Hybrid Propulsion System for an Advanced Rocket-Powered Target Missile
Hybrid Propulsion System for an Advanced Rocket-Powered Target Missile
- Neue Suche nach: R. A. Jones
- Neue Suche nach: R. A. Jones
A demonstration program has been completed to determine the feasibility of a low-cost hybrid propulsion system for an advanced rocket-powered target vehicle. During a 21-month program a flightweight hybrid propulsion system was designed, fabricated, and successfully tested in numerous static firings at ambient conditions, temperature extremes of -65 F to +165 F and at altitude conditions in the AFRPL altitude facility. The final system design demonstrated step-thrust operation over an 8:1 thrust range which was provided on-command from boost thrust to sustain thrust. The sustain thrust level is selected prior to system firing by setting a flow control valve which provides 'dial-a-thrust' flexibility. The final phase of the program involved flight tests with a target vehicle airframe which demonstrated the hybrid propulsion system capability to provide command step-thrust operation, powered flight times approaching 5 min, and reliable operation following aircraft launch at 49,000 ft, Mach 1.5. (Author)
Dokumentinformationen
Hybrid Propulsion System for an Advanced Rocket-Powered Target Missile
1968
372 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Missile Technology , Rocket Propellants , Target drones , Hybrid rocket engines , Hybrid rocket propellants , Aerial targets , Costs , Storage , Solid rocket fuels , Liquid rocket oxidizers , Combustion chambers , Propellant control , Nitrogen oxides , Acrylic resins , Rocket nozzles , Guided missile targets , Feasibility studies , Design , Captive tests , Altitude chambers , Thrust , Flight testing , Air-to-air , Vibration , Controllable-thrust rocket motors , Aqm-37 drones , Nitrogen oxide(NO2) , Nitrogen oxide(NO) , Nitrogen oxide(N2O2)
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