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.
Spacecraft Propulsion Devices and Systems with Microwave Excitation
17.09.2020
Patent
Elektronische Ressource
Englisch
IPC: | B64G Raumfahrt , COSMONAUTICS / H01J Elektrische Entladungsröhren oder Entladungslampen , ELECTRIC DISCHARGE TUBES OR DISCHARGE LAMPS / F03H PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR , Erzeugung von Vortriebskraft [Schub] nach dem Prinzip des Rückstoßes, soweit nicht anderweitig vorgesehen |
Spacecraft Propulsion Devices and Systems with Microwave Excitation
Europäisches Patentamt | 2021
|SPACECRAFT PROPULSION DEVICES AND SYSTEMS WITH MICROWAVE EXCITATION
Europäisches Patentamt | 2024
|Spacecraft Propulsion Devices and Systems with Microwave Excitation
Europäisches Patentamt | 2023
|Spacecraft propulsion devices and systems with microwave excitation
Europäisches Patentamt | 2021
|Spacecraft propulsion devices and systems with microwave excitation
Europäisches Patentamt | 2022
|