近空间高超声速飞行器气动特性研究的若干关键问题

叶友达; 张涵信; 蒋勤学; 张现峰

doi:10.6052/0459-1879-18-247

近空间高超声速飞行器气动特性研究的若干关键问题

doi: 10.6052/0459-1879-18-247

中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳 621000
国家计算流体力学实验室, 北京 100086

基金项目: 1) 国家自然科学基金资助项目(90205013,90505016,91016001,91216203).

详细信息

作者简介:
null

2) 叶友达,研究员,主要研究方向：计算空气动力学. E-mail：youdaye@sina.com

中图分类号: V211.3;
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出版历程
- 收稿日期: 2018-07-27
- 刊出日期: 2018-11-18

SOME KEY PROBLEMS IN THE STUDY OF AERODYNAMIC CHARACTERISTICS OF NEAR-SPACE HYPERSONIC VEHICLES

State Key Laboratory of Aerodynamics,China Aerodynamic Research and Development Center, Mianyang 621000, China
National Laboratory for Computational Fluid Dynamics,Beijing 100086, China

摘要

摘要: 在30$\sim$70km空域机动飞行的高超声速飞行器的优点是可以耦合利用所处空域的空气产生的升力和高速飞行的离心力进行远距离机动滑翔飞行,具有重要的实用价值.尽管过去数十年在高超声速流动研究方面取得显著进展,但在设计研究近空间远程滑翔的高超声速飞行器方面仍然存在许多挑战,特别是对特定飞行条件下的流动机理了解不清楚.本文介绍了作者研究团队在开展近空间高超声速飞行器有关的关键气动问题方面的研究进展,主要包括：建立了近空间高超声速飞行的流动模型,发展了系统的相关计算空气动力学方法,针对高空高速飞行条件下稀薄气体效应和真实气体效应的耦合作用影响研究了合适的滑移边界条件,考虑了不同组分存在条件下的温度、速度和压力的滑移效应影响;提出了飞行器气动外形的动态优化方法,获得了可工程实用化的高升阻比飞行器气动外形;建立了高速飞行器动稳定性理论,在实现高超声速飞行器动态稳定飞行方面取得重大进展;最后讨论了高超声速飞行器设计中进一步需要关注的若干关键技术和科学问题、可能解决的途径及其所涉及的学科发展方向.
- 近空间 /
- 气动模型 /
- 优化设计 /
- 动稳定性 /
- 高超声速飞行器
Abstract: The advantages of the hypersonic vehicle in maneuverable flight in 30$\sim$70km airspace are that it can carry out long-distance maneuverable gliding flight by coupling the lift generated by the air in the airspace and the centrifugal force of high-speed flight, which has important practical value. Although significant progress has been made in the past decades in the study of hypersonic flows, there are still many challenges in the design and research of hypersonic vehicles for near-space long-range gliding, especially the unclear understanding of the flow mechanism under specific flight conditions. This paper introduces the progress of the author's research team in the development of key aerodynamic problems related to hypersonic vehicles in near space, mainly including: the flow model of hypersonic flight in near space is established, and the relative computational aerodynamics method of the system is developed, a suitable sliding boundary condition is studied for the coupling effect of rarefied gas effect and real gas effect under high altitude and high speed flight conditions, the slippage effect including velocity slip condition, temperature slip condition and pressure slip condition in high-temperature chemically reacting flows are considered. A dynamic optimization method for the aerodynamic shape of the aircraft was proposed, and the aerodynamic shape of the aircraft with high lift-drag ratio, which can be used in engineering, was obtained. The dynamic stability theory of high speed aircraft has been established, and great progress has been made in realizing the dynamic stability of hypersonic vehicles. In the end, some key technical and scientific problems that should be paid more attention to in the design of hypersonic vehicles are discussed, and the possible solutions to these problems are discussed.
- near space /
- flow model /
- optimization /
- dynamic stability theory /
- hypersonic vehicles

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