Castor engine
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Multiple-source solid rocket engine. Out of Production. Used in Jupiter C, Juno 2. First flight 1956.
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.
Related
- 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