Spacecraft propulsion devices and systems with microwave excitation
A thruster system for use in a spacecraft includes a microwave source, a resonant cavity coupled to the microwave source, wherein the microwave source is configured to generate a standing wave field in the resonant cavity, a nozzle provided at one end of the resonant cavity; and at least one injector configured to inject propellant into the resonant cavity so as to create a rotating circumferential flow. The standing wave field raises a temperature of the injected propellant to provide thrust by way of a hot gas exiting the resonant cavity via the nozzle.
1. A thruster system for use in a spacecraft, the thruster system comprising:
a microwave source;
a structure configured to rotate relative to a housing of the spacecraft and including a resonant cavity coupled to the microwave source, wherein the microwave source is configured to generate a standing wave field in the resonant cavity;
a nozzle provided at one end of the resonant cavity; and
at least one injector configured to inject propellant into the resonant cavity, wherein rotating the structure imparts angular momentum to the injected propellant and creates a rotating circumferential flow;
wherein the standing wave field heats the injected propellant to provide thrust by way of the heated injected propellant exiting the resonant cavity via the nozzle.
2. The thruster system of claim 1 , wherein the resonant cavity is cylindrical.
3. The thruster system of claim 1 , wherein the structure includes:
a hollow shaft mechanically connected to a motor and attached to a second end of the cavity opposite to the one end of the resonant cavity with the nozzle.
4. The thruster system of claim 1 , further including:
a support bearing configured to support the one end of the resonant cavity with the nozzle.
5. The thruster system of claim 1 , further including:
a cap configured to cover the one end of the resonant cavity with the nozzle to prevent the propellant from leaking out of the resonant cavity in one mode of operation, and to uncover the one end of the resonant cavity with the nozzle in another mode of operation.
6. The thruster system of claim 1 , further including:
two electrodes disposed within the resonant cavity; and
a source of voltage configured to create an arc between the two electrodes by ionizing the injected propellant.
7. The thruster system of claim 6 , wherein
one of the two electrodes is disposed at the nozzle.
8. The thruster system of claim 1 , wherein the structure configured to rotate is a first structure and the thruster system includes:
a second structure configured to rotate relative to the housing of the spacecraft to thereby generate angular momentum in the direction opposite to angular momentum generated by the first structure.
9. The thruster system of claim 8 , wherein:
the second structure configured to generate angular momentum equal in magnitude to the angular momentum generated by the first structure to thereby minimize a total angular momentum of the first structure and the second structure.
10. The thruster system of claim 8 , wherein:
the second structure configured to generate angular momentum different in magnitude to the angular momentum generated by the first structure to thereby cause the spacecraft to turn.
11. A method in a spacecraft for operating a thruster that includes a microwave source, a resonant cavity, and a source of propellant which the thruster uses to generate thrust, the method comprising:
injecting a propellant into the resonant cavity, including imparting angular momentum to the injected propellant, wherein imparting the angular momentum to the injected propellant includes rotating a structure including the resonant cavity relative to a housing of the spacecraft, along a thrust axis; and
causing the microwave source to generate a standing wave within the resonant cavity to heat the injected propellant and provide thrust by way of the heated injected propellant exiting the resonant cavity via a nozzle, wherein the angular momentum imparted to the injected propellant produces a rotating circumferential flow of the injected propellant within the resonant cavity.
12. The method of claim 11 , wherein imparting the angular momentum to the injected propellant includes injecting the propellant into the resonant cavity at an angle relative to a thrust axis.
13. The method of claim 11 , further including:
covering the nozzle with a cap to prevent the propellant from leaking out of the resonant cavity in one mode of operation, and uncovering the nozzle in another mode of operation.
14. The method of claim 11 , wherein rotating the structure includes:
rotating a hollow shaft mechanically connected to a motor and attached to a first end of the resonant cavity.
15. The method of claim 14 , further including:
supporting a second end of the resonant cavity with a support bearing.
16. The method of claim 11 , further including:
generating an arc between two electrodes disposed within the resonant cavity using a source of voltage to ionize the injected propellant.
17. The method of claim 16 , wherein:
at least one of the two electrodes is disposed at the nozzle.
18. The method of claim 11 , wherein the structure configured to rotate is a first structure and the method includes:
rotating a second structure relative to the housing of the spacecraft to thereby generate angular momentum in the direction opposite to angular momentum generated by rotating the first structure.
19. The method of claim 18 , wherein:
rotating the second structure generates angular momentum equal in magnitude to the angular momentum generated by the first structure to thereby minimize a total angular momentum of the first structure and the second structure.
20. The method of claim 18 , wherein:
rotating the second structure generates angular momentum different in magnitude to the angular momentum generated by the first structure to thereby cause the spacecraft to turn.