Author
McKee, Paul Dickson
Other Contributors
Anderson, Kurt S.; Christian, John; Mishra, Sandipan;
Date Issued
2018-08
Subject
Mechanical engineering
Degree
MS;
Terms of Use
This electronic version is a licensed copy owned by Rensselaer Polytechnic Institute, Troy, NY. Copyright of original work retained by author.;
Abstract
This goal of this thesis is to bring together several relevant techniques and methods commonly used in Spacecraft Attitude Control Engineering for the purpose of designing and simulating a complete CubeSat Attitude Control System. The CubeSat in question includes three reaction wheels and a rotate-able solar array (all modeled), totaling 7 degrees of freedom. The complete equations of motion are derived using Kane's method, creating a mathematical model that can be simulated and controlled. Process noise and sensor noise are then added to the system, and their effects are mitigated through the use of a multiplicative extended Kalman Filter (MEKF). Finally, multiple control methods are explored, with an emphasis on Linear Quadratic Regulation (LQR) for fine-pointing steady-state accuracy. The complete controller is then put to the test to see how it fares in three realistic mission phases: initial de-tumble, solar array pointing, and long-term disturbance rejection. Success is demonstrated in all three mission phases.;
Description
August 2018; School of Engineering
Department
Dept. of Mechanical, Aerospace, and Nuclear Engineering;
Publisher
Rensselaer Polytechnic Institute, Troy, NY
Relationships
Rensselaer Theses and Dissertations Online Collection;
Access
Restricted to current Rensselaer faculty, staff and students. Access inquiries may be directed to the Rensselaer Libraries.;