This paper describes the control systems employed by a nano-satellite 'Parikshit' to satisfy the payload requirement to limit the angular velocity of the satellite within 1 deg/sec. Also described is the satellite kinematics and dynamics model in space environment to test and evaluate the performance of the controller to meet the desired stability. The entire dynamics of the satellite have been modelled in terms of quaternions and its advantages over euler angles have also been mentioned. A concise description of the numerical integration techniques and step size determination have also been mentioned. In order to simulate the environment conditions, influential disturbance torques along with their effects have been evaluated and estimated. The results from these simulations used to test the controller in space environment for attitude control have been analysed and used to evaluate the performance of the controller. All graphs pertaining to the simulations have been analysed and discussed.
|Title of host publication
|2015 International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015
|Institute of Electrical and Electronics Engineers Inc.
|Number of pages
|Published - 01-01-2015
|International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015 - Kerala, India
Duration: 10-08-2015 → 13-08-2015
|International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015
|10-08-15 → 13-08-15
All Science Journal Classification (ASJC) codes
- Signal Processing
- Hardware and Architecture
- Information Systems
- Computer Networks and Communications