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ION THRUSTER FOR THRUST VECTORED PROPULSION OF A SPACECRAFT
ION THRUSTER FOR THRUST VECTORED PROPULSION OF A SPACECRAFT
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机译：离子推力器，用于航天飞机的推力矢量化推进
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摘要
The present invention relates to an ion thruster (1) for thrust vectored propulsion of a spacecraft, comprising a reservoir (2) for a propellant (3), an emitter (4) having a base (7) and, on one side (71) of the base (7), at least one outlet (8) for emitting ions (3+) of the propellant (3), wherein the base (7) is connected to the reservoir (2) for providing flow of propellant (3) from the reservoir (2) to said at least one outlet (8), and an extractor (5) facing said one side (71) of the emitter (4) for extracting and accelerating the ions (3+) from the emitter (4), wherein the extractor (5) is split into sectors (5i) about an axis (T) which orthogonally runs through said one side (71) of the emitter (4), wherein said sectors (5i) are electrically insulated from one another.
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机译：本发明涉及一种用于航天器的推力矢量推进的离子推进器（1），包括用于推进剂（3）的容器（2），具有基部（7）的发射器（4）以及在一侧（7）底座（7）的 1 ），至少一个用于发射推进剂（3）的离子（3 + ）的出口（8），其中，底座（7）连接到容器（2）以提供推进剂（3）从容器（2）到所述至少一个出口（8）的流动，以及面向所述一侧（7 1 ），用于从发射器（4）提取和加速离子（3 + ），其中提取器（5）分为扇区（5 i < / Sub>）围绕正交于发射器（4）的所述一侧（7 1 ）的轴（T），其中所述扇区（5 i ）为彼此电绝缘。
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