Characteristic Model-based Attitude Control Method And Application Research For Spacecrafts

With the continuous development of the aerospace technology, the increasing tasks forin-orbit spacecraft and the requirements for spacecraft attitude control are getting more andmore complex. In recent years, the performance and accuracy of the spacecraft attitudecontrol hardware configuration has been improving, meanwhile, the attitude control algorithmresearch has been presenting an increasingly hot trend.The adaptive control based on characteristic model has the advantage of precise controlof the parameters in parameters uncertain and difficult to accurately modeling complexobjects, which shows good application prospects in the field of spacecraft attitude control. Inthis thesis, dynamics modeling, attitude control algorithms for flexible spacecraft are carriedout in-depth study, and the results of the research applies for a control system to a groundtesting of aerospace equipment and a three-axis stabilized satellite Maneuver. Its researchmainly includes the following aspects:The dynamics modeling, attitude control algorithms of the spacecraft at home and abroadhas been introduced, and the progress of the spacecraft attitude control methods has beenanalyzed. A common coordinate system and attitude description method has been geiven, andthe flexible spacecraft attitude kinematic equations have described by Euler angle and unitquaternion.Based on the low-order model, a PD control law which based on the logical differentialhas been designed for the parameter uncertainties, external interference and input saturation ofthe flexible spacecraft. This control law can content well with the demand of the system todifferential function, and its stability has been proved by the Lyapunov stability principle. Theequipment designed by this method has been put into use, security and stability failure.The optimal time control law and nonlinear golden section adaptive control law havebeen designed for the three axis stabilized flexible spacecraft fast maneuver control. In thesimulation process of optimal control, in order to solve the HJB equation, the θ Dmethodhas been recommended, for the weak of the rapid mobility control accuracy and stability,where joined the sliding mode control law to adjust; In the adaptive of the simulation process,the characteristic parameters of the model using the freeze processing method, the controlprecision to the optimal control method have been improved, but also need to carry out furtherin-depth study.Finally, the nonlinear golden section adaptive control law which based on characteristicmodel has been designed for the three-axis stabilized satellite large angle attitude maneuver,then the effect of nonlinear logical differential in the golden section adaptive control has beenverified. According to the simulation results, the designed control system has certain feasibility and value of this thesis.