民机雷达罩的抗鸟撞非线性力学行为仿真研究
Simulation study of nonlinear mechanical behavior of civil aircraft radome against bird strike
庞小强 1朱小龙 1荆雲杰 2龙舒畅 2唐维 1王焰 1刘卫1
作者信息
- 1. 中航成飞民用飞机有限责任公司,四川 成都 610092
- 2. 华南理工大学 土木与交通学院,广东 广州 510641
- 折叠
摘要
为了研究某民机雷达罩结构的抗鸟撞性能,基于ABAQUS建立了采用纤维增强非线性动力本构的雷达罩模型,综合考虑了复合材料与泡沫芯材的非线性行为与应变率效应.该文通过仿真模拟,分析了面板材料(包括复合材料和泡沫芯材)是否考虑非线性与应变率效应、夹芯结构铺层顺序与角度,以及前后面板厚度比对结构鸟撞响应失效行为的影响.结果表明:纤维增强复合材料的非线性动力本构能够很好地描述雷达罩复合材料结构在动态加载下的应变率强化效应.不同铺层角度下的雷达罩面板的破坏形式基本相同,其最主要的失效形式是基体拉伸破坏,而前后面板铺层顺序为[0/-45/45]/[45/-45/0],且前后面板层厚比接近 1 的模型具有较好的吸能效果.
Abstract
In order to study the bird strike resistance of a civil aircraft radome structure,a radome model using fiber-reinforced nonlinear dynamic constitutive is established based on ABAQUS.The constitutive model comprehensively considers the nonlinear behavior and strain rate effect of composite materials and foam materials.In this paper,we consider the nonlinear and strain rate effects of the panel materials(including composites and foam),the layer sequences and angles of the sandwich structure,and the thickness ratio of the front and rear panels.The results show that the nonlinear dynamic constitutive of fiber-reinforced composites can well describe the strain rate strengthening effect of the radome composite structure under shock loading.The damage mechanisms of radome panels of different layer angles are similar,and the primary failure mechanism is matrix tensile damage.The model with the panel layer sequence of[0/-45/45]/[45/-45/0]and a near-one front and rear panel thickness ratio has higher energy absorption capacity.
关键词
复合材料/雷达罩/鸟撞/数值模拟/非线性分析/本构模型Key words
composite materials/radome/bird strike/numerical simulation/nonlinear analysis/constitutive model引用本文复制引用
出版年
2024
国家科技期刊平台
NSTL
万方数据