Thiokol solid rocket engine. 286 kN. Isp=247s. Used as apogee kick motor on Delta D, LT Thor Agena D, Scout X-1, Scout X-2, Scout X-3, Scout X-4, TA Thor Agena B, TA Thor Agena D. First flight 1960.
Thrust (sl): 268.600 kN (60,384 lbf). Thrust (sl): 27,393 kgf.
Gross mass: 3,852 kg (8,492 lb).
Unfuelled mass: 535 kg (1,179 lb).
Height: 5.92 m (19.42 ft).
Diameter: 0.79 m (2.59 ft).
Thrust: 286.00 kN (64,295 lbf).
Specific impulse: 247 s.
Specific impulse sea level: 232 s.
Burn time: 27 s.
Number: 141 .
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Associated Countries
See also
Associated Launch Vehicles
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Scout X-1 American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1B + 1 x Castor + 1 x Antares + 1 x Altair More...
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Scout X-2 American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1D + 1 x Castor + 1 x Antares 2 + 1 x Altair 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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Delta D American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta D + 1 x Altair 2 More...
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Thorad Agena D SLV-2H Thor Agena upgraded with Long Tank Thor stage. Variant with straight tank from Delta was Thorad (Long Tank Augmented Thrust Thor Delta) More...
Associated Manufacturers and Agencies
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Thiokol American manufacturer of rocket engines and rockets. Thiokol Corporation, Ogden, UT, 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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Castor 1 Solid propellant rocket stage. Loaded/empty mass 3,852/535 kg. Thrust 286.00 kN. Vacuum specific impulse 247 seconds. More...
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