 01:50 GMT - Cape Canaveral LC37B. LV Model: Delta IV Heavy . Delta 4H D4-8 (329) 4050H USA 197 Mass: 2,270 kg (5,000 lb). Spacecraft: DSP. Agency: National Security Agency. Perigee: 35,800 km (22,200 mi). Apogee: 36,325 km (22,571 mi). Inclination: 0.00 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.