CSD solid rocket engine. 564.2 kN. Isp=255s. Used on Scout A, Scout B, Scout X-3, Scout X-4; proposed as strap-on for Titan 3BAS2. First flight 1962.
Thrust (sl): 513.300 kN (115,394 lbf). Thrust (sl): 52,347 kgf.
Gross mass: 11,600 kg (25,500 lb).
Unfuelled mass: 1,650 kg (3,630 lb).
Height: 9.09 m (29.82 ft).
Diameter: 1.01 m (3.31 ft).
Thrust: 564.20 kN (126,837 lbf).
Specific impulse: 255 s.
Specific impulse sea level: 232 s.
Burn time: 47 s.
Number: 67 .
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Associated Countries
See also
Associated Launch Vehicles
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Titan 3BAS2 American orbital launch vehicle. Configuration of Titan 3B proposed by Martin in mid-1960's. Titan 3B for deep space missions with Centaur upper stage, Algol strapons for liftoff thrust augmentation. Never flown. More...
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Scout X-3 American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair More...
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Scout X-4 American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair 2 More...
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Scout B American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2B + 1 x Castor 2 + 1 x Antares 2 + 1 x FW4S More...
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Scout A American all-solid orbital launch vehicle. All-solid low cost lightweight launch vehicle. More...
Associated Manufacturers and Agencies
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CSD American manufacturer of rocket engines. Chemical Systems Division, USA. 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...
Associated Stages
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Algol 2 Solid propellant rocket stage. Loaded/empty mass 11,600/1,650 kg. Thrust 564.25 kN. Vacuum specific impulse 255 seconds. More...
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