Encyclopedia Astronautica
Delta IV Medium+ (5.2)



delt4m52.jpg
Delta 4 Med (5.2)
Delta IV Medium+ (5.2)
Credit: © Mark Wade
American orbital launch vehicle. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 5 m diameter payload fairing.

LEO Payload: 10,300 kg (22,700 lb) to a 185 km orbit at 28.50 degrees. Payload: 4,350 kg (9,590 lb) to a GTO, 27 deg. Launch Price $: 150.000 million in 2004 dollars.

Stage Data - Delta IV Medium+ (5.2)

  • Stage 0. 2 x GEM 60. Gross Mass: 33,798 kg (74,511 lb). Empty Mass: 3,849 kg (8,485 lb). Thrust (vac): 826.553 kN (185,817 lbf). Isp: 275 sec. Burn time: 90 sec. Isp(sl): 243 sec. Diameter: 1.52 m (4.98 ft). Span: 1.52 m (4.98 ft). Length: 53.00 m (173.00 ft). Propellants: Solid. No Engines: 1. Engine: GEM 60. Status: In production. Comments: 90.5 bar chamber pressure, 11.0 nozzle expansion ratio. Figures for TVC version. Fixed nozzle version is 599 kg lighter.
  • Stage 1. 1 x Delta RS-68. Gross Mass: 226,400 kg (499,100 lb). Empty Mass: 26,760 kg (58,990 lb). Thrust (vac): 3,312.755 kN (744,737 lbf). Isp: 420 sec. Burn time: 249 sec. Isp(sl): 365 sec. Diameter: 5.10 m (16.70 ft). Span: 5.10 m (16.70 ft). Length: 40.80 m (133.80 ft). Propellants: Lox/LH2. No Engines: 1. Engine: RS-68. Status: In production. Comments: Low cost expendable stage using lower performance engine. Used in Delta 4, Boeing EELV. Engine can be throttled to 60%.
  • Stage 2. 1 x Delta 4 - 2. Gross Mass: 24,170 kg (53,280 lb). Empty Mass: 2,850 kg (6,280 lb). Thrust (vac): 110.050 kN (24,740 lbf). Isp: 462 sec. Burn time: 850 sec. Diameter: 2.44 m (8.00 ft). Span: 4.00 m (13.10 ft). Length: 12.00 m (39.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: RL-10B-2. Status: In production. Comments: Delta 3 second stage with hydrogen tank stretch.

Status: In production.
Gross mass: 292,732 kg (645,363 lb).
Payload: 10,300 kg (22,700 lb).
Height: 77.20 m (253.20 ft).
Diameter: 5.00 m (16.40 ft).
Thrust: 4,183.20 kN (940,421 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • GEM 46 Hercules solid rocket engine. 608.1 kN. Air-ignited versions have nozzle ratio of 24.8:1, specific impulse of 284 sec. Isp=274s. First flight 1998. More...
  • GEM 60 Hercules solid rocket engine. 851.5 kN. In production. Isp=275s. Used as strap-on boosters for Delta 3 , Delta IV Medium. First flight 2002. More...
  • RL-10B-2 Pratt and Whitney lox/lh2 rocket engine. 110 kN. In production. Isp=462s. Used on Delta 3 , Delta IV launch vehicles. First flight 1998. Extendable exit cone for increased specific impulse; electromechanical actuators replace hydraulic systems. More...
  • RS-68 Rocketdyne lox/lh2 rocket engine. 3312 kN. In production. Isp=420s. First new large liquid-fueled rocket engine developed in America in more than 25 years. Powered the Delta IV booster. First flight 2002. More...

See also
  • Delta IV 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. More...

Associated Manufacturers and Agencies
  • Douglas American manufacturer of rockets, spacecraft, and rocket engines. Boeing Huntington Beach, Huntington Beach, CA, USA. More...

Associated Stages
  • Delta 4 - 2 Lox/LH2 propellant rocket stage. Loaded/empty mass 24,170/2,850 kg. Thrust 110.05 kN. Vacuum specific impulse 462 seconds. Delta 3 second stage with hydrogen tank stretch. More...
  • Delta RS-68 Lox/LH2 propellant rocket stage. Loaded/empty mass 226,400/26,760 kg. Thrust 3,312.76 kN. Vacuum specific impulse 420 seconds. Low cost expendable stage using lower performance engine. Used in Delta 4, Boeing EELV. Engine can be throttled to 60%. More...
  • GEM 60 Solid propellant rocket stage. Loaded/empty mass 33,798/3,849 kg. Thrust 826.55 kN. Vacuum specific impulse 275 seconds. 90.5 bar chamber pressure, 11.0 nozzle expansion ratio. Figures for TVC version. Fixed nozzle version is 599 kg lighter. More...

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