机身加筋壁板复合加载损伤容限性能试验
收稿日期: 2016-01-21
修回日期: 2016-03-30
网络出版日期: 2016-04-07
Damage tolerance test of stiffened fuselage panel under complex load
Received date: 2016-01-21
Revised date: 2016-03-30
Online published: 2016-04-07
陈安 , 魏玉龙 , 廖江海 , 董登科 , 王旭 . 机身加筋壁板复合加载损伤容限性能试验[J]. 航空学报, 2017 , 38(1) : 420093 -420093 . DOI: 10.7527/S1000-6893.2016.0106
To investigate the behaviors of the crack propagation and characteristics of the residual strength of the stiffened fuselage panel, a equipment is designed and manufactured based on boundary requirements for internal pressure and axial tension loads of the panel. Static test results prove the rationality and validity of the test. The results of damage tolerance test show that longitudinal crack progresses along nearly straight line. The left and the right cracks are symmetrical. The crack propagation is slow when the crack length is less than 80 mm, which can be detected easily. Longitudinal crack propagating unstably leads to eventual destruction in the farthest frame shown as the T-shaped crack failure mode. The results can provide data for damage tolerance design and fuselage structure assessment.
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