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作 者:赵庆云 孙昂 黄宏 程思锐 张艳[2] ZHAO Qingyun;SUN Ang;HUANG Hong;CHENG Sirui;ZHANG Yan(AVIC Manufacturing Technology Institute,Beijing 100024,China;AVIC Shenyang Aircraft Design Research Insititute,Shenyang 110035,China)
机构地区:[1]中国航空制造技术研究院,北京100024 [2]航空工业沈阳飞机设计研究所,沈阳110035
出 处:《航空制造技术》2023年第16期104-110,123,共8页Aeronautical Manufacturing Technology
摘 要:针对研制的内锥衬套高锁螺栓进行性能试验,开展复合材料/金属双搭多钉连接接头静力和疲劳试验及接头失效分析。结果表明,研制的内锥衬套高锁螺栓抗拉、双剪、疲劳及冶金性能合格,拉伸断口显微特征为韧窝。复材/铝合金多排钉连接接头间隙配合钉载比例差为41%,干涉配合钉载分配比例差为34.7%(1.0%的相对干涉量下);复材/钛合金接头间隙配合钉载分配比例差为43.3%,干涉配合钉载分配比例差为37.7%(1.0%的相对干涉量下),干涉配合可以提高钉载分配的均匀性。复材/铝合金接头干涉配合的疲劳寿命约为间隙配合的1.7倍,复材/钛合金接头干涉配合的疲劳寿命约为间隙配合的3.4倍。间隙配合连接的断裂试样主裂纹萌生于孔壁和试件表面,干涉对孔壁有强化作用,其主裂纹萌生于试件表面孔角和孔壁。7050铝合金呈现解理和韧窝的混合特征,TA15显微显示为准解理断裂,存在少量等轴韧窝和河流花样。Sleeve taper-hi-bolts'performance,double lap joints'static strength and fatigue test were carried out,and failed joints were analyzed.The results show that sleeve taper-hi-bolts'tensile,double shear and fatigue performance are qualified,and tensile fracture surface shows characteristics of dimple.Proportional difference of the pin load distributions for clearance fit is 41% for composite laminates with aluminum plates,while 34.7% for 1.0% interference joints.For composite laminates with titanium plates,proportional difference of the pin load distributions for clearance fit is 43.3%,while 37.7% for 1.0% interference joints.The fatigue life of interference fit composite laminates with aluminum plates is 1.7 times that of clearance fit,while 3.4 times for composite laminates with titanium plates.The main crack of interference fit joints originates from the angle of the hole,and that of clearance fit joints originates from the hole wall.Fracture analysis shows that 7050 exhibits mixed-rupture characteristics of quasi-cleavage and dimples,while TA15 exhibits quasi-cleavage characteristics with equiaxed dimple and river pattern.
关 键 词:衬套 复合材料 螺栓连接 失效分析 干涉配合 钉载分配 疲劳寿命 断口
分 类 号:V215.5[航空宇航科学与技术—航空宇航推进理论与工程]
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