Laser ablation pulsed plasma thruster

Abstract

The invention provides a laser ablation pulsed plasma thruster. The laser ablation pulsed plasma thruster comprises a power processing unit, a capacitor unit, a working medium, a working medium supply device, a cathode, an anode and a laser generating mechanism. The power processing unit is connected with the capacitor unit through a transmission line. The positive output end and the negative output end of the capacitor unit are connected to the cathode and the anode through transmission lines correspondingly. The capacitor unit, the transmission lines, the cathode and the anode form a discharging loop, and gas between the cathode and the anode can be ionized and accelerated. A discharging channel is formed between the cathode and the anode. The working medium supply device for fixing and conveying the working medium is arranged at one end of the discharging channel, and the working medium stretches into the discharging channel from the end. Gaps exist between the working medium and the cathode as well as between the working medium and the anode. The laser generating mechanism emits laser beams into the discharging channel to ablate the working medium, the laser beams continuously ablate the working medium to generate part of ionized gas and particulate matters, the ionized gas and the particulate matters enter the discharging channel to form plasma jets moving along the discharging channel, and thrust is generated. The laser ablation pulsed plasma thruster is high in specific impulse, total impulse, working medium utilization rate and control precision.

Description

technical field [0001] The invention relates to an electric propulsion system for spacecraft attitude adjustment, orbit correction, orbit elevation, deep space exploration, manned moon landing, manned landing on Mars and other space missions. In particular, it is an electromagnetically accelerated pulsed plasma thruster that utilizes laser gasification and partial ionization of solid working fluid. Background technique [0002] Solid ablative pulsed plasma thruster (Ablative Pulsed Plasma Thruster, APPT) is an electromagnetically accelerated electric propulsion system. Its principle is to first charge the capacitor to about 2000V, store energy from a few joules to tens of joules, and then use the spark plug to Ignition induces capacitive discharge to generate an arc and ablates the Teflon working fluid through the arc. Finally, the gasified working fluid is further ionized and accelerated under the action of electromagnetic force. The biggest advantage of this kind of thrus...

AI Technical Summary

Problems solved by technology

[0005] Aiming at the problems of short service life, low utilization rate of working medium, low energy conversion efficiency and easy failure of spark plug of pulsed plasma thruster, it provides spacecraft with a thrust output range, h

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