基于Fokker F27机群载荷谱损伤分散性计算分析

李唐; 贺小帆; 刘文珽

doi:10.13700/j.bh.1001-5965.2014.0195

基于Fokker F27机群载荷谱损伤分散性计算分析

doi: 10.13700/j.bh.1001-5965.2014.0195

北京航空航天大学航空科学与工程学院, 北京 100191

基金项目: 国家自然科学基金资助项目(11002009)

详细信息

作者简介:
李唐(1991—),男,四川成都人,硕士生,litang@buaa.edu.cn

通讯作者:
贺小帆(1976—),男,湖北天门人,教授,xfhe@buaa.edu.cn,主要研究方向为结构耐久性/损伤容限研究.

中图分类号: V215.51
计量
- 文章访问数: 1260
- HTML全文浏览量: 168
- PDF下载量: 621
- 被引次数: 0
出版历程
- 收稿日期: 2014-04-09
- 网络出版日期: 2015-03-20

Calculation and analysis of the scatter of load spectrum damage based on Fokker F27 airplanes

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 为考虑机群载荷谱分散性进行机群可靠性寿命评估,以56架Fokker F27飞机每次飞行的载荷因子-超越数曲线族为基础,编制得到56架飞机的载荷谱,选取SWT公式和线性累积损伤理论计算得到每架飞机的飞行载荷损伤、地-空-地载荷损伤和每次飞行载荷损伤,采用概率坐标回归方法进行拟合优度检验.结果表明,飞行载荷损伤服从威布尔分布、地-空-地载荷损伤服从对数正态分布,综合飞行载荷和地-空-地载荷损伤的每次飞行损伤服从对数正态分布,每次飞行损伤的对数标准差为0.073 7.
- 载荷谱 /
- 损伤 /
- 分散性 /
- 分布 /
- 飞机结构
Abstract: To assess the reliability life of a fleet, the scatter of the load spectrum must be considered. In this paper, 56 individual load spectra are compiled based on the acceleration-exceedance curves corresponding to a fleet of Fokker F27. With the application of the SWT formula and linear accumulative damage rule, the flight damage and the ground-air-ground (GAG) damage, as well as the total damage per flight have been analyzed. Next, the probabilistic coordinate regression is conducted to examine the distribution parameters of the three types of the damage of load spectra respectively. The goodness fit shows that the flight damage follows the Weibull distribution whilst the GAG damage follows the lognormal distribution, and the total damage comprehensively including flight damage and GAG damage follows a lognormal distribution. In addition, the lognormal standard deviation of the total damage is 0.073 7.
- load spectrum /
- damage /
- scatter /
- distribution /
- airplane structure

HTML全文

参考文献(25)

[1]	CCAR-25-R4 中国民用航空条例第25部运输类飞机适航标准[S].北京:中国民用航空局,2011:1-4. CCAR-25-R4 China civil aviation regulations Part 25 transport category aircraft airworthiness standards[S].Beijing:Civil Aviation Administration of China,2011:1-4(in Chinese).
[2]	Schijve J. Statistical distribution functions and fatigue of structures[J].International Journal of Fatigue,2005,27(9):1031-1039.
[3]	Tovo R. On the fatigue reliability evaluation of structural components under service loading[J].International Journal of Fatigue,2001,23(7):587-598.
[4]	de Jonge J B. Load experience variability of fighter aircraft[C]//Australian Aeronautical Conference of Australia.Canberra:The Institution of Engineers,1989:102.
[5]	Freudenthal A M, Gumbel E J.On the statistical interpretation of fatigue tests[J].Proceedings of the Royal Society A:Mathematical and Physical Sciences,1953,216(1126):309-332.
[6]	陈志伟. 载荷谱差异对疲劳寿命影响的研究[C].//第七届全国疲劳会议文集.北京:中国力学学会,1995. Chen Z W.Effect of spectrum difference on fatigue life[C]//Proceedings of the 7th Chinese National Fatigue Conference.Beijing:The Chinese Society of Theoretical and Applied Mechanics,1995(in Chinese).
[7]	Freudenthal A M. The scatter factor in the reliability assessment of aircraft structures[J].Journal of Aircraft,1977,14(2):202-208.
[8]	高镇同. 飞机结构疲劳分散系数,BH-B884[R].北京:北京航空学院,1982. Gao Z T.The fatigue scatter for aircraft structures, BH-B884[R].Beijing:Beijing Institute of Aeronautics,1982(in Chinese).
[9]	施耐康. 规范疲劳寿命及其标准差[J].航空学报,1987,8(10): 467-474. Shi N K.Normalize the fatigue life and standard variation[J].Acta Areonautica et Astronautica Sinica,1987,8(10):467-474(in Chinese).
[10]	Cardrick A W, Mew A B.Scatter considerations in the interpretation of major fatigue tests[C]//Proceedings of the ICAF Symposium.Seattle:International Committee on Aeronautical Fatigue,1999.
[11]	Hoffman M E, Hoffman P C.Corrosion and fatigue research-structural issues and relevance to naval aviation[J].International Journal of Fatigue,2001,23(Sup.1):1-10.
[12]	贺小帆,刘家曦, 王强,等.基于载荷损伤分散的严重谱选取准则初探[J/OL].北京:工程力学,2011(2012-05-11)[2014-05-21].http://gclx.tsinghua.edu.cn/CN/10.6052/j.issn.1000-4750.2011.11.0755. He X F,Liu J X,Wang Q,et al.Primary analysis on the selection method of severe load pectrum based on the fleet lod damage variation[J/OL].Beijing:Engineering Mechanics,2011(2012-05-11)[2014-05-21].http://gclx.tsinghua.edu.cn/CN/10.6052/j.issn.1000-4750.2011.11.0755(in Chinese).
[13]	Lincoln J W, Melliere R A.Economic life determination for a military aircraft[J].Journal of Aircraft,1999,36(5):737-742.
[14]	王智,刘文珽, 王磊.单机结构疲劳分散系数研究[J].机械强度,2009,31(1):150-154. Wang Z,Liu W T,Wang L.Study on the fatigue scatter factor for individual aircraft structure[J].Journal of Mechanical Strength,2009,31(1):150-154(in Chinese).
[15]	He X F, Sui F C,Zhai B,et al.Probabilistic and testing analysis for the variability of load spectrum damage in a fleet[J].Engineering Fatigue Analysis,2013,33:419-429.
[16]	王长江,姚卫星. 使用情况差异对民机载荷谱地空地损伤分散性的影响[J].机械强度,2013,35(5):668-673. Wang C J,Yao W X.GAG damage scatter of civil aircraft load spectra due to variation in aircraft usage[J].Journal of Mechanical Strength,2013,35(5):668-673(in Chinese).
[17]	Locke J E, Smith H W,Gabriel E A,et al.General aviation aircraft-normal acceleration data analysis and collection project,KU-FRL-926-1[R].Kansas:Kansas University Lawrence Flight Research Lab,1993.
[18]	de Jonge J B, Hol P A.Variation in load factor experience:a re-analysis of Fokker F27 and F28 operational acceleration data[M].Amsterdam:National Aerospace Laboratory,1996:1-51.
[19]	贺小帆,王强, 刘文珽.基于Fokker 27飞机过载-超越数曲线族的严重超越数包线选取[J].航空学报,2013,34(4):840-845. He X F,Wang Q,Liu W T.A method for determining the exceedance envelope of severe spectrum based on the acceleration-exceedance curves of Fokker 27 airplanes[J].Acta Aeronautica et Astronautica Sinica,2013,34(4):840-845(in Chinese).
[20]	蒋祖国,田丁栓, 周占廷.飞机结构载荷/环境谱[M].北京:电子工业出版社,2012:98. Jiang Z G Tian D Q,Zhou Z T.The aircraft structure load and environment spectra[M].Beijing:Publishing House of Electronics Industry,2012:98(in Chinese).
[21]	Rustenburg J, Skinn D,Tipps D O.Statistical loads data for boeing 737-400 aircraft in commercial operations,DOT/FAA/AR-98/28[R].Alexander:American Institute of Aeronautics and Astronautics,1998.
[22]	Rustenburg J W, Skinn D A,Tipps D O.Statistical loads data for the airbus a-320 aircraft in commercial operations,UDR-TR-2001-80[R].Alexander:American Institute of Aeronautics and Astronautics,2002.
[23]	Smith K N, Watson P,Topper T H.A stress-strain function for the fatigue of metals[J].Journal of Materials,1970,5(4):767-778.
[24]	刘文珽, 郑旻仲,费斌军,等.概率断裂力学与概率损伤容限/耐久性[M].北京:北京航空航天大学出版社,1998:38-41. Liu W T,Zheng M Z,Fei B J,et al.The probability fracture mechanics and probability damage tolerance/durability[M].Beijing:Beihang University Press,1998:38-41(in Chinese).
[25]	Parish H E. Fatigue test results and analysis 42 piston provost wings,3474[R].London:Her Majesty's Stationery Office,1967.