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SRB-A


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A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z 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. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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