Patent ID: 6378291
Filing Date: 2002-04-30
Classification: C06B,C06D

Abstract:
A reduced toxicity fuel satellite propulsion system comprising:a first liquid propellant supply, wherein the first propellant includes hydrogen peroxide; a thruster, wherein the thruster includes a combustion chamber and a catalytic decomposing element, wherein the catalytic decomposing element is operative to decompose the first propellant; a first supplying means for selectively supplying the first propellant to the catalytic decomposing element, whereby the first propellant is decomposed into hot gases, wherein the catalytic decomposing element is operative to output the hot gases to the combustion chamber; a second liquid propellant supply which includes a reduced toxicity satellite fuel other than hydrogen peroxide; a second supplying means for selectively supplying the second propellant to the combustion chamber of the thruster; and a third supplying means for selectively supplying the first propellant to the combustion chamber, whereby the hot gases, the first propellant and the second propellant auto-ignite and produce thrust for maneuvering the satellite.