基于碳纤维增强复合材料的柔性蒙皮性能研究  

Performance study of flexible skin based on the carbon fiber reinforced composite

作　　者：宁素娟[1] 王帮峰[1] 卢吉云[1] 陆孟雄[1] 

机构地区：[1]南京航空航天大学智能材料结构航空科技重点实验室,江苏南京210016

出　　处：《兵器材料科学与工程》2011年第1期5-9,共5页Ordnance Material Science and Engineering

基　　金：国家自然科学基金资助(10772081)

摘　　要：探索波纹式碳纤维增强复合材料作为变体机翼蒙皮的可行性,推导复合材料的密度、各相所占的分数、复合材料中的孔隙含量以及材料拉伸弹性模量的计算公式,研究结构纵向变形能力和横向承载能力。分析实验数据,并根据复合材料理论分析模型,得出试件理论拉伸曲线和三点弯曲载荷下的理论挠曲线,分别与实验数据进行比较。结果表明:复合材料中的孔隙含量小于1%,证明试件的有效性;弹性模量实验值与理论值误差约为5%;该结构有较好的纵向变形能力和横向承载能力,在弹性变形段内,理论曲线与测试曲线基本吻合,误差小于10%,证明波纹式碳纤维增强复合材料作为变体机翼蒙皮可行。This paper explored the feasibility of corrugated carbon fiber reinforced composite used as the morphing wings.The calculation formulas for the density of reinforced composite,the percentage of each phase,content of pore in reinforced composite and materials tensile elastic modulus were deduced.The longitudinal strain capacity and the transverse carrying capacity were studied,which laid a foundation for further study.According to the analysis of experimental data,and based on the theoretical model of composite,theoretical tensile curve of specimen and the theoretical deflection curves under 3-point bending load were obtained,then,comparison with experimental data was made respectively.The results of analysis show that the content of the pore in composite is less than 1%,which proves the effectiveness of the specimen;the error between experimental value and theoretical value of elastic modulus is about 5%.This structure has better longitudinal strain capacity and the transverse carrying capacity,theoretical curve and test curve fit basically in the elastic deformation section,the error is less than 10%,which proves that the corrugated carbon fiber reinforced composite used as the variant wings is feasible.

关 键 词：变体机翼 碳纤维增强复合材料 波纹式柔性蒙皮 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]