Rapid satellite attitude control using control moment gyros

• Main Author: Sollin Selvan Anbu.
• Other Authors: Go Tiauw Hiong
• Format: Final Year Project
• Language: English
• Published: 2009
• Subjects: DRNTU::Engineering::Mechanical engineering::Control engineering
• Online Access: http://hdl.handle.net/10356/17094
• Institution: Nanyang Technological University

Satellite Attitude Determination and Control is one of the numerous subsystems involved in designing and functioning of a satellite in space. Attitude Determination and Control Systems (ADACS) performs the major role of determining the attitude (satellite position and orientation) and controlling the same. There are several methods of controlling the satellite using thrusters, momentum wheels, reaction wheels, magnetic torquers and control moment gyroscopes (CMG). While the usage of the above mentioned systems depends on the type of mission the satellite undertakes, this project focuses on understanding the functioning of CMGs. CMGs can react to external disturbances in space and also perform active satellite control by transferring angular momentum from its spinning wheels to the satellite. This project aims at designing a Proportional, Integral and Differential controller (PID controller) in a satellite attitude control system equipped CMG. The performance of the above mentioned PID controller is analyzed through their impulse and step responses. Thereby, a parametric study is done on the various parameters involved in the controller. The project seeks to find an optimum gain(s) in order to have the fastest settling time with minimum overshoot.