Spacecraft propulsion devices and systems with microwave excitation
A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.
1. A multi-mode thruster system for use in a spacecraft, the thruster system comprising:
a microwave source;
a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and
a nozzle provided at one end of the cavity;
wherein:
the multi-mode thruster system operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust, and
the multi-mode thruster system operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.
2. The multi-mode thruster system of claim 1 , wherein the cavity receives at least one of (i) water, (ii) hydrozene, (iii) hydrogen peroxide, or (iii) ammonia as the first fluid via the first inlet when the thruster operates in the MET mode.
3. The multi-mode thruster system of claim 1 , wherein the cavity operates as a resonant cavity when the thruster operates in the MET mode.
4. The multi-mode thruster system of claim 1 , wherein the cavity receives an oxidation agent via the first inlet and a reducing agent via the second inlet when operating in the chemical propulsion mode.
5. The multi-mode thruster system of claim 1 , wherein:
the first inlet receives a same fluid in the MET mode and the chemical propulsion mode, and
the fluid operates as propellant in the MET mode and as an oxidation agent in the chemical propulsion mode.
6. The multi-mode thruster system of claim 1 , wherein the first fluid includes hydrogen peroxide.
7. The multi-mode thruster system of claim 1 , further comprising:
a controller configured to (i) activate the MET mode in response to determining that the spacecraft requires a first amount of thrust, and (ii) activate the chemical propulsion mode in response to determining that the spacecraft requires a second amount of thrust larger than the first amount of thrust.
8. The multi-mode thruster system of claim 1 , wherein:
in the MET mode, the first fluid is water; and
in the chemical propulsion mode, the first fluid is oxygen and the second fluid is hydrogen.
9. The multi-mode thruster system of claim 8 , further comprising:
a propellant tank configured to store water; and a fuel cell configured separately store oxygen and hydrogen.
10. The multi-mode thruster system of claim 1 , wherein the first fluid includes an additive for depositing a coating material onto an inner surface of the nozzle.
11. The multi-mode thruster system of claim 10 , wherein the additive incudes at least one of (i) an oxide ceramic, (ii) a non-oxide ceramic, (iii) a refractory metal, or (iv) a coating agent that forms a diamond film or sapphire film.
12. A method of operating, in a spacecraft, a multi-mode thruster system that includes a microwave source, a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity, the method comprising:
operating, during a first period of time, the thruster system in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust; and
operating, during a second period of time, the thruster system in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.
13. The method of claim 12 , further comprising:
receiving, at the cavity and when operating in the MET mode, at least one of (i) water, (ii) hydrozene, (iii) hydrogen peroxide, or (iii) ammonia as the first fluid via the first inlet.
14. The method of claim 12 , further comprising:
operating the cavity as a resonant cavity, when the thruster system is in the MET mode.
15. The method of claim 12 , further comprising:
receiving, at the cavity and when operating in the chemical propulsion mode, an oxidation agent via the first inlet and a reducing agent via the second inlet.
16. The method of claim 12 , wherein:
the first inlet receives a same fluid in the MET mode and the chemical propulsion mode, and
the fluid operates as propellant in the MET mode and as an oxidation agent in the chemical propulsion mode.
17. The method of claim 12 , further comprising:
including, in the first fluid, an additive for depositing a coating material onto an inner surface of the nozzle.
18. The method of claim 12 , further comprising:
using a controller to (i) activate the MET mode in response to determining that the spacecraft requires a first amount of thrust, and (ii) activate the chemical propulsion mode in response to determining that the spacecraft requires a second amount of thrust larger than the first amount of thrust.
19. The method of claim 18 , wherein the additive incudes at least one of (i) an oxide ceramic, (ii) a non-oxide ceramic, (iii) a refractory metal, or (iv) a coating agent that forms a diamond film or sapphire film.