为研究不同气动布局导弹滚转特性。采用三维雷诺平均N-S方程组,对正常式和鸭式布局导弹在非对称姿态流场进行数值模拟。研究了这两种布局形式的滚转力矩变化规律、翼剖面压力分布差异和舵翼面流动相互干扰等。经数值模拟表明,造成这两种布局在非对称姿态下舵面偏转进行滚转控制时不同布局导弹滚转特性差异的原因在于:舵面偏转后在翼面产生非对称洗流,导致翼面诱导滚转力矩不同所致。

To research rolling characteristics of missiles of different configurations, three dimensional compressible Reynolds averaged Navier-Strokes numerical simulations were solved. The flow field of canard control missile and tailcontrol missile at asymmetric attitude was calculated. The two configurations' characteristics including the change of rolling moment, different pressure of section plane on wing and influence between fin and wing were To investigated. The simulation results show that when fin turns to control roll at asymmetric attitude, the downwash brings different influence on the two configurations.