Adaptive Control Applied to the Cal Poly Spacecraft Attitude Dynamics Simulator

The goal of this thesis is to use the Cal Poly Spacecraft Attitude Dynamics Simulator to provide proof of concept of two adaptive control theories developed by former Cal Poly students: Nonlinear Direct Model Reference Adaptive Control and Adaptive Output Feedback Control. The Spacecraft Attitude Dynamics Simulator is a student-built air bearing spacecraft simulator controlled by four reaction wheels in a pyramidal arrangement. Tests were performed to determine the effectiveness of the two adaptive control theories under nominal operating conditions, a “plug-and-play” spacecraft scenario, and under simulated actuator damage. Proof of concept of the adaptive control theories applied to attitude control of a spacecraft is provided. The adaptive control theories are shown to attain similar or improved performance over a Full State Feedback controller. However, the measurement capabilities of the simulator need to be improved before strong comparisons between the adaptive controllers and Full State Feedback can be achieved.

Name thesis:degree_name

MS in Aerospace Engineering

Discipline thesis:degree_discipline

Aerospace Engineering

Year dc:date.available

2010

Author dc:creator

• Downs, Matthew C

Contributors dc:contributor

• Eric Mehiel

• Reaction Wheel Pyramid
• Adaptive Control
• PRWP
• Spacecraft
• Spacecraft Control
• Acoustics, Dynamics, and Controls
• Astrodynamics
• Navigation, Guidance, Control and Dynamics
• Space Vehicles

Identifier

10.15368/theses.2010.6

OAI identifier oai:identifier

oai:digitalcommons.calpoly.edu:theses-1243