Electrically powered supersonic and hypersonic propulsor

A system for electromagnetically exciting certain molecules within a volume of gaseous working fluid or charge via transition frequency heating for propulsion, comprising:

• an electrical energy source (EES);
• an electromagnetic wave generator (EWG);
• wherein said EES supplies power to said EWG;
• a reflection coefficient measurement device (RCMD) that is electrically coupled to said EWG;
• a controllable electrical matching network (EMN);
• a proportional integral derivative controller (PIDC);
• wherein said RCMD is electrically coupled to said EMN and said PIDC;
• wherein said PIDC is electrically coupled to said EMN;
• and a propulsor cavity (PC) that is electromagnetically coupled to said EMN;
• wherein said PC further comprises a transmission line that comprises a waveguide and a radio frequency (RF) window;
• wherein said RF window provides optical access to a heating zone where the charge resides or passes through;
• wherein said heating zone resides in the flow path between a propulsion system's charge inlet and nozzle exhaust;
• wherein said RCMD transmits an electromagnetic signal through said PC to and from said heating zone;
• wherein said heating zone further comprises the location of a final inlet shock.