卷弧尾翼火箭弹侧向气动特性数值计算  

Numerical investigation of side aerodynamic characteristics of 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：《空气动力学学报》2010年第1期66-69,共4页Acta Aerodynamica Sinica

基　　金：国防基础科研项目基金(B222006060)

摘　　要：采用数值模拟的方法,以三维Navier-Stokes方程为控制方程,模拟卷弧尾翼火箭弹流场,得到的气动特性结果与实验数据基本吻合。通过对翼片的压力分析,说明了侧向力产生的机理。分析弹体各部分产生的侧向力,指出了卷弧尾翼对侧向力产生的主要作用。同时对卷弧尾翼火箭弹3组不同展弦比,3组不同翼曲率半径及5个滚转角时的绕流流场进行数值模拟,分析了侧向力系数随这些因素的变化趋势,为减小侧向力和增加火箭弹稳定性提供一定的依据。With the three-dimensional Navier-Stokes equations used as the control equations,the flowfield of a wrap-around fins rocket is simulated using the numerical simulation method.Computational results are in good agreement with the wind tunnel test results.Through pressure analysis of the fins,the formation reason of the side force is illuminated.And it is also found that the fins are the main parts to produce the side force.The flowfields of wrap-around fins rockets with three kinds of span-to-chord ratios,three kinds of curvature radii and five kinds of rolling angles are simulated to get the changing trend of the side force.Thus,the results are useful for reducing the side force and increasing the stability of rockets.

关 键 词：卷弧尾翼 数值模拟 侧向力 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]