Parameter Identification And Online Trajectory Planning Methods For Supersonic Cruise Missile

Supersonic cruise is an indispensable weapon in modern warfare with advantages of large specific impulse,small size,light weight,flexible maneuverability,and strong anti-interference ability.This paper takes the supersonic cruise missile as the research object.Taking online ballistic planning based on parameter identification results as the core task,the problems of parameter identification,trajectory online planning,booster guidance and multi-missile coordinated attack of supersonic cruise missile are studied.This article describes the shape of supersonic cruise missiles.Based on the engineering calculation method,the aerodynamic characteristics of supersonic cruise missiles are obtained.The relationship between aerodynamic coefficients and angle of attack and Mach number was analyzed,and the fitting results were analyzed and evaluated.The batch least square method and recursive least square method commonly used in engineering practice are introduced.In this paper,a ramjet performance parameter model is established and proposed a calculation method for supersonic cruise missile power system.The performance parameters of solid rocket ramjet are identified under various flight conditions,based on the result,the variation rule of ramjet performance parameters is studied,and its mechanism is analyzed,and.Identification of aerodynamic parameters and power system performance parameters of supersonic cruise missile can provide strong support for trajectory online planning.An online trajectory planning method based on parameter identification is proposed.The Gaussian pseudospectral method is used to solve the online ballistic planning problem in segments,which greatly improves the efficiency of the solution.According to the characteristics of the cruise section,the trajectory of the cruise section is processed by subsection dimensionality reduction,which reduces the scale of the problem and improves the solving speed.A guidance method for booster stage based on dynamic inversion is proposed.A guidance model for the boost phase was established,the basic principle of dynamic inversion was introduced,the dynamic inversion idea was used in boost phase guidance,and the boost phase guidance law based on dynamic inversion was deduced.Deflection experiments on thrust,aerodynamic coefficient,initial velocity and initial azimuth angle alignment are carried out to analyze their influence on the ballistic characteristics of the booster section.By comparing the nominal trajectory,the deflected trajectory and the guided control trajectory,the guidance effect of the guidance law designed in this paper is analyzed.A guidance law for multi-missile coordinated attack is designed.The guidance model of two-dimensional plane and three-dimensional space is established,and the decentralized cooperative guidance law of multiple missiles,the cooperative guidance law based on augmented proportional guidance,sliding mode variable structure and dynamic inverse control theory are proposed,which can realize attack time constraint and cooperative attack.The research in this paper can provide technical support for parameter identification and trajectory on-line planning of supersonic cruise missile.It can also provide reference for supersonic cruise missile power system modeling,boost guidance and multi-missile cooperative attack.