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由于机翼为主承力结构,蒙皮修理主要采用机械连接修理方式。本文针对民机复合材料机翼上蒙皮壁板结构的离散源损伤开展了修理方案设计、试验验证及分析研究。首先,根据损伤类型和上蒙皮壁板的传载特性,设计了机械连接金属补片修理方案,并制造了包括损伤和损伤修理两类试验件,进行了试验验证,修理后承载能力提高了133%,能够满足一般民机复合材料机翼蒙皮设计许用应变的要求。但该修理方法使得试验件修理区域较原结构刚度偏大,造成试验件修理区域承载高于两侧长桁。另外,修理补片会造成试验件提前出现载荷偏心弯曲。虽然修理补片的刚度和强度还有待进一步优化,但该修理方法依然可为今后民机复合材料机翼修理方案的设计提供参考。
Due to the main bearing structure of the wing, skin repair mainly used mechanical connection repair. In this paper, the repair scheme design, test verification and analysis are carried out for the discrete source damage of the skin panels on the aircraft composite wing. First of all, according to the type of damage and the transmission characteristics of the upper skin panel, a mechanical repair scheme of the metal patch is designed and two types of test pieces including damage and damage repair are designed and tested. After the repair, the carrying capacity is improved 133%, to meet the general requirements of civil aircraft composite wing skin design allowable strain. However, the repair method makes the repair area of the test piece bigger than the original structure, resulting in the repair area of the test piece bearing the truss above the two sides. In addition, repairing the patch causes the test piece to appear eccentric in load ahead of time. Although the stiffness and strength of the repairing patch need to be further optimized, the repairing method can still provide a reference for the design of the wing repairing scheme of the civil aircraft composite in the future.