View article

Abstract Attitude Determination and Control System of a satellite, can be regarded as one of the major subsystems of satellite design. The dynamics and kinematics of the satellite are important to design a controller. In this paper, the nonlinear mathematical model of a satellite is formulated using quaternions. Further, reaction wheel assembly is chosen as an actuator which provides the necessary torque to control the satellite attitude. To stabilize the satellite at desired attitude and angular velocity, PD and PD β based sliding mode controllers with modified reaching law are proposed. An optimization problem is presented to tune the parameters of the proposed controllers. Numerical simulation is carried out for the satellite system with the tuned controllers at various operating conditions such as (i) without disturbance,(ii) with disturbance and (iii) robustness towards parameter uncertainty. The results of the proposed …