Research On Attitude Control Of Rotating Warhead Under Direct Force

Rotary missile is a short-range, rapid response air defense missile, which has a simple structure and convenient to operate. Compared with the general missile, the rotary missile's biggest characteristics is the body around the longitudinal axis of spin motion. Because of the smaller volume of the body, it is generally required that a pair of operating structures to operate both the longitudinal and lateral motion of the missile at the same time,This unique control mode is known as the single channel control of the rotary missile.In this paper, taking a rotating missile warheads as the object of study and the pulse attitude control engine is installed in the tail of the warhead. The direct force generated by the attitude control engine is modulated by the pulse width. The influence of the aerodynamic force on the rotating warhead is ignored, and only considering the effect of direct force on rotating warhead.The main content of the research includes the following:(I)To establish the kinematics model and dynamics model of direct lateral force control for spinning warhead.Taking into account the projectile warheads around the longitudinal axis of spin characteristics, we need to convert to relevant parameter from elastomer coordinate system to a quasi-body coordinate system, and redefine the registration angle of attack and side-slip angle associate. In the process of modeling,using the small disturbance linearization method and the coefficient freezing method,rotation of the warhead kinematics model and dynamics model is linearized. In addition,it is necessary to establish the transfer function between the overload command and the missile body motion parameters, which lays the foundation for the design of the guidance and control loop.(II)Analysis of the principle of the control force produced by the rotating missile,The missile dynamics model and the kinematics model of the single channel control of the rotary missile under the action of direct force are derived and established.Combined with the classical PID control method, the corresponding controller is designed for the single channel direct force attitude control and dynamic analysis is carried out. The theoretical basis is provided for the simulation analysis of the whole large loop of rotating warhead.(III)For the most commonly used proportional navigation system, the model of the guidance and guidance law is focused on, By establishing the relationship between the relative motion of the missile target under the proportional guidance law, constructs the realization model of the proportional navigation guidance law, and prepares for the simulation model of the whole circuit.(IV)According to the different targets, the corresponding control loop simulation model is established. The guidance model is a dynamic model, which needs to combine the various parts of the model established in this paper, so the process is more complex.Simulation analysis is carried out in the form of packaging module, which greatly reduces the complexity of the system and improves the simulation efficiency.