摘要
介绍了组合翼梁和整体翼梁结构的区别,利用ANSYS软件对整体翼梁损伤容限特性进行分析,讨论了有止裂筋条和无止裂筋条两种情况下的损伤容限特性,研究了止裂筋条在不同结构参数面积下的应力强度因子变化规律。根据静强度理论、断裂力学准则及检查间隔要求,结合整体翼梁结构参数及其传力特点,在止裂筋条面积赋初值的基础上,从止裂筋条面积能否同时满足静强度理论、断裂韧性准则及检查间隔要求角度,采用计算迭代给出了飞机整体翼梁止裂筋条结构参数确定方法。为今后飞机整体翼梁结构损伤容限设计提供了参考依据。
Introduced the difference between the composite beam and the integrated beam for wing beam structure. Analyzed the damage tolerance characteristics of the wing beam integrated structure by using ANSYS software. Discussed the differences of damage tolerance characteristics for wing beam with crack-arresting stringer and no crack-arresting stringer. Studied the change law of the stress intensity factor for crack-arresting stringer in different structure area According to static strength theory and fracture mechanics criterion and inspection interval requirement, taking into account the structure parameters and the stress characteristics of the integral wing beam, given the parameter determination method for the crack-arresting stringer of wing beans integrated structure. Then provided the reference for damage tolerance design of wing beam integrated structure.
出处
《机械设计与制造》
北大核心
2017年第3期40-42,共3页
Machinery Design & Manufacture
关键词
整体翼梁
止裂筋条
静强度准则
断裂韧性准则
应力强度因子
Wing Beam Integrated Structure
Crack-Arresting Stringer
Static-Stress Rule
Fracture Toughness Rule
Stress Intensity Factor
