Solid Ballistic Missile Attitude Control System Algorithm Design

Because of the many advantages of solid ballistic missiles,countries around the world today regard the development of solid ballistic missiles as a key development direction for strategic and tactical ballistic missiles.As an important component of the overall missile design,the attitude control system plays an extremely important role in improving the flight stability of the missile and accurately hitting the target.However,the missile’s altitude and speed are constantly changing during flight,which can make the parameters of the model body dynamics highly uncertain.At the same time,as the missile is not an absolutely rigid structure,elastic modalities must be fully considered in the design,and there is uncertainty in the missile vibration frequency,which increases the difficulty of designing missile attitude control systems.This paper takes the solid ballistic missile attitude control system as the research object,and designs a missile attitude stability control system using classical control theory,robust control theory and adaptive control theory respectively for the problems of missile parameter uncertainty and elastic vibration,and carries out simulation verification and analysis of the designed control system.Firstly,the research background and importance of the topic are explained,the development status of missile attitude system design methods and elastic vibration suppression methods at home and abroad are outlined,and the basics of missile attitude control system are briefly introduced,the mathematical model of missile attitude motion including the elastic vibration equation is also derived,and the stability of non-porous rigid body motion and elastic vibration is briefly analysed to lay the foundation for the subsequent research.Secondly,the PD controller for rigid body missiles is designed using classical control theory,and the trap filter method is used to suppress the elastic vibration of the missile,and the effect of the PD control with trap filter in the missile attitude control system is analysed through simulation.Then,the robust control theory is used to design the attitude control system for the rigid and elastic body models respectively,and the effect of the robust control in the missile attitude control system is verified by simulation.Finally,a model reference adaptive controller is designed using Liapunov stability theory for the rigid body model,and an adaptive trap filter is designed using a least-squares algorithm with forgetting factor for the missile elastic vibration problem.