SRB-A

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SRB-A

Part of M14

Nissan solid rocket engine. In production. Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure. First flight 2001.

AKA: H-2A SRB-A. Status: In production. Number: 20 . Thrust: 2,250.00 kN (505,820 lbf). Gross mass: 76,400 kg (168,400 lb). Unfuelled mass: 10,400 kg (22,900 lb). Specific impulse: 280 s. Burn time: 101 s. Height: 15.20 m (49.80 ft). Diameter: 2.50 m (8.20 ft).

Chamber Pressure: 118.00 bar. Area Ratio: 17.7. Propellant Formulation: HTPB.

Country: Japan. Launch Vehicles: H-IIA 212, H-IIA, H-IIA 202, J-1 F2, H-IIA 2024, H-IIA 2022, H-IIA 204, H-IIB. Propellants: Solid. Stages: SRB-A. Agency: Nissan.

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