Integrally Panel Strength Design Method of the Thick Skin for “T”

Yan Yabin; Yang Hualun

doi:doi:10.11648/j.eas.20190406.15

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Integrally Panel Strength Design Method of the Thick Skin for “T”

Yan Yabin, Yang Hualun

Published in Engineering and Applied Sciences (Volume 4, Issue 6)

Received: 20 November 2019 Accepted: 5 December 2019 Published: 10 December 2019

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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.

Published in	Engineering and Applied Sciences (Volume 4, Issue 6)
DOI	10.11648/j.eas.20190406.15
Page(s)	164-168
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2019. Published by Science Publishing Group

Keywords

T-shaped Integral Panels, The Ratio of the Area, Axial Compression Load

References

[1]	General editorial board of aircraft design manual. Aircraft design manual (volume 10) structural design [M], aerospace industrial press, 2001 (in Chinese).
[2]	Yan yabin, Chen qunzhi, wang jianbang, et al. Design method for axial compression strength of integral stiffened wall panel [J]. China surface engineering, 2013, 26 (2): 102-106 (in Chinese).
[3]	General editorial board of aircraft design manual. Aircraft design manual (volume 9) load, strength and stiffness [M]. Aviation industry press. 2001 (in Chinese).
[4]	Pu chunyu, zhang yining. Optimal design of typical stiffened plate [J]. Aircraft design. 2003 (04) (in Chinese).
[5]	Cui degang. Structural stability design manual [M]. Beijing: aviation industry press, 1996. (in Chinese).
[6]	Bushnell, D., “Theoretical Basis of the PANDA Computer Program for Preliminary Design of Stiffened Panels Under Combined In-plane Loads,” Computers and Structures, Vol. 27, No. 4, 1987, pp. 541–563.
[7]	Xu Jian; Zhu Shuhua; Tong Mingbo; stability analysis of stiffened panel under different boundary conditions j; Aeronautical Computing Technology. 2012 (06). (in Chinese).
[8]	Sun weimin, tong mingbo, dong dengke, li xinxiang. Experimental study on post-buckling stability of stiffened panel under axial compression [J]. Experimental mechanics, 2008 (04) (in Chinese).
[9]	Liao jianghai, Chen xianmin, dong dengke. Stability test and analysis of integral stiffened wall plate under axial pressure [J]. Structural strength research, 2014, 2nd issue. (in Chinese).
[10]	Zhao bin et al. Study on the overall buckling ultimate bearing capacity of stiffened wall panels [J]. Journal of mechanical science and technology, 2011, (12). (in Chinese).
[11]	YU Ming, LING Xiaotao, SHI Jinsong. Stability analysis and test verification of stiffened panel with large cutout [J]. Aeronautical Science & Technology, 2015, 26 (03): 62-66.
[12]	Mu Penggang, Wan Xiaopeng, Zhao Meiying. A study of the stability of composite stiffened plates [J]. Mechanical Science and Technology for Aerospace Engineering, 2009, 28 (9): 1190―1193. (in Chinese).
[13]	Liu bin, zhang bao, sun qin. Study on the overall buckling ultimate bearing capacity of stiffened wall panels [J]. Journal of mechanical science and technology, 2011, 12. (in Chinese).
[14]	Wang haiyan, tong xianxin. Discussion on calculation method of bearing capacity of axial compression stiffened wall plate [J]. Progress of aviation engineering, 2012 (03). (in Chinese).
[15]	MATTHIAS H, PETER H. A new analysis model for the effective stiffness of stiffened metallic panels under combined compression and shear stress [J]. Aerospace Science and Technology, 2006, 10 (4): 316-326.
[16]	YAN yabin, YANG hualun Integrally Stiffened Panel Strength Design Method of the Thick Skin for “T” [J]. Journal of Nanjing University Aeronautics & Astronautics, 2019, 51 (1): 30-34 (in chinese).
[17]	YAN yabin, Ding Wei. The strength design for thin skin of integral plate under compression load [J]. Advances in Aeronautical science and Engineering, 2019, 10 (SI): 30-3462-66 (in chinese).

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APA Style

Yan Yabin, Yang Hualun. (2019). Integrally Panel Strength Design Method of the Thick Skin for “T”. Engineering and Applied Sciences, 4(6), 164-168. https://doi.org/10.11648/j.eas.20190406.15

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ACS Style

Yan Yabin; Yang Hualun. Integrally Panel Strength Design Method of the Thick Skin for “T”. Eng. Appl. Sci. 2019, 4(6), 164-168. doi: 10.11648/j.eas.20190406.15

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AMA Style

Yan Yabin, Yang Hualun. Integrally Panel Strength Design Method of the Thick Skin for “T”. Eng Appl Sci. 2019;4(6):164-168. doi: 10.11648/j.eas.20190406.15

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@article{10.11648/j.eas.20190406.15,
  author = {Yan Yabin and Yang Hualun},
  title = {Integrally Panel Strength Design Method of the Thick Skin for “T”},
  journal = {Engineering and Applied Sciences},
  volume = {4},
  number = {6},
  pages = {164-168},
  doi = {10.11648/j.eas.20190406.15},
  url = {https://doi.org/10.11648/j.eas.20190406.15},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.eas.20190406.15},
  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.},
 year = {2019}
}

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TY  - JOUR
T1  - Integrally Panel Strength Design Method of the Thick Skin for “T”
AU  - Yan Yabin
AU  - Yang Hualun
Y1  - 2019/12/10
PY  - 2019
N1  - https://doi.org/10.11648/j.eas.20190406.15
DO  - 10.11648/j.eas.20190406.15
T2  - Engineering and Applied Sciences
JF  - Engineering and Applied Sciences
JO  - Engineering and Applied Sciences
SP  - 164
EP  - 168
PB  - Science Publishing Group
SN  - 2575-1468
UR  - https://doi.org/10.11648/j.eas.20190406.15
AB  - 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.
VL  - 4
IS  - 6
ER  -

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Author Information

Yan Yabin

AVIC XAC Commercial Aircraft Co. Ltd, Xi'an, China
Yang Hualun

AVIC XAC Commercial Aircraft Co. Ltd, Xi'an, China

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Plain Text BibTeX RIS

APA Style

Yan Yabin, Yang Hualun. (2019). Integrally Panel Strength Design Method of the Thick Skin for “T”. Engineering and Applied Sciences, 4(6), 164-168. https://doi.org/10.11648/j.eas.20190406.15

Copy | Download

ACS Style

Yan Yabin; Yang Hualun. Integrally Panel Strength Design Method of the Thick Skin for “T”. Eng. Appl. Sci. 2019, 4(6), 164-168. doi: 10.11648/j.eas.20190406.15

Copy | Download

AMA Style

Yan Yabin, Yang Hualun. Integrally Panel Strength Design Method of the Thick Skin for “T”. Eng Appl Sci. 2019;4(6):164-168. doi: 10.11648/j.eas.20190406.15

Copy | Download

@article{10.11648/j.eas.20190406.15,
  author = {Yan Yabin and Yang Hualun},
  title = {Integrally Panel Strength Design Method of the Thick Skin for “T”},
  journal = {Engineering and Applied Sciences},
  volume = {4},
  number = {6},
  pages = {164-168},
  doi = {10.11648/j.eas.20190406.15},
  url = {https://doi.org/10.11648/j.eas.20190406.15},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.eas.20190406.15},
  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.},
 year = {2019}
}

Copy | Download

TY  - JOUR
T1  - Integrally Panel Strength Design Method of the Thick Skin for “T”
AU  - Yan Yabin
AU  - Yang Hualun
Y1  - 2019/12/10
PY  - 2019
N1  - https://doi.org/10.11648/j.eas.20190406.15
DO  - 10.11648/j.eas.20190406.15
T2  - Engineering and Applied Sciences
JF  - Engineering and Applied Sciences
JO  - Engineering and Applied Sciences
SP  - 164
EP  - 168
PB  - Science Publishing Group
SN  - 2575-1468
UR  - https://doi.org/10.11648/j.eas.20190406.15
AB  - 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.
VL  - 4
IS  - 6
ER  -

Copy | Download