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

作　　者：敬代勇[1] 李剑[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空计算技术》2013年第1期18-20,共3页Aeronautical Computing Technique

摘　　要：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.

关 键 词：下洗 鸭式布局导弹 数值模拟 滚转力矩 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]