Session
Session 8: Frank J. Redd Student Competition
Abstract
Small satellite missions open the space environment to a wide range of diverse missions. NASA has indicated that these satellites will be a paradigm shift for NASA and the larger space community. Currently, most of these small satellites cannot utilize a propulsion sys- tem due to size and mass constraints; however, research being performed at the Missouri University of Science and Technology may soon change that. The Missouri S&T Satellite Research team is in the process of developing two CubeSat missions that will validate a multi-mode micropropulsion system developed in collaboration with the Missouri S&T Aerospace Plasma Laboratory. Unique challenges to these missions include packaging the propulsion system and validating its performance on orbit. Methods of thruster performance validation being considered include comparison of on-orbit pressure, voltage and temperature telemetry to ground test data and comparing expected orbit/attitude changes resulting from maneuver executions to the actual changes estimated from downlinked spacecraft telemetry. A final mission Concept of Operations is developed to facilitate an effective evaluation/validation of thruster performance.
Presentation
On-Orbit CubeSat Performance Validation of a Multi-Mode Micropropulsion System
Small satellite missions open the space environment to a wide range of diverse missions. NASA has indicated that these satellites will be a paradigm shift for NASA and the larger space community. Currently, most of these small satellites cannot utilize a propulsion sys- tem due to size and mass constraints; however, research being performed at the Missouri University of Science and Technology may soon change that. The Missouri S&T Satellite Research team is in the process of developing two CubeSat missions that will validate a multi-mode micropropulsion system developed in collaboration with the Missouri S&T Aerospace Plasma Laboratory. Unique challenges to these missions include packaging the propulsion system and validating its performance on orbit. Methods of thruster performance validation being considered include comparison of on-orbit pressure, voltage and temperature telemetry to ground test data and comparing expected orbit/attitude changes resulting from maneuver executions to the actual changes estimated from downlinked spacecraft telemetry. A final mission Concept of Operations is developed to facilitate an effective evaluation/validation of thruster performance.
