Predicating And Protecting Control Of The Dangerous State Boundary For Super Maneuver Flight Motion Of Advance Fighters

In the modern military combat, the higher request is given for the super maneuver performanceof fighters due to the improvement of the military demand. At the same time, the flight safety problembecomes an important field for further study. The so called maneuvering flight safety, it mainlymeansthat whether the state variables reach the dangerous state boundary. If the boundary values areknown,the constraint and protection can be imposed on these state variables. Therefore, the researchon predicating and protecting the dangerous state boundary for super maneuver flight motion ofadvanced fighters is an advanced and challenging issue. This dissertations study the advanced fightersmodel. On the basis of the model, the load boundary, the velocity boundary, the angle of attackboundary are studied. Sliding mode control is desigend by using unidirectional auxiliary surfacesbased on power reaching law and the boundary protection is applied to the pitching maneuver.Themain works are as follows:Firstly, a nonlinear flight motion mathematic model for the advanced fighters is established. Andthen, the related analysis is given for the construction, parameter setting, the zero input response ofopen loop model, coupling characteristics of the channel, uncertainty and the interferencecharacteristics of flight environment. Thus, the established model is correct and it can be used as thefoundation of predicating and protecting boundary.Then, aiming at the F16model, the relations between the attitude angle, control surface, attitudeangular rate and the aerodynamic coefficient are analyzed as the reference frame for boundarypredication. On this basis, the load boundary and the velocity boundary are given. Under the conditionof high dynamic pressure, considering the load boundary as constrained condition, the angle of attackboundary is studied. Under the condition of low dynamic pressure, introducing the reachable balancedset concept, the angle of attack boundary is studied. Finally, the dissertations comprehensive theabove Angle boundary.Following, the sliding mode control with unidirectional auxiliary surfaces based on powerreaching law is designed. Simulation results illustrate that the chattering can be effectively reduced,and it ensures the reaching speed near the switching surfaces.Finally, the sliding mode control is studied with unidirectional auxiliary surfaces based onpower reaching law to the flight control system. Simulation results illustrate that the controller canobatin the good super maneuver performance for advanced fighters. And, the convergence rapidly is observed and the chattering resistance is stronger. Thus, the developed sliding mode control schemehas a good control performance.On this basis, the boundary predication and protection system isaddded to the flight control simulation system. Simulation results illustrate that the boundaryprotection system perform good protection characteristic.