鸭式布局导弹滚转控制时的侧向气动特性

Lateral Aerodynamic Characteristics of Canard-configuration Missile Under Rolling Control

为研究鸭式布局导弹滚转控制时鸭舵下洗在尾翼上引起的滚转力矩,并揭示该力矩引起的侧向气动力的特性,对鸭式布局导弹进行了滚转控制的风洞实验,得到了鸭舵洗流对侧向气动特性的影响规律;以三维NavierStokes方程为控制方程,对滚转控制时导弹的流场进行了数值模拟,得到与风洞实验相似的侧向气动特性的变化规律。分析了滚转控制时引起的导弹各部件表面压力和侧向力分力,结果表明:侧向力是由鸭舵洗流在弹身左右两侧不对称干扰引起的;侧向力和偏航力矩随滚转舵偏角的负向增大而增大。

To study the rolling moment on the tail caused by canard-rudder downwash under rolling control of canard-configuration missile（CCM）and to reveal the characteristics of lateral aerodynamics caused by the moment,the wind tunnel test of CCM was carried out to investigate the effect of canard-rudder downwash on lateral aerodynamic characteristics.The flow-field of CCM under rolling control was simulated taking 3D Navier-Stokes equation as control equation.The change regularity of lateral aerodynamic characteristics obtained by simulation is similar to that obtained by wind tunnel test.Missile pressure nephogram was presented,and analysis for rudders and body pressure distribution was included.The surface-pressure and side-force of parts of CCM under rolling control were analyzed.The result shows that the side-force of CCM under rolling control is caused by body unsymmetric airloads due to the downwash of canard rudder.The side-force and yaw-moment increase while the roll-angle increases negatively.