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Orbital launch vehicle. Year: 1999. Family: H-2. Country: Japan. Status: Design 1999. Concept of H-2 augmented with Liquid-Air Cycle Engine boosters and advanced HIMES upper stage. Manufacturer: Mitsubishi. Liftoff Thrust: 2,167.440 kN (487,260 lbf). Total Mass: 183,700 kg (404,900 lb). Core Diameter: 4.00 m (13.10 ft). Total Length: 50.00 m (164.00 ft). Flyaway Unit Cost $: 170.000 million. in: 1985 unit dollars.
Stage Data - H-2 HIMES - Stage Number: 0. 9 x Stage: LACE. Gross Mass: 8,000 kg (17,600 lb). Empty Mass: 2,000 kg (4,400 lb). Thrust (vac): 147.000 kN (33,046 lbf). Isp: 1,200 sec. Burn time: 470 sec. Isp(sl): 1,200 sec. Diameter: 2.40 m (7.80 ft). Span: 2.40 m (7.80 ft). Length: 8.00 m (26.20 ft). Propellants: Liquid Air/LH2. No Engines: 1. Engine: LACE/LE-5. Other designations: Liquid Air Cycle Engine. Status: Design 1999.
- Stage Number: 1. 1 x Stage: H-2-1. Gross Mass: 98,100 kg (216,200 lb). Empty Mass: 11,900 kg (26,200 lb). Thrust (vac): 1,077.996 kN (242,343 lbf). Isp: 446 sec. Burn time: 346 sec. Isp(sl): 349 sec. Diameter: 4.00 m (13.10 ft). Span: 4.00 m (13.10 ft). Length: 28.00 m (91.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: LE-7. Other designations: LE-7.
- Stage Number: 2. 1 x Stage: HIMES. Gross Mass: 13,600 kg (29,900 lb). Empty Mass: 3,100 kg (6,800 lb). Thrust (vac): 274.000 kN (61,597 lbf). Isp: 452 sec. Burn time: 167 sec. Isp(sl): 340 sec. Diameter: 2.40 m (7.80 ft). Span: 9.25 m (30.34 ft). Length: 13.60 m (44.60 ft). Propellants: Lox/LH2. No Engines: 2. Engine: HIMES. Status: Design 1999.
Bibliography and Further Reading - Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al. ISBN: 0710618107. The most comprehensive source of information for current space projects. Too expensive for human beings and most libraries. More at amazon.com...
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