| 机身壁板裂纹容限分析的工程方法在某运输机上的应用 |
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| 引用本文： | 陆富梅,王斌,刘狄青.机身壁板裂纹容限分析的工程方法在某运输机上的应用[J].航空学报,1989,10(12):653-658. |
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| 作者姓名： | 陆富梅 王斌 刘狄青 |
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| 作者单位： | 飞机结构强度研究所
(陆富梅，王斌)，西安飞机制造公司(刘狄青) |
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| 摘 要： | In this paper, the stress strength factor of fuselage stiffened panels of transport airplanes has been obtained by using two-dimensional, analytical solution, curvature correc tion and nonuniform stress correction. Based on the Kc criterion critical crack length has been obtained. By using the fast integral technic the residual strength and residual life under random spectra for skin circumferential crack at the typical broken stringer and for longitudinal crack at the typical broken frame were obtained and analysed. Then by analyzing the above numerical results, the basic information for determining the life of the transport airplane has been provided. The above calculation is conducted on a IBM236 microcomputer.Due to the use of analytical and fast integral approaches the method used in this paper is convenient and economic.It can be used for crack tolerance analysis of other airplane structures.
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| 关 键 词： | |
| 收稿时间： | 1989-04-01; |
THE APPLICATION OF THE ENGINEERING APPROACH FOR ANALYZING CRACK TOLERANCE OF FUSELAGE PANELS TO A TRANSPORT AIRPLANE |
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| Aircraft Strength Research Institute Lu Fumei and Wang Bin Xian Aircraft Company Liu Diqing.THE APPLICATION OF THE ENGINEERING APPROACH FOR ANALYZING CRACK TOLERANCE OF FUSELAGE PANELS TO A TRANSPORT AIRPLANE[J].Acta Aeronautica et Astronautica Sinica,1989,10(12):653-658. |
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| Authors: | Aircraft Strength Research Institute Lu Fumei and Wang Bin Xian Aircraft Company Liu Diqing |
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| Institution: | Aircraft Strength Research Institute Lu Fumei and Wang Bin Xian Aircraft Company Liu Diqing |
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| Abstract: | In this paper, the stress strength factor of fuselage stiffened panels of transport airplanes has been obtained by using two-dimensional, analytical solution, curvature correc tion and nonuniform stress correction. Based on the Kc criterion critical crack length has been obtained. By using the fast integral technic the residual strength and residual life under random spectra for skin circumferential crack at the typical broken stringer and for longitudinal crack at the typical broken frame were obtained and analysed. Then by analyzing the above numerical results, the basic information for determining the life of the transport airplane has been provided. The above calculation is conducted on a IBM236 microcomputer.Due to the use of analytical and fast integral approaches the method used in this paper is convenient and economic.It can be used for crack tolerance analysis of other airplane structures. |
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| Keywords: | stress strength factor residual strength residual life crack tolerance |
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