| 引用本文: | 向锦武,张雪娇,赵仕伟,程云,张志飞,李道春.大展弦比复合材料机翼研究进展[J].哈尔滨工业大学学报,2017,49(10):1.DOI:10.11918/j.issn.0367-6234.201705036 |
| XIANG Jinwu,ZHANG Xuejiao,ZHAO Shiwei,CHENG Yun,ZHANG Zhifei,LI Daochun.Recent advance in high-aspect-ratio composite wing[J].Journal of Harbin Institute of Technology,2017,49(10):1.DOI:10.11918/j.issn.0367-6234.201705036 |
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| 摘要: |
| 长航时无人机普遍采用轻质、高比强度复合材料结构大展弦比机翼，该类机翼在飞行过程中表现出显著的几何非线性和气动非线性，进而导致机翼的气动弹性非线性.大展弦比复合材料机翼的设计分析方法与传统机翼有很大不同.为研究大展弦比复合材料机翼的进展，并预测其未来可能的发展方向，对现有大展弦比复合材料机翼设计、分析、试验方法进行分析总结.首先，对大展弦比复合材料机翼结构设计方法、结构分析方法进行了介绍；然后，介绍了两类用于大展弦比机翼的气动力分析方法：基于片条理论和二元非定常气动力相结合的气动力分析方法以及考虑展向流动效应的三维气动力分析方法，重点总结了复合材料大展弦比机翼静气动弹性、动气动弹性分析方法以及主动控制技术在大展弦比机翼中的应用，并分析了大展弦比复合材料机翼气动弹性剪裁最新进展；最后，综述了大展弦比复合材料机翼试验研究进展.基于文献分析可知，现有大展弦比复合材料机翼的结构模型多采用等效梁板模型，气动模型多采用片条理论与考虑动失速的二元非定常气动力相结合的模型.气动降阶模型与结构模型相耦合进行相关研究，以及大展弦比复合材料机翼的飞行试验，均是大展弦比复合材料机翼未来可能的研究发展方向.
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| 关键词: 大展弦比 几何非线性 气动非线性 气动弹性 主动控制 |
| DOI：10.11918/j.issn.0367-6234.201705036 |
| 分类号:V271.4 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(4,3) |
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| Recent advance in high-aspect-ratio composite wing |
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XIANG Jinwu,ZHANG Xuejiao,ZHAO Shiwei,CHENG Yun,ZHANG Zhifei,LI Daochun
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(School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China)
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| Abstract: |
| The high-aspect-ratio composite wing is generally used in long-endurance Unmanned Aerial Vehicle (UAV), which uses lightweight and high-specific-strength composite structure. This type of wing has significant geometric nonlinearity and aerodynamic nonlinearity during the flight, which further leads to the aeroelastic nonlinearity of the wing. There is a huge difference for design analysis method between the high-aspect-ratio composite wing and the conventional wing. In order to summarize the research status and forecast the future research direction of the high-aspect-ratio composite wing, this paper analyzes and summarizes the design, analysis and experiment methods of the existing high-aspect-ratio composite wing. The aeroelastic characteristics of wing would be affected by the geometric and aerodynamic nonlinearities. The structural design and structural analysis methods of high-aspect-ratio composite wing are introduced. Two kinds of aerodynamic analysis methods are introduced: the aerodynamic analysis method based on the strip theory and binary unsteady aerodynamic method and three dimensional aerodynamic analysis method considering spanwise flow effect. Static aeroelasticity method, dynamic aeroelastic analysis method and active control technology applied in the high-aspect-ratio wing are introduced. The recent advance in aeroelastic tailoring of high-aspect-ratio composite wing is analyzed. Finally, the experimental research progress of high-aspect-ratio composite wing is introduced. Based on the literature analysis, it can be seen that the structural model of the existing high-aspect-ratio composite wing adopts the equivalent beam plate model, while the aerodynamic model adopts the combination of the strip theory and the binary unsteady aerodynamics considering the dynamic stall. The flight test, as well as the research based on the coupling of aerodynamic reduced-order model and the structural model of the high-aspect-ratio composite wing may be the research and development directions of the high-aspect-ratio composite wing in the future.
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| Key words: high-aspect-ratio geometric nonlinearity aerodynamic nonlinearity aeroelastic active control |
