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Castor engine

Encyclopedia Astronautica
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Castor engine
Multiple-source solid rocket engine. Out of Production. Used in Jupiter C, Juno 2. First flight 1956.
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AKA: Sergeant. Status: Out of Production. Number: 285 . Thrust: 6.66 kN (1,497 lbf). Gross mass: 42 kg (92 lb). Unfuelled mass: 21 kg (46 lb). Specific impulse: 235 s. Specific impulse sea level: 214 s. Burn time: 6.00 s. Height: 1.00 m (3.20 ft). Diameter: 0.30 m (0.98 ft).

Thrust (sl): 6.073 kN (1,365 lbf). Thrust (sl): 619 kgf. Propellant Formulation: Polysulfide.

Subtopics
Jupiter C-2 Aerojet solid rocket stage. 80.00 kN (17,985 lbf) thrust. Mass 500 kg (1,102 lb).
Juno II-3 Aerojet solid rocket stage. 22.00 kN (4,946 lbf) thrust. Mass 100 kg (220 lb).
RTV-100 Aerojet solid rocket engine.
Country: USA. Launch Vehicles: Jupiter C, X-17, Bold Orion 1, Sergeant 5-stage, Juno II, Bold Orion 2, Journeyman, Sergeant Sounding Rocket, Sergeant Hydac, Talos Sergeant Hydac, Space Data LCLV, Starbird, Storm. Propellants: Solid. Stages: Castor engine.
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