Castor 4B engine

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Castor 4B engine

Part of Castor 4

Thiokol solid rocket engine. 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). First flight 1982. Solid propellant rocket stage. Optimized for high altitude (Conestoga).

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

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

Country: USA. Launch Vehicles: Maxus, EER Aries, Conestoga 1620, Castor 4B, Castor-M57A1. Propellants: Solid. Stages: Castor 4B engine. Agency: Thiokol.

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