Solid propellant rocket stage. Loaded/empty mass 816,000/102,000 kg. Thrust 11,120.00 kN. Vacuum specific impulse 285 seconds. Conceptual motor to be used as first stage of a solid Nova design. 4 used as first stage of solid Nova design. Extended high-expansion nozzles. Masses estimated based on total vehicle thrust, performance, and stage volumes.
Status: Study 1960.
Gross mass: 816,000 kg (1,798,000 lb).
Unfuelled mass: 102,000 kg (224,000 lb).
Height: 35.10 m (115.10 ft).
Diameter: 5.20 m (17.00 ft).
Span: 5.20 m (17.00 ft).
Thrust: 11,120.00 kN (2,499,870 lbf).
Specific impulse: 285 s.
Burn time: 175 s.
More... - Chronology...
Associated Countries
Associated Engines
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200 inch solid segment x 4 Notional solid rocket engine. 11,120 kN. Study 1960. Isp=285s. 4 used as first stage of NASA all-solid Nova design. Extended high-expansion nozzles. More...
Associated Launch Vehicles
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Nova 5S American heavy-lift orbital launch vehicle. NASA Nova design using segmented solid motors in first and second stages. Five six segment motors in first stage; four four segment motors in second stage, equivalent to 9 x F-1 first stage and 4 x F-1 second 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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