复合材料直升机平尾结构概率损伤容限评估

doi:10.7527/S1000-6893.2021.25557

论文

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

复合材料直升机平尾结构概率损伤容限评估

万傲霜

中国民航大学航空工程学院, 天津 300300

收稿日期:2021-03-23 修回日期:2021-07-21 出版日期:2022-06-15 发布日期:2021-07-20
通讯作者: 万傲霜,E-mail:aswan@cauc.edu.cn E-mail:aswan@cauc.edu.cn
基金资助:
中央高校基本科研业务费专项资金（3122021042）

Probabilistic assessment on damage tolerance of composite helicopter horizontal tail structure

WAN Aoshuang

College of Aeronautical Engineering, Civil Aviation University of China, Tianjin 300300, China

Received:2021-03-23 Revised:2021-07-21 Online:2022-06-15 Published:2021-07-20
Supported by:
Fundamental Research Funds for the Central Universities of Civil Aviation University of China (3122021042)

摘要/Abstract

摘要： 考虑工作应力和剩余强度的随机性，建立了航空复合材料结构概率损伤容限评估的应力-剩余强度干涉模型，以复合材料直升机平尾结构为研究对象，统计分析了工作应力、损伤尺寸、初始强度和疲劳极限等随机因素，基于考虑损伤尺寸效应的剩余强度模型，利用Monte-Carlo方法，评估了复合材料直升机平尾结构的失效概率。结果表明，建立的航空复合材料结构概率损伤容限评估方法是可行的，考虑了复合材料结构制造和服役过程中众多随机因素对剩余强度的影响，符合实际情况；损伤类型和损伤修复效率对复合材料直升机平尾结构的失效概率有显著影响，穿透型损伤对平尾结构可靠度的不利影响大于分层损伤，平尾结构的失效概率随着修复效率增大而降低。

关键词: 复合材料, 损伤容限, 平尾, 剩余强度

Abstract: Considering the randomness of working stress and residual strength, this article develops a stress-residual strength interference model for probabilistic assessment on damage tolerance of the aircraft composite structure. The stochastic factors including working stress, damage size, initial strength and fatigue limit of the composite helicopter horizontal tail structure are statistically analyzed. Based on the residual strength model considering the effect of damage size, the failure probability of composite helicopter horizontal tail structure is evaluated using the Monte-Carlo method. The results indicate that the proposed probabilistic damage tolerance assessment method for the aircraft composite structure is feasible. The effects of various stochastic factors during manufacture and service of the composite structure on residual strength are taken into consideration, which are consistent with the actual situation. It is found that the damage type and damage repair efficiency have significant influence on the failure probability of the structure. The through-thickness damage has more adverse effect on the reliability of the structure than the delamination damage. The failure probability of the structure decreases with the increase of repair efficiency.

Key words: composite materials, damage tolerance, horizontal tail, residual strength

中图分类号:

V215.2

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.

WAN Aoshuang. Probabilistic assessment on damage tolerance of composite helicopter horizontal tail structure[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 525557.

参考文献

[1] Federal Aviation Administration. Composite aircraft structure:AC20-107B[R]. Washington, D.C.:Federal Aviation Administration, 2010:11-18.
[2] Society of Automotive Engineers. Composite materials handbook, Volume 3-Polymer matrix composites materials usage, design, and analysis:Handbook-MIL-HDBK 17-3F[S]. Warrendale:Society of Automotive Engineers, 2002.
[3] 陈普会, 肖闪闪. 飞机复合材料结构的概率设计方法[J]. 南京航空航天大学学报, 2012, 44(5):683-693. CHEN P H, XIAO S S. Probabilistic design methodology for composite aircraft structure[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2012, 44(5):683-693(in Chinese).
[4] HUANG C, LIN K E. A method for reliability assessment of aircraft structures subject to accidental damage[C]//46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston:AIAA, 2005:1830.
[5] LIN K, DU J J, DAVID R. Structural design methodology based on concepts of uncertainty[R]. Washington, D.C.:NASA, 2000.
[6] AFSHARI S S, POURTAKDOUST S H, CRAWFORD B J, et al. Time-varying structural reliability assessment method:application to fiber reinforced composites under repeated impact loading[J]. Composite Structures, 2021, 261:113287.
[7] 邵传金, 左洪福, 陆晓华, 等. 民机复合材料典型结构件检修间隔的概率分析[J]. 航空计算技术, 2017, 47(4):76-79. SHAO C J, ZUO H F, LU X H, et al. Probabilistic analysis method for typical structural inspection interval of civil aircraft composites[J]. Aeronautical Computing Technique, 2017, 47(4):76-79(in Chinese).
[8] CARDOSO J B, DE ALMEIDA J R, DIAS J M, et al. Structural reliability analysis using Monte Carlo simulation and neural networks[J]. Advances in Engineering Software, 2008, 39(6):505-513.
[9] CHIACHIO M, CHIACHIO J, RUS G. Reliability in composites-A selective review and survey of current development[J]. Composites Part B:Engineering, 2012, 43(3):902-913.
[10] IBRAHIM Y. Observations on applications of importance sampling in structural reliability analysis[J]. Structural Safety, 1991, 9(4):269-281.
[11] KAYMAZ I, MCMAHON C A. A response surface method based on weighted regression for structural reliability analysis[J]. Probabilistic Engineering Mechanics, 2005, 20(1):11-17.
[12] DODWELL T J, KYNASTON S, BUTLER R, et al. Multilevel Monte Carlo simulations of composite structures with uncertain manufacturing defects[J]. Probabilistic Engineering Mechanics, 2021, 63:103116.
[13] 刘成龙, 周金宇, 邱睿, 等. 复合材料层合板终层失效概率分析的通用生成函数法[J]. 机械强度, 2020, 42(2):350-356. LIU C L, ZHOU J Y, QIU R, et al. Probability analysis on last ply failure of composite laminates based on universal generating function method[J]. Journal of Mechanical Strength, 2020, 42(2):350-356(in Chinese).
[14] GARY P, RISKALLA M. Development of probabilistic design methodology for composite structures:DOT/FAA/AR-95/17[R]. Alexandria:National Technical Information Service, 1997.
[15] KAN H P, CORDERO R, WHITEHEAD R S. Advanced certification methodology for composite structures:NAWCAOPAX-96-262-TR[R]. Washington,D.C.:Naval Air Warfare Center-Aircaft Division Department of the Nary, 1997.
[16] SHIAO M. Evaluation of the probabilistic design methodology and computer code for composite structures:DOT/FAA/AR-99/12[R]. Alexandria:National Technical Information Service, 2001.
[17] USHAKOV A, STEWART A, MISHULIN I, et al. Probabilistic design of damage tolerant composite aircraft structures:DOT/FAA/AR-01/55[R]. Alexandria:National Technical Information Service, 2002.
[18] 梁鹏. 直升机尾部升力面组合设计方法研究[D]. 南京:南京航空航天大学, 2012. LIANG P. Research on the helicopter empennage combinatorial design[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2012(in Chinese).
[19] KIM S Y, KOO J M, KIM D W, et al. Prediction of the static fracture strength of hole notched plain weave CFRP composites[J]. Composites Science and Technology, 2011, 71(14):1671-1676.
[20] KHECHAI A, TATI A, GUERIRA B, et al. Strength degradation and stress analysis of composite plates with circular, square and rectangular notches using digital image correlation[J]. Composite Structures, 2018, 185:699-715.
[21] ZHAO L B, LIU Y L, HONG H M, et al. Compressive failure analysis for low length-width ratio composite laminates with embedded delamination[J]. Composites Communications, 2018, 9:17-21.
[22] WAN A S, XU Y G, XIONG J J. Notch effect on strength and fatigue life of woven composite laminates[J]. International Journal of Fatigue, 2019, 127:275-290.
[23] WAN A S, XIONG J J, XU Y G. Fatigue life prediction of woven composite laminates with initial delamination[J]. Fatigue & Fracture of Engineering Materials & Structures, 2020, 43(9):2130-2146.
[24] American Society of Testing Materials. Standard test method for open-hole tensile strength of polymer matrix composite laminates:ASTM-D5766-D5766M-11[S]. Washington, D.C.:American Society of Testing Materials, 2011.
[25] American Society of Testing Materials. Standard test method for open-hole compressive strength of polymer matrix composite laminates:ASTM D6484/D6484M-20[S]. Washington, D.C.:American Society of Testing Materials, 2009.
[26] 高镇同, 熊峻江. 疲劳可靠性[M]. 北京:北京航空航天大学出版社, 2000. GAO Z T, XIONG J J. Fatigue reliability[M]. Beijing:Beijing University of Aeronautics & Astronautics Press, 2000(in Chinese).
[27] 李湘郡, 李彦斌, 郭飞, 等. C/C复合材料的压缩强度分布与可靠性评估[J]. 航空学报, 2019, 40(8):222853. LI X J, LI Y B, GUO F, et al. Compression strength distribution and reliability assessment of C/C composites[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(8):222853(in Chinese).
[28] 穆志韬, 曾本银, 金平. 直升机结构疲劳[M]. 北京:国防工业出版社, 2009. MU Z T, ZENG B Y, JIN P. Fatigue of helicopter structures[M]. Beijing:National Defense Industry Press, 2009(in Chinese).
[29] 熊峻江. 疲劳断裂可靠性工程学[M]. 北京:国防工业出版社, 2008. XIONG J J. Fatigue and fracture reliability engineering[M]. Beijing:National Defense Industry Press, 2008(in Chinese).
[30] BERENS A P. Probability of detection (POD) analysis for the advanced retirement for cause (RFC)/engine structural integrity program (ENSIP) nondestructive evaluation (NDE) system-volume 1:Pod analysis[R]. Dayton:University of Dayton, 2000.

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

复合材料直升机平尾结构概率损伤容限评估

Probabilistic assessment on damage tolerance of composite helicopter horizontal tail structure

RichHTML

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]	龚煜廉, 张建国, 吴志刚, 褚光远, 范晓铎, 黄赢. 主动学习基自适应PC⁃Kriging模型的复合材料结构可靠度算法[J]. 航空学报, 2024, 45(8): 228982-228982.
[2]	贾文斌, 方磊, 张根, 史剑, 何泽侃, 宣海军. CNT树脂基复合材料断裂韧性的优化设计[J]. 航空学报, 2024, 45(7): 428971-428971.
[3]	张春云, 陈雄斌, 刘健, 崔苗. 酚醛树脂气凝胶复合材料热物性参数预测方法[J]. 航空学报, 2024, 45(6): 428848-428848.
[4]	黄领才. 纤维增强聚合物复合材料无损检测方法进展[J]. 航空学报, 2024, 45(5): 529697-529697.
[5]	高志廷, 马壮, 柳彦博. CVD-SiC阵列结构对ZrB₂/SiC涂层抗烧蚀性影响[J]. 航空学报, 2024, 45(3): 428842-428842.
[6]	李海星, 周峰, 颜巍, 白峰, 赵克良. 砂纸冰对民机平尾气动特性的影响[J]. 航空学报, 2024, 45(2): 128657-128657.
[7]	张超, 曹勇, 赵振强, 张海洋, 孙建波, 王志华, 蔚夺魁. 树脂基复合材料在民用航空发动机中的应用与关键技术研究进展[J]. 航空学报, 2024, 45(2): 28556-028556.
[8]	王文煜, 李锋, 任飞翔, 韦兴宇, 熊健. 轻质高强复合材料网格加筋壳体结构设计方法及力学性能研究进展[J]. 航空学报, 2024, 45(17): 530001-530001.
[9]	曹关关, 许可. 近零应力等效温度场驱动的CFRP复杂构件固化变形控制方法[J]. 航空学报, 2024, 45(16): 429703-429703.
[10]	方子唯, 何晶靖, 林京. 石墨烯掺杂聚合物复合材料介电性能建模[J]. 航空学报, 2024, 45(14): 429510-429510.
[11]	束静, 廖文和, 郑侃, 董松, 孙连军. 旋转超声加工碳纤维复合材料研究现状与展望[J]. 航空学报, 2024, 45(13): 628939-628939.
[12]	姜卓群, 黄盛, 王占学. 2D编织C/SiC孔边致密化结构多尺度混合模型与拉伸性能[J]. 航空学报, 2024, 45(13): 628713-628713.
[13]	杨倩, 王彦哲, 杨迪, 李泽众, 曲巍崴. 基于数据驱动的纤维增强复合材料自动铺放速度预测与规划[J]. 航空学报, 2024, 45(10): 429313-429313.
[14]	马莹, 陈奡, 邓聪颖, 陈翔, 禄盛, 曾宪君. 纺织复合材料多尺度网格划分方法[J]. 航空学报, 2024, 45(10): 429180-429180.
[15]	王宏越, 王兵, 方国东, 孟松鹤. 2.5D机织浅交弯联复合材料数字单元建模分析[J]. 航空学报, 2023, 44(9): 227478-227478.