The use of a liquid oxidizer-solid fuel hybrid propellant combination in booster rocket motors appears extremely attractive due to the integration of the best features of liquid and solid propulsion systems. The hybrid rocket combines the high performance, clean exhaust, and safety of liquid propellant engines with the low cost and simplicity of solid propellant motors. Additionally, the hybrid rocket has unique advantages such as an inert fuel grain and a relative insensitivity to fuel grain and oxidizer injection anomalies. The advantages mark the hybrid rocket as a potential replacement or alternative for current and future solid propellant booster systems. The issues are addressed and recommendations are made concerning oxidizer feed systems, injectors, and ignition systems as related to hybrid rocket propulsion. Early in the program a baseline hybrid configuration was established in which liquid oxygen would be injected through ports in a solid fuel whose composition is based on hydroxyl terminated polybutadiene (HTPB). Liquid oxygen remained the recommended oxidizer and thus all of the injector concepts which were evaluated assumed only liquid would be used as the oxidizer.
Hybrid Propulsion Technology Program: Phase 1, Volume 4
1989
59 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Booster rocket engines , Hybrid propulsion , Oxidizers , Propulsion system configurations , Propulsion system performance , Feed systems , Fuel injection , Htpb propellants , Hybrid propellants , Ignition systems , Injectors , Liquid oxygen , Liquid rocket propellants , Solid propellant rocket engines
Hybrid propulsion technology program: Phase 1, volume 1
NTRS | 1989
|Hybrid Propulsion Technology Program: Phase 1, Volume 2
NTIS | 1989
|Hybrid propulsion technology program: Phase 1, volume 4
NTRS | 1989
|Hybrid Propulsion Technology Program: Phase 1, Volume 1
NTIS | 1989
|Hybrid propulsion technology program: Phase 1, volume 2
NTRS | 1989
|