基于Fokker 27飞机过载-超越数曲线族的严重超越数包线选取

doi:10.7527/S1000-6893.2013.0144

固体力学与飞行器总体设计

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基于Fokker 27飞机过载-超越数曲线族的严重超越数包线选取

贺小帆, 王强, 刘文珽

北京航空航天大学航空科学与工程学院, 北京 100191

收稿日期:2012-05-21 修回日期:2012-09-14 出版日期:2013-04-25 发布日期:2013-04-23
通讯作者: 贺小帆,Tel.: 010-82315738 E-mail: xfhe@buaa.edu.cn E-mail:xfhe@buaa.edu.cn
作者简介:贺小帆男, 博士, 副教授。主要研究方向: 疲劳与断裂力学、结构耐久性与损伤容限、腐蚀环境下使用寿命评定、加速疲劳试验方法。 Tel: 010-82315738 E-mail: xfhe@buaa.edu.cn;王强男, 硕士研究生。主要研究方向: 加速疲劳试验方法。 Tel: 010-82315738 E-mail: wq_060412@126.com;刘文珽男, 教授, 博士生导师。主要研究方向: 疲劳与断裂力学、结构耐久性/损伤容限及可靠性、腐蚀环境下使用寿命评定、飞机结构定延寿技术。 Tel: 010-82315738 E-mail: lwt_jiang@163.com
基金资助:
国家自然科学基金(11002009);航空科学基金(2010ZA51002)

A Method for Determining the Exceedance Envelope of Severe Spectrum Based on the Acceleration-exceedance Curves of Fokker 27 Airplanes

HE Xiaofan, WANG Qiang, LIU Wenting

School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China

Received:2012-05-21 Revised:2012-09-14 Online:2013-04-25 Published:2013-04-23
Supported by:
National Natural Science Foundation of China (11002009); Aeronautical Science Foundation of China (2010ZA51002) *Corresponding author. Tel.: 010-82315738 E-mail: xfhe@buaa.edu.cn

摘要/Abstract

摘要：

以Fokker 27机群的过载-超越数曲线族为基础,建立了严重谱对应的严重超越数包线的获取方法。首先对外场使用的Fokker 27飞机机群的过载-超越数曲线进行筛选,得到59架飞机的过载-超越数曲线,采用线性累积损伤理论计算得到59架飞机每次飞行的损伤;假定机群载荷损伤服从对数正态分布,以严重谱下安全寿命满足机群寿命可靠度要求为准则,给出了严重谱的损伤程度。其次,采用对数正态分布描述指定过载下超越数的分布特性,外推得到满足损伤要求的严重超越数包线及对应的概率要求。结果表明,Fokker 27飞机严重过载-超越数曲线包线对应的超越数增量为1.117倍标准差。

关键词: 疲劳, 寿命, 严重谱, 载荷谱, 超越数

Abstract:

To develop the severe spectrum, a method for determining the exceedance envelope of a severe spectrum is proposed based on the analysis of the exceedance curves of a fleet of Fokker 27 airplanes. First, the exceedance curves of 59 airplanes with similar service methods are selected, and the damage per flight of the fleet is calculated on the basis of the accumulated linear damage theory. Assuming the damage per flight of the Fokker 27 fleet follows the log-normal distribution, the damage degree of the severe spectrum is obtained according to the reliability requirement on the safe life of a fleet. Next, a log-normal distribution is used to depict the scatter of exceedance under a specified acceleration. Thus, an exceedance envelope of the severe spectrum is obtained by the extrapolation of the exceedance curve. The analysis shows that the exceedance of the severe spectrum should be increased with 1.177 times of its standard deviation.

Key words: fatigue, life, severe spectrum, load spectrum, exceedance

中图分类号:

V215.5

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, doi: 10.7527/S1000-6893.2013.0144.

HE Xiaofan, WANG Qiang, LIU Wenting. A Method for Determining the Exceedance Envelope of Severe Spectrum Based on the Acceleration-exceedance Curves of Fokker 27 Airplanes[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, doi: 10.7527/S1000-6893.2013.0144.

参考文献

[1] Tovo R. On the fatigue reliability evaluation of structural components under service loading. International Journal of Fatigue, 2001, 23(7): 587-598.
[2] Svensson T. Prediction uncertainties at variable amplitude fatigue. International Journal of Fatigue, 1997, 17(Suppl.1): S295-S302.
[3] Anon. Defense standard 00-970 part 1, Issue 2: design and airworthiness requirements for service. Aircraft Structures. London: UK Ministry of Defense, 1999.
[4] White P, Molent L, Barter S. Interpreting fatigue test results using a probabilistic fracture approach. International Journal of Fatigue, 2005, 27(7): 752-767.
[5] Payne A O. The fatigue of aircraft structures. Engineering Fracture Mechanics, 1976, 8(1): 157-203.
[6] Anon. JSSG-2006 Joint service specification guide. Aircraft Structure. 2nd ed. USA: Department of Defense, 2002.
[7] Anon. AFS-120-73-2 Fatigue evaluation of wing and associated structure on small airplanes. USA: FAA, 1973.
[8] Anon. AC-23-13A Fatigue, fail-safe, and damage tolerance evaluation of metallic structure for normal, utility, acrobatic, and commuter category airplanes. USA: FAA, 2005.
[9] Margery E H, Paul C H. Corrosion and fatigue research-structural issues and relevance to naval aviation. International Journal of Fatigue, 2001, 23(S1): 1-10.
[10] Paul C H. Fleet management issues and technology needs. International Journal of Fatigue, 2009, 31(11-12): 1631-1637.
[11] Iyyer N, Sarkar S, Merrill R, et al. Aircraft life management using crack initiation and crack growth models—P-3C aircraft experience. International Journal of Fatigue, 2007, 29(9-11): 1584-1607.
[12] Reyer W M. Probability basis of safe-life evaluations in small airplanes. 9th Joint FAA/DoD/NASA Aging Aircraft Conference, 2006.
[13] He X F, Wang Q, Liu W T. Primary analysis on the selection method of severe load spectrum based on the fleet load damage variation. Engineering Mechanics, 2012. (in Press)(in Chinese) 贺小帆, 王强, 刘文珽. 基于载荷损伤分散的严重谱选取方法初探. 工程力学, 2012. (录用).
[14] de Jonge J B, Hol P A. Variation in load factor experience—a re-analysis of Fokker F27 and F28 operational acceleration data. NLR TP 96512, 1996.
[15] Lincoln J W, Melliere R A. Economic life determination for a military aircraft. AIAA-1998-25192, 1998.
[16] Wang Z, Liu W T, Wang L. Study on the fatigue scatter factor for individual aircraft structure. Journal of Mechanical Strength, 2009, 31(1): 150-154. (in Chinese) 王智, 刘文珽, 王磊. 单机疲劳分散系数研究. 机械强度, 2009, 31(1): 150-154.
[17] Liu W T, Zheng M Z, Fei B J. Structural durability and probability fracture mechanics/damage tolerance. Beijing: Beihang University Press, 1998. (in Chinese) 刘文珽, 郑旻仲, 费斌军. 结构耐久性与概率断裂力学/损伤容限. 北京: 北京航空航天大学出版社, 1998.
[18] He X F, Dong Y M, Liu W T. Reliability analysis on fatigue life with separated structural and load spectrum scatters. Acta Aeronautica et Astronautica Sinica, 2010, 31(4): 732-737. (in Chinese) 贺小帆, 董彦民, 刘文珽. 结构和载荷分散性分离的寿命可靠性分析方法. 航空学报, 2010, 31(4): 732-737.

E-mail：hkxb@buaa.edu.cn

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基于Fokker 27飞机过载-超越数曲线族的严重超越数包线选取

A Method for Determining the Exceedance Envelope of Severe Spectrum Based on the Acceleration-exceedance Curves of Fokker 27 Airplanes

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