Solid propellant rocket stage. Loaded/empty mass 561,100/57,600 kg. Thrust 11,143.20 kN. Vacuum specific impulse 263 seconds. 260 inch solid booster - full length.
Status: Development 1968.
Gross mass: 561,100 kg (1,237,000 lb).
Unfuelled mass: 57,600 kg (126,900 lb).
Height: 21.65 m (71.03 ft).
Diameter: 6.60 m (21.60 ft).
Span: 6.60 m (21.60 ft).
Thrust: 11,143.20 kN (2,505,091 lbf).
Specific impulse: 263 s.
Specific impulse sea level: 238 s.
Burn time: 114 s.
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Associated Countries
Associated Engines
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AJ-260X 1/3 Aerojet solid rocket engine. 11,143 kN. Design concept 1960's. Isp=263s. More...
Associated Propellants
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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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