复合材料机翼壁板离散源损伤修理技术研究  

INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE

作　　者：陈向明[1] 张阿盈[1] 柴亚南[1] 刘红武[2] 王力立[1] 于飞[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,西安710065 [2]中航工业第一飞机设计研究院,西安710089

出　　处：《机械强度》2017年第3期551-556,共6页Journal of Mechanical Strength

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,针对民机复合材料机翼下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、有限元分析及改进设计研究。首先,根据损伤类型和下蒙皮壁板的传载特性,设计了机械连接金属补片修理方案,并制造了包括含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124%,能够满足一般民机复合材料机翼蒙皮设计许用应变。然后,建立了两类试验件的有限元模型,进行了进一步计算分析,通过对试验数据和计算结果的对比分析发现,原修理方案偏于保守,增加了结构重量成本。最后,经计算分析提出了三种改进的修理设计方案,改进后的修理构型II承载能力相对于原修理方案提高了4.7%,而结构重量降低了3.9%,该修理方法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 principle bearing structure of aircraft, wing skin is repaired by using mechanically fastened joints. In this paper, scheme design, experimental verification, finite element analysis and design improvement investigation of aircraft composite wing panel with discrete-source damage were carried out. Firstly, the specimen with discrete-source damage and the repaired which used fastened joint repair method were designed and manufactured. Experimental verification of scheme design was performed. Load-carrying capacity of the repaired specimen increases about 124% , compared to the unrepaired, which fully meet the design requirements. Then, for further analysis, two different specimens＇ FEM models were established. The results showed that the initial repaired scheme was conservative, and the cost of structure weight was increased. Finally, three improved design configurations were proposed, and the load-carrying capacity of configuration II increased by 4. 7% , its structure weight decreased by 3.9%. This repaired scheme provides reference for the repair design of aircraft 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 方案改进 

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]