Solid propellant rocket stage. Loaded/empty mass 751,212/100,350 kg. Thrust 15,480.36 kN. Vacuum specific impulse 265 seconds. Five-segment version of Shuttle RSRM studied in 1999-2003 to increase shuttle payload to ISS. Test fired in 2003 but not proceeded with. Another version proposed in 2005 for use as lateral boosters for the Constellation Cargo Vehicle.
Propellant Formulation: PBAN.
Status: In development.
More... - Chronology...
Gross mass: 751,212 kg (1,656,138 lb).
Unfuelled mass: 100,350 kg (221,230 lb).
Height: 53.87 m (176.73 ft).
Diameter: 3.77 m (12.36 ft).
Span: 5.10 m (16.70 ft).
Thrust: 15,480.36 kN (3,480,122 lbf).
Specific impulse: 265 s.
Specific impulse sea level: 234 s.
Burn time: 110 s.
RSRM Thiokol solid rocket engine. 11,520 kN. Study 1996. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements. Isp=267s. More...
Associated Launch Vehicles
Ares I American heavy-lift orbital launch vehicle. Shuttle-derived launch vehicle design selected by NASA Administrator Mike Griffin to boost the manned CEV Crew Exploration Vehicle into low earth orbit. A single five-segment version of the shuttle solid rocket booster would be mated with a Lox/LH2 upper stage powered by a single J-2S engine. More...
Ares V American heavy-lift orbital launch vehicle. NASA baseline heavy-lift vehicle to renew manned lunar exploration by 2020. More...
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...
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