An innovative propulsion system is proposed that uses a monopropellant consisting of liquid oxygen and solid kerosene particles uniformly suspended in the liquid oxygen. This original and imaginative approach combines the best features of solid and liquid propulsion. Like a solid propulsion system, the fuel and oxidizer are premixed into a uniform mixture with reliable ignition and combustion properties. Yet, the propellant is a liquid so it can be burned in a small combustion chamber, loaded into a rocket at the launch pad and be injected at variable rates to throttle the engine during a mission. This propulsion system will benefit NASA by supporting the need for lower cost boosters, upper stages and orbital transfer vehicles by using a low cost propellant and a reduced number of components when compared to conventional propulsion systems. The Phase I objective is to determine the LOX/kerosene rocket engine's feasibility by evaluating key components with subscale engine tests. Critical monopropellant properties will also be measured to determine its feasibility for use in launch vehicles.Phase I results are expected to be positive and lay the foundation for Phase II which will be the development of a test weight rocket engine system. The first commercial application will be the incorporation of this engine system into a new low cost sounding rocket. This new rocket will have capabilities similar to the Black Brant V. Other commercial applications include strap-on boosters (Castor Class) and small launch vehicles (Scout Class). Future commercial sales may include a pump-fed version targeted as a replacement for the main engines of the Atlas and Delta rockets. At NASA's discretion, these engines may also be considered for man-rated applications such as replacements for the Shuttle SRBs and OMS engines.
