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Journal articles on the topic 'Curved panels'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

Lange, Jörg, Peter Groche, Stefan Schäfer, Sören Grimm, Mathias Moneke, Jakob Reising, and Marvin Kehl. "Curved Sandwich Panels." ce/papers 4, no. 2-4 (September 2021): 803–8. http://dx.doi.org/10.1002/cepa.1364.

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2

Ock, Jong-Ho. "Testing as-Built Quality of Free-Form Panels: Lessons Learned from a Case Study and Mock-up Panel Tests." Applied Sciences 11, no. 4 (February 5, 2021): 1439. http://dx.doi.org/10.3390/app11041439.

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Constructing free-form buildings is very complex due to the difficulty in fabricating the curved façade. To install the façade, the complex geometric shapes of the façade need to be divided into panels. The panels developed are classified into three categories in terms of their curvatures, i.e., planar, single-curved, double-curved panels. The quality of the curved façade is determined by the geometric difference between as-built and as-designed panel shapes. Among the three types of curved panels, the double-curved panel is very difficult to form, showing greater quality discrepancy than the other two panel types. Ensuring the as-built quality of the curved façade is for contractors. The main objective of this study is to enhance small/mid-size contractors’ capacity of managing the as-built quality of the double-curved panel. To meet the study objectives, a case study of a small free-form building and empirical mock-up tests of curved panels were performed and beneficial lessons for the contractors were identified through the tests. Among diverse materials, aluminum and glass-fiber-reinforced concrete (GFRC) were utilized for the mock-up tests. Three-dimensional laser scanning technology was employed to foster the as-built data of the case study project and the mocked-up double-curved panels. The data superimposition method was used to measure the deviation between the as-designed and the as-built data of the case study.

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3

Pany, C., and S. Parthan. "Axial Wave Propagation in Infinitely Long Periodic Curved Panels." Journal of Vibration and Acoustics 125, no. 1 (January 1, 2003): 24–30. http://dx.doi.org/10.1115/1.1526510.

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Propagation of waves along the axis of the cylindrically curved panels of infinite length, supported at regular intervals is considered in this paper to determine their natural frequencies in bending vibration. Two approximate methods of analysis are presented. In the first, bending deflections in the form of beam functions and sinusoidal modes are used to obtain the propagation constant curves. In the second method high precision triangular finite elements is used combined with a wave approach to determine the natural frequencies. It is shown that by this approach the order of the resulting matrices in the FEM is considerably reduced leading to a significant decrease in computational effect. Curves of propagation constant versus natural frequencies have been obtained for axial wave propagation of a multi supported curved panel of infinite length. From these curves, frequencies of a finite multi supported curved panel of k segments may be obtained by simply reading off the frequencies corresponding to jπ/kj=1,2…k. Bounding frequencies and bounding modes of the multi supported curved panels have been identified. It reveals that the bounding modes are similar to periodic flat panel case. Wherever possible the numerical results have been compared with those obtained independently from finite element analysis and/or results available in the literature.

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4

Zhou, Jian, Minglong Xu, and Zhichun Yang. "Nonlinear Flutter Response of Heated Curved Composite Panels with Embedded Macrofiber Composite Actuators." Advances in Materials Science and Engineering 2018 (December 26, 2018): 1–12. http://dx.doi.org/10.1155/2018/3103250.

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The nonlinear flutter response of heated curved composite panels with embedded macrofiber composite (MFC) actuators in supersonic airflow is investigated. Prescribed voltages are statically applied to the piezoelectric actuators, inducing a prestress field which results in an additional stiffness effect on the curved panel, and it will change the aeroelastic behavior of curved composite panels. The aeroelastic equations of curved composite panels with embedded MFC actuators are formulated by the finite element approach. The von Karman large deflection panel theory and the first-order piston theory aerodynamics are adopted in the formulation. The motion equations are solved by a fourth-order Runge–Kutta numerical scheme, and time history, phase portrait, Poincaré map, bifurcation diagram, and Lyapunov exponent are used for better understanding of the pre/postflutter responses. The results demonstrate that the nonlinear flutter response characteristics of the curved panel differs from those of the flat panels significantly, and the transverse displacement of the curved composite panels with embedded MFC actuators in the preflutter region shows a gradual static displacement; the chaotic motions occur directly after static motion because of the effect of the temperature elevation. The applied voltages can increase the critical dynamic pressure and change the bifurcation diagram of the curved composite panels with embedded MFC actuators, and the response amplitudes can be reduced evidently.

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5

SAHU, S. K., and A. V. ASHA. "PARAMETRIC RESONANCE CHARACTERISTICS OF ANGLE-PLY TWISTED CURVED PANELS." International Journal of Structural Stability and Dynamics 08, no. 01 (March 2008): 61–76. http://dx.doi.org/10.1142/s0219455408002557.

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The present study deals with the dynamic stability of laminated composite pre-twisted cantilever panels. The effects of various parameters on the principal instability regions are studied using Bolotin's approach and finite element method. The first-order shear deformation theory is used to model the twisted curved panels, considering the effects of transverse shear deformation and rotary inertia. The results on the dynamic stability studies of the laminated composite pre-twisted panels suggest that the onset of instability occurs earlier and the width of dynamic instability regions increase with introduction of twist in the panel. The instability occurs later for square than rectangular twisted panels. The onset of instability occurs later for pre-twisted cylindrical panels than the flat panels due to addition of curvature. However, the spherical pre-twisted panels show small increase of nondimensional excitation frequency.

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6

Shen, Hui-Shen, Yang Xiang, and Yin Fan. "Large amplitude vibration of doubly curved FG-GRC laminated panels in thermal environments." Nanotechnology Reviews 8, no. 1 (December 31, 2019): 467–83. http://dx.doi.org/10.1515/ntrev-2019-0042.

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Abstract A study on the large amplitude vibration of doubly curved graphene-reinforced composite (GRC) laminated panels is presented in this paper. A doubly curved panel is made of piece-wise GRC layers with functionally graded (FG) arrangement along the thickness direction of the panel. A GRC layer consists of polymer matrix reinforced by aligned graphene sheets. The material properties of the GRC layers are temperature dependent and can be estimated by the extended Halpin-Tsai micromechanical model. The modelling of the large amplitude vibration of the panels is based on the Reddy’s higher order shear deformation theory and the effects of the von Kármán geometric nonlinearity, the panel-foundation interaction and the temperature variation are included in the derivation of the motion equations of the panels. The solutions for the large amplitude vibration of the doubly curved FG-GRC laminated panels are obtained by applying a two-step perturbation approach. A parametric study is carried out to determine the influences of foundation stiffness, temperature variation, FG distribution pattern, in-plane boundary condition and panel curvature ratio on the natural frequencies and the nonlinear to linear frequency ratios of the doubly curved FG-GRC laminated panels.

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7

Wang, Chun, Xuan Ming Zhang, and Xiao Wang. "Scanning and Modeling of Large Thin-Walled Curved Surface Part." Advanced Materials Research 299-300 (July 2011): 810–15. http://dx.doi.org/10.4028/www.scientific.net/amr.299-300.810.

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The large sandwich structure composed of thin-walled aluminum alloy panels, and variable thickness of honeycomb or Polymethacrylimide (PMI) foam core is usually manufactured by pre-bonded forming process, that is pre-forming panels and sandwich core, and then curing adhesive them to be sandwich structure. Welding process of large thin-walled panel causes the panel surface to be irregular and have greater errors relative to the design surface. Simply CNC machining the sandwich core according to the design surface cannot guarantee an exact match sandwich core consistent with the panels. The actual topography of the panels must be scanned. It is proposed that the use of a new hand-held laser scanner, Handyscan to scan large thin-walled curved surface parts, of Geomagic software to handle the acquired point clouds and construct the surface model.

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8

Ballere, Ludovic, Philippe Viot, Laurent Guillaumat, and Jean-Luc Lataillade. "OS14-3-3 Residual tensile strength of impacted curved panels." Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics 2007.6 (2007): _OS14–3–3——_OS14–3–3—. http://dx.doi.org/10.1299/jsmeatem.2007.6._os14-3-3-.

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9

Szelag, Agata, Tadeusz Kamisiński, Mirosława Lewińska, Jarosław Rubacha, and Adam Pilch. "The Characteristic of Sound Reflections from Curved Reflective Panels." Archives of Acoustics 39, no. 4 (March 1, 2015): 549–58. http://dx.doi.org/10.2478/aoa-2014-0059.

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Abstract The paper presents the verification of a solution to the narrow sound frequency range problem of flat reflective panels. The analytical, numerical and experimental studies concerned flat panels, panels with curved edges and also semicircular elements. There were compared the characteristics of sound reflected from the studied elements in order to verify which panel will provide effective sound reflection and also scattering in the required band of higher frequencies, i.e. above the upper limit frequency. Based on the conducted analyzes, it was found that among some presented solutions to narrow sound frequency range problem, the array composed of panels with curved edges is the most preferred one. Nevertheless, its reflection characteristic does not meet all of the requirements, therefore, it is necessary to search for another solution of canopy which is effective over a wide frequency range.

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10

Shen, Hui-Shen, and X.-Q. He. "Large amplitude free vibration of nanotube-reinforced composite doubly curved panels resting on elastic foundations in thermal environments." Journal of Vibration and Control 23, no. 16 (December 16, 2015): 2672–89. http://dx.doi.org/10.1177/1077546315619280.

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A large amplitude vibration analysis is presented for nanocomposite doubly curved panels resting on elastic foundations in thermal environments. The doubly curved nanocomposite panels are studied with the consideration of different types of distributions of uniaxial aligned single-walled carbon nanotubes (SWCNTs). The material properties of the functionally graded carbon nanotube-reinforced composites (FG-CNTRCs) are assumed to be graded in the thickness direction according to linear distributions of the volume fraction of CNTs and are estimated through a micromechanical model. The motion equations are based on a higher order shear deformation theory and von Kármán strain-displacement relationships. The thermal effects are also included and the material properties of CNTRCs are assumed to be temperature-dependent. The motion equations are solved by a two-step perturbation approach to determine the nonlinear frequencies of the CNTRC doubly curved panel. The numerical illustrations cover small- and large-amplitude vibration characteristics of CNTRC doubly curved panels resting on Pasternak elastic foundations. The present solutions also highlight the effects of CNT volume fraction, temperature variation, foundation stiffness, panel curvature ratio as well as in-plane boundary conditions on the nonlinear free vibration behaviors of CNTRC doubly curved panels.

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11

Pottmann, Helmut, Alexander Schiftner, Pengbo Bo, Heinz Schmiedhofer, Wenping Wang, Niccolo Baldassini, and Johannes Wallner. "Freeform surfaces from single curved panels." ACM Transactions on Graphics 27, no. 3 (August 2008): 1–10. http://dx.doi.org/10.1145/1360612.1360675.

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12

Ganapathi, M., and T. K. Varadan. "Supersonic Flutter of Laminated Curved Panels." Defence Science Journal 45, no. 2 (January 1, 1995): 147–59. http://dx.doi.org/10.14429/dsj.45.4114.

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13

Ochinero, T. T., and M. W. Hyer. "Manufacturing Distortions of Curved Composite Panels." Journal of Thermoplastic Composite Materials 15, no. 2 (March 2002): 79–87. http://dx.doi.org/10.1177/0892705702015002445.

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14

Ballère, L., P. Viot, J. L. Lataillade, L. Guillaumat, and S. Cloutet. "Damage tolerance of impacted curved panels." International Journal of Impact Engineering 36, no. 2 (February 2009): 243–53. http://dx.doi.org/10.1016/j.ijimpeng.2008.03.004.

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15

Bidi, A., Gh Liaghat, and Gh Rahimi. "Impact Deformation of Curved Nanocomposite Panels." Iranian Journal of Science and Technology, Transactions of Mechanical Engineering 43, S1 (August 7, 2018): 551–58. http://dx.doi.org/10.1007/s40997-018-0177-6.

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16

Keshav, Vasanth, Shuvendu Narayan Patel, and Rajesh Kumar. "Stability and Failure Study of Suddenly Loaded Laminated Composite Cylindrical Panel." International Journal of Applied Mechanics 11, no. 10 (December 2019): 1950093. http://dx.doi.org/10.1142/s1758825119500935.

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In this paper, nonlinear dynamic buckling of laminated composite cylindrical panels subjected to in-plane impulsive compressive load is studied along with the failure analysis. Balanced and symmetric angle-ply laminated composite curved panels are considered. Convergence study is performed, and results are validated with the results from the existing literature, and then the dynamic buckling loads are calculated. The failure index of laminated composite curved panel is also calculated to check the precedence of first ply failure load over nonlinear dynamic buckling load. The effect of aspect ratio, loading function, and radius of curvature is studied. The analysis is carried out using finite element method. It is observed that the first ply failure for balanced and symmetric angle-ply laminated composite curved panels occurs after the panel has buckled due to dynamic impulse loads.

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17

Amir, Mohammad, and Mohammad Talha. "Influence of Large Amplitude Vibration on Geometrically Imperfect Sandwich Curved Panels Embedded with Gradient Metallic Cellular Core." International Journal of Applied Mechanics 12, no. 09 (November 2020): 2050099. http://dx.doi.org/10.1142/s1758825120500994.

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This study investigates the influence of large amplitude vibration on geometrically imperfect sandwich curved panels embedded with gradient metallic cellular (GMC) core using an efficient nonlinear finite element formulation based on higher-order shear deformation theory (HSDT). The cores of the sandwich curved panels are assumed to have three distinct porosity distributions. The material properties of the sandwich curved panel’s GMC core layer vary in the thickness direction as a function of porosity coefficient and mass density. The present nonlinear finite element model is validated with limited results available in the open literature, and few new results are also computed that can be used as a benchmark solution. The influence of porosity coefficient, porosity distribution type, amplitude ratio, imperfection amplitude, and curvature ratio on the free vibration characteristics of the geometrically imperfect sandwich curved panels with the GMC core are studied in detail.

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18

Mahapatra, Trupti Ranjan, Vishesh Ranjan Kar, and Subrata Kumar Panda. "Large amplitude bending behaviour of laminated composite curved panels." Engineering Computations 33, no. 1 (March 7, 2016): 116–38. http://dx.doi.org/10.1108/ec-05-2014-0119.

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Purpose – The purpose of this paper is to analyse the nonlinear flexural behaviour of laminated curved panel under uniformly distributed load. The study has been extended to analyse different types of shell panels by employing the newly developed nonlinear mathematical model. Design/methodology/approach – The authors have developed a novel nonlinear mathematical model based on the higher order shear deformation theory for laminated curved panel by taking the geometric nonlinearity in Green-Lagrange sense. In addition to that all the nonlinear higher order terms are considered in the present formulation for more accurate prediction of the flexural behaviour of laminated panels. The sets of nonlinear governing equations are obtained using variational principle and discretised using nonlinear finite element steps. Finally, the nonlinear responses are computed through the direct iterative method for shell panels of various geometries (spherical/cylindrical/hyperboloid/elliptical). Findings – The importance of the present numerical model for small strain large deformation problems has been demonstrated through the convergence and the comparison studies. The results give insight into the laminated composite panel behaviour under mechanical loading and their deformation behaviour. The effects of different design parameters and the shell geometries on the flexural responses of the laminated curved structures are analysed in detailed. It is also observed that the present numerical model are realistic in nature as compared to other available mathematical model for the nonlinear analysis of the laminated structure. Originality/value – A novel nonlinear mathematical model is developed first time to address the severe geometrical nonlinearity for curved laminated structures. The outcome from this paper can be utilized for the design of the laminated structures under real life circumstances.

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19

Panda, H. S., S. K. Sahu, and P. K. Parhi. "Thermal Effects on Parametric Instability of Delaminated Woven Fabric Composite Curved Panels." International Journal of Structural Stability and Dynamics 17, no. 01 (January 2017): 1750008. http://dx.doi.org/10.1142/s0219455417500080.

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The present study highlights the parametric instability characteristics of delaminated woven fabric composite curved panels under in-plane harmonic loadings exposed to the thermal environment. The equation of motion of the delaminated curved panel is reduced to a system of Mathieu–Hill equations with periodic coefficients. The development of the region of instability arises from Floquet’s theory and the solution is obtained using Bolotin’s approach by the finite element method (FEM). An eight-noded isoparametric finite element is developed considering the effects of delamination and thermal exposure of the composite panel for predicting the dynamic instability regions (DIRs). The first-order shear deformation theory (FSDT) is used for all the numerical computations. The results predicted from the present finite element analysis are validated with those available in the literature. The effects of static load factor, curvature, delamination, temperature and boundary conditions on the DIRs of curved composite panels are investigated. Noteworthy effects of these parameters on the parametric instability of composite panels are witnessed and discussed.

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20

Singh, A. V., and V. Kumar. "On Free Vibrations of Fiber Reinforced Doubly Curved Panels, Part 2: Applications." Journal of Vibration and Acoustics 120, no. 1 (January 1, 1998): 295–300. http://dx.doi.org/10.1115/1.2893820.

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The applications of a Ritz-type numerical scheme, in which the displacement fields are prescribed by Bezier surface patches, are presented for the analysis of doubly curved laminated open panels. The fundamental strain-displacement relations and energy expressions are developed in orthogonal curvilinear coordinates. The higher-order shear deformation theory and the effects of rotary inertia are considered in the formulation. Good comparisons of the results are obtained for a class of open panels. For example, values of the natural frequencies of open cylindrical and spherical panels made of isotropic material are compared with the results from the finite element analysis. Cases of cantilevered and simply supported angle-ply laminated cylindrical panel and a fully clamped isotropic conical panel are also examined for comparison with the available sources in the literature. In addition, the natural frequencies are presented for angle-ply laminated circular cylindrical, conical and spherical panels and the influence of the fiber orientation on the fundamental frequency is also examined for the angle ply having one, two [φ/−φ] and four [φ/−φ/φ/−φ] laminae arrangements.

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21

Elumalai, E. S., G. Krishnaveni, R. Sarath Kumar, D. Dominic Xavier, G. Kavitha, S. Seralathan, V. Hariram, and T. Micha Premkumar. "Buckling analysis of stiffened composite curved panels." Materials Today: Proceedings 33 (2020): 3604–11. http://dx.doi.org/10.1016/j.matpr.2020.05.662.

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22

Martins, J. P., Darko Beg, Franc Sinur, L. Simões da Silva, and A. Reis. "Imperfection sensitivity of cylindrically curved steel panels." Thin-Walled Structures 89 (April 2015): 101–15. http://dx.doi.org/10.1016/j.tws.2014.12.014.

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23

Asnafi, Nader. "On springback of double-curved autobody panels." International Journal of Mechanical Sciences 43, no. 1 (January 2001): 5–37. http://dx.doi.org/10.1016/s0020-7403(99)00101-0.

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24

Pany, Chitaranjan, and S. Parthan. "Flutter analysis of periodically supported curved panels." Journal of Sound and Vibration 267, no. 2 (October 2003): 267–78. http://dx.doi.org/10.1016/s0022-460x(02)01493-1.

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25

Sheinman, Izhak, and Yeoshua Frostig. "Postbuckling analysis of stiffened Laminated Curved Panels." Journal of Engineering Mechanics 116, no. 10 (October 1990): 2223–36. http://dx.doi.org/10.1061/(asce)0733-9399(1990)116:10(2223).

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26

Sivasubramonian, B., A. M. Kulkarni, G. Venkateswara Rao, and A. Krishnan. "FREE VIBRATION OF CURVED PANELS WITH CUTOUTS." Journal of Sound and Vibration 200, no. 2 (February 1997): 227–34. http://dx.doi.org/10.1006/jsvi.1996.0637.

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27

Ljubinkovic, Filip, João Pedro Martins, Helena Gérvasio, Luís Simões da Silva, and Carlos Leitao. "EXPERIMENTAL ANALYSIS OF UNSTIFFENED CYLINDRICALLY CURVED PANELS." ce/papers 1, no. 4 (December 2017): 448–57. http://dx.doi.org/10.1002/cepa.544.

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28

Pidaparti, R. M. V. "Flutter analysis of cantilevered curved composite panels." Composite Structures 25, no. 1-4 (January 1993): 89–93. http://dx.doi.org/10.1016/0263-8223(93)90154-i.

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29

Chun, Lu, and K. Y. Lam. "Dynamic analysis of clamped laminated curved panels." Composite Structures 30, no. 4 (January 1995): 389–98. http://dx.doi.org/10.1016/0263-8223(94)00056-5.

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30

Muc, A., and A. Stawiarski. "Location of delaminations in curved laminated panels." Composite Structures 133 (December 2015): 652–58. http://dx.doi.org/10.1016/j.compstruct.2015.07.030.

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31

SAHU, S. K., and P. K. DATTA. "DYNAMIC STABILITY OF CURVED PANELS WITH CUTOUTS." Journal of Sound and Vibration 251, no. 4 (April 2002): 683–96. http://dx.doi.org/10.1006/jsvi.2001.3961.

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32

RAVI KUMAR, L., P. K. DATTA, and D. L. PRABHAKARA. "VIBRATION AND STABILITY BEHAVIOR OF LAMINATED COMPOSITE CURVED PANELS WITH CUTOUT UNDER PARTIAL IN-PLANE LOADS." International Journal of Structural Stability and Dynamics 05, no. 01 (March 2005): 75–94. http://dx.doi.org/10.1142/s0219455405001507.

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The present paper is concerned with the vibration, buckling and dynamic instability behavior of laminated composite, cross-ply, doubly-curved panels with a central circular hole subjected to in-plane static and periodic compressive loads. A generalized shear deformable Sanders' theory is used to model the curved panels, considering the effects of transverse shear deformation and rotary inertia. Bolotin's approach is used for studying the dynamic instability regions of doubly-curved panels. The effects of non-uniform edge loads, curvature with different cutout ratios, static and dynamic load factors, and lamination parameters on curved panels are investigated with the results discussed.

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33

Ouadia, Mouhat, Khamlichi Abdellatif, Hasnae Boubel, Oumnia Elmrabet, Mohamed Rougui, El Mehdi Echebba, and Ahmed El Bouhmidi. "Dynamic buckling of laminated composite stringer stiffened CFRP panels under axial compression." MATEC Web of Conferences 149 (2018): 01044. http://dx.doi.org/10.1051/matecconf/201814901044.

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In this work, the dynamic buckling of stiffened panels is evolved numerically through a nonlinear incremental expression through making use of a specific time integration procedure via the finite element software program. the buckling and post-buckling behaviours of hat-stringer-stiffened composite curved panel under axial compression load .Dynamic buckling is extracted from the curve abandoning the very last shortening as a characteristic of time while the shape is subjected with the aid of a square compression pulse movement carried out inside the axial direction. The duration of the heart beat and the amplitude of curvature of decreasing of the cloth inside the band tormented by the warmth, the dynamic buckling motion, are constant. The method approach was proposed to predict the dynamic buckling load of curved panel. Finite element analysis was used to investigate these tests and the FE models were performed by ABAQUS.Approach to determine the reliability of the stiffened panel in dynamic buckling state.

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34

Ota, Yasuyuki, Taizo Masuda, Kenji Araki, and Masafumi Yamaguchi. "Curve-Correction Factor for Characterization of the Output of a Three-Dimensional Curved Photovoltaic Module on a Car Roof." Coatings 8, no. 12 (November 27, 2018): 432. http://dx.doi.org/10.3390/coatings8120432.

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For modeling the energy generation of three-dimensional car roof photovoltaic (PV) panels, it is essential to define a scientifically accurate method to model the amount of solar irradiance received by the panel. Additionally, the average annual irradiance incident on car roofs must be evaluated, because the PV module is often shaded during driving and when parked. The curve-correction factor, which is a unique value depending on the three-dimensional curved shape of the PV module, is defined in this paper. The curve-correction factor was calculated using a ray-trace simulator. It was found that the shape of the curved surface affected the curve-correction factor. The ratio of the projection area to the curved surface area of most car roofs is 0.85–0.95, and the annual curve-correction factor lies between 0.70 and 0.90. The annual irradiance incident on car roofs was evaluated using a mobile multipyranometer array system for one year (September 2017–August 2018). It is estimated that the effective annual solar radiation for curved PV modules is 2.53–3.52 kWh m−2/day.

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35

Yossef, Nashwa, M. El-Aghoury, M. Dabaon, M. El-Boghdadi, and M. Hassanen. "Finite Element Analysis of Curved Thin-Walled Panels." International Conference on Civil and Architecture Engineering 7, no. 7 (May 1, 2008): 13–22. http://dx.doi.org/10.21608/iccae.2008.45511.

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36

Xu, Lei, Yanglin Gong, and Ping Guo. "Compressive tests of cold-formed steel curved panels." Journal of Constructional Steel Research 57, no. 12 (December 2001): 1249–65. http://dx.doi.org/10.1016/s0143-974x(01)00048-7.

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37

Nagati, M. G., J. D. Iversen, and J. M. Vogel. "Vortex sheet modeling with curved higher-order panels." Journal of Aircraft 24, no. 11 (November 1987): 776–82. http://dx.doi.org/10.2514/3.45520.

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38

Skvortsov, Vitaly, and Elena Bozhevolnaya. "Overall behaviour of shallow singly-curved sandwich panels." Composite Structures 37, no. 1 (January 1997): 65–79. http://dx.doi.org/10.1016/s0263-8223(97)80004-9.

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39

Ohga, Mitao, Hideki Takao, and Tsunemi Shigematsu. "Vibration analysis of curved panels with variable thickness." Engineering Computations 13, no. 2/3/4 (March 1996): 226–39. http://dx.doi.org/10.1108/02644409610114549.

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40

White, S. C., G. Raju, and P. M. Weaver. "Initial post-buckling of variable-stiffness curved panels." Journal of the Mechanics and Physics of Solids 71 (November 2014): 132–55. http://dx.doi.org/10.1016/j.jmps.2014.07.003.

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41

shooshtari, Alireza, and Soheil Razavi. "Large amplitude free vibration of magnetoelectroelastic curved panels." Scientia Iranica 23, no. 6 (October 1, 2016): 2606–15. http://dx.doi.org/10.24200/sci.2016.3970.

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42

Pany, Chitaranjan, S. Parthan, and M. Mukhopadhyay. "Wave Propagation in Orthogonally Supported Periodic Curved Panels." Journal of Engineering Mechanics 129, no. 3 (March 2003): 342–49. http://dx.doi.org/10.1061/(asce)0733-9399(2003)129:3(342).

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43

Hayashi, Kazutaka, Yasumasa Kato, Yousuke Sato, Yusuke Kobayashi, and Masaya Kunigita. "P-75: Mechanical Reliability of Curved Display Panels." SID Symposium Digest of Technical Papers 48, no. 1 (May 2017): 1524–27. http://dx.doi.org/10.1002/sdtp.11939.

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Fatt, Michelle S. Hoo, Yifei Gao, and Dushyanth Sirivolu. "Foam-core, curved composite sandwich panels under blast." Journal of Sandwich Structures & Materials 15, no. 3 (May 2013): 261–91. http://dx.doi.org/10.1177/1099636213481469.

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Tran, Khanh Le, Laurence Davaine, Cyril Douthe, and Karam Sab. "Stability of curved panels under uniform axial compression." Journal of Constructional Steel Research 69, no. 1 (February 2012): 30–38. http://dx.doi.org/10.1016/j.jcsr.2011.07.015.

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Shen, Jianhu, Guoxing Lu, Zhihua Wang, and Longmao Zhao. "Experiments on curved sandwich panels under blast loading." International Journal of Impact Engineering 37, no. 9 (September 2010): 960–70. http://dx.doi.org/10.1016/j.ijimpeng.2010.03.002.

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Barai, A., and S. Durvasula. "Vibration and buckling of hybrid laminated curved panels." Composite Structures 21, no. 1 (January 1992): 15–27. http://dx.doi.org/10.1016/0263-8223(92)90076-o.

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An, Xiaomin, Boo Cheng Khoo, and Yongdong Cui. "Nonlinear aeroelastic analysis of curved laminated composite panels." Composite Structures 179 (November 2017): 377–414. http://dx.doi.org/10.1016/j.compstruct.2017.07.042.

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Zhang, Xi, Qingmin Chen, Jiaxin Gao, Mingwei Wang, Ya Zhang, and Zhongyi Cai. "Numerical Study on the Plastic Forming of Doubly Curved Surfaces of Aluminum Foam Sandwich Panel Using 3D Voronoi Model." Metals 11, no. 5 (April 21, 2021): 675. http://dx.doi.org/10.3390/met11050675.

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Abstract:

This paper presents a numerical investigation on the plastic forming of doubly curved surfaces of aluminum foam sandwich panel (AFSP). A mesoscopic 3D Voronoi model that can describe the structure of closed-cell aluminum foam relatively realistically was established, and a series of numerical simulations using the model of the sandwich panel with a Voronoi foam core were conducted on the plastic forming of two typical doubly curved surfaces including spherical and saddle-shaped surfaces of AFSPs to analyze the deformation behaviors and the forming defects in detail. Multi-point forming experiments of spherical and saddle-shaped AFSPs with different target radii were implemented and the doubly curved panels with good forming quality were obtained. The simulated results of the surface illumination maps, the face sheet profiles, and the maximum strain differences in selected areas of the face sheet and the experimental results indicated that the Voronoi AFSP model can reflect the actual defects occurred in the plastic forming of doubly curved sandwich panels, and the high forming accuracy of the sandwich panel model was also demonstrated in terms of the shape error and the thickness variation.

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Bidi, A., Gh Liaghat, and Gh Rahimi. "Low-velocity impact on cylindrically curved bilayers." Proceedings of the Institution of Mechanical Engineers, Part K: Journal of Multi-body Dynamics 232, no. 4 (March 19, 2018): 568–76. http://dx.doi.org/10.1177/1464419318756661.

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Abstract:

In this study, low-velocity impact response of cylindrically curved bilayer panels is studied. A large number of parameters affect the impact dynamics and many models have been used for solution previously. These models can be classified as energy balance model, spring–mass model, and complete models in which the dynamic behavior of the structure is exactly modeled. In this study, a two degrees of freedom spring–mass model is used to evaluate contact force between the composite panel and impactor. This work uses the modified Hertz contact model which is linearized form of general Hertz contact law. First-order shear deformation theory coupled with Fourier series expansion is used to derive the governing equations of the curved bilayer panel. The effects of panel curvature, impact velocity, and mass of impactor on the panel behavior under low-velocity impact are investigated. The results show that changing the panel radius of curvature will change the impact force, impact duration, and local panel deformation. Finally, analytical solutions have been compared with numerical results.

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