Patent ID: 6640536
Filing Date: 2003-11-04
Classification: F02K

Abstract:
A hybrid rocket motor, comprising:a) a container having a fluid reactant therein and an outlet; b) a combustion chamber containing a solid reactant therein; c) an injector between said container and said combustion chamber; d) a turbopump including a turbine and a pump axially aligned with said outlet, said pump adapted to increase a pressure of fluid reactant exiting said outlet and injected through said injector into said combustion chamber; e) a heat exchanger having an inlet and an outlet; f) a fluid pathway extending between said inlet and one of said container and said pump; and g) an expansion chamber coupled to said outlet of said heat exchanger, said turbine being provided in said expansion chambers, wherein a first portion of said fluid reactant travels from said container through said fluid pathway and into said heat exchanger, and is heated within said heat exchanger and expanded within said expansion chamber, and said expanded fluid reactant powers said turbine of said turbopump, and a second portion of said fluid reactant travels from said container and is pumped by said pump of said turbopump into said combustion chamber.