Patent ID: 6311477
Filing Date: 2001-11-06
Classification: C06B,C06D

Abstract:
A reduced toxicity fuel satellite propulsion system comprising:a first reduced toxicity propellant supply;a second propellant supply;an axial thruster, wherein the axial thruster includes an axial decomposing element and a combustion chamber, wherein the axial decomposing element is operative to decompose the first propellant into a hot gas, and wherein the decomposing element is operative to output the hot gas into the combustion chamber;an altitude control system (ACS) thruster, wherein the ACS thruster includes an ACS decomposing element, wherein the ACS decomposing element is operative to decompose the second propellant;means for selectively supplying the first propellant to the axial decomposing element;means for selectively supplying the second propellant to the combustion chamber of the axial thruster, whereby the second propellant and the hot gases auto-ignite and produce thrust for maneuvering the satellite; andmeans for selectively supplying the first propellant to the ACS decomposing element, whereby the first propellant is decomposed into a propulsive gas and thrust for stationkeeping is produced.