Residual thermal stresses around bonded fibre metal laminate repair patches on an aircraft fuselage
Residual thermal stresses around bonded fibre metal laminate repair patches on an aircraft fuselage
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飞机机身上粘合纤维金属层压板修复补丁周围的残余热应力
DOI：
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发表时间：
1998
期刊：
影响因子：
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通讯作者：
J. Schelling
中科院分区：
文献类型：
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作者：
A. Vlot;T. Soerjanto;I. Yeril;J. Schelling
飞机结构开裂后，粘接补丁高温固化后会产生残余应力。这些残余应力会影响修复的性能和耐久性。在维修过程中和维修后的三个位置，对真实的飞机机身部分进行了应变和温度测量。观察到了皮肤的热屈曲，因此采用了较低温度的预固化。此外，在较低的温度下，可以观察到皮肤的显著向外弯曲，这影响了残余应力。测得的温度场与Rose的理论模型符合较好。
Residual stresses are present after elevated temperature cure of adhesively bonded patches to cracked aircraft structures. These residual stresses will affect the performance and the durability of the repair. Strain and temperature measurements were taken on a real aircraft fuselage section during and after repair at three locations. Thermal buckling of the skin was observed and therefore a precuring at a lower temperature was employed. Also at a lower temperature a significant outward bending of the skin was observed which influences the residual stresses. The measured temperature field corresponded weil with the theoretical model of Rose.