Encyclopedia Astronautica
Castor 4


Thiokol solid rocket engine. 407.2 kN. Series of motors used as Delta strap-on boosters and as first and upper stages for low-cost all-solid-propellant designs. Isp=261s. First flight 1975.

Thrust (sl): 355.700 kN (79,965 lbf). Thrust (sl): 36,274 kgf.

AKA: Castor 4; TX-526.
Gross mass: 10,534 kg (23,223 lb).
Unfuelled mass: 1,269 kg (2,797 lb).
Height: 9.07 m (29.75 ft).
Diameter: 1.02 m (3.34 ft).
Thrust: 407.20 kN (91,542 lbf).
Specific impulse: 261 s.
Specific impulse sea level: 228 s.
Burn time: 54 s.
Number: 342 .

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Associated Countries
See also
Associated Manufacturers and Agencies
  • Thiokol American manufacturer of rocket engines and rockets. Thiokol Corporation, Ogden, UT, USA. More...

Associated Propellants
  • 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
  • Castor 4 Solid propellant rocket stage. Loaded/empty mass 10,534/1,269 kg. Thrust 407.21 kN. Vacuum specific impulse 261 seconds. More...

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