摘要
随着复合材料夹层结构在直升机上应用越来越广泛,其结构边设计变得极为重要,既要满足零件连接和气动外形设计要求,又要尽可能地实现轻量化设计目标。设计典型层压板元组件试验件,通过试验与理论相结合的方法,对SynCore胶膜材料进行了应用验证研究。结果表明:HC9823.1K20aero胶膜的元组件试验数据稳定可靠,用挤压强度44.8MPa可作为直升机复合材料夹层结构设计与强度校核的参考依据。
Sandwich composites are becoming more acceptable as primary components in the structure of helicopter,so the design of laminate zone is extremely important,not only need to meet the requirements of the design of part assemble and aerodynamic shape,but also to achieve the goal of the light weight design as possible.An investigation with experiment and analysis on typical laminate test article of SynCore film has been accomplished.The results show that the experiment data of HC 9823.1 K20 aero laminate is steady and reliable,take the extrusion strength of 44.8MPa could be the reference of the helicopter structure design and check analysis of sandwich composites.
作者
徐茂
唐义号
洪少波
Xu Mao;Tang Yihao;Hong Shaobo(China Helicopter Research and Development Institute,Tianjin 300300,China)
出处
《航空工程进展》
CSCD
2019年第A01期24-27,33,共5页
Advances in Aeronautical Science and Engineering
