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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Bibliographic Details
Main Authors SEIFERT, Bernhard, BULDRINI, Nembo, REISSNER, Alexander
Format Patent
LanguageEnglish
Published 30.09.2021
Subjects
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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Summary: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.
Bibliography:Application Number: US201917264893