摘要
整体加筋板被广泛用于飞机机身和机翼结构设计,因此需要准确地预计其在轴压载荷作用下的承载能力。在研究整体加筋破坏试验的基础上,提出了轴压承载能力计算改进的Johnson-Euler方程。利用目前工程中常用的3类(T、工和Z字形)15件机身机翼整体壁板试验件,对其适用性进行了验证。结果表明,所给出改进的Johnson-Euler方程,可以较为准确地预计整体加筋板破坏载荷,相对误差绝对值都不大于12%,满足飞机设计部门对整体加筋板强度设计的需求,研究结果为飞机设计人员对整体壁板强度设计提供参考。
Integrally stiffened panels are widely used in the fuselage and wing design.It is important to predict load-carrying capacity under axial compression loads.Based on the investigation of integrally stiffened panel tests,an improved Johnson-Euler equation is put forward to evaluate the failure loads of integrally stiffened panels and its applicability is verified by three kinds of integrally stiffened panels with T,I and Z shape of 15 test specimens.The results show the proposed improved Johnson-Euler equation can be used to calculate failure loads of integrally stiffened panels accurately,and the relative errors are less than 12 percent for all the test specimens.The results of the paper will be beneficial to engineers who design integrally stiffened panels in compression.
作者
吴存利
张国凡
聂小华
万春华
郭瑜超
WU Cunli;ZHANG Guofan;NIE Xiaohua;WAN Chunhua;GUO Yuchao(Aircraft Strength Research Institute of China,Xi’an 710065,China)
出处
《飞机设计》
2022年第1期48-52,共5页
Aircraft Design
关键词
整体壁板
改进Johnson-Euler方程
承载能力
压损
轴压
integrally stiffened panel
improved Johnson-Euler equation
load carrying capacity
crippling stress
axial compression
