Patent ID: 8387361
Filing Date: 2013-03-05
Classification: F02K,F05D

Abstract:
1. A hybrid rocket motor comprising: a container having a first fluid and/or gel reactant, a combustion chamber containing at least a first solid reactant therein and having at least one thrust nozzle at one end; a conduit in fluid communication between the container and the combustion chamber; at least one moveable combustion control member comprising an extensible or movable port sleeve located within the hybrid rocket motor and attached to a partitioning portion that defines an empty space receiving the first fluid reactant, the extensible/movable port sleeve restricting contact of the first fluid reactant to the first solid reactant in the combustion chamber such that it is then possible to regulate the exposure of the first solid reactant to the first fluid reactant; actuators controlled by a microprocessor to achieve a desired mass flow rate of the first fluid reactant and an extensible/movable position of the port sleeve; the partitioning portion prohibiting the first fluid reactant in the empty space from reacting with the solid reactant adjacent the empty space; and a flight computer using flight control algorithms to achieve control of the first fluid reactant and position of the extensible/moveable port sleeve, wherein: