导弹头部融合旋成体构型实现及气动优化  

Realization and aerodynamic optimization of flat-nosed hypersonic missile integrated with an axis-symmetrical front-tip

作　　者：唐啸 莫然 陈俊杰 范晓樯[1] TANG Xiao;MO Ran;CHEN Junjie;FAN Xiaoqiang(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《航空动力学报》2020年第7期1383-1391,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(11572347,11872071)。

摘　　要：为解决扁平导弹头部空间利用率低,天线罩加工困难且电气性能差的问题,采用形状函数变换技术(CST)造型法在其前端融入旋成体,并提出"旋成体埋头角"以实现融合区域光滑过渡。CFD计算得到旋成体弹头、扁平弹头、和"旋成体埋头角"为0°~5°时融合弹头的气动性能,结果表明:旋成体弹头、"无埋头"融合弹头和"有埋头"融合弹头的最大升阻比分别为扁平弹头的81.58%、86.16%和89.46%。以最大升力系数和最大升阻比为目标对"旋成体埋头角"为2°和3°的融合弹头进行优化计算,在Pareto前缘中,随着旋成体末端半径从150 mm增大至210 mm,两构型的最大升力系数分别上升5.99%和4.16%,最大升阻比分别下降19.96%和18.39%。此外,当旋成体末端半径小于165 mm时,上述2°构型的最大升阻较大(峰值可达扁平弹头的97.79%),反之上述3°构型构型的最大升阻较大。In the current application of flat nosecones in the missiles,the disadvantages such as low front space use efficiency,difficulties in the manufacturing,and poor transmission performance bring about a great demand for the integration of a class function/shape function transformation technique(CST)based flat nosecone to an axis-symmetrical front-tip with a‘front-tip-down angle’.The‘front-tip-down angle’was used to realize the smooth transition of the merging region.The computational fluid dynamics calculation results were obtained for the axis-symmetrical nosecone,the flat nosecone,and the integrated nosecone at‘front-tip-down angle’varying from 0 to 5 degree.The results showed that the maximum lift-drag ratios of the axis-symmetrical nosecones,the integrated nosecones at zero angle of front-tip-down,and the ones at non-zero angle of front-tip-down were 81.58%,86.16%,and 89.46%,respectively,to that of the flat nosecone.An optimization was processed in order to obtain the maximum lift-drag ratio and lift coefficient in the integrated nosecones at 2 and 3 degrees of"front-tip-down angle".In the 2 and 3 degrees of"front-tip-down angle"cases,lift-coefficient pareto-optimal fronts increased by 5.99%and 4.16%,lift-drag ratio pareto-optimal fronts decreased by 19.96%and 18.39%,respectively,while the terminal radius of the axis-symmetrical front-tip increased from 150 mm to 210 mm.Furthermore,when the terminal radius was less than 165 mm,the lift-drag ratio in the configuration with 2 degrees of"front-tip-down angle"was larger(peak value could reach up to 97.79%to that of flat nosecone).While the terminal radius was larger than 165 mm,the lift-drag ratio in the other one was larger.

关 键 词：导弹头部 高超声速 构型融合 参数化设计 气动优化 

分 类 号：V222[航空宇航科学与技术—飞行器设计]