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基于非结构网格空间推进的高超声速飞行器背脊线优化

高昌 张小庆 贺元元 吴颖川 乐嘉陵

高昌, 张小庆, 贺元元, 吴颖川, 乐嘉陵. 基于非结构网格空间推进的高超声速飞行器背脊线优化[J]. 航空动力学报, 2019, 34(8): 1731-1740. doi: 10.13224/j.cnki.jasp.2019.08.012
引用本文: 高昌, 张小庆, 贺元元, 吴颖川, 乐嘉陵. 基于非结构网格空间推进的高超声速飞行器背脊线优化[J]. 航空动力学报, 2019, 34(8): 1731-1740. doi: 10.13224/j.cnki.jasp.2019.08.012
Unstructured grid space marching based design optimization of hypersonic vehicle back sketch lines[J]. Journal of Aerospace Power, 2019, 34(8): 1731-1740. doi: 10.13224/j.cnki.jasp.2019.08.012
Citation: Unstructured grid space marching based design optimization of hypersonic vehicle back sketch lines[J]. Journal of Aerospace Power, 2019, 34(8): 1731-1740. doi: 10.13224/j.cnki.jasp.2019.08.012

基于非结构网格空间推进的高超声速飞行器背脊线优化

doi: 10.13224/j.cnki.jasp.2019.08.012

Unstructured grid space marching based design optimization of hypersonic vehicle back sketch lines

  • 摘要: 针对高超声速飞行器背脊线优化进行了研究。结合自由曲面变形(FFD)方法和Hicks-Henne型函数建立背脊线参数化模型,保证了飞行器背部曲面光滑连续。为减少计算耗时,采用非结构网格空间推进方法求解高超声速无黏流场,通过钝锥算例对该方法计算效率和精度进行了参数分析,并对飞行器流场计算进行了验证,对比表明表明:非结构网格空间推进算法计算效率提高4.5倍以上,计算结果与常规时间迭代法符合较好。采用优化拉丁超立方抽样建立响应面模型,分析了各设计变量对目标函数的影响。采用非支配排序NSGA-Ⅱ(non-dominated sorting genetic algorithm-Ⅱ)算法以阻力系数和升阻比为目标对背脊线优化,约束飞行器体积变化不超过20%。结果表明,飞行器阻力系数和升阻比呈负相关,优化后阻力系数降低7.1%,升阻比提高16.9%。

     

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出版历程
  • 收稿日期:  2019-01-16
  • 刊出日期:  2019-08-28

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