Argon Laser-Plasma Thruster
Design and Test of a Laboratory Model
E.E. Duplay (TU Delft - Aerospace Engineering)
B.T.C. Zandbergen – Mentor (TU Delft - Space Systems Egineering)
Angelo Cervone – Graduation committee member (TU Delft - Astrodynamics & Space Missions)
Alessandra Menicucci – Graduation committee member (TU Delft - Space Systems Egineering)
A.J. Higgins – Mentor (McGill University)
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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.