Development and testing of a microwave-heated plasma thruster

Abstract

Within the Decentralized Energy Electric Propulsion (DEEP) project1 a microwave-heated plasma thruster is developed. The thruster is operated intermittently in combination with a battery and supercapacitor. This allows the use of a battery and solar panel system designed for a lower power on the satellite itself as well as a reduction in overall mass, therefore increasing the available payload mass and power. Due to the intermittent operation, the thruster needs to ignite fast and reliable, while each firing will only last τ = 10 − 600 s depending on the duty cycle and necessary velocity increment ∆v. The thruster itself consists of an electroncyclotron-resonance (ECR) discharge in combination with an magnetic nozzle for plasma acceleration. The accelerated plasma is therefore quasi-neutral and no neutralizer is necessary. Erosion of the components exposed to the plasma is minimized. In addition to the thruster, a flow management system (FMS) and power control and distribution unit (PCDU) are developed from commercial off-the-shelf components.