高超声速“准乘波体”构型优化设计方法
Design method of a new hypersonic waverider configuration
查看参考文献37篇
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文摘
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乘波体构型以其非常高的气动效率,在高超声速飞行器设计中有着广阔的应用前景.基于各种基准流场的乘波体生成方法的发展,使得在飞行器设计过程中可以根据不同需求选择不同类型的乘波体构型.但是,乘波体构型一般难以直接满足容积率、配平、稳定性等基本的飞行器设计工程需求.针对这一情况,本文结合遗传算法和考虑强黏性干扰效应影响的气动力工程算法,提出了一种“准乘波体”构型优化设计方法.所谓“准乘波体”,是指在外形生成过程中保留了乘波体的前缘线,然后对于不同的纵向截面,以相同的型线方程从前缘点出发生成下表面.型线方程以一组幂函数为基函数,通过改变基函数系数即可以不同工程需求为约束条件,借助遗传算法优化获得最优构型.分别获得了无约束条件、以容积率为约束和以在设计点自配平且纵向静稳定为约束的最优“准乘波体”构型.通过CFD数值模拟对相应构型的气动力特性进行了评估,结果表明: “准乘波体”构型流场能够保持较好的“乘波”特性且下表面压力分布较为均匀,可以获得比原乘波体更高的升阻比;通过引入不同约束条件获得的最优“准乘波体”构型,可以在一定范围内灵活地改变容积率,并且在优化过程中可以实现在设计点处满足配平和纵向静稳定要求. |
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其他语种文摘
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The waverider configuration has a wide application prospect in the design of hypersonic vehicles due to its excellent aerodynamic efficiency. Various kinds of waveriders have been developed based on different basic flowfield, which can be chosen according to different design requirements. However, it's generally difficult for the waverider to directly satisfy the engineering requirements of volume efficiency, trim, stability, etc. To overcome these drawbacks, the paper proposes a new design method of hypersonic waverider configuration. In the generation process, the leading edge of the original waverider is kept unchanged. Then at different longitudinal cross section, the profile of the lower surface is determined by the same curve equation, started from the point at the leading edge and cut off at the base plane. The profile function is determined by the sum of a series of power law functions, whose coefficients can be changed according to different design requirements. Different waveriders are obtained according to different constraints. Results show that for this kind of configurations, good shock attachment near the leading edge can be achieved and the pressure distribution on the lower surface is uniform. What's more, the maximum lift-to-drag ratio is even higher than that of the original waverider. Different waveriders with excellent aerodynamic efficiency can also be generated by different constraints of volume efficiency and stability. |
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来源
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中国科学. 技术科学
,2019,49(3):255-267 【核心库】
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DOI
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10.1360/n092017-00373
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关键词
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高超声速
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乘波体
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黏性干扰
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稳定性
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地址
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1.
西北工业大学, 翼型、叶栅空气动力学国防科技重点实验室, 西安, 710072
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中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1674-7259 |
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学科
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航空;航天(宇宙航行) |
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基金
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中国科学院战略性先导科技专项
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国家自然科学基金
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文献收藏号
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CSCD:6465393
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