Ion thruster discharge chamber magnetic pole structure and design method thereof

Abstract

The invention discloses an ion thruster discharge chamber magnetic pole structure which comprises a lower magnetic pole (1), a middle magnetic pole (2), an upper magnetic pole (3), a lower pole shoe (4), a middle pole shoe (5) and an upper pole shoe (6). The lower pole shoe (4), the middle pole shoe (5) and the upper pole shoe (6) are correspondingly connected with the lower magnetic pole (1), the middle magnetic pole (2) and the upper magnetic pole (3). The structure further comprises permanent magnets (9 and 10). A magnetic force line loop is formed among the magnetic poles through the pole shoes (4, 5 and 6) and the permanent magnets (9 and 10). A loop tip cusped magnetic field is formed in a discharge chamber. The structure is characterized in that positive pole cylinders (7 and 8) of the discharge chamber are arranged in the cusped magnetic field, all the magnetic poles extend to the inner surfaces of the positive pole cylinders (7 and 8) and are charged with negative electricity relative to the positive pole cylinders (7 and 8), and a discharge chamber negative pole (11) installed on the lower pole shoe (4) directly extends into the discharge chamber under the circumstance without the positive pole cylinders ahead. The invention further discloses a design method for the ion thruster discharge chamber magnetic pole structure. When the structure is used, the primary electron utilization rate can be increased, and the discharging efficiency and the beam uniformity are improved.

Description

technical field [0001] The invention relates to a magnetic pole structure of an ion thruster discharge chamber and a design method thereof, belonging to the fields of aerospace technology and low-temperature plasma technology. Background technique [0002] As an advanced space propulsion technology, the ion thruster has the advantages of high specific impulse, long life, compact structure, precise and controllable thrust, etc. It has become one of the most widely used space electric propulsion devices at home and abroad. The level of comprehensive performance of the ion thruster is mainly reflected in the realization of efficiency indicators and plasma confinement capabilities, including high working fluid utilization, low discharge loss and high beam straightness. The physical basis for achieving the above goals is the size and layout design of the magnetic poles of the discharge chamber. The optimized magnetic pole structure produces an optimized magnetic field configurati...

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Problems solved by technology

Otherwise, the ion density near the central axis of the grid will be higher than the edge density, and the focusing performance of the grid holes near the central axis will deteriorate, resulting in poor grid stability.

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