LIQUID/SOLID FUEL HYBRID PROPELLANT SYSTEM FOR A ROCKET

摘要

A hybrid propulsion system comprises a liquid fuel section and a solid fu el section. The liquid fuel section contains an aqueous solution of hydrogen peroxide. An injector system is located between the liquid fuel section and the solid fuel section. The injector system injects a stream of hydrogen peroxide or a decomposed stream of hydrogen peroxide at elevated temperatures into the solid fuel section to effect combustion of the fuel grain in the solid fuel section.