鸭式导弹舵面后缘后掠角对滚转影响数值研究  

Numerical research of rolling characteristics on canard missiles by fin trailing edge sweepback angle

作　　者：敬代勇[1,2] 李剑[2] 

机构地区：[1]上海交通大学航空航天学院,上海200030 [2]中国空空导弹研究院总体部,河南洛阳471009

出　　处：《飞行力学》2011年第4期77-79,共3页Flight Dynamics

摘　　要：鸭式布局导弹的滚转特性是抑制其性能提升的重要约束。采用数值模拟方法对鸭式导弹滚转特性进行研究,分析舵面后缘后掠角对其影响。以三维可压缩雷诺平均N-S方程为主控方程来模拟流场特性,湍流模型采用SST的k-ω二方程,基于气动特性和流场特性分析研究了固定尾翼鸭式气动布局导弹的横滚特性。仿真结果表明,鸭式布局导弹的舵面后缘后掠角对滚转特性有重要的影响。The capability of a canard-controlled missile is mainly restricted in rolling characteristics. In this thesis, to investigate the rolling characteristics of a canard-controlled missile by numerical simulation, and to analyze the influence on the fin trailing edge sweepback angle of it. Three dimensional compressible Reynolds averaged Navier-Strokes numerical simulations were carried out to predict the flowfield characteristics. The SST k-to two-equation turbulence model was used for the numerical simulations here. To reseach rolling characteristics of a canard-controlled missile with fixed-tail is based on the aerodynamics characteristics and the flow field. The simulation results show the fin trailing edge sweepback angle on a canard-controlled missile has an important influence on rolling characteristics.

关 键 词：鸭式导弹 后掠角 数值仿真 滚转特性 气动特性 

分 类 号：TJ760.11[兵器科学与技术—武器系统与运用工程]