Date of Award:
Master of Science (MS)
Mechanical and Aerospace Engineering
R. Rees Fullmer
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.
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. 4228.
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