Bidirectional wave plasma thruster for spacecraft

Abstract

The invention relates to aerospace engineering, and discloses a bidirectional wave plasma thruster for a spacecraft, comprising a gas discharge chamber defining a thrust axis, an antenna, a radio frequency generator module electrically coupled to the antenna, a magnetic system, the antenna forms two thrust vectors in opposite directions, the common axis is the axis of the gas discharge chamber, the antenna is located outside the gas discharge chamber and surrounded by a dielectric material ring from the outside, and each opposite end of the gas discharge chamber is provided with a magnetic system. The gas discharge chamber is in gas power connection with the gas discharge chamber through two radial gas feed-through pipes, and the two radial gas feed-through pipes are tightly connected with the gas discharge chambers at the two upstream positions of the magnetic system. The weight and the size of the thruster can be reduced, the specific thrust and the specific impulse of each power consumption unit are increased, and damage to the thruster and structural components of a spacecraft is eliminated.

Description

technical field [0001] The present invention relates to space engineering, and in particular to an electric propulsion system (EP) equipped with an electrodeless plasma source and an electric rocket motor of an acceleration stage using various substances as propellants, mainly designed for installation in aerospace on the vehicle, transfer it from the parked track to the target track, track maintenance, attitude control, altitude control, unload attitude control system, maneuvering between tracks and deorbiting. Background technique [0002] The prior art discloses more efficient radio frequency plasma electric thrusters (patent US62090B1, published September 25, 2001). The invention relates to plasma thrusters. It mainly contains a radio frequency generator, a set of radiating elements, a gas discharge chamber defining the main shaft of the thruster, a magnetic system, a power source for the magnetic system and a propellant supply system connected to the gas discharge cham...

AI Technical Summary

Problems solved by technology

[0008] The technical problem to be solved by the present invention is to manufacture a light-weight, small-sized two-way wave plasma thruster for the spacecraft, which is used for the orbital transfer, orbital maintenance, attitude control, altitude control, and unloading attitude control systems of the spacecraft. , inter-orbit maneuvering and deorbiting, which increases the specific thrust and specific impulse of the thruster per unit of power consumed, and without parasitic discharges that damage thrusters and structural components of the spacecraft, without power loss on the electromagnetic coupling line of the antenna plasma, Propulsion system components and spacecraft structural components are protected from electromagnetic radiation that would cause the spacecraft to rotate in space

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