直升机尾梁蜂窝夹层结构四点弯曲试验

王佳敏; 门坤发; 王刚; 宋瑶; 曹金华

直升机尾梁蜂窝夹层结构四点弯曲试验

1. 航空工业哈尔滨飞机工业集团有限责任公司;
2. 陆军装备部驻哈尔滨地区航空军事代表室

详细信息

作者简介:
王佳敏(1992-),女,汉族,硕士研究生,工程师,主要研究方向:飞机结构疲劳强度与损伤容限分析研究

中图分类号: V275.1
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出版历程
- 收稿日期: 2021-02-22
- 刊出日期: 2021-06-29

Four-point Bending Test for Honeycomb Sandwich Structure of Helicopter Tail Boom

1. Aviation Industry Harbin Aircraft Industry Group Co.,Ltd.;
2. Aviation Military Representative Office of Army Equipment Department in Harbin

摘要

摘要: 对民用直升机尾梁蜂窝夹层结构进行了弯曲加载试验,应用四点弯曲的加载方式分析考核区的纯弯曲性能。设计了一种试验件的加强方式以防止加载区提前发生破坏,并对某型直升机尾梁封边框处使用不同胶膜的蜂窝夹层结构进行切割和修理来制备试验件,通过试验对直升机尾梁蜂窝区的界面连接强度与45°封边框处使用不同胶膜的相关性进行了分析。对比分析结果表明,封边框使用膨胀胶膜降低了蜂窝区夹层结构的弯曲性能,其中在内面板加载,弯曲破坏值降低了4.68%;反面加载,弯曲破坏值降低了3.27%。试验结果表明,无损检测未发现脱粘的蜂窝区,面板与芯子存在弱连接。
- 尾梁 /
- 蜂窝夹层结构 /
- 膨胀胶膜 /
- 封边框
Abstract: A failure mechanism of civil helicopter tail boom under bending load is studied by four-point bending test. The tail boom skin with different adhesive films of a certain type of helicopter is selected to prepare test pieces for four-point bending test,and a strengthening method of specimens is designed to avoid undesirable failure. The interface strength of sandwich’s core and face between different films at 45° ramp close frame is studied. The test results indicate that the usage of intumescent film in 45° ramp close frame can reduce the bending performance of the sandwich area. Compared with the specimens used Redux 322,the bending failure value reduced 4. 68% which loading at inner face,and loading at the outer face reduced 3. 27%. That means kissing bonding exists between the face and the core at the area where debonding cannot be found by non-destructive testing.
- tail boom /
- honeycomb sandwich structure /
- intumescent /
- close frame

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