Abstract Title
Preliminary Design of a Cube Satellite Compliant Hall Thruster
Faculty Mentor Name
Daniel White
Format Preference
Poster
Abstract
The purpose of this research is to conduct the preliminary design, manufacturing, and testing of a miniaturized, singlestage Stationary Plasma Thruster (SPT) type Hall thruster. Dimensionally, the thruster should be consistent with the requirements put forth in the most current CubeSat Design Specification document. The most restricting criterion is the size limitation, which confines the engine envelope to 100 mm in cross-sectional diameter. Considerate deliberation will be provided to the thermal specifications to be compliant with future integration into CubeSat module applications. The target input power for this engine will be approximately 100 W. Argon will be used for primary testing utilizing a direct feed system. The thruster will take advantage of a solid (LaB6) cathode as its electron source. The magnetic circuit will be powered independently via a stand-alone power supply. The exploratory design will focus exclusively on synthesizing a procurable and realizable plasma accelerator stage. Engine success, as based on the long-term mission objective, will be contingent upon having a firing time between 1 and 2 kh, corresponding to a propellant throughput of approximately 2 to 2.5 kg. Testing will need to be completed to demonstrate that the erosion rates observed on the thruster metallic structures, ceramic channel walls, and cathode are broadly consistent with these mission requirements.
- POSTER PRESENTATION
- ARIZONA SPACE GRANT AWARD AND PORTZ FELLOWSHIP
Preliminary Design of a Cube Satellite Compliant Hall Thruster
The purpose of this research is to conduct the preliminary design, manufacturing, and testing of a miniaturized, singlestage Stationary Plasma Thruster (SPT) type Hall thruster. Dimensionally, the thruster should be consistent with the requirements put forth in the most current CubeSat Design Specification document. The most restricting criterion is the size limitation, which confines the engine envelope to 100 mm in cross-sectional diameter. Considerate deliberation will be provided to the thermal specifications to be compliant with future integration into CubeSat module applications. The target input power for this engine will be approximately 100 W. Argon will be used for primary testing utilizing a direct feed system. The thruster will take advantage of a solid (LaB6) cathode as its electron source. The magnetic circuit will be powered independently via a stand-alone power supply. The exploratory design will focus exclusively on synthesizing a procurable and realizable plasma accelerator stage. Engine success, as based on the long-term mission objective, will be contingent upon having a firing time between 1 and 2 kh, corresponding to a propellant throughput of approximately 2 to 2.5 kg. Testing will need to be completed to demonstrate that the erosion rates observed on the thruster metallic structures, ceramic channel walls, and cathode are broadly consistent with these mission requirements.
- POSTER PRESENTATION
- ARIZONA SPACE GRANT AWARD AND PORTZ FELLOWSHIP