Research On Aerodynamic Parameter Online Identification And Guidance Of Glide Phase For Tactical Missile

Because of high striking precision and great ability of penetration,the boost-glide missile effectively combines the advantages of traditional ballistic missile and aerodynamic missile,and is becoming the hot spot in the global research.As an effective approach of fast and precise striking for medium and short range,boost-glide missile must evolve to the full-range controllability,maneuvering flight and unpredictably flexible trajectory to face the daily challenge from missile defense system.The range of glide phase holds the main portion of the whole range,so the character of glide phase almost determines the flight quality of the missile.With complex flight environment,the difference of aerodynamic parameter on the ground and in the sky and the atmosphere disturbance both will decrease the flight stability and guidance precision.To cope with the guidance of glide phase for tactical missile,this dissertation has maken systematic research on online identification of aerodynamic parameter and predictor corrector guidance.Simulation and analysis of range optimization and trajectory character of endoatmosphere boost-glide tactical missile in glide phase have been made.The proportion of the covering area is estimated based on the result of range optimization,and the ability of range covering is analysed.The change law of aerodynamic load,heat flow and dynamic pressure are analysed.Flight corridor is built in altitude-velocity profile,and the influence of control and limitation on the boundary of flight corridor is summarized.The most influential characteristic quanlity is further determinted.The methods of aerodynamic parameter modeling and online identification have been coped with.The colinearity of candidate items is diagnosed through the method of singular value disintegration.And then the aerodynamic model is set up through choosing and rejection of the items by stepwise regression.Parameter identifiability is the basis of online identification.Method of analysis of identifiability based on magnitude is proposed,and the method is chicked based on the identification result by extended Kalman filter.The aerodynamic parameter online identification in condition lacking of obversation is studied by extended increment Kalman filter when the obversation model contains nonrandom error.The simulations demonstrate that the aerodynamic models built can well represent the change law of aerodynamic parameter following the flight state.The analysis method of identifability can effectively confirm the parameter which cannot be identificated.Extened increment Kalman filter can ensure the convergance and identification precision in obversation-lacked condition.The numerical predictor corrector guidance has been deliberated.Nondimensionlization motion model concerning normalization energy parameter in glide phase is established.The glide trajectory is divided into three phases,load-increasing,load-decreasing and final-glide on the basis of load change.The magnitude of bank angle is designed based on the former division.A mehod of attack angle adjusting by the feedback of maximum load is proposed in load-increasing phase.Considering both guidance efficiency and trajectory limitation,a multiple iteration strategy is used.The bank angle is iterated according the range error,and attack angle is adjusted to meet the load limitation in load-increasing phase.The attack and bank angles are iterated based on the range and altitude errors in final-glide phase.The terminal velocity limitation is met by the terminal egergy.Finally,a logic reversal strategy of bank angle is designed.Simulation results demonstrate the guidance method designed depends on no standard trajectory,and is adaptive to variable tasks and has enough robustness to environment disturbance.The guidance method based on environmental parameter online identification is finally researched.Comprehensive lift and drag coefficients are introduced,regarding the influence of atmospheric density and aerodynamic parameter.The output of identification is determinted by identifability analysis.Environmental online prediction models are built about altitude.Parameters of the models are fitting and gradually revised by gradual fading-menory recursion least square method based on identification output.And then a predictor corrector guidance strategy based on environmental parameter online identification is proposed.The simulations with atmosphere density and aerodynamic disturbance demonstrate environmental parameter online prediction model can accurately estimate the flight environment and the guidance precision in disturbance condition is increased by introducing the online identification into trajectory prediction.Works of the dissertation can support the research of aerodynamic parameter online identification with nonrandom modeling error,trajectory online planning,adaptive guidance and control.