Fuzzy PD and Fuzzy $\text{PD}+\mathrm{I}$ Controllers Design for Attitude Control of Innovative Nano-Satellite

There are too many interference torques in space that might deviate the satellite from the desired attitude. Satellite stabilization must be provided in order to counteract the effects of the disruption torque. This paper describes the development of a nano-satellite Attitude Control System (ACS), which uses Fuzzy PD (FPD), based on Direct action and Fuzzy $\text{PD} +\mathrm{I}(\text{FPD}+\mathrm{I})$ based on Hybrid type. This paper aims to measure the time response of the FPD and $\text{FPD} +\mathrm{I}$ to improve the efficiency of the stability of the three-axis attitude. Innovative Satellite (InnoSAT) is the nano-satellite plant that was used in this simulation. The performance of the FPD controller was compared with $\text{FPD} +\mathrm{I}$ . Both controllers used step input reference and the same Fuzzy rules with two input $5^{\ast}5$ and twenty-five rules. The simulation results indicated that the $\text{FPD} +\mathrm{I}$ controller has significant improvement over the FPD controller for different operating conditions like varying gain.