北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (12): 2587-2595.doi: 10.13700/j.bh.1001-5965.2015.0847

• 论文 • 上一篇    下一篇

面向总体性能的高速飞行器布局优化

邓帆1,2, 焦子涵1, 付秋军1, 陈林1, 田书玲3, 张栋4   

  1. 1. 中国运载火箭技术研究院 空间物理重点实验室, 北京 100076;
    2. 谢菲尔德大学 机械工程学院, 谢菲尔德 S1;
    3. 南京航空航天大学 航空宇航学院, 南京 210016;
    4. 西北工业大学 航天飞行动力学技术重点实验室, 西安 710072
  • 收稿日期:2015-12-25 出版日期:2016-12-20 发布日期:2016-04-11
  • 通讯作者: 邓帆,Tel.:010-68199538,E-mail:dengfan8245@sina.cn E-mail:dengfan8245@sina.cn
  • 作者简介:邓帆,男,博士,高级工程师。主要研究方向:飞行器总体设计。Tel.:010-68199538,E-mail:dengfan8245@sina.cn;焦子涵,男,硕士,工程师。主要研究方向:飞行器气动布局设计。Tel.:010-88531845,E-mail:zihan325@126.com;付秋军,男,博士,研究员。主要研究方向:飞行器总体设计。Tel.:010-68381167,E-mail:fuqiujun@163.com;陈林,男,博士,高级工程师。主要研究方向:空气动力学、飞行器设计。Tel.:010-88531845,E-mail:chenlincfd@gmail.com;田书玲,男,博士,副教授。主要研究方向:计算流体力学、飞行器优化设计。Tel.:025-84892735,E-mail:shulingtian@nuaa.edu.cn;张栋,男,博士,讲师。主要研究方向:飞行器动力学建模与控制。Tel.:029-88492788,E-mail:zhangdong@nwpu.edu.cn

Hypersonic vehicle shape optimal design based on overall performance

DENG Fan1,2, JIAO Zihan1, FU Qiujun1, CHEN Lin1, TIAN Shuling3, ZHANG Dong4   

  1. 1. Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China;
    2. Department of Mechanical Engineering, University of Sheffield, Sheffield S1;
    3. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    4. National Key Laboratory of Aerospace Flight Dynamics, Northwestern Polytechnical University, Xi'an 710072, China
  • Received:2015-12-25 Online:2016-12-20 Published:2016-04-11

摘要: 飞行器气动布局的选型和优化技术在总体设计中处于关键地位,在临近空间飞行的飞行器对升阻比和操控性能都提出了更高的要求。翼身组合的升力体外形由于兼顾内部装填以及升阻特性成为了目前高速飞行器主要的设计方向。以一类具有普适性的面对称升力体外形为基础,采用相关性分析手段提取出飞行器的关键几何参数,挖掘出几何参数对所关心的总体性能指标的影响度大小,并建立起基于CFD方法的气动布局优化平台,以总体性能指标为约束,优化出高升阻比外形,通过风洞试验验证了优化设计方法的有效性,为高速飞行器的气动布局工程化设计提供了有效的技术手段。

关键词: 高速飞行器, 优化设计, 总体性能, 风洞试验, 数值计算

Abstract: Aerodynamic configuration design and optimization are vital to overall design of aircraft. Higher requirements of lift-drag ratio and control performance are put forward for near space vehicles. The lifting-body shape of the wing-body combination has become the main design direction of the hypersonic vehicle due to its internal loading and lift-drag characteristics. According to a class of universal symmetry lifting-body configuration, the key geometry parameters of vehicle were extracted using interrelation analysis method. The effect of geometry parameters on concerned overall performance was dug out. Aerodynamic shape optimization platform was established based on CFD method. With several key overall performance constraints, high lift-drag ratio shape was designed and optimized. The effectiveness of optimal design has been verified by wind tunnel test, which will provide an effective technical means for rapid engineering aerodynamic shape design of hypersonic vehicle.

Key words: hypersonic vehicle, optimal design, overall performance, wind tunnel test, numerical calculation

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