Analysis of Dynamic Characteristics of Active Defense System During Rapid Attitude Adjustment

The faster the missile attitude adjustment speed of the active defense system is, the higher the accuracy requirement is. By symmetrically arranging impulse thrusters to achieve rapid attitude adjustment of the missile body, the success rate of interception can be improved. Firstly, the distribution curve of the normal force increment per unit length of the tail of the X-tail projectile along the axis direction at different angles of attack was analyzed, in order to more intuitively analyze the influence of the lateral jet interference flow field on the surface pressure distribution of the X-tail projectile. On the basis of the out-of-pitch-plane aerodynamic calculation model of pitch and the six degree of freedom exterior ballistic model, the attitude adjustment results of the X-tail structure projectile under the action of the impulse thruster are analyzed. The influence of X-tail structure and different states of external flow field on the aerodynamic attitude adjustment results was analyzed, providing a theoretical basis for the subsequent application of the impulse thruster.