Spacecraft Attitude Measurement and Control Integration Using a Novel Configuration of Variable Speed Magnetically Suspended Control and Sensing Gyroscope

Abstract

For the sake of achieving the high-accuracy and high-bandwidth attitude measurement and control integration of flexible spacecraft, an integrated method based on a novel configuration of Variable Speed Magnetically Suspended Control and Sensitive Gyroscope (VSMSCSG) and Radial Basis Function (RBF) neural network control is proposed in this paper. First, the structure and principle of a novel VSMSCSG configuration are given, and its modelling is established. VSMSCSGs are employed as both actuators and attitude-rate sensors. Second, the attitude measurement method based on the configuration is proposed in the case of rotor spin speed and deflection angle changing. Based on the characteristics of the novel configuration, the corresponding RBF neural network attitude control law of spacecraft and the adaptive saturation avoidance steering laws of the VSMSCSGs have been further designed; the rotor can deflect at high frequency and change speed simultaneously to output a high bandwidth attitude control moment which dramatically improves the moment output capability of VSMSCSG configuration. Compared with the traditional method of attitude measurement and control integration, the proposed one not only improves the speed and accuracy of attitude control under high bandwidth disturbance but also greatly improves the accuracy of attitude measurement by fully using the dynamic information of novel configuration. Semiphysical simulation results demonstrate the correctness and superiority of the proposed method.