Research On Angle Constraint Guidance And Control Method Of BTT Missile

With the development of modern weapon technology,BTT missile has more and more advantages in maneuverability due to bank to turn.This paper mainly studies the angle constraint guidance method and BTT control system method of BTT missile to realize the high angle attack and stability control of BTT missile.In the introduction,the research background,research methods and control methods of BTT are introduced.Then,the definition of the coordinate system is defined,the attitude transformation matrix between the coordinate systems is determined,the dynamic and kinematic equations are derived,the angle relationship equation and lateral overload equation are given,which establishes the mathematical model for the research of guidance method and control method.Thirdly,the extraction model of LOS angle rate signal of Strapdown Los seeker is derived,the method of LOS angle rate extraction by particle filter algorithm is studied,the detailed derivation process of trajectory shaping guidance law based on optimal control method is given,and the fixed time convergence non-singular terminal sliding mode guidance method is studied.The simulation results show that the particle filter estimation can accurately estimate LOS angle rate of inertia.The simulation miss distance and fall angle of the two guidance laws meet the design requirements.Then,the classical BTT coordinated decoupling control method is studied.Based on the linear model of small disturbance,three channels of independent control are carried out.For the coupling problem,the coordinated decoupling term is introduced to compensate the coupling effect.The single channel fixed-point simulation,nonlinear fixed-point simulation and six degrees of freedom mathematical simulation analysis are carried out.The results show that the coordinated decoupling control method can effectively compensate the coupling effect and meet the control system design requirements.Finally,the active disturbance rejection control method of BTT missile is studied.The design of active disturbance rejection controller for BTT missile is designed,which includes arrangement of transition process,nonlinear feedback law and extended state observer.The six degree of freedom mathematical simulation analysis is carried out.The results show that compared with the classical design method,the ADRC design method is simple and effective,and meets the requirements of BTT missile control system.