航空学报 > 2001, Vol. 22 Issue (3): 270-273

复合材料蜂窝夹芯结构修理后强度研究

汪海1, 陈秀华1, 郭杏林2, 任明法2   

  1. 1. 沈阳飞机设计研究所二部, 辽宁沈阳 110035;2. 大连理工大学力学系, 辽宁大连 116024
  • 收稿日期:2000-01-19 修回日期:2000-04-27 出版日期:2001-06-25 发布日期:2001-06-25

STRENGTH INVESTIGATION OF COMPOSITE HONEYCOMB STRUCTURES AFTER REPAIR

WANG Hai1, CHEN Xiu-hua1, GUO Xing-lin2, REN Ming-fa2   

  1. 1. Shenyang Aircraft Design Institute, Shenyang 110035, China;2. Dalian University of Technology, Dalian 116024, China
  • Received:2000-01-19 Revised:2000-04-27 Online:2001-06-25 Published:2001-06-25

摘要:

对复合材料蜂窝夹芯结构受损伤之后的几种典型修理方法及修理材料、修理工艺等内容进行了试验研究。试验件分别模拟伤及单侧面板的非穿透损伤和伤及双侧面板的穿透损伤,分别采用单侧挖补、单侧加衬挖补和双面贴补法进行修理,然后进行面内单向压缩试验。给出了复合材料蜂窝夹芯结构修理前后的刚度和强度变化规律。为了同试验结果进行对比,还采用 NASTRAN软件对典型的非穿透挖补修理件进行了三维有限元应力分析,计算结果与试验结果吻合较好。

关键词: 复合材料, 蜂窝, 修理, 强度, 有限元分析, 试验验证

Abstract:

A few methods, materials and techniques of repair on composite honeycomb sandwich structures after damages are investigated experimentally in this paper. The specimens are designed to simulate the one sided dig out repair, one sided bottom added repair and two sided bonded patch repair due to non penetrating and penetrated damages simultaneously. The authors also present the rule of changes of stiffness and strength of composite honeycomb sandwich before and after repair. In order to compare with those from experiments, the software NASTRAN was used in the 3 D finite element stress analysis on the typical non penetrating dig out repair specimen. The results from both computation and experiment indicate good agreement.

Key words: composite, honeycomb, r epair, st reng th, finite element analyses, ex periment al v alidat ion