Research On Guidance Algorithm For Rolling Missile With Strapdown Seeker And Design Of Control System

With the rapid development of military technology,the requirements for the precision,miniaturization,and low-cost of tactical missiles have become higher and higher.The rolling missile has the advantages of simple control structure,low cost and strong anti-interference ability.The full strap-down seeker has the advantages of small size,low cost,and high end precision.The rolling missile and full strap-down seeker both comply with the development trend of tactical missiles.The research on the application of the full strap-down seeker to the rolling missile has received widespread concern and attention.In this paper,the research object is the rolling missile with the end guide of the full strap-down laser seeker.The full strap-down guidance algorithm and the design technology of the rolling missile control system are studied.The full strap-down seeker can only obtain the line-of-sight measurement signal based on the projectile coordinate system,which cannot be directly applied to the terminal guidance law of the rolling missile.Moreover,the optical and electronic systems on the seeker have greater measurement noise and interference.Therefore,it is necessary to estimate the seeker guidance information.In this paper,a decoupled inertial line-of-sight angular velocity nonlinear mathematical model is established for the full strap-down laser seeker of the rolling missile.The guidance information is estimated by the extended Kalman filter and unscented Kalman filter.Then,Mathematical simulation program is written in MATLAB language,and the filtering effect of two filtering methods is verified through mathematical simulation.The design of the overload autopilot on the pitch and yaw channels for the rolling missile is carried out after the estimation of the inertial line-of-sight angular velocity of the full strapdown seeker.Firstly,according to the relationship between dynamics and kinematics of the rolling missile,the mathematical model of projectile motion of the rolling missile is established,and the projectile transfer function of the rolling missile is deduced.Then,the design of the overload autopilot of the rolling missile was completed by using the classical PID control method and the model reference adaptive control method.And the phase compensation method of the servo is used to weaken the coupling problem of the pitch and yaw channel of the rolling missile.The Simulink simulation tool is used to establish the mathematical simulation model,and the design result of the autopilot is verified.Finally,the whole trajectory simulation model of the rolling missile is established by combining with the strap-down navigation algorithm and the control system design results.Through the whole trajectory mathematical simulation,the validity and the guidance effect of the UKF and EKF filtering estimation algorithm for the rolling missile are verified.