Volume 4, Issue 6, December 2019, Page: 164-168
Integrally Panel Strength Design Method of the Thick Skin for “T”
Yan Yabin, AVIC XAC Commercial Aircraft Co. Ltd, Xi'an, China
Yang Hualun, AVIC XAC Commercial Aircraft Co. Ltd, Xi'an, China
Received: Nov. 20, 2019;       Accepted: Dec. 5, 2019;       Published: Dec. 10, 2019
DOI: 10.11648/j.eas.20190406.15      View  67      Downloads  44
Abstract
Based on the design methodology of the integral panel in the "aircraft design manual", the structure with the higher load-carrying capacity can be obtained under the optimal design area ratio. However, the determination of the of the separation surface location between the skin and the stringer is great obstacle during the actual design work. In this paper, some research works have been done to solve this problem. For the T-shaped integral panel with skin thickness ranging from 4mm-6mm, the position of a separating surface has been determined, and the area ratio of the skin to the stringer has been determined. At the same time, the optimal design area ratio of the skin to the stringer is obtained by calculation and experimental verification under the condition that the structural quality is certain and the maximum unstable load is taken as the design objective. The 4mm-6mm-thickness skin T-shaped integral panel designed with this area ratio has the strongest ability to bear axial compression load and the smallest structure weight. This paper makes up some defects of the integral panel design in the data, provides some basic data support for the majority of aircraft designers, and facilitates the engineering designers to carry out fine design work and improve the quality of aircraft design.
Keywords
T-shaped Integral Panels, The Ratio of the Area, Axial Compression Load
To cite this article
Yan Yabin, Yang Hualun, Integrally Panel Strength Design Method of the Thick Skin for “T”, Engineering and Applied Sciences. Vol. 4, No. 6, 2019, pp. 164-168. doi: 10.11648/j.eas.20190406.15
Copyright
Copyright © 2019 Authors retain the copyright of this article.
This article is an open access article distributed under the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0/) which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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