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摘要: 在交变载荷作用下, 在机翼腹板结构件表面粘贴应变花, 实时监测疲劳试验时试件的应力应变状况, 采用X射线确定了疲劳破坏后的试件表面和内部裂纹的大小与位置, 分析了结构件结构损伤的部位和损伤程度, 预测了结构件的裂纹扩展寿命。测试结果表明: 在40kN正弦交变压缩载荷作用下, 试件的疲劳寿命约为100万次, 符合疲劳寿命分布预期1万~100万次; 疲劳试验测得的应力与理论计算结果有相近的变化趋势, 误差约为10%;高锁螺栓和薄板断裂破坏是该处过大的载荷和绕x轴的弯矩共同导致的; 估算的疲劳裂纹扩展寿命为10 183次。Abstract: Under the alternating loads, the strain gauges were arranged on the test pieces' surfaces of airfoil web, the stresses and strains of test pieces were recorded, and the sizes and positions to fatigue damage in the test pieces were detected by X-rays. The positions and damage severities of test pieces were determined, and the crack growth lifes of airfoil structural parts were predicted. Test result shows that the fatigue lifes of test pieces are approximate one million cycles under 40 kN sinusoidal alternating compression load, and they are in good agreement with the expected distribution of fatigue life(ten thousand-one million cycles). The stresses and strains from fatigue test and theory calculation are similar in variation trends, and the errors are about 10%. The high load and the moment around x axis cause the rivet failure and sheet fracture of test pieces, and the predicted fatigue crack growth life is 10 183 cycles.
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Key words:
- structural part of airfoil /
- fatigue damage /
- crack detection /
- life prediction
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图 9 静态加载下某一应变花的应变曲线
Figure 9. Strain curves of a certain strain gauge under static loads
图 10 静态加载下某一应变花的应力曲线
Figure 10. Stress curves of a certain strain gauge under static loads
图 11 试件1测点8的应力-疲劳循环次数曲线
Figure 11. Curves of stresses and fatigue cycles at measuring point 8 of specimen 1
图 12 试件2测点5的应力-疲劳循环次数曲线
Figure 12. Curves of shear stresses and fatigue cycles at measuring point 5 of specimen 2
图 13 试件2测点8的应力-疲劳循环次数曲线
Figure 13. Curves of stresses and fatigue cycles at measuring point 8 of specimen 2
图 14 试件2测点1的应力-疲劳循环次数曲线
Figure 14. Curves of stresses and fatigue cycles at measuring point 1 of specimen 2
图 15 试件2不同应变花剪应力-疲劳循环次数曲线
Figure 15. Curves of shear stresses and fatigue cycles at different strain gauges of specimen 2
图 16 试件2某应变花处剪应力理论值与试验值对比
Figure 16. Comparison between calculation and test results of shear stresses at a certain strain gauge of specimen 2
表 1 零件参数
Table 1. Specifications of parts
零件 腹板 缘条 立柱 类型 薄板 型材 型材 尺寸/mm 1.2×174.5×272.4 L1=272.4 L2=174.5(177.0) 材料型号 2024-T42 XCJ113-40-2 XCJ211-14-1 T42 材料规格 AMS-QQ-A-250/4 AMS-QQ-A-200/11 AMS-QQ-A-200/3 
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[1] 朱新宇, 卢俊文. 复合材料结构健康监测技术在飞机中的应用[J]. 宇航材料工艺, 2011, 41(6): 23-27. doi: 10.3969/j.issn.1007-2330.2011.06.006ZHU Xin-yu, LU Jun-wen. Application of structural health monitoring on composite aircraft[J]. Aerospace Materials and Technology, 2011, 41(6): 23-27. (in Chinese). doi: 10.3969/j.issn.1007-2330.2011.06.006 [2] 李航航, 吴剑勇. 飞机结构设计技术现状与发展趋势研究[J]. 航空科学技术, 2007, 19(3): 20-22. doi: 10.3969/j.issn.1007-5453.2007.03.006LI Hang-hang, WU Jian-yong. Status and development trend of aircraft structure design[J]. Aeronautical Science and Technology, 2007, 19(3): 20-22. (in Chinese). doi: 10.3969/j.issn.1007-5453.2007.03.006 [3] 袁慎芳, 邱雷, 吴键, 等. 大型飞机的发展对结构健康监测的需求与挑战[J]. 航空制造技术, 2009, 52(22): 62-67. doi: 10.3969/j.issn.1671-833X.2009.22.012YUAN Shen-fang, QIU Lei, WU Jian, et al. Challenge in structural health monitoring of large aircraft development[J]. Aeronautical Manufacturing Technology, 2009, 52(22): 62-67. (in Chinese). doi: 10.3969/j.issn.1671-833X.2009.22.012 [4] HUR J W. An experimental study on fatigue safety life assessment of aircraft engine support structure[J]. International Journal of Precision Engineering and Manufacturing, 2011, 12(5): 843-848. doi: 10.1007/s12541-011-0112-x [5] NESTERENKO G I, NESTERENKO B G. Ensuring struc-tural damage tolerance of Russian aircraft[J]. International Journal of Fatigue, 2009, 31(6): 1054-1061. doi: 10.1016/j.ijfatigue.2008.05.022 [6] BATHIAS C, PARIS P C. Gigacycle fatigue of metallic air-craft components[J]. International Journal of Fatigue, 2010, 32(6): 894-897. doi: 10.1016/j.ijfatigue.2009.03.015 [7] 董彦民, 刘文珽, 杨超. 军用飞机结构耐久性设计的细节疲劳额定值方法[J]. 航空学报, 2010, 31(12): 2357-2364. https://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201012011.htmDONG Yan-min, LIU Wen-ting, YANG Chao. Military aircraft durability design method based on detail fatigue rating[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(12): 2357-2364. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201012011.htm [8] 陈国乐, 康建设, 刘夺, 等. 飞机机翼结构损伤仿真研究[J]. 火力与指挥控制, 2012, 37(7): 66-69. doi: 10.3969/j.issn.1002-0640.2012.07.017CHEN Guo-le, KANG Jian-she, LIU Duo, et al. Study on simulation of model damage in aircraft wing structures[J]. Fire Control and Command Control, 2012, 37(7): 66-69. (in Chinese). doi: 10.3969/j.issn.1002-0640.2012.07.017 [9] 李清蓉, 喻溅鉴. 直升机尾桨轴疲劳试验技术研究[J]. 直升机技术, 2009(3): 104-107. doi: 10.3969/j.issn.1673-1220.2009.03.022LI Qing-rong, YU Jian-jian. Fatigue test technique research of helicopter tail rotor mast[J]. Helicopter Technique, 2009(3): 104-107. (in Chinese). doi: 10.3969/j.issn.1673-1220.2009.03.022 [10] 斯而健. 民用飞机结构的全尺寸疲劳试验[J]. 民用飞机设计与研究, 2012(1): 47-52. doi: 10.3969/j.issn.1674-9804.2012.01.021SI Er-jian. Full-scale fatigue test of commercial airplane structure[J]. Civil Aircraft Design and Research, 2012(1): 47-52. (in Chinese). doi: 10.3969/j.issn.1674-9804.2012.01.021 [11] 翟新康, 黄其青, 殷之平, 等. 飞机整体翼梁结构裂纹扩展试验与分析[J]. 机械强度, 2007, 29(6): 987-991. doi: 10.3321/j.issn:1001-9669.2007.06.025ZHAI Xin-kang, HUANG Qi-qing, YIN Zhi-ping, et al. Crack propagation experiment and analysis of wing beam inte-grated structure[J]. Journal of Mechanical Strength, 2007, 29(6): 987-991. (in Chinese). doi: 10.3321/j.issn:1001-9669.2007.06.025 [12] PITROPAKIS I, PFEIFFER H, WEVERS M. Crack detec-tion in aluminium plates for aerospace applications electro-magnetic impedance spectroscopy using flat coil sensors[J]. Sensors and Actuators A: Physical, 2012, 176(1): 57-63. [13] KORDATOS E Z, AGGELIS D G, MAKTIKAS T E. Moni-toring mechanical damage in structural materials using com-plimentary NDE techniques based on thermography and acoustic emission[J]. Composites Part B: Engineering, 2012, 43(6): 2676-2686. doi: 10.1016/j.compositesb.2011.12.013 [14] ZHAO Xiao-liang, GAO Hui-dong, ZHANG Guang-fan, et al. Active health monitoring of an aircraft wing with embedded piezoelectric sensor actuator network: I. defect detection, localization and growth monitoring[J]. Smart Materials Structures, 2007, 16(4): 1208-1217. doi: 10.1088/0964-1726/16/4/032 [15] HURLEY R K, DRUMMOND J L, VIANA G C, et al. The effects of environment and cyclic fatigue on the mechanical properties of an indirect composite[J]. Journal of Dentistry, 2012, 40(10): 787-92. [16] 王逾涯, 李岷, 陈群志, 等. 飞机结构静强度与疲劳试验双向加载技术研究[J]. 实验室研究与探索, 2007, 26(11): 297-299. https://www.cnki.com.cn/Article/CJFDTOTAL-SYSY200711101.htmWANG Yu-ya, LI Min, CHEN Qun-zhi, et al. Research on an aircraft structure loading apply technique[J]. Research and Exploration in Laboratory, 2007, 26(11): 297-299. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-SYSY200711101.htm [17] 张京娟, 秦海霞, 吴君. 飞机机翼结构变形量测量装置[J]. 仪表技术与传感器, 2012, 49(2): 100-102. https://www.cnki.com.cn/Article/CJFDTOTAL-YBJS201202036.htmZHANG Jing-juan, QIN Hai-xia, WU Jun. Design of meas-uring device for deformation of airplane's wing structure[J]. Instrument Technique and Sensor, 2012, 49(2): 100-102. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-YBJS201202036.htm [18] 袁伟, 孙秦. DFR法结构细节疲劳强度分析[J]. 陕西理工学院学报: 自然科学版, 2007, 23(1): 9-11. https://www.cnki.com.cn/Article/CJFDTOTAL-SXGX200701005.htmYUAN Wei, SUN Qin. Fatigue intensity analysis structure detail based on detail fatigue rating[J]. Journal of Shaanxi University of Technology: Natural Science Edition, 2007, 23(1): 9-11. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-SXGX200701005.htm [19] 崔建国, 赵朋元, 董世良, 等. 飞机结构部件疲劳寿命预测技术研究[J]. 沈阳航空航天大学学报, 2011, 28(3): 43-47. https://www.cnki.com.cn/Article/CJFDTOTAL-HKGX201103012.htmCUI Jian-guo, ZHAO Peng-yuan, DONG Shi-liang, et al. Fatigue life prediction research on aeroplane structures com-ponent[J]. Journal of Shenyang Aerospace University, 2011, 28(3): 43-47. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKGX201103012.htm [20] 孙明琦. 典型结构件疲劳寿命分析研究[J]. 哈尔滨理工大学学报, 2007, 12(1): 118-121. https://www.cnki.com.cn/Article/CJFDTOTAL-HLGX200701031.htmSUN Ming-qi. Fatigue life analysis and research for typical structure part[J]. Journal of Harbin University of Science and Technology, 2007, 12(1): 118-121. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HLGX200701031.htm -
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