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介绍了飞机翼梁损伤试验,针对试验中蒙皮孔边早期出现疑似可检裂纹可能导致试验无法正常进行的情况,提出了拆除裂纹孔边铆钉的方法达到延缓裂纹扩展的目的。通过有限元分析软件,建立含裂纹结构应力强度计算模型,研究了拆除铆钉法在飞机整体翼梁损伤容限试验中的具体应用,通过静强度理论及断裂力学理论分析,对蒙皮孔边铆钉孔的受力状态、临界裂纹长度、疲劳寿命进行计算,指出拆除铆钉法本质是通过疲劳危险部位的逐渐转移来延长结构的疲劳寿命。给出的理论分析方法,可供飞机结构设计及修理参考。
In this paper, the damage test of the aircraft wing beam is introduced. In view of the situation that the test can not be carried out normally in the early stage of the blind skin test, the method of removing the rivets on the crack hole is proposed to delay the crack propagation. Through the finite element analysis software, the calculation model of the stress intensity of the cracked structure is established, and the concrete application of the rivet removal method in the damage tolerance test of the whole wing of the aircraft is studied. By analyzing the static strength theory and the fracture mechanics theory, The stress state of the hole, the length of the critical crack and the fatigue life are calculated. It is pointed out that the essence of the riveting method is to extend the fatigue life of the structure through the gradual transfer of the dangerous parts of fatigue. The theoretical analysis method given is available for aircraft structure design and repair reference.