复合材料层合板钝头体高能量低速冲击响应与损伤特性
Response and damage characteristics of composite laminates under high-energy wide-area blunt impact
邹君 1刘佳鑫 1王计真 2郭亚周 2李玲玲 3冯振宇3
作者信息
- 1. 中国民航大学 安全科学与工程学院,天津 300300
- 2. 中国飞机强度研究所,西安 710065
- 3. 民航航空器适航审定技术重点实验室,天津 300300
- 折叠
摘要
高能量大面积钝物冲击(HEWABI)会导致复合材料飞机结构内部发生严重损伤,但在机身外部几乎目视不可见,从而会对飞机运营安全带来较大的威胁.采用不同形状的刚性冲头和橡胶冲头对层合板进行高能量准静态加载试验,随后建立了基于连续介质损伤力学(CDM)的仿真分析模型.结果表明:建立的仿真分析模型可有效预测在刚性和橡胶冲头下的响应和损伤情况.当载荷达到 40 kN时,刚性冲头下的层合板会发生严重的分层损伤;而橡胶冲头在加载过程中发生大变形,降低了层合板的局部应力,直至 90 kN时仍未对层合板产生任何损伤.层合板损伤情况受刚性冲头形状影响较大,橡胶冲头形状则几乎无影响.
Abstract
High-energy wide-area blunt impact(HEWABI)can lead to severe internal damage to the composite aircraft,which is barely visible from the outside of fuselage and cause a significant threat to flight safety.High energy quasi-static loading tests were carried out on the laminates with different shapes of rigid impactors and rubber impactors,then the finite element simulation models based on continuum damage mechanics(CDM)were developed.The results show that the established simulation analysis models can effectively predict the response and damage of the laminated panels under rigid or rubber impactors.When the load reaches 40 kN,severe delamination damages will occur in the laminated panel for the rigid impactors.On the other hand,no damage can be observed at 90 kN for the rubber impactors,which can be attributed to the significant deformation of rubber impactors and the reduced local contact loads.The shape of rigid impactors has great effect on the damage to laminated panels,while the shape of the rubber impactors has almost no impact on the damages.
关键词
层合板/高能量大面积钝物冲击/橡胶冲击/冲击响应/损伤特性Key words
laminate/high-energy wide-area blunt impact/rubber impact/impact response/damage charac-teristics引用本文复制引用
基金项目
机械结构力学及控制国家重点实验室开放基金(MCMS-E-0522Y03)
中央高校项目(3122022099)
出版年
2024
NETL
NSTL
万方数据