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唐啸,莫然,陈俊杰.导弹头部融合旋成体构型实现及气动优化[J].航空动力学报,2020,(7):1383~1391
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
投稿时间:2019-12-17  
DOI:10.13224/j.cnki.jasp.2020.07.006
中文关键词:  导弹头部  高超声速  构型融合  参数化设计  气动优化
英文关键词:missiles nosecone  hypersonic  surface fusion  parameterization  ,aerodynamic optimization
基金项目:国家自然科学基金(11572347,11872071)
作者单位
唐啸 College of Aerospace Science and Engineering,,National University of Defense Technology,Changsha 410073,China 
莫然 College of Aerospace Science and Engineering,,National University of Defense Technology,Changsha 410073,China 
陈俊杰 College of Aerospace Science and Engineering,,National University of Defense Technology,Changsha 410073,China 
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中文摘要:
      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。
英文摘要:
      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.
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