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为了获取增压载荷作用下机身蒙皮疲劳分析部位较为精确的应力分布,结合某机型机身等直段结构,采用NASTRAN有限元分析软件,在总体有限元模型基础上,对局部区域进行网格细化,建立了细节有限元模型,给出了窗周区域载荷施加的简化处理方法,获得了机身典型壁板区域以及窗周区域蒙皮应力分布规律,并将典型壁板区域某截面细节有限元模型分析结果与试验测试结果进行了比较,结果表明,两者数据吻合较好。最后,提出一种用于疲劳强度分析的蒙皮细节应力分布获取方法,采用该方法能够类比获取同一机型同类结构蒙皮细节应力分布。
In order to get a more accurate stress distribution of the body fatigue analysis part under the action of supercharging load, the NASTRAN finite element analysis software was used in combination with the straight section structure of a fuselage. Based on the overall finite element model, A detailed finite element model is established and a simplification approach of load applied in the window area is given. The stress distribution rules of the typical panel area and the skin area in the window area are obtained, and the typical panel area The results of the finite element analysis of the section details and the test results are compared. The results show that the two data agree well with each other. Finally, a new method for obtaining the stress distribution of the skin in fatigue strength analysis is proposed. By using this method, the detailed stress distribution of the skin of the same type can be obtained by analogy.