Integrated Guidance And Control Forlongitudinal Motion Of Hypersonic Vehicle

As the science and technology develops, the hypersonic vehicle has more important strategic position militarily. Compared to the regular method that the guidance loop and control loop are designed separately, the controller integrated guidance and control can get the utmost out of the efficiency of vehicle ’s mobile to improve the vehicle attacking accuracy. This dissertation is focus on the system modeling, integrated controller designing and the controller with the constraints of terminal pitching angle for the longitudinal motion of hypersonic vehicle.First, the Winged-Cone hypersonic vehicle is chosen as the research object to get the dynamics equations of its longitudinal motion and deduce the guidance state equation with the design target of Zero-miss-distance. Appropriate system state variables and input/output are selected to get the integrated guidance and control system model of longitudinal motion for hypersonic vehicle. Then with the consideration of constraits of piting angle at the intercept point, new system state variables are selected to build the integrated guidance and control model with pitching angle constraints. Besides, the paper also introduces related simulation model and structure.Secondly, the method being used in this paper—adaptive filtering backstepping is introduced in detail, which can avoid the “computing inflation ” problem caused by backstepping effectively. And a berief overview of the basic controller’s designing steps with backstepping is introduced with an example and the fundamental of choosing sliding surface and virtual control is also presented. Besides, the specific form of filter in this paper is presented, and the thought on designing adaptive rate to estimate the uncertainty is introduced.Next, the integral control algorithm for the integrated control model is given to solve the control problem of time-varying nonlinear system with mismatched uncertainy. Then with the consideration the change of aerodynamic parameters explicitly, the paper gives an improved version of control algorithm. The simulation results shows that the integrated control algorithm can keep system stable and attack the static/maneuvering target precisely.Finally, the integrated control algorithm is given to solve the control problem with pitching angle constraints at the point of inteception. The simulation results shows the effectiveness of the controller. The system guide the target precisely and stably and attack the target in an excepting pitching angle in the end.