Solid propellant rocket stage. Loaded/empty mass 725,500/49,250 kg. Thrust 18,181.00 kN. Vacuum specific impulse 263 seconds. 4 Segment version of basic 3-segment UA 156 motor.
Cost $ : 50.000 million.
Status: Study 1965.
Gross mass: 725,500 kg (1,599,400 lb).
Unfuelled mass: 49,250 kg (108,570 lb).
Height: 38.00 m (124.00 ft).
Diameter: 3.96 m (12.99 ft).
Span: 3.96 m (12.99 ft).
Thrust: 18,181.00 kN (4,087,251 lbf).
Specific impulse: 263 s.
Specific impulse sea level: 238 s.
Burn time: 94 s.
More... - Chronology...
Associated Countries
Associated Engines
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UA-156 CSD solid rocket engine. 8924.3 kN. Tested 1968. Isp=263s. Proposed as strap-on booster for Saturn INT-27, Saturn V-25(S)B, Saturn V-25(S)U. More...
Associated Launch Vehicles
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Saturn INT-27 American orbital launch vehicle. UA study, 1965. Saturn variant using various combinations of 156 inch rocket motors as first and second stages, with S-IVB upper stage. 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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