Date of Award:
5-2014
Document Type:
Thesis
Degree Name:
Master of Science (MS)
Department:
Mechanical and Aerospace Engineering
Committee Chair(s)
R. Rees Fullmer
Committee
R. Rees Fullmer
Committee
Steven L. Folkman
Committee
David Geller
Abstract
A small satellite simulator with attitude determination and control was designed and implemented in hardware. The simulator consists of inertial sensors for attitude determination and a pyramidal four-wheel momentum exchange system as the control actuators. A linearized PV controller with trajectory generation and feedback linearization was implemented, with the focus on controlling yaw. The simulator was tested on a spherical air bearing platform to allow three-degree-of-freedom operation. The simulator software was developed to read measurements from the sensors, apply the control algorithm, and send commands to the actuators. A data processing routine was developed. Electromechanical testing for the system as well as test results are presented.
Checksum
29d77e5f4d0d015e941972633235c802
Recommended Citation
Samuels, Marina A., "The Design and Testing of a Three-Degree-of-Freedom Small Satellite Simulator Using a Linear Controller with Feedback Linearization and Trajectory Generation" (2014). All Graduate Theses and Dissertations, Spring 1920 to Summer 2023. 4228.
https://digitalcommons.usu.edu/etd/4228
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