A discharge chamber structure of an ion thruster

Abstract

An ion thruster discharge chamber structure comprises a conical segment portion and a column segment portion, the conical segment portion is composed of two conical segments forming an angle, and specifically, the structure is composed of a cathode magnetic conductive ring at one end of a discharge chamber cathode, a conical segment middle magnetic conductive ring at t he middle segment of the discharge chamber conical segment and a middle magnetic conductive ring arranged at the juncture of the discharge chamber conical segment and the column segment. The column segment portion is composed of two column segments, and is specially composed of a middle magnetic conductive ring, a column segment middle magnetic conductive ring in the middle of the discharge chamber column segment and a screen grid magnetic conductive ring at the end, close to the grid electrode, of the discharge chamber; an annular tip discharge chamber magnetic field is formed by column permanent magnets circumferentially and uniformly mounted between two sequential adjacent parts in the cathode magnetic conductive ring, the conical segment middle magnetic conductive ring, the middle magnetic conductive, the column segment middle magnetic conductive and the screen grid magnetic conductive ring, wherein according to the annular tip discharge chamber magnetic field, the magnetic directions of N and S in the discharge chamber are alternatively changed. The ion thruster discharge chamber structure has the beneficial effects of being high in ionization efficiency, uniform in plasma distribution, good in beam straightness, uniform in beam distribution, weak in magnetic induction intensity of a permanent magnet and the like.

Description

technical field [0001] The invention relates to the technical field of ion thrusters, in particular to a discharge chamber structure of an ion thruster. Background technique [0002] Compared with the conventional chemical propulsion system, the electric propulsion system has the characteristics of small thrust, high specific impulse, long life, adjustable thrust and good safety, so that it can perform the same aerospace mission in the space field. It saves propellant quality demand, greatly improves control accuracy, and is more suitable for long-term high-speed flight. The design of the discharge chamber of the ion thruster is its core design content. Optimizing the magnetic field design of the discharge chamber can better confine the primary electrons, thereby reducing discharge loss, improving working fluid utilization, beam flatness and prolonging working life. [0003] According to Chinese patent CN201510410241.8, in the design of the existing ion thruster discharge c...

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Problems solved by technology

[0003] According to Chinese patent CN201510410241.8, in the design of the existing ion thruster discharge chamber ring tip magnetic field discharge chamber, the cone section of the discharge chamber is designed to be two sections, but the two sections of cone sections are on a straight line, forming a 45° clip with the axis of the discharge chamber At the same time, there is only one section of the column section. This design causes the "magnetic void" in the discharge chamber to account for no more than 50% of the entire discharge chamber, resulting in poor uniformity and straightness of the beam. When the axis of the discharge chamber is close to the grid The beam density is too high, in the design of the ion thruster that requires high beam density and long life, it cannot meet the requirements of the thruster working for a long time, so the magnetic field distribution of the discharge chamber is no longer applicable

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