机身加筋壁板复合加载损伤容限性能试验

doi:10.7527/S1000-6893.2016.0106

材料工程与机械制造

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

机身加筋壁板复合加载损伤容限性能试验

陈安¹, 魏玉龙¹, 廖江海¹, 董登科¹, 王旭²

1. 中国飞机强度研究所, 西安 710065;
2. 上海飞机设计研究院, 上海 201210

收稿日期:2016-01-21 修回日期:2016-03-30 出版日期:2017-01-15 发布日期:2016-04-07
通讯作者: 陈安,E-mail:andychen1986@163.com E-mail:andychen1986@163.com

Damage tolerance test of stiffened fuselage panel under complex load

CHEN An¹, WEI Yulong¹, LIAO Jianghai¹, DONG Dengke¹, WANG Xu²

1. Aircraft Strength Research Institute of China, Xi'an 710065, China;
2. Shanghai Aircraft Design and Research Institute, Shanghai 201210, China

Received:2016-01-21 Revised:2016-03-30 Online:2017-01-15 Published:2016-04-07

摘要/Abstract

摘要：

为研究机身加筋壁板裂纹扩展规律和剩余强度特性，按照机身壁板承受内压和轴拉载荷边界条件的要求，设计并制造试验装置，通过静力试验验证了试验方案的正确性和合理性。损伤容限试验结果表明：纵向裂纹沿直线扩展，左右两侧裂纹扩展对称性较好，半裂纹长度小于80 mm时呈缓慢裂纹扩展特性，该裂纹可检性好，检出概率较高；纵向裂纹失稳扩展导致最终破坏，在最远的框处呈现“T”字状的裂纹扩展破坏模式。研究结果可为新型客机机身结构损伤容限分析与设计提供数据支持。

关键词: 机身壁板, 纵向裂纹, 裂纹扩展, 剩余强度, 损伤容限试验

Abstract:

To investigate the behaviors of the crack propagation and characteristics of the residual strength of the stiffened fuselage panel, a equipment is designed and manufactured based on boundary requirements for internal pressure and axial tension loads of the panel. Static test results prove the rationality and validity of the test. The results of damage tolerance test show that longitudinal crack progresses along nearly straight line. The left and the right cracks are symmetrical. The crack propagation is slow when the crack length is less than 80 mm, which can be detected easily. Longitudinal crack propagating unstably leads to eventual destruction in the farthest frame shown as the T-shaped crack failure mode. The results can provide data for damage tolerance design and fuselage structure assessment.

Key words: fuselage panel, longitudinal crack, crack propagation, residual strength, damage tolerance test

中图分类号:

V216.1⁺1

陈安, 魏玉龙, 廖江海, 董登科, 王旭. 机身加筋壁板复合加载损伤容限性能试验[J]. 航空学报, 2017, 38(1): 420093-420093.

CHEN An, WEI Yulong, LIAO Jianghai, DONG Dengke, WANG Xu. Damage tolerance test of stiffened fuselage panel under complex load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(1): 420093-420093.

参考文献

[1] PITT S, JONES R. Compliance measurements for assessing structural integrity[J]. Engineering Failure Analysis, 2001(8):371-397.
[2] 牛春匀. 实用飞机结构工程设计[M]. 北京:航空工业出版社, 2008:118-121. NIU C Y. Airframe structure design[M]. Beijing:Aviation Industry Press, 2008:118-121(in Chinese).
[3] 王志瑾, 姚卫星. 飞机结构设计[M]. 北京:国防工业出版社, 2004:152-153. WANG Z J, YAO W X. Aircraft structure design[M]. Beijing:National Defence Industrial Press, 2004:152-153(in Chinese).
[4] JAMES H, STARNES J, DAMODAR R, et al. Experimental verification of the analytical methodology to predict the residual strength of metallic shell structure:VA 23681-2199[R]. Washington, D. C.:NASA, 1999.
[5] SWIFT T. Important considerations in commercial aircraft damage tolerance[J]. International Journal of Vehicle Design, 1986, 7(3-4):264-287.
[6] MUNROE J, WILKINS K, GTUBER M. Integral airframe structures (IAS)-validated feasibility study of integrally stiffened metallic fuselage panels for reducing manufacturing cost:NASA/CR-2000-209337[R]. Washington, D. C.:NASA, 2000.
[7] RETTIT R G, WANG J J, TOH C. Validated feasibility study of integrally stiffened metallic fuselage panels for reducing manufacturing costs:NASA/CR-2000-209342[R]. Washington, D. C.:NASA, 2000.
[8] HAHN T, YANG M J, SUH S, et al. Damage tolerance and durability of selectively stitched, stiffened panels:DOT/FAA/AR-03/46[R]. Washington, D. C.:FAA, 2003.
[9] FURUKAWA C H, BUCALM M L, MAZELLA I J G. On the finite element modeling of fatigue crack growth in pressurized cylindrical shells[J]. International Journal of Fatigue, 2009, 31(4):629-635.
[10] FOSSATI M, COLOMBO D, MANRS A, et al. Numerical modelling of crack growth profiles in integral skin-stringer panels[J]. Engineering Fracture Mechanics, 2011(78):1341-1352.
[11] NESTERENKO G I. Comparison of damage tolerance of integrally stiffened and riveted structures[C]//ICAS 2000 Congress, 2000.
[12] 李亚智, 张向. 整体加筋壁板的破损安全特性与断裂控制分析[J]. 航空学报, 2006, 27(5):842-846. LI Y Z, ZHANG X. An analysis of fail-safety and fracture control of integrally stiffened panels[J]. Acta Aeronautica et Astronautica Sinica, 2006, 27(5):842-846(in Chinese).
[13] 殷之平, 黄其青, 傅祥炯. 变厚度壁板损伤容限特性研究[J]. 应用力学学报, 2005, 22(4):665-668. YIN Z P, HUANG Q Q, FU X J. Damage tolerance behavior of plates with variable thickness[J]. Chinese Journal of Applied Mechanics, 2005, 22(4):665-668(in Chinese).
[14] 臧伟锋, 董登科, 张海英. 机身壁板内压载荷强度试验方法研究[J]. 机械强度, 2015, 37(5):972-977. ZANG W F, DONG D K, ZHANG H Y. Research on test method of fuselage panel subjected to internal pressure load[J]. Journal of Mechanical Strength, 2015, 37(5):972-977(in Chinese).
[15] 王生楠, 张妮娜, 秦剑波. 整体机身结构纵向裂纹转折与止裂特性分析[J]. 西北工业大学学报, 2007, 25(4):472-477. WANG S N, ZHANG N N, QIN J B. Exploring engineering significance of turning of longitudinal crack in integral airframe structure[J]. Journal of Northwestern Polytechnical University, 2007, 25(4):472-477(in Chinese).
[16] 肖群力, 黄其青, 殷之平. 典型机翼整体壁板止裂特性分析及优化设计[J]. 机械强度, 2012, 34(1):92-96. XIAO Q L, HUANG Q Q, YIN Z P. Analysis of crack-arrest property and optimum design for typical stiffened panel[J]. Journal of Mechanical Strength, 2012, 34(1):92-96(in Chinese).
[17] 卢秉贺, 李萍, 赵继伟. 民用飞机后机身壁板控制失效模式和控制载荷工况分析[J]. 沈阳航空航天大学学报, 2012, 29(3):60-63. LU B H, LI P, ZHAO J W. Research on controlling load case and controlling failure mode for aft fuselage panel of civil aircraft[J]. Journal of Shenyang Aerospace University, 2012, 29(3):60-63(in Chinese).
[18] 张海英, 牛智奇, 董登科, 等. 疲劳裂纹扩展试验载荷谱加重方法研究[J]. 工程力学, 2015, 32(9):236-242. ZHANG H Y, NIU Z Q, DONG D K, et al. Research on load enhancement method for fatigue crack growth test[J]. Engineering Mechanics, 2015, 32(9):236-242(in Chinese).
[19] 龚志钰, 李章致. 材料力学[M]. 北京:科学出版社, 1999:187-191. GONG Z Y, LI Z Z. Material mechanics[M]. Beijing:Science Press, 1999:187-191(in Chinese).
[20] 郑晓玲. 民机结构耐久性与损伤容限设计手册(下册):损伤容限设计[M]. 北京:航空工业出版社, 2003:14-16. ZHENG X L. Durability and damage tolerance design handbook on civil aviation aircraft structure (Ⅱ):Damage tolerance design[M]. Beijing:Aviation Industry Press, 2003:14-16(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

机身加筋壁板复合加载损伤容限性能试验

Damage tolerance test of stiffened fuselage panel under complex load

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	景向嵘, 程盼, 罗振兵, 高天翔, 周岩, 邓雄. 电弧放电激励器破除冰特性及裂纹扩展规律[J]. 航空学报, 2022, 43(S2): 204-213.
[2]	张子瑜, 郝林. 扩展有限元法在断裂力学相场模型中的应用[J]. 航空学报, 2022, 43(9): 225976-225976.
[3]	李晓阳, 陶昭, 张慰. 基于不确定微分方程的疲劳可靠性建模[J]. 航空学报, 2022, 43(8): 225820-225820.
[4]	万傲霜. 复合材料直升机平尾结构概率损伤容限评估[J]. 航空学报, 2022, 43(6): 525557-525557.
[5]	冯振宇, 傅博宇, 解江, 段竹煊, 潘汉源. 爆炸冲击载荷下机身壁板的动态响应[J]. 航空学报, 2022, 43(6): 525513-525513.
[6]	汪厚冰, 王夏涵, 林国伟, 李新祥, 杨胜春. 含离散源损伤的复合材料壁板的剩余强度评估[J]. 航空学报, 2022, 43(6): 525899-525899.
[7]	王秋懿, 吴彦增, 鲍蕊. 疲劳裂纹扩展过程中的CTOD相关参量分析[J]. 航空学报, 2022, 43(6): 526632-526632.
[8]	李崇, 柴亚南, 王彬文, 陈向明, 于振波, 周红. 大型机身壁板复杂应力场试验技术[J]. 航空学报, 2022, 43(6): 526409-526409.
[9]	苏少普, 常文魁, 陈先民. 飞机典型壁板结构剪切屈曲疲劳试验与分析方法[J]. 航空学报, 2022, 43(5): 225219-225219.
[10]	杨夏炜, 彭冲, 马铁军, 温国栋, 王艳莹, 柴小霞, 徐雅欣, 李文亚. 高温合金线性摩擦焊接头疲劳裂纹扩展有限元分析[J]. 航空学报, 2022, 43(2): 625004-625004.
[11]	段佳桐, 隋福成, 刘汉海, 解放, 欧阳天, 鲍蕊. 弯曲载荷下薄壁结构疲劳裂纹扩展性能[J]. 航空学报, 2021, 42(5): 524326-524326.
[12]	奚蔚, 李强, 沈培良, 何瑞, 杨刚, 刘世杰. 一种多部位损伤全寿命分析的工程方法[J]. 航空学报, 2021, 42(5): 524328-524328.
[13]	刘宗兴, 刘军, 李维娜. 爆炸冲击载荷下典型机身结构动响应及破坏[J]. 航空学报, 2021, 42(2): 224252-224252.
[14]	李真, 王俊, 邓凡臣, 于振波. 复合材料机身壁板的强度分析与试验验证[J]. 航空学报, 2020, 41(9): 223688-223688.
[15]	常琦, 杨维希, 赵恒, 孟瑶, 刘君, 高鹤明. 基于多传感器的裂纹扩展监测研究[J]. 航空学报, 2020, 41(2): 223336-223336.