金属机身飞机框间距及截面参数分析
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摘要
目前,大部分设计参考书目中对于机身隔框间距都是以经验值20 in作为说明,对于框距值的确定原因以及影响因素未作详细的分析。通过以隔框间距参数为设计变量,以机身强度和机身局部稳定性为设计约束,并以机身重量为目标函数对隔框间距值的确定进行研究,给出一种隔框框距值的确定方法,并通过实例计算验证150座级飞机框间距20 in的经验值;同时利用有限元分析(FEA)和试验设计(DOE)方法对飞机普通隔框的截面形式进行结构参数分析,分析隔框各个设计参数对蒙皮应力水平的影响大小,给出150座级飞机隔框截面参数可行域。结果表明:本文分析计算值与一般150座级飞机的隔框间距设计经验值20 in (508 mm)相比,结果吻合很好;采用有限元分析,腹板高度设计为80～95 mm,内缘条宽度和外缘宽度条设计为15 mm;采用DOE分析,隔框外缘条宽度应大于内缘条宽度。
At present, most of the references just give a frame pitch of 20 in as an empirical value, but no more other analysis about the reason of the pitch and the influence factors of the frame pitch. The frame pitch is taken as a parameter, the fuselage strength and stability as constraints and the fuselage weight as objective function to make an analysis of the frame pitch, and give a method that how the frame pitch can be designed. And with that method the 20 in frame pitch is verified for aircraft of 150 seats. Meanwhile, the section parameter of the frame and its influence on the skin stress are analyzed by finite element analysis(FEA) and design of experiment(DOE), and a feasible region for the section parameter of the frame is given. The result shows that the value calculated by this method is in good agreement with the empirical value(20 in) for the aircraft of 150 seats. By using FEA, the height of frame should be 80～95 mm, the width of inner flange and outer flange should be 15 mm. By DOE analysis, the width of frame outer flange should be bigger than the inner flange.
At present, most of the references just give a frame pitch of 20 in as an empirical value, but no more other analysis about the reason of the pitch and the influence factors of the frame pitch. The frame pitch is taken as a parameter, the fuselage strength and stability as constraints and the fuselage weight as objective function to make an analysis of the frame pitch, and give a method that how the frame pitch can be designed. And with that method the 20 in frame pitch is verified for aircraft of 150 seats. Meanwhile, the section parameter of the frame and its influence on the skin stress are analyzed by finite element analysis(FEA) and design of experiment(DOE), and a feasible region for the section parameter of the frame is given. The result shows that the value calculated by this method is in good agreement with the empirical value(20 in) for the aircraft of 150 seats. By using FEA, the height of frame should be 80～95 mm, the width of inner flange and outer flange should be 15 mm. By DOE analysis, the width of frame outer flange should be bigger than the inner flange.
引文
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[2] Hans-Jürgen Schmidt,General.Metallic technologies and design principles of basic components[R].Toulouse:Airbus,2005:18-19.
[3] 邓扬晨,刘晓欧,朱继宏.飞机加强框的一种结构拓扑优化设计方法[J].飞机设计,2004(4):11-16.Deng Yangchen,Liu Xiaoou,Zhu Jihong.An approach to structural topology optimization about aircraft reinforced frames design[J].Aircraft Design,2004(4):11-16.(in Chinese)
[4] 邓扬晨,熊严,张卫红,等.改型设计中飞机普通框一种设计方法[J].飞机设计,2004(3):25-30.Deng Yangchen,Xiong Yan,Zhang Weihong,et al.A design approach to fuselage frames in aircraft upgrade design[J].Aircraft Design,2004(3):25-30.(in Chinese)
[5] 陈振兴,曾小苗.大型民用飞机框与长桁、蒙皮的连接结构分析[J].大众科技,2014,16(181):166-168.Chen Zhenxing,Zeng Xiaomiao.Large civil aircraft frame and stringer & skin connection analysis[J].Popular Science & Technology,2014,16(181):166-168.(in Chinese)
[6] 姜晓伟.飞机框类重件的逆向设计及数字化加工[J].工具技术,2015,49(2):65-67.Jiang Xiaowei.Reverse design and digital processing of aircraft frame parts[J].Tool Engineering,2015,49(2):65-67.(in Chinese)
[7] 郑辉洲.机身整体壁板结构分析[D].南京:南京航空航天大学,2007.Zheng Huizhou.Fuselage integral panel structure analysis[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2007.(in Chinese)
[8] 赖宇阳.Isight参数优化理论与实力详解[M].北京:北京航空航天大学出版社,2012:138-142.Lai Yuyang.Isight parameters optimization theory and case explanation[M].Beijing:Beihang University Press,2012:138-142.(in Chinese)
[9] 北京思易特科技有限公司.多学科目标优化软件Isight入门与提高[M].北京:北京思易特科技有限公司,2014.Beijing Etemal Co.,Ltd.Introduction and improvement of multidisciplinary optimization software Isight[M].Beijing:Beijing Etemal Co.,Ltd.,2014.(in Chinese)
[10] 曾超,徐惠民.民用飞机机身剖面参数化设计分析[J].民用飞机设计与研究,2012(增刊):46-53.Zeng Chao,Xu Huimin.Design and analysis of cross section of civil airplane[J].Civil Aircraft Design & Research,2012(S):46-53.(in Chinese)