Single-Stage Bismuth Fed Stationary Plasma Thruster
Faculty Mentor Name
Daniel White
Format Preference
Poster
Abstract
This research conducts initial design, manufacturing, and testing of a miniaturized, single-stage Stationary Plasma Thruster (SPT) type Hall thruster, that is dimensionally consistent with the current CubeSat Design Specification requirements. Consideration 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, progressing to a bismuth direct feed system. The thruster will take advantage of a solid (LaB6) cathode as its electron source. The magnetic circuit will be powered by a stand-alone power supply. The exploratory design will focus exclusively on synthesizing a procurable and realizable plasma accelerator stage. After further maturation, attention will be given to creating a feed system suitable for canisterized spacecraft applications. 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 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
- IGNITE GRANT AWARD
Location
ERAU - Prescott, AZ; AC1-Atrium, 11 am - 3 pm | Eagle Gym, 7 - 9 pm
Start Date
3-29-2019 11:00 AM
End Date
3-29-2019 9:00 PM
Single-Stage Bismuth Fed Stationary Plasma Thruster
ERAU - Prescott, AZ; AC1-Atrium, 11 am - 3 pm | Eagle Gym, 7 - 9 pm
This research conducts initial design, manufacturing, and testing of a miniaturized, single-stage Stationary Plasma Thruster (SPT) type Hall thruster, that is dimensionally consistent with the current CubeSat Design Specification requirements. Consideration 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, progressing to a bismuth direct feed system. The thruster will take advantage of a solid (LaB6) cathode as its electron source. The magnetic circuit will be powered by a stand-alone power supply. The exploratory design will focus exclusively on synthesizing a procurable and realizable plasma accelerator stage. After further maturation, attention will be given to creating a feed system suitable for canisterized spacecraft applications. 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 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
- IGNITE GRANT AWARD