 | Delta 4 Med (4.2)
Credit - © Mark Wade
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Orbital launch vehicle. Year: 2002. Family: Delta. Country: USA. Status: In production. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 4 m diameter payload fairing. Manufacturer: Douglas. Launches: 1. Success Rate: 100.00%. First Launch Date: 2002-11-20. Last Launch Date: 2002-11-20. Launch data is: continuing. 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.
Stage Data - Delta IV Medium+ (4.2) - Stage Number: 0. 2 x Stage: 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: 16.20 m (53.10 ft). Propellants: Solid. No Engines: 1. Engine: GEM 60. Status: In production. 90.5 bar chamber pressure, 11.0 nozzle expansion ratio. Figures for TVC version. Fixed nozzle version is 599 kg lighter.
- Stage Number: 1. 1 x Stage: 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. Low cost expendable stage using lower performance engine. Used in Delta 4, Boeing EELV. Engine can be throttled to 60%.
- Stage Number: 2. 1 x Stage: 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. Delta 3 second stage with hydrogen tank stretch.
Delta IV Medium+ (4.2) Chronology 2002 December 13 - Launch Vehicle: Atlas V, Delta IV Medium+ (4.2). - USAF to subsidise EELV's Nation: USA. 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.
Bibliography and Further Reading - McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.
- Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...
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