Chemical-Microwave-Electrothermal Thruster

A thruster system for use in a spacecraft, the thruster system comprising:

• a cavity including at least one inlet to receive a monopropellant configured to chemically decompose within the cavity to generate a plurality of decomposition products;
• an energy source coupled to the cavity and configured to heat and ionize at least one of the plurality of decomposition products or the monopropellant by emitting electromagnetic radiation;
• and
• a nozzle provided at one end of the cavity and configured to direct at least one of the plurality of decomposition products out of the cavity to generate thrust.

A method of spacecraft propulsion comprising:

• receiving at a cavity via at least one inlet a first fluid and a second fluid configured to chemically react with the first fluid within the cavity to generate a reaction product;
• heating content of the cavity by electromagnetic radiation emitted by an energy source coupled to the cavity;
• and
• directing, via a nozzle, the heated content out of the cavity to generate thrust.