首页|高超声速变体飞行器宽速域气动特性研究

高超声速变体飞行器宽速域气动特性研究

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  • 国家科技期刊平台
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宽速域飞行是高超声速飞行器的重要设计目标和发展方向。然而，复杂的环境变化给固定外形飞行器在不同飞行条件下的气动布局设计带来了矛盾。高超声速变体飞行器可以通过呈现不同的构型来适应各种飞行条件并满足性能要求。本文通过数值模拟的方法来研究折叠翼高超声速飞行器的气动性能。研究重点是在不同飞行高度和马赫数下，探究不同机翼折叠状态对应气动布局的升阻比、纵向静稳定性和航向静稳定性。比较了不同机翼折叠角度(0°、45°、90°)对气动性能的影响。结果表明，在所研究的整个速度范围内(Ma=0～5)，较小的机翼折叠角会导致较高的升力系数、阻力系数和升阻比。机翼折叠角为0°时，升阻比最高。在纵向稳定性方面，折叠角度较小的布局具有更好的纵向稳定性。随着马赫数的增加，不同折叠角度之间的纵向稳定性差异最初减小，然后增大。静态稳定裕度从1∶0。95∶0。84变为1∶0。98∶0。88，后变为1∶0。89∶0。79。此外，具有较大机翼折叠角的构型表现出更好的航向稳定性。所有3种机翼折叠布局状态在低速飞行阶段都是航向静稳定的。随着马赫数的增加，0°和45°折叠角逐渐变得航向静不稳定。
Study on Aerodynamic Performance of Morphing Hypersonic Vehicle in Wide-Speed Range
Wide-speed range flight is a critical design objective and development direction for hypersonic vehicles.However,the complex environmental changes pose design conflicts for fixed-configuration vehicles under different flight conditions.Hypersonic morphing vehicles can adapt to various flight conditions and meet performance requirements by presenting different configurations.This paper introduces numerical simulations to investigate the aerodynamic characteristics of a foldable-wing vehicle,and focuses on the lift-to-drag ratio,longitudinal static stability,and directional static stability of the aerodynamic configuration in different wing folding states at various flight altitudes and Mach numbers.The impact of varying wing folding angles(0°,45°,90°)on the aerodynamic performance are compared.The results indicate that across the entire range of speeds studied(Ma=0-5),the smaller wing folding angles result in the higher lift coefficients,drag coefficients,and lift-to-drag ratios.The wing folding angle of 0° exhibits the highest lift-to-drag ratio.In terms of longitudinal stability,the configuration with a smaller folding angle has better longitudinal stability.As the Mach number increases,the differences in longitudinal stability between different folding angles initially decrease and then increase.The static stability margins change from 1∶0.95∶0.84 to 1∶0.98∶0.88,then to 1∶0.89∶0.79.In addition,configurations with larger wing folding angles exhibit better directional stability.All three wing folding configurations are directionally stable during the low-speed flight phase.As the Mach number increases,the 0° and 45° folding angles gradually become directionally unstable.

wide-speed rangemorphing vehiclefolding wingaerodynamic performancehypersonic vehicle

罗世彬、岳航、刘俊、宋佳文、曹文斌

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中南大学航天技术研究院,长沙 410083,中国

宽速域 变体飞行器 折叠翼:气动性能 高超声速飞行器

foundation of National Key Laboratory of Science and Technology on Aerodynamic Design and ResearchKey R&D Projects of Hunan ProvinceKey R&D Projects of Hunan Province

6142201210201142021GK20112023GK2022

2024

10.16356/j.1005?1120.2024.02.005

南京航空航天大学学报(英文版)
南京航空航天大学

南京航空航天大学学报(英文版)

CSTPCD
影响因子：0.279
ISSN：1005-1120
年,卷(期)：2024.41(2)
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