Abstract:
A reactor for a high specific impulse rocket motor and a method of generating a thrust with a high specific impulse propellant having a hydrogen or like working fluid. Combustion is accomplished by injecting a liquid oxidizer on a fuel grain characterized by an open-celled foamed matrix having a high degree of porosity to hold lithium or other fuel that becomes partially liquid under combustion chamber conditions. The matrix structure includes a metal, graphite or graphite-felt matrix having a melting temperature greater than the vaporization temperature of the lithium so that the liquefied lithium adheres to the matrix structure by surface tension under combustion conditions. The metal matrix may itself be a high performance fuel, such as aluminum or beryllium, coated with a metal of higher melting temperature. The fuel is loaded into the matrix structure while in a liquid state and in an inert atmosphere, either by immersion or by use of vacuum.
Abstract:
A system and method for utilizing and disposing of carbonaceous waste products accumulated aboard a spaceship, including human body generated wastes and other carbonaceous wastes, by processing the waste products into rocket propellants and utilizing such propellants for spaceship propulsion. The propellant compositions thus formulated are characterized by the presence of one or more fuel constituents and one or more inorganic oxidizer constituents (e.g., ammonium nitrate) in homogeneous admixture with the human body generated waste materials (e.g., human excrement).