四参数疲劳定寿方法

宁向荣; 陈伟; 蔡显新; 廖学军; 米栋

四参数疲劳定寿方法

1.
南京航空航天大学能源与动力学院,南京 210016
2.
中国航空工业集团公司中国航空动力机械研究所,湖南株洲 412002

基金项目: 国家高科技研究发展计划(2006AA04Z418)

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出版历程
- 收稿日期: 2012-04-02
- 刊出日期: 2012-08-28

Four-parameter life prediction method

1.
College of Energy and Power Engineering, Nanjing University of Aeronautic and Astronautics,Nanjing 210016,China
2.
China Aviation Powerplant Research Institute, Aviation Industry Corporation of China,Zhuzhou Hunan 412002,China

摘要

摘要: 对直升机传动系统采用的一种疲劳定寿方法——四参数法进行了研究:首先介绍了四参数应力-循环(S-N)曲线,然后详细介绍了通过材料平均 S-N 曲线获取构件安全 S-N 曲线的步骤以及直升机传动系统四参数疲劳定寿的程序和方法,研究了定寿流程中的各个技术细节.同时介绍了传动系统机匣疲劳试验中的多路协调加载技术以及某传动系统尾减机匣(TGB)的全尺寸疲劳试验情况.最后采用四参数疲劳定寿方法,根据某传动系统尾减机匣全尺寸疲劳试验结果和飞行实测载荷谱,对尾减机匣进行了安全寿命评估.该实例分析表明:四参数疲劳定寿方法为一种有效、可靠的寿命评估方法,具有推广价值.
- 直升机传动系统 /
- 疲劳定寿 /
- 四参数应力-循环 (S-N)曲线 /
- 全尺寸疲劳试验 /
- 多路协调加载
Abstract: Four-parameter life prediction method for helicopter transmission system was studied.Four-parameter stress-number of cycles (S-N) curve was presented first,and then,the derivation of helicopter transmission component safe S-N curve from material mean S-N curve and the scheme for the component life prediction were introduced in detail.Multi-load coordinating loading technology in fatigue test and a tail gear box(TGB) casing full-scale fatigue test were introduced at the same time.Finally,according to the full-scale fatigue test result and flight load survey data,applying the four-parameter life prediction method,the TGB casing life prediction was performed,which indicates that four-parameter life prediction method is a reliable and effective method and is worth to be generalized.
- helicopter transmission system /
- life prediction /
- four-parameter stress-number of cycles (S-N) curve /
- full-scale fatigue test /
- multi-load coordinating loading

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参考文献(16)

[1]	军用直升机强度和刚度规范编制组.军用直升机强度和刚度规范(GJB720.4-89)使用说明[M].北京:航空工业出版社,1990.
[2]	陈智伟.从疲劳试验寿命到结构安全寿命[J].航空学报,1991,12(8):443-446. CHEN Zhiwei.From fatigue test life to structure safe life[J].Acta Aeronautica et Astronautica,1991,12(8):443-446.(in Chinese)
[3]	穆志韬,曾本银.直升机结构疲劳[M].北京:国防工业出版社,2009.
[4]	Vaughan R E,CHANG Junghua.Life prediction for high cycle dynamic components using damage tolerance and small thrshold cracks .Phoenix,Arizona: Presented at the American Helicopter Society 59th Annual Forum,2000: 82-88.
[5]	Stanzl-Tschegg S E,Mager H.How and why the fatigue S-N curve does not approach a horizontal asymptote[J].International Journal of Fatigue,2001,23(Supplement):231-237.
[6]	曾本银.直升机疲劳定寿技术 .北京:北京航空航天大学,2005. ZENG Benyin.Fatigue evaluation of helicopter .Beijing:Beijing University of Aeronautics and Astronautics,2005.(in Chinese)
[7]	赵少汴.抗疲劳设计[M].北京:机械工业出版社,1994.
[8]	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.
[9]	曾玖海,曾本银,史思佃.直升机动部件安全寿命和破损安全相结合定寿技术[J].直升机技术,2003(3):15-20. ZENG Jiuhai,ZENG Benyin,SHI Sidian.The helicopter dynamic component’s life evaluating technique combining safe-life and fail-safe[J].Helicopter Technique,2003(3):15-20.(in Chinese)
[10]	熊峻江.飞行器结构疲劳与寿命设计[M].北京:北京航空航天大学出版社,2003.
[11]	姚卫星.结构疲劳寿命分析[M].北京:国防工业出版社,2003.
[12]	康丽霞,曹义华,宁向荣.直升机传动系统疲劳定寿技术研究.航空动力学报,2011,26(6):1431-1435. KANG Lixia,CAO Yihua,NING Xiangrong.Fatigue evaluation of helicopter transmission system[J].Acta Aeronautica et Astronautica,2011,26(6):1431-1435.(in Chinese)
[13]	HU Baian.Study on general principle for structure fatigue substantiation of helicopter transmission system[J].Applied Mechanics and Materials,2011,86(1):90-95.
[14]	王智,陈志伟,刘文琦.飞机载荷谱不同编制方法的对比研究 //第五届全国疲劳会议论文集.威海:中国航空学会,1991:699-703.
[15]	中国直升机设计研究所.直升机载荷手册[M].北京:航空工业出版社,1996.
[16]	张蕾.单机寿命监控系统设计研究[J].陆军航空兵学院学报,2003,2(3):70-72. ZHANG Lei.Single life monitoring system design and research[J].Journal of Army Aviation Institute,2003,2(3):70-72.(in Chinese)