Research On Spinning Missile Control Method

Spinning missile refers to a class of missiles that spin around the longitudinal axis during flight, which can control the pitch and yaw movement of the missile by single channel. With the improvement of modern warfare’s demand for precision strike capability, the demand of "smart upgrade" for the original uncontrolled or simple controlled munition is growing. While spinning missile is the main way to achieve low-cost and high-precision control, it’s of great practical significance to invest the spinning missile’s control method. In this paper, we take spinning missiles as the study objective. The main research is as follows.The spinning missile motion model is established. The spinning missile motion equations based on the corresponding coordinate system is derived. Through the uncontrolled trajectory numerical simulation of spinning missile, the uncontrolled movement characteristic is analyzed. The transfer function based on the spinning missile perturbation motion equations is derived. The dynamic stability and rotary speed range are discussed.The spinning missile control mechanism is investigated. The periodic equivalent control force is introduced and calculated under several typical deflection motion of rudder. The working process of typical spinning missile autopilot system is introduced. In consideration of the study object in this paper and the mission requirement, a rudder deflection strategy based on the current rotational position is presented.The spinning missile guidance law is designed. In consideration of inertial/GPS integrated navigation mode applied in spinning missile, a overload command guidance law using the proportional navigation method is designed. Simulation results show that spinning missile can hit the target with small miss distance under the guidance law, and the required overload in the entire process can be achieved.The spinning missile control system is designed. Based on the LQR controller and linear extended state observer, the spinning missile overload control loop is designed, and the control performance on the feature points is analyzed. A numerical simulation of the guidance and control systems for whole trajectory and Monte-Carlo targeting experiments considered the parameter bias is conducted. The outcome of numerical simulation verify the correctness of the designed guidance and control systems, and achieve the accuracy of impact point, which provides a reference for further research.This paper makes a more comprehensive study of the spinning missile control problems. The research is a useful exploration for spinning missile control method, which has some extent of theoretical significance and reference value.