Ion thruster for thrust vectored propulsion of a spacecraft

The disclosed subject matter relates to an ion thruster for thrust vectored propulsion of a spacecraft, comprising a reservoir for a propellant, an emitter having a base and, on one side of the base, at least one outlet for emitting ions of the propellant, wherein the base is connected to the reserv...

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Bibliographische Detailangaben
Hauptverfasser:	Buldrini, Nembo, Seifert, Bernhard, Reissner, Alexander
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT AVIATION BLASTING COSMONAUTICS HEATING LIGHTING MACHINES OR ENGINES FOR LIQUIDS MECHANICAL ENGINEERING OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR PERFORMING OPERATIONS PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDEDFOR PRODUCING MECHANICAL POWER TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR WEAPONS WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS
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Beschreibung
Zusammenfassung:	The disclosed subject matter relates to an ion thruster for thrust vectored propulsion of a spacecraft, comprising a reservoir for a propellant, an emitter having a base and, on one side of the base, at least one outlet for emitting ions of the propellant, wherein the base is connected to the reservoir for providing flow of propellant from the reservoir to said at least one outlet, and an extractor facing said one side of the emitter for extracting and accelerating the ions from the emitter, wherein the extractor is split into sectors about an axis which orthogonally runs through said one side of the emitter, wherein said sectors are electrically insulated from one another.