摘要
应用非线性有限元计算技术研究了加筋壁板结构试验件在受压状态下的非线性变形及稳定性特性,所得到的结果与试验吻合。为真实模拟机翼中的加筋壁板结构在空气动力作用下的稳定性问题,又针对典型机翼模型进行了更为细致的非线性屈曲分析。最后,将两次模拟结果进行比较,给出了根据结构的加载响应曲线判断结构的屈曲类型、结构的屈曲临界点以及分析结构后屈曲承载能力的方法。
The stability analysis of the aircraft wall structure is one of the important parts in structural design. Based on the application of nonlinear finite element computational technique, we studied the nonlinear features and stability characteristics of the stiffened wall structure specimen under the press and the results showed a good agree- ment with the experimental results. In order to simulate the stability of a stiffened wall structure in the wings, a more detailed nonlinear buckling analysis for the wing model is carried out. Finally, the results of the two simula- tions are compared. A method for estimating the buckling type, buckling critical point and the loading capacity of postbuckling is proposed. The analytical method proposed in this paper is helpful for the stability buckling analysis in engineering.
出处
《机械科学与技术》
CSCD
北大核心
2008年第11期1301-1303,共3页
Mechanical Science and Technology for Aerospace Engineering
基金
航空科学基金项目(20060953013)资助
关键词
非线性有限元
加筋壁板结构
非线性屈曲
临界点
后屈曲
nonlinear finite element
stiffened wall structure
nonlinear buckling
critical point
postbuckling
