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Engine Model: M14. Designer: Nissan. Gross Mass: 83,560 kg (184,210 lb). Empty Mass: 12,070 kg (26,600 lb). Propellants: Solid. Thrust(vac): 3,780.300 kN (849,845 lbf). Thrust(sl): 3,369.400 kN (757,471 lbf). Isp: 276 sec. Isp (sea level): 246 sec. Burn time: 46 sec. Diameter: 2.50 m (8.20 ft). Length: 13.80 m (45.20 ft). Chambers: 1. Chamber Pressure: 59.00 bar. Area Ratio: 11.00. Country: Japan. First Flight: 1997. Last Flight: 2006. Flown: 7.00.

Engine Model: SRB-A. Designer: Nissan. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Propellants: Solid. Thrust(vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Diameter: 2.50 m (8.20 ft). Length: 15.20 m (49.80 ft). Chambers: 1. Chamber Pressure: 118.00 bar. Area Ratio: 17.70. Country: Japan. Status: In production. First Flight: 2001. Last Flight: 2006. Flown: 20.

Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure.

SRB-A used on Rocket Stages
  • Used on stage: H-2-0. on launch vehicle: J.
  • Used on stage: M-V-1. on launch vehicle: M-V.
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© Mark Wade, 1997 - 2008 except where otherwise noted.