High Resolution Quick Small Satellite Attitude Maneuver Control For Control Moment Gyro

High resolution quick small satellite demands that satellite platform has largeangle maneuver ability and high stability control ability. Because of the simplestructure and large output torque etc of single gimbal control moment gyro(SGCMG), it becomes the preferred execution mechanism of small satellite infuture.This paper made an in-depth analysis of the main factors that effect controlperformance of high resolution quick small satellite based on SGCMGs, and putforward feasible and effective attitude maneuver control scheme.Firstly, in the paper, Euler angle and four element theory were descript,SGCMGs working principle of Pyramid conformation was introduced, kinematicsmodel and dynamic model of small satellite based on SGCMGs were established,and the main disturbance torque of near-earth orbit small satellite was analyzed.Secondly, this paper studied high stability control problem of small satellitebased on SGCMGs. Using ADRC theory (ADRC), the nonlinear quaternion errorfeedback control scheme based on the nonlinear extended state observer (NESO)was proposed. NESO realizes satellite dynamics decoupling and disturbanceobservation. Nonlinear combining functions as a feedback controller effectivelysuppresses the interference. The simulation results show that the scheme has better steady control performance.Thirdly, considering parameters not easy to adjust based on nonlinearquaternion error feedback controller with NESO, the linear quaternion errorfeedback control algorithm based on linear extended state observer (LESO) wasproposed. The controller reduces the tuning difficulty of controller parameter andsimplifies the design of system. Compared to traditional PD control algorithm, thedesigned controller has higher static control performance. A simple and feasiblescheme is presented for large angle attitude control of high resolution quick smallsatellite.Fouthly, the fast maneuver problem of high resolution quick small satellitebased on SGCMGs was studied. Through in-depth analysis of the sliding modevariable structure control theory (SMC), the quaternion error feedback controlscheme based on the quasi sliding mode was proposed to effectively weaken thechattering problem and to realize satellite fast maneuver. But considering that thecontrol system based on quasi sliding mode existes steady error in the presence ofdisturbances, the attitude control algorithm based on the quasi sliding mode andLESO was proposed. The designed controller achieved large angle maneuver andhigh stability control.Finally, based on the dumbbell type three axis air bearing physical simulationplatform,30°maneuver simulation was given using the error quaternion feedbackcontroller based on LESO. The results show that, the designed control system hashigher steady-state precision and pointing accuracy than traditional PD attitudecontroller, pointing accuracy is better than0.05degrees (3σ), attitude stability isbetter than0.006deg/s (3σ), and the control system achieves an average of3deg/s maneuvering speed. The research on this paper has very high application value toachieve large angle attitude maneuver and high stability control of small satellite.