H-2-0

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Model: H-2-0. Gross Mass: 70,400 kg (155,200 lb). Empty Mass: 11,250 kg (24,800 lb). Thrust (vac): 1,539.997 kN (346,205 lbf). Isp: 273 sec. Burn time: 94 sec. Propellants: Solid. Isp(sl): 237 sec. Diameter: 1.81 m (5.93 ft). Span: 1.81 m (5.93 ft). Length: 23.36 m (76.64 ft). Country: Japan. No Engines: 1. Motor: H-2-0. Status: Retired 1999. Cost $ : 20.000 million. First Flight: 1994. Last Flight: 1999. No Launched: 24.

Model: J-1-1. Gross Mass: 71,100 kg (156,700 lb). Empty Mass: 11,900 kg (26,200 lb). Thrust (vac): 1,556.600 kN (349,938 lbf). Isp: 273 sec. Burn time: 94 sec. Propellants: Solid. Isp(sl): 248 sec. Diameter: 1.80 m (5.90 ft). Span: 1.80 m (5.90 ft). Length: 18.00 m (59.00 ft). Country: Japan. No Engines: 1. Motor: H-2-0. Status: In production. First Flight: 1996. Last Flight: 1996. No Launched: 1.

Shorter monolithic motor using filament-wound case technology from Thiokol. Version for J-1 has 1,000 kg less propellant and 1,200 kg less empty mass than later H-2 SRB.

Model: H-2A SRB-A. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Thrust (vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Propellants: Solid. Propellant Formulation: HTPB. Isp(sl): 230 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 15.20 m (49.80 ft). Country: Japan. No Engines: 1. Motor: SRB-A. Status: In production. First Flight: 2001. Last Flight: 2007. No Launched: 48. No Failed: 1.

Used on Launch Vehicles:

H-2.

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