Patent ID: 6679049
Filing Date: 2004-01-20
Classification: F02K

Abstract:
A hybrid rocket motor, comprising:a) a container having a first fluid reactant therein and an outlet; b) a main combustion chamber containing a first solid reactant therein; c) a first fluid reactant injector between said container and said main combustion chamber through which said first fluid reactant is injected into said main combustion chamber to be combusted with said first solid reactant; d) a precombustion chamber at a head end of said main combustion chamber; e) a second fluid reactant which is injected into said precombustion chamber; and f) a third reactant which is contacted with said second fluid reactant in said precombustion chamber to form a combustible propellant, wherein heat generated from combustion of combustible propellant heats said injected first fluid reactant.