Residual Self-turning And High-accurate Control Algorithm Of Hypersonic Vehicle

With human beings’ stepping into the brand-new21st century, hypersonicvehicles are the aerospace vehicles that need to develop, which has huge militaryand potential economic values. Overseas, some developed countries have masteredcertain key technologies of hypersonic vehicles, but our country is still at thepreliminary study level on it. Thus various aspects of hypersonic vehicles requirefurther investigation for us. Because hypersonic vehicles are influenced by all kindsof unknown aerodynamic interaction in atmosphere, the focus of the thesis are howto restrain them, meanwhile avoid the flutter phenomenon of hypersonic vehiclesand enhance the accuracy of the controlling system.Almost all existing documents on interference suppression of hypersonicvehicles require that the structure model of the system is known and the disturbancemodel is accurate. However, if the real disturbance doesn’t match the disturbancemodel, it will cause the failure of the whole system. Thus, the thesis proposed anoptimization method that controller is based on data-driven instead of model, whichavoided the negative effect of control method that is based on model. The maincontents of the research consist of several aspects as following:In order to do a better research on the complex aerodynamics characteristics ofhypersonic vehicles, nonlinear six-DOF motion equation in all states of hypersonicvehicles were established; the thesis decoupled nonlinear motion equation ofhypersonic vehicles in all states, and established longitudinal motion model ofhypersonic vehicles under the condition of equilibrium flying; for the disturbinginfluence to hypersonic vehicles, the thesis analyzed the flutter phenomenon ofhypersonic vehicles.For the longitude motion model of hypersonic vehicles, the research conductedliner discretization of the system, respectively built LTI and LPV models ofhypersonic vehicles; for LTI model of hypersonic vehicles, the thesis designed Youlaparameter stability controller based on observer through Pole Assignment; for LPVmodel of hypersonic vehicles, linear matrix inequality was used to design Youlaparameter stability controller based on observer; the purpose of the stabilitycontroller design was to realize the stability within the closed-loop system and thegeneration of residual.For LTI system of hypersonic vehicles which was based on Youla parametricstructure of observer, the thesis proposed a method based on data-optimal tooptimize the closed-loop performance indicator of the system, thus to restrain theun-modeled disturbing effect of the system and increase control accuracy; for LPV system of hypersonic vehicles which was based on Youla parametric structure ofobserver, the thesis proposed a residual-based iterative gain-scheduling controlapproach which scheduled Youla parameter online thus to restrain the un-modeleddisturbing effect of the system, increase control accuracy and reduce the energyconsumption in control.