复合材料加筋壁板修理后压缩性能试验研究  

Experimental Research on Compression Performance of Repaired Composite Stiffened Panel

作　　者：陈向明[1] 张阿盈[1] 王力立[1] 高敏[1] 

机构地区：[1]中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室,陕西西安710065

出　　处：《工程与试验》2017年第1期9-13,86,共6页Engineering and Test

摘　　要：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。Since the wing is the primary bearing structure of aircraft, wing skin is repaired by using mechanically fastened joint. In this paper, scheme design, experimental verification and analysis of composite wing panel with discrete source damage are carried out. Two kinds of specimen with discrete source damage and damage repaired by using fastened joint repair method are designed and manufactured. Then the experimental verification of scheme design is performed. Load- carrying capacity of the repaired specimen increases about 133%, compared to the unrepaired specimen, which fully meets the design requirements. The test results show that the load carried in the repaired region is higher than the stringer from two sides of the specimen, because the stiffness of the repaired region is larger than original panel. In addition, local bending of the repaired specimen is appeared, because the patch induced off-center load transfer. The stiffness and strength of the patch need to be further optimized, though the repaired scheme still provides reference for the repair design of composite wing panel with discrete source damage.

关 键 词：复合材料机翼 加筋壁板 离散源损伤 修理设计 试验研究 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]