基于飞行科目统计分析的严重谱编制方法
|
摘要
我国飞机的疲劳试验绝大多数采用均值谱,具有疲劳周期较长的缺陷,若采用载荷严重谱则可以大大缩短试验时间。为满足全机试验疲劳寿命评估的需要,响应国内外飞机强度规范的要求,以国内某教练机的起落数据为基础,将任务分析法与统计思想相结合,建立基于飞行科目统计分析的严重谱编制方法,整理和完善编谱流程,编制得到各飞行科目包含加权中值载荷谱,一倍标准差谱,两倍标准差谱,90%存活概率95%置信度的严重谱,以及所有科目的总严重谱。通过K-S检验方法验证了载荷损伤分布的合理性,并根据当量损伤计算的统计结果给出严重谱代表起落的选取方法。结果表明:此严重谱编制方法合理有效,得到的编谱结果符合严重谱特征,选出的代表起落能够代表各飞行科目不同严重程度的使用情况。
Nowadays, the mean load spectra is mostly used in fatigue test for aircraft, but it has the defects of long fatigue cycle. The severe load spectra is used instead, which can shorten the test time greatly. In order to meet the demand of full-scale fatigue test for life evaluation and aircraft strength criterion at home and abroad, on the basis of take-off and landing data of an instructional airplane, the task analysis method is combined with statistic analysis method to establish a severe load spectra generation method, and arrange and perfect the spectra generation process. The severe load spectra of each flight subject and all subjects are generated and obtained, including weighted median load spectrum, one time standard deviation spectrum, two times standard deviation spectrum, severe load spectrum with 90% survival probability and 95% confidence coefficient, and total severe load spectrum. The K-S test method is used to verify the rationality of load damage distribution, and the selection method of severe spectra representing take-off and landing is give according to statistical results of equivalent damage calculation. The results show that the method of compiling severe spectra is reasonable and effective, the compilation results can fit the severe spectrum characteristics, and the selected representative take-off and landing can represent the conditions of different severity of flight subjects.
Nowadays, the mean load spectra is mostly used in fatigue test for aircraft, but it has the defects of long fatigue cycle. The severe load spectra is used instead, which can shorten the test time greatly. In order to meet the demand of full-scale fatigue test for life evaluation and aircraft strength criterion at home and abroad, on the basis of take-off and landing data of an instructional airplane, the task analysis method is combined with statistic analysis method to establish a severe load spectra generation method, and arrange and perfect the spectra generation process. The severe load spectra of each flight subject and all subjects are generated and obtained, including weighted median load spectrum, one time standard deviation spectrum, two times standard deviation spectrum, severe load spectrum with 90% survival probability and 95% confidence coefficient, and total severe load spectrum. The K-S test method is used to verify the rationality of load damage distribution, and the selection method of severe spectra representing take-off and landing is give according to statistical results of equivalent damage calculation. The results show that the method of compiling severe spectra is reasonable and effective, the compilation results can fit the severe spectrum characteristics, and the selected representative take-off and landing can represent the conditions of different severity of flight subjects.
引文
[1] 李宴宾.飞机结构疲劳加速谱和多部位损伤概率模型研究[D].西安:中国飞机强度研究所,2011.Li Yanbin.Research on the fatigue accelerated spectra of aircraft structure and damage probability model of multiple part[D].Xi’an:China Aircraft Strength Institute,2011.(in Chinese)
[2] 贺小帆,刘文珽.服从不同分布的疲劳寿命分散系数分析[J].北京航空航天大学学报,2002,28(1):47-49.He Xiaofan,Liu Wenting.On scatter factors of fatigue life obeying different distributions[J].Journal of Beijing University of Aeronautics and Astronautics,2002,28(1):47-49.(in Chinese)
[3] 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 Zhi,Liu Wenting,Wang Lei.Study of fatigue scatter factor of individual aircraft structure[J].Journal of Mechanical Strength,2009,31(1):150-154.(in Chinese)
[4] 贺小帆,董彦民,刘文珽.结构和载荷谱分散性分离的寿命疲劳可靠性[J].航空学报,2010,31(4):732-737.He Xiaofan,Dong Yanmin,Liu Wenting.Reliability analysis on fatigue life with separated structural and load spectrum scatters[J].Acta Aeronautica et Astronautica Sinica,2010,31(4):732-737.(in Chinese)
[5] 贺小帆,刘家曦,王强,等.基于载荷损伤分散的严重谱选取方法初探[J].工程力学,2015,32(7):32-37.He Xiaofan,Liu Jiaxi,Wang Qiang,et al.Primary analysis on the selection method of severe load spectrum based on the fleet load damage variation[J].Engineering Mechanics,2015,32(7):32-37.(in Chinese)
[6] 周蓓,朱如鹏.国内外飞机疲劳寿命分散系数计算[J].机械工程师,2005(2):50-51.Zhou Pei,Zhu Rupeng.Fatigue life scatter factor’s computing formulas of airplane structures in countris[J].Mecha-nical Engineer,2005(2):50-51.(in Chinese)
[7] 中国人民解放军总装备部GJB 67.6A-2008军用飞机结构强度规范,第6部分:重复载荷、耐久性和损伤容限[S].北京:中国人民解放军总装备部,2008.General Armament Department of the Chinese People’s Liberation Army GJB67.6A-2008 Military airplane structural strength specification.Part 6:Repeated loads,dusrability and damage tolerance[S].Beijing:General Armament Department of the Chinese People’s Liberation Army,2008.(in Chinese)
[8] 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 Zuguo,Tian Dingshuan,Zhou Zhanting.Aircraft structural load/environmental spectrum[M].Beijing:Electronic Industry Press,2012:98.(in Chinese)
[9] Department of Defense JSSG-2006 Joint service specification guide,Aircraft structures[S].USA:Department of Defense,1998,2000,2002.
[10] 蒋祖国.飞机耐久性严重载荷谱研究[R].西安:中国飞行试验研究院,2017.Jiang Zuguo.Aircraft durability severe load spectrum study[R].Xi’an:Chinese Flight Test Estabalishment,2017.(in Chinese)
[11] 郦正能,张纪奎.飞机结构疲劳和损伤容限设计[M].北京:北京航空航天大学出版社,2016.Li Zhengneng,Zhang Jikui.Aircraft structural fatigue and damage tolerance design[M].Beijing:University of Aeronautics and Astronautics Press,2016.(in Chinese)
[12] 王磊,薛军.基于严重谱的飞机结构疲劳寿命分析方法研究[R].北京:北京航空工程技术研究中心,2010.Wang Lei,Xue Jun.Research on fatigue life analysis method of aircraft structure based on severe spectrum[R].Beijing:Beijing Aeronautical Engineering Technology Research Center,2010.(in Chinese)
[13] Lowak H,de Jonge J B,Franz J,et al.“MiniTWIST,a Shortened Version of TWIST”[R].LBF-Bericht TB-146,NLR MP 79018 U,Amsterdam:National Aerospace Laboratory,1979.
[14] Xiong J J,Shenoi R A.A load history generation approach for full-scale accelerated fatigue tests[J].Engineering Fracture Mechanics,2008,75(10):3226-3243.
[15] FAA.General aviation aircraft-normal acceleration data analysis and collection project[R].DOT/FAA/CT-91/20,Atlantic City:FAA,1993.
[16] 张福泽.飞机载荷谱编制的新方法研究[J].航空学报,1998,19(5):7-13.Zhang Fuze.New method of drawing up aircraft load spectrum[J].Acta Aeronautica et Astronautica Sinica,1998,19(5):7-13.(in Chinese)
[17] 王智,李京珊,张福泽.用代表中值损伤的“飞行大纲”编排飞机载荷谱的方法[J].机械强度,2004,26(5):517-521.Wang Zhi,Li Jingshan,Zhang Fuze.Method of developing aircraft spectrum based on the flight training program with median damage[J].Journal of Mechanical Strength,2004,26(5):517-521.(in Chinese)
[18] 陆华.第三代先进歼击机疲劳载荷谱编制方法[D].沈阳:东北大学,2005.Lu Hua.A method for fatigue load spectrum of the third generation advanced fighter plane[D].Shenyang:Northeastern University,2005.(in Chinese)
[19] 徐明波.一种民机低载截除限试验载荷谱编制方法[J].中国科技信息,2014(14):34-36.Xu Mingbo.Method for drawing low-load cut-off limit test load spectrum of civil aircraft[J].China Science and Technology Information,2014(14):34-36.(in Chinese)
[20] 李唐,贺小帆,刘文珽.基于Fokker 27机群载荷谱损伤分散性计算分析[J].北京航空航天大学学报,2015,41(3):551-558.Li Tang,He Xiaofan,Liu Wenting.Calculation and analysis of the scatter of load spectrum based on Fokker F27 airplanes[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(3):551-558.(in Chinese)
[21] FAA Technical Center.Variation in load factor experience of Fokker F27 and F28 operational acceleration exceedance data[R].DOT/FAA/AR-96/114,US:FAA Technical Center,1993.
[22] 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 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 Aeronautica et Astronautica Sinica,2013,34(4):840-845.(in Chinese)
[23] 姚卫星.结构疲劳寿命分析[M].北京:国防工业出版社,2003.Yao Weixing.Structural fatigue life analysis[M].Beijing:National Defense Industry Press,2003.(in Chinese)
[24] 高镇同.飞机结构疲劳分散系数[R].北京:北京航空航天大学,2005.Gao Zhentong.Aircraft structure fatigue scatter factor[R].Beijing:Beihang University,2005.(in Chinese)
[25] He Xiaofan,Li Tang,Li Yuhai,et al.Developing an acce-lerated flight load spectrum based on the nz-N curves of a fleet[J].International Journal of Fatigue,2018,117:246-256.
[26] 陈亮,刘道庆,隋福成.飞机实际使用的比较损伤分布规律研究[J].飞机设计,2009,29(5):19-23.Chen Liang,Liu Daoqing,Sui Fucheng.The research about distribution of the compared damage of the aircraft[J].Aircraft Design,2009,29(5):19-23.(in Chinese)
[2] 贺小帆,刘文珽.服从不同分布的疲劳寿命分散系数分析[J].北京航空航天大学学报,2002,28(1):47-49.He Xiaofan,Liu Wenting.On scatter factors of fatigue life obeying different distributions[J].Journal of Beijing University of Aeronautics and Astronautics,2002,28(1):47-49.(in Chinese)
[3] 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 Zhi,Liu Wenting,Wang Lei.Study of fatigue scatter factor of individual aircraft structure[J].Journal of Mechanical Strength,2009,31(1):150-154.(in Chinese)
[4] 贺小帆,董彦民,刘文珽.结构和载荷谱分散性分离的寿命疲劳可靠性[J].航空学报,2010,31(4):732-737.He Xiaofan,Dong Yanmin,Liu Wenting.Reliability analysis on fatigue life with separated structural and load spectrum scatters[J].Acta Aeronautica et Astronautica Sinica,2010,31(4):732-737.(in Chinese)
[5] 贺小帆,刘家曦,王强,等.基于载荷损伤分散的严重谱选取方法初探[J].工程力学,2015,32(7):32-37.He Xiaofan,Liu Jiaxi,Wang Qiang,et al.Primary analysis on the selection method of severe load spectrum based on the fleet load damage variation[J].Engineering Mechanics,2015,32(7):32-37.(in Chinese)
[6] 周蓓,朱如鹏.国内外飞机疲劳寿命分散系数计算[J].机械工程师,2005(2):50-51.Zhou Pei,Zhu Rupeng.Fatigue life scatter factor’s computing formulas of airplane structures in countris[J].Mecha-nical Engineer,2005(2):50-51.(in Chinese)
[7] 中国人民解放军总装备部GJB 67.6A-2008军用飞机结构强度规范,第6部分:重复载荷、耐久性和损伤容限[S].北京:中国人民解放军总装备部,2008.General Armament Department of the Chinese People’s Liberation Army GJB67.6A-2008 Military airplane structural strength specification.Part 6:Repeated loads,dusrability and damage tolerance[S].Beijing:General Armament Department of the Chinese People’s Liberation Army,2008.(in Chinese)
[8] 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 Zuguo,Tian Dingshuan,Zhou Zhanting.Aircraft structural load/environmental spectrum[M].Beijing:Electronic Industry Press,2012:98.(in Chinese)
[9] Department of Defense JSSG-2006 Joint service specification guide,Aircraft structures[S].USA:Department of Defense,1998,2000,2002.
[10] 蒋祖国.飞机耐久性严重载荷谱研究[R].西安:中国飞行试验研究院,2017.Jiang Zuguo.Aircraft durability severe load spectrum study[R].Xi’an:Chinese Flight Test Estabalishment,2017.(in Chinese)
[11] 郦正能,张纪奎.飞机结构疲劳和损伤容限设计[M].北京:北京航空航天大学出版社,2016.Li Zhengneng,Zhang Jikui.Aircraft structural fatigue and damage tolerance design[M].Beijing:University of Aeronautics and Astronautics Press,2016.(in Chinese)
[12] 王磊,薛军.基于严重谱的飞机结构疲劳寿命分析方法研究[R].北京:北京航空工程技术研究中心,2010.Wang Lei,Xue Jun.Research on fatigue life analysis method of aircraft structure based on severe spectrum[R].Beijing:Beijing Aeronautical Engineering Technology Research Center,2010.(in Chinese)
[13] Lowak H,de Jonge J B,Franz J,et al.“MiniTWIST,a Shortened Version of TWIST”[R].LBF-Bericht TB-146,NLR MP 79018 U,Amsterdam:National Aerospace Laboratory,1979.
[14] Xiong J J,Shenoi R A.A load history generation approach for full-scale accelerated fatigue tests[J].Engineering Fracture Mechanics,2008,75(10):3226-3243.
[15] FAA.General aviation aircraft-normal acceleration data analysis and collection project[R].DOT/FAA/CT-91/20,Atlantic City:FAA,1993.
[16] 张福泽.飞机载荷谱编制的新方法研究[J].航空学报,1998,19(5):7-13.Zhang Fuze.New method of drawing up aircraft load spectrum[J].Acta Aeronautica et Astronautica Sinica,1998,19(5):7-13.(in Chinese)
[17] 王智,李京珊,张福泽.用代表中值损伤的“飞行大纲”编排飞机载荷谱的方法[J].机械强度,2004,26(5):517-521.Wang Zhi,Li Jingshan,Zhang Fuze.Method of developing aircraft spectrum based on the flight training program with median damage[J].Journal of Mechanical Strength,2004,26(5):517-521.(in Chinese)
[18] 陆华.第三代先进歼击机疲劳载荷谱编制方法[D].沈阳:东北大学,2005.Lu Hua.A method for fatigue load spectrum of the third generation advanced fighter plane[D].Shenyang:Northeastern University,2005.(in Chinese)
[19] 徐明波.一种民机低载截除限试验载荷谱编制方法[J].中国科技信息,2014(14):34-36.Xu Mingbo.Method for drawing low-load cut-off limit test load spectrum of civil aircraft[J].China Science and Technology Information,2014(14):34-36.(in Chinese)
[20] 李唐,贺小帆,刘文珽.基于Fokker 27机群载荷谱损伤分散性计算分析[J].北京航空航天大学学报,2015,41(3):551-558.Li Tang,He Xiaofan,Liu Wenting.Calculation and analysis of the scatter of load spectrum based on Fokker F27 airplanes[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(3):551-558.(in Chinese)
[21] FAA Technical Center.Variation in load factor experience of Fokker F27 and F28 operational acceleration exceedance data[R].DOT/FAA/AR-96/114,US:FAA Technical Center,1993.
[22] 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 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 Aeronautica et Astronautica Sinica,2013,34(4):840-845.(in Chinese)
[23] 姚卫星.结构疲劳寿命分析[M].北京:国防工业出版社,2003.Yao Weixing.Structural fatigue life analysis[M].Beijing:National Defense Industry Press,2003.(in Chinese)
[24] 高镇同.飞机结构疲劳分散系数[R].北京:北京航空航天大学,2005.Gao Zhentong.Aircraft structure fatigue scatter factor[R].Beijing:Beihang University,2005.(in Chinese)
[25] He Xiaofan,Li Tang,Li Yuhai,et al.Developing an acce-lerated flight load spectrum based on the nz-N curves of a fleet[J].International Journal of Fatigue,2018,117:246-256.
[26] 陈亮,刘道庆,隋福成.飞机实际使用的比较损伤分布规律研究[J].飞机设计,2009,29(5):19-23.Chen Liang,Liu Daoqing,Sui Fucheng.The research about distribution of the compared damage of the aircraft[J].Aircraft Design,2009,29(5):19-23.(in Chinese)