Dual mode chemical rocket engine, and dual mode propulsion system comprising the rocket engine
OwnerKjell Anflo, Göran Bergmaninventors
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Abstract
The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit manoeuvres and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes. The present invention also relates to a dual mode chemical rocket engine for use in such systems. The engine uses low-hazardous storable liquid propellants and can be operated either in monopropellant mode or in bipropellant mode. The monopropellants used are a low-hazard liquid fuel-rich monopropellant, and hydrogen peroxide, respectively.
Claims13
A dual mode chemical rocket engine (100) having a primary reaction chamber (140) for hydrogen peroxide comprising a catalyst bed for hydrogen peroxide, which primary reaction chamber is connected to a secondary reaction chamber (150) having means for injection (125) therein of a fuel-rich monopropellant, characterized in that the fuel-rich monopropellant is a liquid ADN based, or HAN based monopropellant.
The dual mode chemical rocket engine of 1, additionally comprising in the secondary reaction chamber (150) a high temperature resistant catalytic device (135).
A method of generating thrust, comprising injecting a fuel-rich liquid monopropellant into a flow of hot oxidizer-rich gas obtained from the decomposition of hydrogen peroxide, so that the fuel-rich liquid monopropellant thereby is decomposed and combusted along with the oxidizer-rich gas, wherein the fuel-rich liquid monopropellant is ADN, or HAN based.
Dependencies are inferred from the claim text.