Patent ID: 6546714
Filing Date: 2003-04-15
Classification: C06B,C06D

Abstract:
A reduced toxicity fuel satellite propulsion system comprising:a first reduced toxicity liquid propellant supply, wherein the first propellant includes a reduced toxicity satellite fuel; a thruster, wherein the thruster includes a decomposing element, wherein the decomposing element is operative to decompose the propellant; and wherein the decomposing element includes a plasmatron; means for selectively supplying the propellant to the decomposing element, whereby the propellant is decomposed into hot gases; a second liquid propellant supply, wherein the second propellant includes an oxidizer; a second supplying means for selectively supplying the second propellant to the thruster, and wherein the second supplying means is operative to selectively supplying the second propellant to the thruster.