Isogeometric analysis and design of variable-stiffness aircraft panels with multiple cutouts by level set method

被引：39

作者：

Hao, Peng ^{[1
]}

Liu, Chen ^{[1
]}

Liu, Xuanxiu ^{[1
]}

Yuan, Xiaojie ^{[1
]}

Wang, Bo ^{[1
]}

Li, Gang ^{[1
]}

Dong, Manhong ^{[2
]}

Chen, Liang ^{[3
]}

机构：

[1] Dalian Univ Technol, Dept Engn Mech, State Key Lab Struct Anal Ind Equipment, Dalian 116023, Peoples R China

[2] Beijing Inst Astronaut Syst Engn, Beijing 100076, Peoples R China

[3] Shenyang Aircraft Design & Res Inst, Shenyang 110035, Liaoning, Peoples R China

来源：

COMPOSITE STRUCTURES | 2018年 / 206卷

基金：

中国国家自然科学基金;

关键词：

Variable-stiffness aircraft panel; Cutout; Isogeometric method; Level set method; Gradient-based optimization; LAMINATED COMPOSITE PLATES; RESPONSE-SURFACE METHOD; BUCKLING ANALYSIS; FREE-VIBRATION; STIFFENED PANELS; FINITE-ELEMENTS; CONICAL SHELLS; CAD SURFACES; OPTIMIZATION; NURBS;

D O I：

10.1016/j.compstruct.2018.08.086

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

For composite panels with cutouts, curvilinear fiber path can adjust the in-plane stiffness distribution to increase the buckling resistance, but it results in huge computational cost for the buckling analysis when FEA is employed. In this study, variable-stiffness panels with cutouts are analyzed via isogeometric method, where cutouts are represented by the level set method. The method for suppressing artificial buckling modes is proposed to improve the prediction accuracy. Moreover, the analytical sensitivity is derived to facilitate fiber path optimization, and a new bi-level optimization framework considering manufacturing constraints is established. Finally, the proposed method is verified by variable-stiffness aircraft panel with multiple cutouts, which can not only provide an accurate prediction of buckling load, but also exhibit high convergence rate and low computational cost for fiber path optimization.

引用

页码：888 / 902

页数：15

共 55 条

[1] Large deflection and stresses in variable stiffness composite laminates with curvilinear fibres
Akhavan, Hamed
Ribeiro, Pedro
de Moura, M. F. S. F.
[J]. INTERNATIONAL JOURNAL OF MECHANICAL SCIENCES, 2013, 73 : 14 - 26
[2] Layer optimisation for maximum fundamental frequency of laminated composite plates for different edge conditions
Apalak, M. Kemal
Yildirim, Mustafa
Ekici, Recep
[J]. COMPOSITES SCIENCE AND TECHNOLOGY, 2008, 68 (02) : 537 - 550
[3] A simple approach to the numerical simulation with trimmed CAD surfaces
Beer, G.
Marussig, B.
Zechner, J.
[J]. COMPUTER METHODS IN APPLIED MECHANICS AND ENGINEERING, 2015, 285 : 776 - 790
[4] Isogeometric shell analysis: The Reissner-Mindlin shell
Benson, D. J.
Bazilevs, Y.
Hsu, M. C.
Hughes, T. J. R.
[J]. COMPUTER METHODS IN APPLIED MECHANICS AND ENGINEERING, 2010, 199 (5-8) : 276 - 289
[5] Design of variable-stiffness conical shells for maximum fundamental eigenfrequency
Blom, Adriana W.
Setoodeh, Shahriar
Hol, Jan M. A. M.
Gurdal, Zafer
[J]. COMPUTERS & STRUCTURES, 2008, 86 (09) : 870 - 878
[6] Chai GB, 1997, COMPOS STRUCT, V35, P357
[7] Free vibration of symmetrically laminated thick-perforated plates
Chen, CC
Kitipornchai, S
Lim, CW
Liew, KM
[J]. JOURNAL OF SOUND AND VIBRATION, 2000, 230 (01) : 111 - 132
[8] An efficient and robust rotational formulation for isogeometric Reissner-Mindlin shell elements
Dornisch, W.
Mueller, R.
Klinkel, S.
[J]. COMPUTER METHODS IN APPLIED MECHANICS AND ENGINEERING, 2016, 303 : 1 - 34
[9] Elastic buckling analysis of perforated thin-walled structures by the isoparametric spline finite strip method
Eccher, G.
Rasmussen, K. J. R.
Zandonini, R.
[J]. THIN-WALLED STRUCTURES, 2008, 46 (02) : 165 - 191
[10] A hierarchic family of isogeometric shell finite elements
Echter, R.
Oesterle, B.
Bischoff, M.
[J]. COMPUTER METHODS IN APPLIED MECHANICS AND ENGINEERING, 2013, 254 : 170 - 180

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