Encyclopedia Astronautica
SRB-A


Nissan solid rocket engine. 2250 kN. In production. Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure. Isp=280s. First flight 2001.

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

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

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • H-2A Japanese orbital launch vehicle. Low-cost version of H-2 developed for the commercial market. The two SRB-A solid rocket boosters can be supplemented by 4 smaller SSB solid boosters. 0 or 2 SSB's can be fitted for reduced 9,940 kg or 10,740 kg LEO payloads. More...

Associated Manufacturers and Agencies
  • Nissan Japanese manufacturer of rocket engines and rockets. Nissan, Japan. More...

Associated Propellants
  • Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

Associated Stages
  • H-2A SRB-A Solid propellant rocket stage. Loaded/empty mass 76,400/10,400 kg. Thrust 2,250.00 kN. Vacuum specific impulse 280 seconds. More...

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