飞行器机翼变形驱动机构研究

郭广宇; 陈青山; 高宏

doi:10.13433/j.cnki.1003-8728.20220250

飞行器机翼变形驱动机构研究

doi: 10.13433/j.cnki.1003-8728.20220250

1.
北京信息科技大学仪器科学与光电工程学院, 北京　100192

详细信息

作者简介:
郭广宇，硕士， 827527627@qq.com

通讯作者:
陈青山，教授，硕士生导师，chenqqss@sina.com

中图分类号: TH13; V224
计量
- 文章访问数: 27
- HTML全文浏览量: 13
- PDF下载量: 0
- 被引次数: 0
出版历程
- 收稿日期: 2021-12-31
- 刊出日期: 2024-03-25

Study on Deformation Driving Mechanism of Aircraft Wing

1.
School of Instrument Science and Opto-Electronics Engineering, Beijing Information Science & Technology University, Beijing 100192, China

摘要

摘要: 为了优化飞行器气动特性，提升飞行效率，研究用于连续变弯度机翼的多级连杆驱动机构。采用ANSYS流体分析功能研究最大弯曲角度下变弯度机翼的气动特性；采用ANSYS静力学分析功能研究极限载荷条件下驱动机构的结构强度；并通过仿真分析与样机测试对驱动机构的运动情况进行研究。研究结果表明：变形机翼获得升力系数为1.4，所受最大气流动压1 078 Pa，小于下表面屈服气流动压4 916 Pa；驱动机构所受最大应力37.3 MPa，小于结构屈服强度55.2 MPa；机翼弯曲变形角度可达±25°，满足了飞行器对改善飞行特性方面的需要。
- 驱动机构 /
- 多级连杆 /
- 变弯度机翼 /
- 结构强度 /
- 样机测试
Abstract: For the purpose of optimizing the aerodynamic characteristics and improving the flight efficiency of aircraft, a variable camber wing with multi-stage linkage driving mechanism is studied. The aerodynamic characteristics of the wing at the maximum deformation angle are studied by the fluid analysis function of ANSYS. The structural strength of the driving mechanism under the limit load condition is studied by the static analysis function of ANSYS. The motion of the driving mechanism is studied through simulation analysis and prototype test. The results indicate that the maximum lift coefficient of the deformed wing is 1.4, and the maximum aerodynamic pressure is 1 078 Pa, which is less than the yield aerodynamic pressure of the lower surface of 4 916 Pa. The maximum stress of the driving mechanism is 37.3 MPa, which is less than the structural yield strength of 55.2 MPa. The wing deformation angle is greater than ±25°, which meets the requirement of improving aerodynamic characteristics of aircraft.
- driving mechanism /
- multi-stage linkage /
- variable camber wing /
- structural strength /
- prototype test

HTML全文

图 1 变弯度机翼构成

Figure 1. Composition of variable camber wing

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图 2 机翼驱动机构

Figure 2. Driving mechanisms of wing

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图 3 驱动机构原理

Figure 3. Principle of driving mechanisms

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图 4 驱动机构

Figure 4. Driving mechanisms

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图 5 驱动机构整体布局

Figure 5. Overall layout of a driving mechanism

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图 6 变弯度机翼压力场分布

Figure 6. Pressure field distribution of variable camber wing

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图 7 驱动机构应力分布

Figure 7. Stress distribution of a driving mechanism

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图 8 输出轴转动角度

Figure 8. Rotation angle of output shaft

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图 9 实验样机模型

Figure 9. Experimental prototype model

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图 10 变弯度机翼控制系统示意

Figure 10. Schematic diagram of variable camber wing control system

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图 11 变弯度机翼偏转角度

Figure 11. Deformation angle of variable camber wing

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表 1 变形机翼蒙皮常见材料与结构性能参数

Table 1. Common materials and structural performance parameters of deformed wing skin

参数	拉伸强度/MPa	形变量/%
硅橡胶材料	3.5 ~ 14.7	>100
形状记忆环氧聚合物	40	50 ~ 100
波纹结构	6.3	2 ~ 5
聚合碳纤维蜂窝结构	1800	2 ~ 10

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表 2 机翼极限载荷条件及几何参数

Table 2. Limit load conditions and geometric parameters of wing

机翼特征	指标参数
机翼全长/cm	248
变形区域长度/cm	168
上表面压力系数	0.295
下表面压力系数	0.488
上表面气流动压/Pa	2855
下表面气流动压/Pa	4916
上表面压力/N	1258
下表面压力/N	2540

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参考文献(20)

[1]	白鹏, 陈钱, 徐国武, 等. 智能可变形飞行器关键技术发展现状及展望[J]. 空气动力学学报, 2019, 37(3): 426-443. BAI P, CHEN Q, XU G W, et al. Development status of key technologies and expectation about smart morphing aircraft[J]. Acta Aerodynamica Sinica, 2019, 37(3): 426-443. (in Chinese)
[2]	BARBARINO S, BILGEN O, AJAJ R M, et al. A review of morphing aircraft[J]. Journal of Intelligent Material Systems and Structures, 2011, 22(9): 823-877. doi: 10.1177/1045389X11414084
[3]	NIU W, ZHANG Y F, CHEN H X, et al. Numerical study of a supercritical airfoil/wing with variable-camber technology[J]. Chinese Journal of Aeronautics, 2020, 33(7): 1850-1866. doi: 10.1016/j.cja.2020.01.008
[4]	ZHAO A M, ZOU H, JIN H C, et al. Structural design and verification of an innovative whole adaptive variable camber wing[J]. Aerospace Science and Technology, 2019, 89: 11-18. doi: 10.1016/j.ast.2019.02.032
[5]	许云涛. 智能变形飞行器发展及关键技术研究[J]. 战术导弹技术, 2017(2): 26-33. doi: 10.16358/j.issn.1009-1300.2017.02.05 XU Y T. Research on the development and key technology of smart morphing aircraft[J]. Tactical Missile Technology, 2017(2): 26-33. (in Chinese) doi: 10.16358/j.issn.1009-1300.2017.02.05
[6]	景藜, 张永红, 葛文杰, 等. 基于多目标载荷路径法的形状变形机翼后缘柔性机构拓扑优化[J]. 机械科学与技术, 2010, 29(10): 1420-1425. doi: 10.13433/j.cnki.1003-8728.2010.10.023 JING L, ZHANG Y H, GE W J, et al. Topology optimization for shape morphing compliant trailing edge using multi-objective load path approach[J]. Mechanical Science and Technology for Aerospace Engineering, 2010, 29(10): 1420-1425. (in Chinese) doi: 10.13433/j.cnki.1003-8728.2010.10.023
[7]	GUO L Q, TAO J, WANG C, et al. Fuel efficiency optimization of high-aspect-ratio aircraft via variable camber technology considering aeroelasticity[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2021, 235(7): 782-793.
[8]	李小飞, 张梦杰, 王文娟, 等. 变弯度机翼技术发展研究[J]. 航空科学技术, 2020, 31(2): 12-24. doi: 10.19452/j.issn1007-5453.2020.02.002 LI X F, ZHANG M J, WANG W J, et al. Research on variable camber wing technology development[J]. Aeronautical Science & Technology, 2020, 31(2): 12-24. (in Chinese) doi: 10.19452/j.issn1007-5453.2020.02.002
[9]	ELZEY D M, SOFLA A Y N, WADLEY H N G. A bio-inspired high-authority actuator for shape morphing structures[C]//Proceedings of SPIE 5053, Smart Structures and Materials 2003: Active Materials: Behavior and Mechanics. San Diego, CA: SPIE, 2003: 92-100.
[10]	杨媛, 徐志伟. 基于SMA的飞行器变体机翼驱动结构研究[J]. 兵器材料科学与工程, 2010, 33(1): 25-30. doi: 10.3969/j.issn.1004-244X.2010.01.007 YANG Y, XU Z W. Research of the airfoil structure based on a shape-memory alloy actuated morphing wing[J]. Ordnance Material Science and Engineering, 2010, 33(1): 25-30. (in Chinese) doi: 10.3969/j.issn.1004-244X.2010.01.007
[11]	PREVITALI F, MOLINARI G, ARRIETA A F, et al. Design and experimental characterisation of a morphing wing with enhanced corrugated skin[J]. Journal of Intelligent Material Systems and Structures, 2016, 27(2): 278-292. doi: 10.1177/1045389X15595296
[12]	ARENA M, AMOROSO F, PECORA R, et al. Numerical and experimental validation of a full scale servo-actuated morphing aileron model[J]. Smart Materials and Structures, 2018, 27(10): 105034. doi: 10.1088/1361-665X/aad7d9
[13]	王帮峰, 牟常伟, 周春华. 用于变体机翼的波纹式纤维增强复合材料蒙皮基体变形特性研究[J]. 机械科学与技术, 2011, 30(7): 1047-1050. doi: 10.13433/j.cnki.1003-8728.2011.07.031 WANG B F, MOU C W, ZHOU C H. Tensile deformation properties of wave style fiber reinforced composite skin for a morphing wing[J]. Mechanical Science and Technology for Aerospace Engineering, 2011, 30(7): 1047-1050. (in Chinese) doi: 10.13433/j.cnki.1003-8728.2011.07.031
[14]	谭巧. 形状记忆环氧聚合物及其复合材料的典型力学行为研究[D]. 哈尔滨: 哈尔滨工业大学, 2015. TAN Q. Typical mechanical behavior of epoxy shape memory polymer and its composite[D]. Harbin: Harbin Institute of Technology, 2015. (in Chinese)
[15]	尹维龙, 石庆华. 变体飞行器蒙皮材料与结构研究综述[J]. 航空制造技术, 2017, 60(17): 24-29. doi: 10.16080/j.issn1671-833x.2017.17.024 YIN W L, SHI Q H. Review of material and structure for morphing aircraft skin[J]. Aeronautical Manufacturing Technology, 2017, 60(17): 24-29. (in Chinese) doi: 10.16080/j.issn1671-833x.2017.17.024
[16]	YOKOZEKI T, SUGIURA A, HIRANO Y. Development of variable camber morphing airfoil using corrugated structure[J]. Journal of Aircraft, 2014, 51(3): 1023-1029. doi: 10.2514/1.C032573
[17]	AMENDOLA G, DIMINO I, CONCILIO A, et al. A linear guide-based actuation concept for a novel morphing aileron[J]. The Aeronautical Journal, 2019, 123(1265): 1075-1097. doi: 10.1017/aer.2019.35
[18]	RIVERO A E, WEAVER P M, COOPER J E, et al. Parametric structural modelling of fish bone active camber morphing aerofoils[J]. Journal of Intelligent Material Systems and Structures, 2018, 29(9): 2008-2026. doi: 10.1177/1045389X18758182
[19]	艾森, 聂小华, 王立凯, 等. 利用精细有限元模型实现大型机翼尺寸优化设计[J]. 机械科学与技术, 2021, 40(3): 487-492. AI S, NIE X H, WANG L K, et al. Optimization design of large scale wing size via refined finite element model[J]. Mechanical Science and Technology for Aerospace Engineering, 2021, 40(3): 487-492. (in Chinese)
[20]	TAKAHASHI H, YOKOZEKI T, HIRANO Y. Development of variable camber wing with morphing leading and trailing sections using corrugated structures[J]. Journal of Intelligent Material Systems and Structures, 2016, 27(20): 2827-2836. doi: 10.1177/1045389X16642298