Research On Rapid Stabilize Intelligent Adaptive Control Method For Satellite Attitude

With the complexity of space missions,higher requirements for attitude stability control of satellites and rapid maneuverability of satellites have been put forward.Therefore,it is necessary to design a control algorithm which has strong anti-interference ability and can achieve the satellite rapid maneuver effect.This also requires the implementation of satellite attitude control process,the use of a larger torque output ability of the implementation of components.Compared to the conventional momentum wheel system,Control Moment Gyroscope can provide greater output torque and have great torque amplification capability,and can be an ideal actuator for satellite rapid maneuver..But the singular problem of single frame moment gyro group affects its practical engineering application,in the singular state,the Control Moment Gyro can not produce the desired torque,and the satellite attitude is out of control.Therefore,this article has carried on the research to these problems.In order solve the above problems,We first introduced the concept of the Control Moment Gyroscope,and introduced the characteristics of the Control Moment Gyro.At the same time,we introduce the working principle of the CMG,and the common configuration and common performance index of the CMG.A mathematical model is set up for further simulation verification.In this paper,the singularity principle of the moment gyro is also introduced,which lays a foundation for further research.At the same time,the performance index is introduced,and the configuration of the five pyramid control moment gyroscope is designed.Then,the control rate of various Control Moment Gyros is introduced,and the configuration of Pyramid shape moment gyro is taken as the control object.According to the simulation results,the characteristics and applicability of various control torque control rates are compared and analyzed.According to the characteristics of the five pyramid designed a new control rate,and complete the simulation results show that the control rate can effectively avoid the moment gyros in moving into singular,and reduces the torque error in the control process.Then,the design of satellite attitude control is prepared.Two satellite attitude description methods are introduced,and their advantages and disadvantages are compared.Their conversion is summarized.Thirdly,the satellite attitude mathematical model is established,including satellite attitude dynamics model and satellite attitude kinematics model.Finally,an adaptive satellite attitude stabilization algorithm is designed,and the stability is proved by Lyapunov theory.On this basis,the corresponding parameters are optimized by fuzzy control in view of the influence of the corresponding parameters in the algorithm.And introduces the characteristics and mechanism of fuzzy algorithm in detail.In the Matlab/Simulink environment,a series of simulations including the initial attitude shift,the stationary position and the satellite disturbance are carried out,and compared with the traditional control algorithm.