Comparison of Lead-Controller and Pid-Lead Controller to Control InnoSAT Attitude System

Abstract

Space technology advancement is gaining popularity as it is one of the measures used to gauge a nation's level of development. One of the countries that is starting to develop into a nation involved in the exploration of satellite technology is Malaysia. Finding all appropriate prospective solutions is crucial. One of the problems that may occur in space is a satellite's position being altered by various events. The stability and orientation of a satellite can be controlled and maintained using an attitude control system (ACS). The Malaysian Innovative Satellite (InnoSAT) nano-satellite system can be stabilized by focusing on the control method. Therefore, the purpose of this study is to improve the three axes of the control system-Roll, Pitch and Yaw. Next, two control strategies for the InnoSAT system ACS have been proposed by this study: Lead Controller and PID-Lead Controller. The simulation was done using reference inputs composed of unit step functions. In comparison to the PID-Lead Controller, research has demonstrated that the Lead Controller successfully produces lower tracking performance. The key result of the study is that a PID-Lead controller is more suitable for managing satellite attitude.