Argon Laser-Plasma Thruster

Design and Test of a Laboratory Model

Master thesis (2024)

Authors

E.E. Duplay Aerospace Engineering

Contributors

B.T.C. Zandbergen Space Systems Egineering (supervisor 1)
A. Cervone Astrodynamics & Space Missions - Aerospace Engineering (supervisor 2)
A. Menicucci Space Systems Egineering (supervisor 2)
A.J. Higgins McGill University (supervisor 1)
Faculty
Aerospace Engineering
Copyright: © 2024 Emmanuel Duplay
Laser Propulsion Plasma Fiber Laser-thermal propulsion Laser-sustained Argon Directed-energy Bremsstrahlung
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Published Date

30-01-2024

Language

English

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Faculty

Aerospace Engineering

Abstract

A laser-sustained plasma (LSP) generator capable of operating as a laser-thermal thruster was designed and tested. The apparatus was powered by a 3-kW 1070-nm fiber-optic laser and was operated with argon gas. The laser absorption, radiated spectrum, and change in static pressure were recorded, and high-speed video footage of the LSP was acquired. Of special interest is the heat-deposition efficiency into the working gas resulting from LSP ignition, which was estimated by tracking the pressure change in the test section. Laser transmission through the plasma was also measured to quantify two energy loss mechanisms: incomplete laser absorption and radiation of heat to the walls of the test section. Minimizing these losses would be critical in the realization of a practical and efficient laser-thermal propulsion (LTP) thruster, as most of the laser energy should be deposited as heat in the propellant to maximize thruster specific impulse.