Encyclopedia Astronautica
Castor 4B


Thiokol solid rocket engine. 430.6 kN. Out of production. The Castor 4B, which incorporated thrust vector control in the series for the first time, was developed for ESA's Maxus (first flown in 1991). Isp=281s. First flight 1982.

Thrust (sl): 337.100 kN (75,783 lbf). Thrust (sl): 34,378 kgf. Chamber Pressure: 32.50 bar. Area Ratio: 12.1.

AKA: Castor 4B; TX-780B.
Status: Out of production.
Gross mass: 11,400 kg (25,100 lb).
Unfuelled mass: 1,400 kg (3,000 lb).
Height: 9.20 m (30.10 ft).
Diameter: 1.02 m (3.34 ft).
Thrust: 430.60 kN (96,803 lbf).
Specific impulse: 281 s.
Specific impulse sea level: 220 s.
Burn time: 64 s.
Number: 3 .

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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 4B Solid propellant rocket stage. Loaded/empty mass 11,400/1,400 kg. Thrust 430.61 kN. Vacuum specific impulse 281 seconds. Optimized for high altitude (Conestoga) More...

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