导弹头部融合旋成体构型实现及气动优化

唐啸; 莫然; 陈俊杰

doi:10.13224/j.cnki.jasp.2020.07.006

导弹头部融合旋成体构型实现及气动优化

doi: 10.13224/j.cnki.jasp.2020.07.006

基金项目: 国家自然科学基金（11572347,11872071)

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- 被引次数: 0
出版历程
- 收稿日期: 2019-12-17
- 刊出日期: 2020-07-28

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

College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China

摘要

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。
- 导弹头部 /
- 高超声速 /
- 构型融合 /
- 参数化设计 /
- 气动优化
Abstract: 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.
- missiles nosecone /
- hypersonic /
- surface fusion /
- parameterization /
- ,aerodynamic optimization

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