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Information Journal Paper

Title

Improving the performance of satellite attitude control with a reaction wheel actuator and considering sensor noise

Pages

  91-100

Abstract

 In this paper, a robust and Reliable optimization approach has been used to reduce the effect of Sensor Noise on the performance of the spacecraft attitude control system with Reaction wheel actuators. The absolute mean value of the pointing error on the satellite attitude has been chosen as the main control performance criterion. The optimizer algorithm is based on the genetic method and based on Monte Carlo successive iterations to include the effect of noise and obtain control coefficients. The first-order dynamics was used to model the Reaction wheel as the main control operator, taking into account the practical limits of the maximum production torque, and a proportional-integral-derivative (PI-D) controller modified by the method, the observer is used to control the satellite. Gaussian white noise signal after passing through a first-order filter is added to the angle and angular velocity feedback path signals and applied to the control circuit. In order to compare the results fairly, the control coefficients for the same simulation conditions were obtained for the two approaches of deterministic optimization and robust and Reliable optimization, and the performance criteria in terms of the noise power spectral density function were investigated for the two optimization approaches. The comparative results show that the control system adjusted by robust and reliability optimization method, its performance criterion is more robust in the face of noise and its performance reliability number is higher than the results of deterministic optimization. The results indicate the preference of using a robust and Reliable optimization approach

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