Research On Reentry Attitude Control Methods For Folding Hypersonic Morphing Gliding Vehicle

Hypersonic glide vehicle has the ability of large-space gliding and large-scale maneuvering in near space,which has important strategic value and significance.In order to further improve the environmental adaptability and anti-defense survivability of the vehicle,the hypersonic morphing gliding vehicle comes into being.This paper takes a folding hypersonic morphing gliding vehicle as the research object,comprehensively considers dynamic changes caused by the deformation of aerodynamic characteristics and kinetics characteristics,and the influence of model uncertainties and external disturbances,carries out the research on vehicle motion modeling,aerodynamic characteristics analysis,aerodynamic parameter identification,and reentry attitude control method.The main research works are as follows:Firstly,the reentry motion model of the hypersonic morphing gliding vehicle is established.The multi-body dynamics modeling method is used to model the six degrees of freedom of kinematics and dynamics of the hypersonic morphing gliding vehicle in reentry phase,where the additional forces and additional moments caused by wing folding during the deformation process are studied emphatically.A mathematical model for reentry attitude control of hypersonic variant glide vehicle is established by further simplifying the motion model.Secondly,the aerodynamic model of the hypersonic morphing gliding vehicle is established and its characteristics are analyzed.Based on the aerodynamic data fitting,the complete aerodynamic model of the hypersonic morphing gliding vehicle under different deforming conditions is obtained.The static aerodynamic characteristics of the vehicle are studied,and the effect of folding deformation on the static aerodynamic characteristics of the vehicle is analyzed.The open-loop and closed-loop dynamic characteristics of the vehicle are studied,and the influence of deformation on the reentry attitude motion characteristics of the vehicle is explored.Then,a reentry attitude control method with guaranteed performance based on disturbance compensation is studied.A finite-time disturbance observer is designed based on the multivariable super-twisting algorithm,accurately estimating the composite disturbance consisting of disturbances and uncertainties.Based on the prescribed performance control framework,a novel appointed-time prescribed performance function is designed to quantitatively describe the desired performance constraints,and an attitude controller with guaranteed performance is devised using the dynamic surface control technique.The effectiveness and robustness of the proposed method are verified by the simulation of the whole trajectory and the test condition respectively.Finally,an adaptive method for reentry attitude control based on online identification of aerodynamic parameters is proposed.The model for aerodynamic parameter identification is established based on the reentry motion model of the hypersonic morphing gliding vehicle.An online identification method is designed based on the extended Kalman filter algorithm,in order to realize online identification of unknown aerodynamic parameters.An adaptive reentry attitude control method is proposed by combining with the aerodynamic parameters identified and the control scheme based on sliding mode control and disturbance observer.The effectiveness and adaptability of the proposed method are verified by numerical simulation.