摘要
飞机机身和机翼结构多采用中长加筋板,中长加筋板在轴压载荷作用下的破坏载荷一直是工程中研究的热点;目前中长加筋板破坏载荷计算多采用Johnson-Euler方程,涉及到蒙皮有效宽度计算。对国内外常用的有效宽度计算方法进行分析,说明其产生的根源,并通过机身加筋板试验结果对其适应性进行验证。结果表明:对于薄蒙皮铆接Z型机身加筋板破坏载荷计算,本文介绍的有效宽度计算方法都能使计算误差控制在10%,可为飞机设计人员对轴压加筋板设计提供帮助。
It is well known that the fuselage and wing mainly consist of thin-skin stiffened panels and the failure load of stiffened panels is hot topic in aircraft engineering.Johnson-Euler equation is used to evaluate the failure loads,thus the effective width computation of skin needs to be determined.Several kinds of methods to calculate the effective width of skin are analyzed to quest for its origin,and their applicability is verified with test results of thin-skin stiffened panel.The results show that,the calculation errors of the effective width calculation methods are less than 10%for the calculation of riveting Z-typed fuselage stiffened panel failure load,and the methods can be helpful to engineers who design thin-skin stiffened panels in compression.
作者
吴存利
聂小华
WU Cunli;NIE Xiaohua(Computation Structure Technique&Simulation Center,Aircraft Strength Research Institute of China,Xi’an 710065,China)
出处
《航空工程进展》
CSCD
2020年第3期387-393,407,共8页
Advances in Aeronautical Science and Engineering
