飞机机身壁板结构压损稳定性研究

Investigations on crippling of fuselage panel structure

本文旨在通过对比飞机中广泛运用的机身壁板结构的压损稳定性试验和“板元法”[1]分析结果,得出航空设计中常用的工程算法“板元法”的保守量,供航空设计师参考.本文选取常用铝合金长桁进行压损稳定性试验,选取了“Z”形和“T”形两种飞机设计中常用的型材,而每种截面又选用了两种不同的材料,同时采用板元法对此进行理论分析,对比试验结果和板元法分析结果,最终发现：对于单根长桁, “板元法”算法具有10％～1 5％左右的保守量,而对于组合长桁, “板元法”保守量则要降低,大约为3％ ～ 10％左右.

This research focused on crippling of fuselage panel structure. By comparing the results from test and the plate element method. The conserved quantity can be referenced by aircraft designers. The material of the stringers for the test is aluminum alloy. Each stringer has two sections, Z and T. Also each section has two types material. At the same time, using the plate element method to analysis all the stringers. The results shown that, if there is only one stringer in the panel , by the plate element method, it has about 10%-15% conserved quantity： if there are the stringers in the panel, it has about 3%-10% conserved quantity.