The Influence Of Different Tail Structure Of Canard-missile To Missile-rolling And Other Aerodynamic Characteristics

In this thesis, the rolling moment characteristics of canard missiles are studied, the mechanism and influence of downwash of canard is analyzed. First, I design six groups of missile model, then process them by steel. Wind tunnel investigation is conducted on this six different canard configuration models over the range of Mach from 0.8 to 2.5. Based on the experiment data, I analyze the regulation of rolling characteristics, lift characteristics, drag characteristics and pitching moment characteristics with Mach number and angle of attack, and the effect of these characteristics for different canard configurations is compared. The results indicate that canards are ineffective as rolling control devices for normal canard missiles, because noticeable reverse rolling moments are induced when the canards have rolling command deflection. With canard of big aspect ratio, and sweep angle, the reversed induced rolling moments could be reduced, even the phenomenon of anti-effect has disappeared completely when the configurations are logical. Wind tunnel experiments show that some new configurations improve the rolling control efficiency, allowing the canard to execute the rolling control, with the change of configurations, its lift characteristics, drag characteristics and pitching moment characteristics also change. So, it is helpful for aerodynamic configuration design of canard missiles.