鸭式导弹尾翼滚转特性数值研究

Numerical Research of Rolling Characteristics on Wing of Canard-controlled Missile

为了分析鸭式布局导弹翼面滚转特性,采用求解三维可压缩雷诺平均N-S方程组的方法,分析研究表明,鸭式布局导弹尾翼诱导滚转力矩主要来源于翼面。当舵面进行差动偏转进行滚转控制时,不对称下洗流动会上在翼面附加滚转力矩,这种影响随攻角变化。

To study roiling characteristics of canard- controlled missile, the three dimensional compressible Reynolds averaged Navier- Stokes equations were solved. The results indicate the mainly additional rolling moment from wing. When canard- controlled missile control rolling by turning fin, the asymmetric down- wash will lead to additional rolling moment on wing. The influence change with angle of attack.