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为研究常用于飞机垂尾的复合材料加筋壁板的冲击疲劳特性,设计了该型加筋壁板多点冲击试验、高周疲劳试验及剩余压缩强度试验。讨论了不同冲击能量对筋条边缘冲击损伤的影响,及施加低应力水平的疲劳载荷后各冲击损伤区域的扩展情况,对比分析了疲劳对冲击后剩余压缩强度的影响。结果表明:40J能量冲击后的损伤面积和凹坑深度较大,C扫描损伤形貌很不规则。100万次低应力疲劳后主损伤区附近衍生出新损伤,导致压缩破坏时产生向上、下夹具扩展的裂痕。该型加筋壁板疲劳后破坏载荷保持率为95.6%,有较好的抗冲击疲劳能力,为加筋壁板耐久性及后屈曲设计提供了思路。
In order to study the impact fatigue properties of composite stiffened panels which are commonly used for aircraft tail, the multi-point impact test, high-cycle fatigue test and residual compressive strength test of the stiffened panel were designed. The impact of different impact energy on the impact damage of the edge of tendons and the expansion of each impact damage area under the fatigue load of low stress level are discussed. The effect of fatigue on the residual compressive strength after impact is analyzed. The results show that the damage area and pit depth of 40J energy impact are large, and the morphology of C-scan damage is irregular. A million new low-stress fatigue damage zone near the new derivative derived damage, resulting in compression damage up, the cracks under the fixture expansion. The fatigue damage load retention ratio of this type of stiffened wall was 95.6%, which had better impact fatigue resistance, which provided the idea for the durability and post-buckling design of stiffened wall.