Modeling And Control For The Hypersonic Vehicle

Hypersonic vehicle has strategic significance and high application val-ues. Because of strong coupling, uncertainty, parameters changing and uniqueaerodynamics, modeling and controller designs face the severe challenge. Re-searches in this paper are carried out in three aspects, which are modeling,equilibrium and controller design for hypersonic vehicle. Main results are asfollows:Six-degree model of generic hypersonic vehicle(GHV) is established inSimulink. The whole model consists of aerodynamics, propulsion systems,aircraft inertia, total acceleration, air atmosphere, equations of motion andearth module. Quality time-varying and environment parameters changing aresoundly considered. Wind and turbulence module are also introduced into themodel. The model based on the data of NASA, provides a simulation platformfor later research. Furthermore, characters of open loop are discussed.For solving the equilibrium of GHV with unstable modal, a hybrid op-timization technique GA-SQP is developed. According to integral of timemultiplied by the absolute value of error criterion, adopting chaos searchingand elimination, the improved genetic algorithm is used to calculate equi-librium states, which are transformed into solving the minimum of the costfunction. Furthermore, sequential quadratic programming is introduced soas to accelerate the local optimum. Attacking angle, elevator de?ection andthrottle setting are obtained by steps. Based on Simulink dynamic model ofthe vehicle, simulation results show that the new GA-SQP algorithm, withdesired steadiness, is able to determine the final solution accurately while it isnot sensitive to the initial point. The algorithm of this paper provides a prac-tical and e?ective method to solve the equilibrium of the complex nonlinearsystems.Based on nonlinear dynamic inversion, a robust adaptive sliding mode controller is designed for GHV with input-output linearization technology. Theadaptive gains not only decrease the chattering, but also improve robustness.The stability of the system is guaranteed in the sense of Lyapunov stabilitytheorem under a certain conditions. Simulations demonstrate the e?ectivenessof the controller.An adaptive backstepping sliding mode control approach is proposed forGHV. RBF networks are adopted to approximate the unknown nonlinearities.The control law and adaptive updating laws of neural networks are derived inthe sense of Lyapunov function, so the stability can be guaranteed. Further-more, adaptive sliding controller with command filters are studied, which notonly guaranteed the stability of system, but also cut down the calculations forthe derive of virtual control. Simulation results under the hypersonic conditionshow the e?ectiveness of the proposed approach.For the guidance of GHV, robust guidance laws are designed based onguaranteed cost control. With linear matrix inequalities, the guaranteedcost(GC) and optimal guaranteed cost(OGC)laws are given. Interception sim-ulations of di?erent maneuvering targets show that GC and OGC controllerscan guidance missile attacking the maneuver target successfully. To comparedwith proportional navigation, the proposed GC controllers are not only againstdisturbance, but also posses small overload on the encountering time and smalltarget-missing distance.