摘要
为研究机身加筋壁板裂纹扩展规律和剩余强度特性,按照机身壁板承受内压和轴拉载荷边界条件的要求,设计并制造试验装置,通过静力试验验证了试验方案的正确性和合理性。损伤容限试验结果表明:纵向裂纹沿直线扩展,左右两侧裂纹扩展对称性较好,半裂纹长度小于80mm时呈缓慢裂纹扩展特性,该裂纹可检性好,检出概率较高;纵向裂纹失稳扩展导致最终破坏,在最远的框处呈现"T"字状的裂纹扩展破坏模式。研究结果可为新型客机机身结构损伤容限分析与设计提供数据支持。
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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2017年第1期305-312,共8页
Acta Aeronautica et Astronautica Sinica
关键词
机身壁板
纵向裂纹
裂纹扩展
剩余强度
损伤容限试验
fuselage panel
longitudinal crack
crack propagation
residual strength
damage tolerance test
