The Aerodynamic Configuration Design Of Stability And Control Of Canard Configuration Guided Rocket

In this thesis, the aerodynamic configuration design of stability and control for canard configuration guided rocket was studied, and the effect of stability and control of canard configuration guided rocket for different aerodynamic configurations was analyzed. Two sets of wind tunnel experiment were designed. The first set researched on longitudinal stability and control characteristics of the aerodynamic configuration of the guided rocket. The second set experimental researched on rolling control characteristics of the canard configuration guided rocket.Three models were designed in the first set. Warheads, missile bodies and collembola were the same,the canard had the same size, elevator angles of the canard were different. Wind tunnel test was conducted on this three different canard configuration models at different Mach number, attack angle and elevator angles. Based on the experiment data, the lift characteristics ,drag characteristics and pitching moment with variety of Mach number, attack angle and elevator angles were analyzed. The regulation of stability and trim ratio of canard configuration guided rocket with variety of Mach number were also analyzed . The results showed that the aerodynamic configuration of canard configuration guided rocket was in line with the tactical index.In the second set there were three models. Warheads and missile bodies were the same, and the collembola were fixed tail, free rotation tail and tailless. Wind tunnel test were conducted on this three different canard configuration models at different Mach number and attack angle. Based on the experiment data, the regulation of rolling characteristics, lift characteristics and drag characteristics with variety of Mach number and attack angle were analyzed, and the effect of this three characteristics for different tail were compared. The results indicated that lift characteristics and drag characteristics of the fixed tail and free rotation tail with variety of Mach number and angle attack were basically the same, but the rolling characteristics for fixed tail, free rotation tail and tailless were obviously different. Rolling moment coefficient of tailless one was the largest, the free rotation tail one second, the tailless one minimum.