Rocket Propulsion Engineering Company (RP) will design and build a working prototype of a hydrogen film-cooled liquid propellant rocket engine. This engine will be ready for test. Propellants will be liquid oxygen and liquid hydrogen, but because of the nature of the engine coolant system, little modification should be required to adapt the engine design to other propellant combinations, such as liquid oxygen (Lox)/kerosene and hydrogen peroxide. Engines of this class will run cool (~400 F) to the touch, and have low manufacturing tolerances, permitting fabrication in low-cost machine shops from light weight materials, such as aluminum and composites, that are easy and inexpensive to manufacture. For that reason, engine thrust to weight should be outstanding.
Keywords: Liquid Cooled Rocket Engines, Lox/Hydrogen, Low Cost, Film Cooled, High Thrust-To-Weight
