The Aerodynamic Analysis On Cornerning Of Rolling Flight Of Canard Configuration Missiles

In this dissertation, canard configuration missiles are studied from the view of aerodynamic. First, the reasons which cause the conrnerning of rolling flight of canard configuration missiles may have two. One is that the cornerning is caused by the non-ideal conditions of rudder swinging, and the other one is that the cornerning is caused by the asymmetric downwash flow acting on the empennage. By the way of wind tunnel experiment, we got aerodynamic data of non-rudder model and other three kinds of models. According to the experimental results of different kinds of models, we got the variation regularity of resistance, lift force, pitching moment, rolling moment, yawing moment and yawing force of the models which vary with Mach number, attack angle, elevator angle and roll angle. By crossed comparative analysising the data of different kind of models, investigate similarities and differences of the aerodynamic characteristics of each kind of model, and analysis the regularity and characteristic of cornering which is caused by the asymmetric downwash flow.Experimental results showed that, the four kinds of modes have the same variation mechanism and regularity in resistance, lift and pitching moment. Number 4 model vary moer violently with attack angle than other three kinds of models. When the missile body is on asymmetric posture of the vertical plane, with attack angle increasing, asymmetry of downwash flow show up more obviously, and rolling moment coefficient raise rapidly. This situation explains that why the missiles in actual flight have the phenomenon that rotation speed is uneven. Lateral force and yawing moment of the models with rudders are obviously bigger than the ones without rudders. With the attack angle and elevator angle raising, the influence asymmetric downwash flow acting on cornerning becomes harder, lateral force and yawing moment increase. Lateral force and yawing moment vary in sine or cosine when roll angle change. When the missile body is on symmetric posture, the values about cornerning are small and vary around zero. When the missile body is on asymmetric posture, the values about cornerning show obviously fluctuation.