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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。
In order to study the law of crack propagation and residual strength of ribbed stiffened panel, the test device was designed and manufactured according to the requirements of boundary conditions of internal panel wall subjected to internal pressure and axial load. The correctness of the test scheme was verified by static test And rationality. The results of the damage tolerance tests show that the longitudinal crack propagates along a straight line and the crack propagation symmetry is better on both the left and right sides. When the half crack length is less than 80mm, the crack propagates slowly, and the crack has good detectability and high detection probability. Unstable expansion led to the final destruction, in the farthest box showing “T ” crack growth damage pattern. The research results can provide data support for the damage tolerance analysis and design of the fuselage structure of new passenger aircraft.