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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1989, Vol. 10 ›› Issue (12): 653-658.

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THE APPLICATION OF THE ENGINEERING APPROACH FOR ANALYZING CRACK TOLERANCE OF FUSELAGE PANELS TO A TRANSPORT AIRPLANE

Lu Fumei1, Wang Bin1, Liu Diqing2   

  1. 1. Aircraft Strength Research Institute;2. Xian Aircraft Company
  • Received:1989-04-01 Revised:1900-01-01 Online:1989-12-25 Published:1989-12-25

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.