摘要
根据复合材料的力学特性,结合有限元理论和工程经验,提出了一种计算复合材料加筋板结构后屈曲承载能力的工程简化理论与方法,并以复合材料J型加筋板计算模型为例,从工程角度说明了计算后屈曲承载能力的思路与公式.利用该方法通过算例计算,将计算结果与实验结果进行对比,发现该种复合材料加筋板稳定性计算方法可以解决后屈曲的几何非线性带来的计算难度,能保持较高的精度,并可用于飞机结构设计的实际应用中.
A project simplified theory and a method of calculating post-buckling loading capacity of com- posite stiffened panels based on the basic mechanics characters of composite materials were presented, which combining with FEM theory and engineering experience. Composite J-stiffened panels were taken as an exam- ple to illustrate thinking and computational formula of post-buckling analysis from the perspective of engineer- ing. The validity and effectiveness of the method were demonstrated with the experiment. It is shown that the computing method of stability loading capability can solve the geometric non-linear analysis of composite stiff- ened structure load capability and keep high accuracy faced in the aerostructure design.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2013年第4期494-497,共4页
Journal of Beijing University of Aeronautics and Astronautics
关键词
复合材料
加筋板
后屈曲
承载能力
composite materials
stiffened panels
post-buckling
loading capacity
