Design Of Strapdown Guidance And BTT Control System For Small Patrol Missile

Patrol missile is a new type of high-tech fusion of intelligent ammunition,the trend of modern warfare information has shown great potential.The development of patrol missile has higher requirements for seeker and guidance control technology,and it is of great significance for the research of strapdown seeker,guidance and control technology.In this paper,a small patrol missile is studied,and the design method of the strapdown guidance system and the design of BTT control system are mainly studied.Firstly,this paper introduces the research background and significance of the subject,introduces the patrol missile research status and the research status of strapdown guidance and BTT control.Secondly,the mathematical model of small patrol missile is established.This paper defines the common coordinate system,and give the transformation relations between the coordinate systems;the dynamic equation of centroid of patrol missile and the dynamics equations of body rotation around centroid,the kinematics equation of centroid of patrol missile and kinematics equation of projectile body around centroid rotation,the angle relation between coordinate system,and the lateral overload equation of projectile body are given as the basis of subsequent research.Thirdly,a strapdown guidance system of line-of-sight angle is designed.The angle-feedback-constrained optimal terminal guidance is studied in detail.In view of the problem that the inertial line-of-sight angle of the single axle semi strapdown seeker cannot be measured,in this paper,the direct reconstruction method and the Unscented Kalman filter method based on line-of-sight dynamics model are used to extract the inertial line-of-sight angle,and the optimal terminal guidance of the strapdown integral proportional guidance law and the angular feedback form is studied.Then,a strapdown guidance system with angular rate of sight is designed.This paper studies the method of line-of-sight angular rate estimation based on line-of-sight dynamics model,and carries out the method of line-of-sight angular rate extraction based on TD tracking differentiator.This paper studies the terminal guidance law of line-of-sight angular rate based on the optimal control theory,pushes the terminal guidance law of missile path,and compares and analyzes the non singular fast terminal sliding mode guidance law.Finally,the BTT control system is designed.The small perturbation linearization control modeling of BTT missile control system is carried out,coordinated decoupling and three-channel independent design,and carries out six degrees of freedom simulation.The integrated shooting simulation of the guidance control system is carried out,and the simulation results are summarized and analyzed.