Multiple-source solid rocket engine. 80 kN. Typical ideal dV=259 m/s; gravity and drag losses = 25 m/s.
Gross mass: 272 kg (599 lb).
Unfuelled mass: 153 kg (337 lb).
Height: 1.80 m (5.90 ft).
Diameter: 0.33 m (1.08 ft).
Thrust: 80.00 kN (17,984 lbf).
Burn time: 2.50 s.
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Associated Countries
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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...
Associated Stages
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Aerobee 300A-1 Solid propellant rocket stage. Loaded/empty mass 272/153 kg. Thrust 80.00 kN. Vacuum specific impulse 167 seconds. Typical ideal dV=259 m/s; gravity and drag losses = 25 m/s. More...
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