Investigation On Hardware-in-the-loop Simulation Algorithm Of Diving Guidance Technology For Hypersonic Vehicle

Guidance control and simulation technology about setting up hardware-in-the-loop simulation environment of guidance and control system for hypersonic vehicles with high lift-drag ratio aerodynamic configuration is investigated in this dissertation.Introduces the constructing hardware-in-the-loop simulation environment and sets up various kinds of mathematical model that the simulat ion environment software system needs.To solve the problem of hinge moment too high in dive phase for hypersonic vehicle,the terminal impact point,falling angle and incoming azimuth angle constrained diving guidance method with optimal hinge moment is investigated.First of all,building the linear relationship of hinge moment and overload by transient equilibrium assumption,hinge moment was described indirectly by overload in the optimal index.Secondly,the state space equation of relativity motion was established by selecting overload as control variable.Finally,based on optimal control theory,choosing the optimal index of minimum overload and leading into the pseudo control variable,an optimal analytic form guidance law with minimum overload was inferred.About the robustness insufficient of traditional Dynamic Inverse Control,a high precision and strong robustness attitude control method by active disturbance rejection technology to strengthen the robustness of dynamic Inverse control for hypersonic vehicles is investigated.According to time-scale separation principle,the attitude control model of hypersonic vehicles is divided into two subsystems,a quick loop and a slow loop.Then,the highly coupled control channels and serious nonlinearity model of quick loop and slow loop are linearized and decoupled by dynamic Inverse control method.Nonlinear Law State Error Feedback is designed to control the linearized and decoupled system.Uncertainty factor is real-time estimated and compensated by extended state observer.To solve the defect of simulating and validating about guidance algorithm for hypersonic vehicles by the traditional three-degree-of-freedom simulation method,a new simulation method considering angle of rudder reflection in simulat ing return circuit is proposed.Basing on the new simulation method,a hardware-in-the-loop simulation scheme about guidance algorithm is formulated.Validating and analyzing the rationalities of new simulation method and hardware-in-the-loop simulation scheme by simulating case.Finally,in order to validate the function of guidance law and the optimal effect of maximum hinge moment further,simulation about the diving guidance method with optimal hinge moment investigated in chapter three is experimentalized in different pattern.In general,the dissertation expands the guidance,control and simulation theory for hypersonic vehicles.The proposed algorithms are usable in practice,and can provide some reference for the guidance control system of hypersonic vehicle,RLV,anti-ship missiles etc.