Abstract
The presence of external disturbance torques causes the gimbals angle of Control Moment Gyros (CMG) used to control satellite drift from their preferred initial value. This scenario will drive the CMG into singular states or result in attitude error thus reducing the chance to do slew maneuver. In this paper, a novel method to compensate drifted gimbals of CMG based controlled small satellite operated in low earth orbit is adopted. The satellite is equipped with four Single Gimbal CMG (SGCMG) pyramid-array configuration. Three magnetic torquers are used to generate the compensation control torque where the controlleris designed based on the gimbal angle converging time. Simulations are performed using Matlab®/Simulink® software for various value of gimbals angle converging time to optimize the compensator performance. Results from simulation show that the optimal performance of the system is when the converging time is set at100s.
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