The Aerodynamic Analysis On Rolling Controlling Flight Of Close-coupled Double-canard Configuration Missles

Guided rockets in the active and passive period of flight have certain static stability. with the end of the active period, the center pressure of guided rockets will move toward the head, it will increase the static stability. With the reducing of velocity in the passive period of flight, the pressure centre of the rocket will move toward the tail, which not only increases guided rocket’s static stability obviously, but also declines maneuverability. To improve maneuverability, make it pop-up an additional canard, which named close-coupled double-canard, in front of the canard at right time. But it will be bound to affect the flow characteristics of the flow field, the downwash of the close-coupled double-canard will affect the characteristics on the tail surface.To solve this problem, designed two models in different forms, include the canard and close-coupled double-canard. All shells aerodynamic data by wind tunnel experiments were given and then analyzed the variation of the aerodynamic coefficients especially the rolling moment coefficient. The experimental results show that the affection of the downwash reduced in the sonic and transonic stage, especially when the angle of attack4°～8°rangeThe aerodynamics coefficients of the canard, tail and whole model also can be gotten through CFD. Through comparison and analysis of the results gotten from wind tunnel experiments and CFD, seek a method to weaken the affection of downwash.It was discovered by CFD and wind-tunnel test that the pressure of the canard and tail was reduced from the general point of view, the affection of the downwash of the canard on the tail was reduced. In general, it improved the affection of Canard’s underwash on the rocket tail. The rocket’s roll control ability was improved.