Pulse electro-magnetic micro-newton propulsion device

Abstract

The invention discloses a pulse electro-magnetic micro-newton propulsion device, and belongs to the technical field of plasma micro-propulsion. According to the pulse electro-magnetic micro-newton propulsion device, the problems that an existing thruster is single in ionization adjusting means so as not to meet high-efficiency and stable operation of wide-range adjustment and the requirement for rapid response in satellite towless control are solved. A discharge chamber main body is of a cylindrical structure; a through hole, a first annular channel and a second annular channel are coaxially formed in a base; an inner sleeve is inserted into the first annular channel and fixedly connected with the base; an outer sleeve is inserted into the second annular channel and fixedly connected withthe base; coils wind an outer wall, outside the discharge chamber, of each sleeve correspondingly; a microwave input unit is inserted into the through hole and fixedly connected with the base; an annular microwave antenna is coaxially and fixedly arranged on one end, in the discharge chamber, of the microwave input unit; a plurality of air supply holes sharing the same quantity as a plurality of air supply units are further formed in the base; and the plurality of air supply units correspondingly communicate with a discharge chamber through the plurality of air supply holes.

Description

technical field [0001] The invention relates to a pulse electric excitation micro-bovine propulsion device, which belongs to the technical field of plasma micro-propulsion. Background technique [0002] Compared with the chemical system, the electric propulsion system has the advantages of high specific impulse and small thrust. The completion of the same task requires less fuel, reduces costs, has a larger speed increment, can work for a longer time, and enables longer-distance Space missions become a reality. The electric thruster is the core subunit of the electric propulsion system. According to the different acceleration methods of the propellant, it can be divided into three categories: electrothermal type, electrostatic type and electromagnetic type. The electrostatic ion thruster uses an electrostatic field to accelerate charged particles. The reaction force generated by the high-speed ejected ion beam is the thrust of the thruster, and the electron cyclotron resona...

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Problems solved by technology

[0005] The present invention aims to solve the problem that the existing thruster ionization adjustment method is single, cannot meet the high-efficiency and stable work of lar

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