Pulsed plasma thruster with ceramic air spout electrode

Abstract

The invention relates to a pulse plasma thruster provided with a ceramic nozzle electrode in the mechanical technical field, wherein, the tail of a feeding spring is unfolded and pressed under propellants and generates a feeding force for the propellants; a firing circuit supplies electrical energy to a spark plug for ignition and discharge; the spark plug is fixed on a cathode; the propellants are horizontally fixed by the feeding spring and a lug boss of an anode and vertically fixed by the cathode and the anode; a high-voltage capacitor is connected wit the cathode and the anode; and a power source is connected to a binding post of the high-voltage capacitor through a wire. The invention designs an electrode structure provided with a microcrystal mica ceramic nozzle to replace the prior parallel electrode through analysis of the operating process of the thruster. The invention is characterized by improvement of the pressure of a discharging area and the electric heating acceleration, thereby the thrust and the efficiency of the pulse plasma thruster are greatly improved.

Description

technical field [0001] The invention relates to a thruster in the technical field of power machinery, in particular to a pulse plasma thruster with a ceramic nozzle electrode. Background technique [0002] Traditional chemical propulsion has low specific impulse, large mass, and complex structure, which greatly limits its application in microsatellites. The pulse plasma thruster, which emerged in the 1960s, is a small-thrust electromagnetic electric thruster, which has the advantages of high specific impulse and small mass, and can be applied to attitude control, orbit transfer and lifting, and orbit correction of micro-satellites , drag compensation, position maintenance, repositioning, and off-orbit handling tasks, compared with chemical propulsion, it can greatly save propellant and reduce launch costs. In 1974, a pulsed plasma thruster of the United States was deployed on a geosynchronous meteorological satellite (SMS); in 2000, NASA used a pulsed plasma thruster on the...

AI Technical Summary

Problems solved by technology

[0003] Found through literature search to relevant technology, " Investigation of propellant inefficiencies in a pulsed plasma thruster " (pulse plasma thruster " published by Gregory G.Spanjers et al. Propellant Low Efficiency Research), the paper proposes that the low efficiency of the pulsed plasma thruster is due to the low acceleration efficiency caused by the low utilization rate of the propellant, and improving the efficiency of the thruster should increase the acceleration efficiency of the propellant

Its shortcoming is that it does not give a specific method to improve the performance of the thruster

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