Research On Aerodynamic Parameter Online Identification And Guidance For The Boost-glide Tactical Missile

With the advantages of excellent penetration ability and strong maneuverability,the boost-glide tactical missile becomes one of the focuses in current high-performance weapon gradually.As the boost-glide tactical missile in the atmosphere all the way,the inconsistency of aerodynamic parameters of heaven and earth affects the normal stability of missile flight,increase the burden of guidance control system.In this paper,the goal to the aerodynamic parameter online identification and reentry guidance key technical are under research,in order to study the ballistic characteristics systematically,aerodynamic parameter online identification and gliding segments of reentry guidance and other issues are studied.The boost-glide tactical missile gliding ballistic properties are analyzed.Analyzed the basic motion of missile in gliding flight,on the basis of the analysis of the gliding ballistic shape and range and gliding slippage parameters,the relationship between the simulation,get the best speed and slippage angle corresponding optimal range;Analyzed the overload and dynamic pressure constraints on the influence law of gliding ballistic.According to the mission requirements,the gliding ballistic optimization design was carried out,and complete the range coverage analysis and the simulation calculation of area.Studied the boost-glide tactical missile aerodynamic parameter online identification method.The aerodynamic parameter identification model is established.Theoretical analysis of the aerodynamic parameter identification,was proposed based on factor analysis method combined with parameter estimation covariance method as a parameter to identification criterion;Based on the basic form of excitation input design is studied,and the boost-glide tactical missile movement modal characteristics,puts forward the quasi-square wave dipole was optimized by using particle swarm optimization as the excitation input scheme.The performance of EKF,UKF,CKF three filtering algorithm were studied,based on the simulation results clearly using CKF as parameter identification algorithm in this paper.The simulation results show that the use of input effectively stimulate the missile movement modal of aerodynamic parameter identification with strong real-time and high accuracy.Based on the Lyapunov stability of aerodynamic parameter identification strategy step by step.Missile is analyzed by perturbation motion model and aerodynamic parameters to be identified on the disturbance response.Proposed the parameter identification strategy step by step,the parameter is deduced more new law and parameter estimation boundary expression,based on Lyapunov theory to prove the convergence of the method.The simulation results show that the parameter identification strategy step by step can effectively improve the efficiency of parameter identification.Missile is studied gliding flight process guidance problems under the new mission requirements.Was deduced based on the transverse process and iteration deviation correction track angle and heading angle of the algorithm and the guidance instruction generation process;Iteration precision parameters and highly guided step length was optimized;Based on the glide middle new task to decide the placement accuracy and efficiency of the simulation verified the guidance method,and the robustness is analyzed.Using the optimal guidance law with fall angle constraint solving boost-glide tactical missile down period of guidance,and the simulation test and verify.The research of the strategy of online aerodynamic parameters identification and the key technology of reentry guidance of boost glide missile,which will provide theoretical support for the overall design and key technology development of this kind of vehicle.