大长径比卷弧尾翼火箭弹气动特性数值研究  

Numerical investigation of aerodynamic characteristics of large fineness ratio wrap-around fins rocket

作　　者：谢志敏[1] 杨树兴[1] 陈伟[1] 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081

出　　处：《固体火箭技术》2009年第6期596-599,共4页Journal of Solid Rocket Technology

基　　金：国防基础科研项目基金(B222006060)

摘　　要：采用CFD方法对大长径比卷弧尾翼火箭弹流场进行了模拟,对比风洞实验数据,验证了数值方法可靠性。对比单个弹体和翼身组合体的气动特性,得到了卷弧尾翼对全弹气动特性的影响。利用正交设计方法,建立以卷弧尾翼6个几何参数为因素的正交数值实验表,得到卷弧尾翼几何参数对各个气动系数的影响。分析零安装角卷弧尾翼在超音速下零度攻角时流场,指出翼面压力分布差异,得到自诱导滚转力矩产生机理,同时分别指出超音速时其随攻角、曲率半径、展弦比和马赫数的变化趋势。The flowfield of a wrap-around fins rocket was simulated by means of the CFD numerical method. Reliability of the CFD method was certified by the good agreement between the wind tunnel test results and numerical results. By comparing the aerodynamic characteristics of a single body with those of a combination of body and the fins, the effect of wrap-around fins on the rocket was obtained. With orthogonal design method, the orthogonal tables of numerical experiment were established to get the effects of six geometrical parameters of the wrap-around fin on each aerodynamic coefficient. Pressure distribution of flowfield was analyzed to illu- minate the formation reasons of induced rolling moment. Meanwhile, the changing trend of induced rolling moment with attack angle, curvature radius, span to chord ratio and mach number was pointed out individually.

关 键 词：大长径比卷弧尾翼火箭弹 数值模拟 正交设计 自诱导滚转力矩 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]