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Family: H. Country: Japan. Status: Development. Other Designations: H-IIA 212.
Low-cost version of H-2 developed for the commercial market. This version uses two core stages side-by-side in an asymmetric configuration, supplemented by two SRB solid rocket boosters.
SpecificationsLEO Payload: 17,280 kg. to: 300 km Orbit. at: 30.4 degrees. Payload: 7,500 kg. to a: Geosynchronous transfer trajectory. Liftoff Thrust: 653,000 kgf. Total Mass: 406,000 kg. Core Diameter: 4.0 m. Total Length: 52.5 m.
- Stage Number: 0. 2 x H-2A SRB-A Gross Mass: 76,400 kg. Empty Mass: 10,400 kg. Thrust (vac): 230,000 kgf. Isp: 280 sec. Burn time: 101 sec. Isp(sl): 230 sec. Diameter: 2.5 m. Span: 2.5 m. Length: 15.2 m. Propellants: Solid No Engines: 1. SRB-A
- Stage Number: 1. 1 x H-2A LRB Gross Mass: 117,000 kg. Empty Mass: 17,800 kg. Thrust (vac): 224,000 kgf. Isp: 440 sec. Burn time: 193 sec. Isp(sl): 338 sec. Diameter: 4.0 m. Span: 4.0 m. Length: 36.7 m. Propellants: Lox/LH2 No Engines: 2. LE-7A
- Stage Number: 2. 1 x H-2A-1 Gross Mass: 113,600 kg. Empty Mass: 13,600 kg. Thrust (vac): 112,000 kgf. Isp: 440 sec. Burn time: 390 sec. Isp(sl): 338 sec. Diameter: 4.0 m. Span: 4.0 m. Length: 37.2 m. Propellants: Lox/LH2 No Engines: 1. LE-7A
- Stage Number: 3. 1 x H-2A-2 Gross Mass: 19,600 kg. Empty Mass: 3,000 kg. Thrust (vac): 14,000 kgf. Isp: 447 sec. Burn time: 534 sec. Diameter: 4.0 m. Span: 4.0 m. Length: 9.2 m. Propellants: Lox/LH2 No Engines: 1. LE-5B
Bibliography:- 455 - Isakowitz, Steven J,, International Reference to Space Launch Systems Third Edition, AIAA, Washington DC, 2000.
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Last update 12 March 2001.
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