摘要
以NACA2412为基准翼型设计充气弹翼,采用柔性蒙皮应力分析理论并根据弹翼蒙皮材料强度极限理论建立考虑分布质量影响的改进应力表达模型,据此得到柔性薄膜弹翼允许充气压力范围。分析结果发现:柔性弹翼充气单元尺寸越小,相应的充气压力允许范围越大。采用ABAQUS/CAE软件以不可压缩壳单元仿真柔性充气弹翼在不同充气压力条件下的变形情况,发现非对称翼型充气后中间下凹的翘曲方式并确定柔性蒙皮的危险点,利用翼面典型线分析了充气翼局部力学变形特性。进一步对充气弹翼进行表面覆膜改进分析,获得了良好的结构力学性能改进效果。
Based on NACA2412 airfoil,the improved stress expression model established by considering the influence of distribution mass can achieve the allowable range of inflation pressure of the flexible film wings. The results show that smaller the size of the flexible wing inflatable units are,the greater the allowable range of the inflation pressure can be. ABAQUS/CAE software was used for simulating the stress and deformation of flexible aerated wing under different inflation pressure conditions. The unique way of warping of asymmetric airfoil after inflating was found. The risk points of flexible skin were determined. The typical lines were used to analyze the local mechanical properties of the inflatable wing. The improved inflatable wing with surface coating obtained a good effect of improving the structure mechanical properties.
作者
刘龙斌
贾逸聪
魏元
胡凡
张士峰
LIU Longbin;JIA Yicong;WEI Yuan;HU Fan;ZHANG Shifeng(College of Aeronautics and Astronautics,National University of Defense Technology,Changsha 410073,China)
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2018年第6期30-37,共8页
Journal of National University of Defense Technology
基金
国家自然科学基金资助项目(11802334)
国防科技大学校科研计划资助项目(ZK-16-03-33)
湖南省自然科学基金资助项目(2018JJ3591)
关键词
充气翼
变形分布
外覆膜改进
薄膜理论
inflatable wing
deformation distribution
outer film improvement
film theory
