Surface plasma resonance and electron cyclotron resonance double-excitation type microwave thruster

Abstract

The invention discloses a surface plasma resonance and electron cyclotron resonance double-excitation type microwave thruster, relates to the technical field of spacecraft power, and relates to the thruster which is based on low-temperature non-equilibrium plasma, namely surface plasma, resonance and electron cyclotron resonance and is applied to a microsatellite power system for performing the tasks of satellite formation, deep space exploration and the like. The surface plasma resonance and electron cyclotron resonance double-excitation type microwave thruster is fixed into a vacuum environment through a thruster supporting frame, and comprises a permanent magnet ring, a discharge chamber, a metal antenna and a tail spraying pipe; the permanent magnet ring is mounted at the external part of the discharge chamber in a sleeving manner; the metal antenna is embedded into the interior of the discharge chamber; the permanent magnet ring is embedded into the thruster supporting frame; the tail spraying pipe is butted with an outlet of the discharge chamber. The surface plasma resonance and electron cyclotron resonance double-excitation type microwave thruster has the characteristics of being novel in structure, convenient in machining, small in size, high in stability, strong in specific impulse, long in thruster service life and the like.

Description

technical field [0001] The surface plasmon resonance and electron cyclotron resonance dual-excitation microwave thruster of the present invention relates to the field of spacecraft power technology, in particular to a low-temperature non-equilibrium plasma, that is, surface plasmon resonance and electron cyclotron resonance plasma applied to micro Satellite power systems, thrusters for missions such as satellite formation and deep space exploration. Background technique [0002] There is a growing need for electric propulsion in satellites and space probes. The high specific impulse of the plasma thruster can greatly reduce the propellant consumption and improve the payload quality. It can be said that future deep space probes will rely on plasma thrusters to achieve. [0003] In the past few years, the research heat of the quasi-neutral electrodeless plasma thruster has continued to heat up, which does not require an external neutralizer, saving parts of the thruster. El...

AI Technical Summary

Problems solved by technology

It is used to solve the problems in the prior art that microwave energy alone, especially low power fed into the discharge chamber, will have insufficient electric field energy, resulting in unstable breakdown voltage of the working fluid, low plasma formation efficiency, and high-density plasma region The small size leads to technical problems such as low stability of the thruster

Images