基于滑模控制的飞行器螺旋机动、制导与控制一体化设计研究

To solve the problems of the capability deficiency of air-to-ship aircraft in the terminal guidance process and the inefficient control due to the separation of guidance and control loop design with unsatisfied assumption of bandwidth separation, an integrated design method was proposed for the guidance and control loop of the aircraft. Taking a ballistic maneuvering form with three-dimensional spiral maneuver, the design method was arranged to achieve spiral maneuvering, guidance and control integration. Firstly, an integrated model was established for the guidance and control loops at the end of the flight. And then, a sliding mode control method was applied to complete the control law design for guidance and control integration. Finally, introducing a period inclination rate of the line of sight obliquity and the line of sight deflection rate, the integrated design was carried out for spiral maneuvering, guidance and control integration. The simulation results show that the control law designed in this paper can improve the strike accuracy and provide a ballistic spiral maneuverability in the attack process.