Date of Award
12-2015
Degree Name
Master of Science
Department
Mechanical and Aerospace Engineering
First Advisor
Dr. Jennifer Hudson
Second Advisor
Dr. Kristina Lemmer
Third Advisor
Dr. Kapsong Ro
Keywords
Mechanical engineering, optimal control, orbital mechanics, aerospace engineering, attitude mechanics
Access Setting
Masters Thesis-Open Access
Abstract
This thesis implements a linear quadratic attitude control system for a low-thrust spacecraft. The goal is to maintain spacecraft alignment with a time-varying thrust vector needed for trajectory change maneuvers. A linear quadratic attitude control approach is used to maintain spacecraft pointing throughout flight. This attitude control strategy uses the thrust-acceleration input obtained from a linear quadratic optimal trajectory control model that simulates the trajectory of a spacecraft in orbit maneuvers. This attitude model simulates a CubeSat, a small satellite that is equipped with a low-thrust propulsion and attitude control system. An orbit raising and a plane change scenario is modelled for this spacecraft. The results of the attitude model show that for the orbit raising maneuver, the attitude controller exhibits periodic behavior with the same frequency as the calculated spacecraft thrust acceleration.
Recommended Citation
Kolosa, Daniel, "Implementing a Linear Quadratic Spacecraft Attitude Control System" (2015). Masters Theses. 661.
https://scholarworks.wmich.edu/masters_theses/661