Reduced toxicity fuel satellite propulsion system

A reduced toxicity fuel satellite propulsion system comprising:

• a reduced toxicity liquid propellant supply;
• a second liquid propellant supply;
• a thruster, wherein the thruster includes a decomposing element and a combustion chamber;
• means for selectively supplying the reduced toxicity liquid propellant to the decomposing element, wherein the decomposing element is operative to decompose the reduced toxicity liquid propellant into hot gases and output the hot gases into the combustion chamber;
• means for selectively supplying the second propellant to the combustion chamber of the thruster;
• and
• means for selectively supplying the reduced toxicity liquid propellant to the combustion chamber;
• whereby the hot gases, the reduced toxicity liquid propellant and the second propellant auto-ignite and produce thrust for maneuvering the satellite.

A method for propelling a satellite comprising the steps of:

• supplying a thruster with a first reduced toxicity propellant, wherein the first reduced toxicity propellant includes methylamine;
• decomposing the first propellant into hot gases;
• supplying the thruster with a second propellant, wherein the second propellant includes liquid oxygen;
• and
• combining the hot gases with the second propellant inside a combustion chamber of the thruster, whereby the second propellant and hot gases auto-ignite and produce thrust for maneuvering the satellite.