Reduced toxicity fuel satellite propulsion system including axial thruster and ACS thruster combination

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;
• and
• means 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.