Research On The Integrated Guidance And Control Method For The Gliding Phase Of Hypersonic Aircraft

With the development and maturity of hypersonic technology,hypersonic vehicle have become the focus and goal of development for countries around the world.However,due to the nonlinear,strong coupling,and fast time-varying characteristics of hypersonic vehicle,as well as the coupling effect between aerodynamic models,centroid motion models,and around centroid models,the design of hypersonic vehicle guidance and control systems is difficult.Therefore,the guidance and control methods of hypersonic vehicle are currently a difficult and hot research topic.The integrated guidance and control method studied in this article is an important development direction in the field of hypersonic vehicle guidance and control.Compared to traditional guidance and control methods,the integrated guidance and control method considers the coupling characteristics of vehicle centroid motion and surrounding centroid motion,and designs the guidance and control circuits as a whole circuit to improve flight performance and reduce costs.This article takes hypersonic vehicle as the research object,designs two integrated guidance and control methods for the gliding flight phase,and compares them with traditional guidance and control methods,highlighting the superiority of the integrated guidance and control method.Research the design of glide guidance and control methods based on the principle of time scale separation.The attack angle and pitch angle commands are obtained through longitudinal range control and lateral azimuth error control.The controller is designed using backstepping control method,and the effectiveness of numerical simulation is verified by combining guidance and control.This lays the foundation for comparison and verification with the integrated guidance and control method design method in the future.The integrated design method of guidance and control based on adaptive dynamic surface is studied.Firstly,the relationship between the component of vehicle acceleration in the ballistic coordinate system and the three channel angular rate is established.This relationship is used to replace the kinematics equation of rotating around the center of mass expressed by the airflow angle in the traditional control loop.Combined with the dynamic equation of rotating around the center of mass,the integrated guidance and control model is established;Secondly,based on the dynamic surface control method,the uncertain terms in the model are estimated and compensated using an adaptive estimation law;Finally,the effectiveness and robustness of this method were verified,and compared with traditional guidance and control methods designed based on the principle of time scale separation through simulation analysis.To further improve the robustness of the integrated guidance and control method,a linear active disturbance rejection guidance and control integrated design method considering Anti windup is proposed to address the problem of sustained full rudder deviation when the vehicle is subjected to strong interference.Based on the existing integrated guidance and control model,a new integrated guidance and control model is constructed by improving its dynamic equation of rotating around the center of mass,satisfying the distribution of torque in three channels,and considering anti windup feedback.The integrated control law is designed by integrating the linear active disturbance rejection method and Anti windup structure,and the effectiveness and robustness of the proposed method are verified through simulation.It is also compared with traditional guidance and control methods based on time scale separation Simulation and comparative analysis of guidance control design methods based on adaptive dynamic surfaces.