TY - GEN
T1 - Power Analysis of Optimal Earth Observation Micro-Satellite Design under Different Control Parameter
AU - Ubay, Muhammad Sulaiman Nur
AU - Halim, Abdul
N1 - Publisher Copyright:
© 2018 IEEE.
PY - 2018/11/26
Y1 - 2018/11/26
N2 - The main task of an earth observation satellite is to deliver accurate and valid earth surface information to the ground station. In order to perform this task, the satellite is equipped with an attitude control system. The control system establishes closed-loop with attitude sensors, especially in the imaging operation. However, the limitation of satellite power supply capacity causes the restriction of attitude control operation, which in turn, limits the satellite imaging capacity. The aim of this paper is to analyze the power performance of optimal satellite design by observing the effects of a Proportional Integral Differential (PID) parameter changes to satellite power consumption. In this paper, firstly optimal satellite parameters are chosen. The parameter choice is based on a quadratic objective function that representing power consumption. In the sequence, the PID attitude control system is designed for the satellite. Through simulation, the effects of various PID parameters have been studied.
AB - The main task of an earth observation satellite is to deliver accurate and valid earth surface information to the ground station. In order to perform this task, the satellite is equipped with an attitude control system. The control system establishes closed-loop with attitude sensors, especially in the imaging operation. However, the limitation of satellite power supply capacity causes the restriction of attitude control operation, which in turn, limits the satellite imaging capacity. The aim of this paper is to analyze the power performance of optimal satellite design by observing the effects of a Proportional Integral Differential (PID) parameter changes to satellite power consumption. In this paper, firstly optimal satellite parameters are chosen. The parameter choice is based on a quadratic objective function that representing power consumption. In the sequence, the PID attitude control system is designed for the satellite. Through simulation, the effects of various PID parameters have been studied.
KW - PID
KW - attitude control system
KW - imaging operation
KW - power supply capacity
KW - satellite
UR - http://www.scopus.com/inward/record.url?scp=85061819143&partnerID=8YFLogxK
U2 - 10.1109/ICARES.2018.8547065
DO - 10.1109/ICARES.2018.8547065
M3 - Conference contribution
AN - SCOPUS:85061819143
T3 - ICARES 2018 - Proceedings of the 2018 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology
SP - 134
EP - 139
BT - ICARES 2018 - Proceedings of the 2018 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2018 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology, ICARES 2018
Y2 - 20 September 2018 through 21 September 2018
ER -