An applied research and development program has been conducted on prepackaged hybrid propellant systems suitable for application to advanced tactical missile requirements. An 18-in.-diameter flight configuration hybrid motor has been designed, fabricated, and tested. A high density, high specific impulse, hybrid propellant combination has been formulated; and a fuel grain geometry has been developed which will provide nearly constant fuel flow rate and permit nearly complete fuel utilization. Dual-thrust oxidizer injectors have been developed and successfully tested. A simple thrust control system has been designed, which will control the motor thrust at two levels and will permit multiple starts at either thrust level. The results of the program indicate that high density impulse hybrid propulsion systems are feasible for application to advanced tactical missiles. (Author)
Experimental Investigation of Prepackaged Hybrid Propellant Systems
1967
126 pages
Report
Keine Angabe
Englisch
Rocket Propellants , Rocket Engines & Motors , Combustion & Ignition , Hybrid rocket propellants , Packaging , Dual thrust rocket engines , Design , Hybrid rocket engines , Specific impulse , Thrust , Starting , Feasibility studies , Combustion chambers , Injection , Liquid rocket oxidizers , Solid rocket fuels , Control systems , Rocket nozzles , Burning rate , Rocket propellant grains , Solid rocket propellant binders , Bromine pentafluoride , Chlorine pentafluoride , End burning propellants , Guanidine azide/triamino , Guanidine hydrazine diazide/triamino
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