초록 ▼

A hybrid heater vaporization system (280, 380) including hybrid heaters (250, 350) can be used to vaporize liquid oxygen as it enters a motor (200, 300) to improve the combustion characteristics of a hybrid rocket (11). The motor (200, 300) preferably includes hybrid fuel both in a substantially cyl

A hybrid heater vaporization system (280, 380) including hybrid heaters (250, 350) can be used to vaporize liquid oxygen as it enters a motor (200, 300) to improve the combustion characteristics of a hybrid rocket (11). The motor (200, 300) preferably includes hybrid fuel both in a substantially cylindrical portion (216, 316) in the substantially cylindrical portion of the motor and a substantially multi-toroidal shaped portion (217, 316) in the forward end of the motor (200, 300). The vaporization system (280, 380) of the present invention finally makes hybrid rockets (11) practical for aerospace applications.

대표청구항 ▼

[ I claim:] [1.] A method of improving combustion of a rocket comprising a first fluid propellant component and a second propellant component, wherein the second propellant component is in a casing, wherein the first fluid propellant component enters the casing in a stream, and wherein the rocket ha

[ I claim:] [1.] A method of improving combustion of a rocket comprising a first fluid propellant component and a second propellant component, wherein the second propellant component is in a casing, wherein the first fluid propellant component enters the casing in a stream, and wherein the rocket has a burn of a duration characterized by the burning of said propellant components, comprising the following steps:(a) providing a first oxygen-driven hybrid heater having an exhaust stream having combustion products when ignited;(b) positioning the hybrid heater such that the exhaust stream of combustion products of the hybrid heater are directed into the casing of the second propellant component when the hybrid heater is ignited and intersects the stream of the first fluid propellant component within the casing substantially throughout the burning of said propellant components;(c) providing a sufficient quantity of oxygen to enable the hybrid heater to burn during substantially the entire duration of the rocket burn; and(d) igniting the hybrid heater and supplying the sufficient quantity of oxygen to the hybrid heater such that the hybrid heater burns during substantially the entire duration of the rocket burn.