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.
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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1989年第12期B653-B658,共6页
Acta Aeronautica et Astronautica Sinica
关键词
运输机
裂纹
壁板
强度因子
机身
stress strength factor, residual strength, residual life, crack tolerance.
