机身加筋壁板复合加载损伤容限性能试验

doi:10.7527/S1000-6893.2016.0106

Abstract

Abstract:

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.

Key words: fuselage panel, longitudinal crack, crack propagation, residual strength, damage tolerance test

CLC Number:

V216.1⁺1

CHEN An, WEI Yulong, LIAO Jianghai, DONG Dengke, WANG Xu. Damage tolerance test of stiffened fuselage panel under complex load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(1): 420093-420093.

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Damage tolerance test of stiffened fuselage panel under complex load

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