Low Mass Low Specific Power Hall Effect Thruster

ABSTRACT: Busek proposes to develop a high power, low mass Hall Effect thruster. The baseline thruster is tentatively sized at the nominal 8kW power level. Specific features to be implemented include the use of SmCo permanent magnets. The goal of the effort is to reduce thruster specific power to<1kg/kW which is a 3-fold decreased over SOA systems of comparable power. The thruster will also be infused an advanced propellant distribution methodology. Thruster lifetime will be evaluated through a combination of magnetic modeling and erosion analysis and modeling. The target thruster efficiency is>60%. In Phase I we will evaluate an existing permanent magnet thruster to develop the theoretical and experimental underpinnings of the full power design. Following the experimental effort we will prepare the detailed design of the thruster. The thruster design will be supported by magnetic modeling, lifetime predications, and thermal and structural analysis. In Phase II we will build, performance test and conduct environmental testing of an advanced version of the thruster to raise the maturity level to TRL 6. We plan to work closely with AFRL in this project in order to maximize the utility of the deliverable thruster to support IHPRPT RP21 goals. BENEFIT: Broadly speaking high power Hall thrusters can serve DoD space needs, the in-space transportation of DoD space assets, all-electric commercial Comsats for both orbit transfer and station keeping as well as NASA science missions. The thruster is also compatible with alternate propellants such as krypton and/or iodine.