Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load
С использованием экспериментальных и численных расчетных методик исследовано поведение цилиндрических панелей после потери устойчивости. Проанализировано влияние длины, угловых параметров секторов и различных граничных условий цилиндрических панелей на величину нагрузки, при которой происходит пот...
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Інститут проблем міцності ім. Г.С. Писаренко НАН України
2011
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| Zitieren: | Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load / M. Shariati, J. Saemi, M. Sedighi, H.R. Eipakchi // Проблемы прочности. — 2011. — № 2. — С. 108-121. — Бібліогр.: 18 назв. — англ. |
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| author | Shariati, M. Saemi, J. Sedighi, M. Eipakchi, H.R. |
| author_facet | Shariati, M. Saemi, J. Sedighi, M. Eipakchi, H.R. |
| citation_txt | Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load / M. Shariati, J. Saemi, M. Sedighi, H.R. Eipakchi // Проблемы прочности. — 2011. — № 2. — С. 108-121. — Бібліогр.: 18 назв. — англ. |
| collection | DSpace DC |
| container_title | Проблемы прочности |
| description | С использованием экспериментальных и численных расчетных методик исследовано поведение
цилиндрических панелей после потери устойчивости. Проанализировано влияние длины, угловых параметров секторов и различных граничных условий цилиндрических панелей на величину
нагрузки, при которой происходит потеря устойчивости. Экспериментальные исследования
проводились на сервогидравлической испытательной машине Instron 8808, для расчетов
использовался конечноэлементный пакет программ Abaqus. Получено хорошее соответствие
расчетных результатов с экспериментальными.
Із використанням експериментальних і числових розрахункових методик
досліджено поведінку циліндричних панелей після втрати стійкості. Проаналізовано вплив довжини, кутових параметрів секторів і різних граничних
умов циліндричних панелей на величину навантаження, за якого відбувається
втрата стійкості. Експериментальні дослідження проводили на сервогідравлічній випробувальній машині Instron 8808, для розрахунків використовували
скінченноелементний пакет програм Abaqus. Отримано хорошу збіжність
розрахункових результатів з експериментальними.
|
| first_indexed | 2025-12-07T15:30:07Z |
| format | Article |
| fulltext |
UDC 539.4
Experimental and Numerical Studies on Buckling and Post-Buckling
Behavior of Cylindrical Panels Subjected to Compressive Axial Load
M. Shariati, J. Saemi, M. Sedighi, and H. R. Eipakchi
Shahroud University of Technology, Shahroud, Iran
ÓÄÊ 539.4
Ýêñïåðèìåíòàëüíîå èññëåäîâàíèå è ÷èñëåííîå ìîäåëèðîâàíèå
ïîòåðè óñòîé÷èâîñòè öèëèíäðè÷åñêèõ ïàíåëåé ïðè ñæàòèè îñåâîé
íàãðóçêîé
Ì. Øàðèàòè, Äæ. Ñàåìè, Ì. Ñåäèãè, Õ. Ð. Ýéïàê÷è
Òåõíîëîãè÷åñêèé óíèâåðñèòåò ã. Øàõðóä, Èðàí
Ñ èñïîëüçîâàíèåì ýêñïåðèìåíòàëüíûõ è ÷èñëåííûõ ðàñ÷åòíûõ ìåòîäèê èññëåäîâàíî ïîâåäåíèå
öèëèíäðè÷åñêèõ ïàíåëåé ïîñëå ïîòåðè óñòîé÷èâîñòè. Ïðîàíàëèçèðîâàíî âëèÿíèå äëèíû, óãëî-
âûõ ïàðàìåòðîâ ñåêòîðîâ è ðàçëè÷íûõ ãðàíè÷íûõ óñëîâèé öèëèíäðè÷åñêèõ ïàíåëåé íà âåëè÷èíó
íàãðóçêè, ïðè êîòîðîé ïðîèñõîäèò ïîòåðÿ óñòîé÷èâîñòè. Ýêñïåðèìåíòàëüíûå èññëåäîâàíèÿ
ïðîâîäèëèñü íà ñåðâîãèäðàâëè÷åñêîé èñïûòàòåëüíîé ìàøèíå Instron 8808, äëÿ ðàñ÷åòîâ
èñïîëüçîâàëñÿ êîíå÷íîýëåìåíòíûé ïàêåò ïðîãðàìì Abaqus. Ïîëó÷åíî õîðîøåå ñîîòâåòñòâèå
ðàñ÷åòíûõ ðåçóëüòàòîâ ñ ýêñïåðèìåíòàëüíûìè.
Êëþ÷åâûå ñëîâà: ìåõàíè÷åñêèå èñïûòàíèÿ, óïðóãîïëàñòè÷åñêîå äåôîðìèðî-
âàíèå, àíàëèç ïîòåðè óñòîé÷èâîñòè.
Introduction. Shell structures are widely used in pipelines, aerospace and
marine structures, large dams, shell roofs, liquid-retaining structures and cooling
towers [1]. Buckling is one of the main failure considerations when designing these
structures [2]. At first, researchers focused on the determination of the buckling
load in the linear elastic zone, but experimental studies [3, 4] showed that the
buckling capacity of thin cylindrical shells is much lower than that predicted by
classic theories [5]. Thin cylindrical panels are used in different structures. When
the stress distribution in this structure is compressive, the structure will collapse
usually before yielding or the buckling phenomena determines its loading capacity
due to large value of radius to thickness ratio. This subject is usually studied using
the numerical methods based on the finite elements (FE) and analytical methods in
elastic region. The exact solution for isotropic and anisotropic panels has been
presented by Timoshenko [6] and Lekhnitskii [7]. El-Raheb [8] investigated the
stability of simply supported panels subjected to uniform external pressure.
Magnucki et al. [9] solved the Donnell equation for buckling of panels with three
simply supported edges and one free edge subjected to axial load using the
Galerkin method. Patel et al. [10] discussed static and dynamic stability of panels
with edge harmonic loading. Buermann et al. [11] presented a semi-analytical
© M. SHARIATI, J. SAEMI, M. SEDIGHI, H. R. EIPAKCHI, 2011
108 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2011, ¹ 2
model for the post-buckling analysis of stiffened cylindrical panels using
trigonometric Fourier series as approximated solutions for displacements. Lanzi et
al. [12] performed a multi-objective optimization procedure based on Genetic
Algorithms for the design of composite stiffened panels capable to operate in
post-buckling conditions. The results without considering any kind of imperfection,
are closed and in good agreement with the tests in terms of buckling and post-
buckling stiffness, as well as of collapse loads. Jiang et al. [13] studied the buckling
of panels subjected to compressive stress using the differential quardrature element
method. Keweon [14, 15] carried out numerical and experimental studies of the
post-buckling behavior of axially loaded cylindrical panel with clamped curved
edges and with simply supported straight edges. Bisagni et al. [16] presented an
analytical formulation for the study of linearized local skin buckling load and
nonlinear post-buckling behavior of isotropic and composite stiffened panels
subjected to axial compression. The results are compared with the FE analysis.
In this paper, numerical and experimental studies have been performed on
cylindrical panels for determining the buckling load and investigating the post-
buckling behavior of panels. For numerical analysis Abaqus FE package has been
used to study the effects of the length, sector angle, thickness and different
boundary conditions and the experimental tests have been applied to the panels
using a servo-hydraulic machine. The experimental results are in good agreement
with the experimental ones.
1. Panels Characteristics. Figure 1 shows the schematic of a panel. The
mechanical properties of metal panels have been determined using tensile tests. For
this purpose, some standard test specimens have been prepared from the original
tubes according to ASTM E8 [17] standard and tensile tests were performed using
an Instron 8802 tensile test machine.
Figure 2 shows the stress–strain diagram for a specimen. Poisson’s ratio was
assumed to be 0.33. The geometrical and mechanical properties of panels are listed
in Table 1.
Experimental and Numerical Studies on Buckling ...
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Fig. 1. Schematic of a cylindrical panel.
2. Boundary Conditions. For applying boundary conditions at the edges of
the cylindrical panel, two rigid plates were used that were attached to the edges of
the cylindrical panel. In order to analyze the buckling under axial loading similar to
the experimental conditions, a 15-mm displacement was applied to the center of the
upper plate, which resulted in a distributed compressive load on both edges of the
cylindrical panel. Additionally, all degrees of freedom in the lower plate and upper
plate, except in the direction of longitudinal axis, were constrained.
In the section of experimental results, it will be shown that the fulcrum used in
these tests has an edge that is 18.1 mm high (Fig. 3). For this reason, in numerical
simulations, the edges of the shell are constrained to this elevation, except in the
direction of the cylinder axis.
M. Shariati, J. Saemi, M. Sedighi, and H. R. Eipakchi
110 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2011, ¹ 2
T a b l e 1
Mechanical and Geometrical Properties of Panels
Outer diameter D , mm 60
Thickness t, mm 0.9
Sector angle � , deg 90, 120, 180, 355, and 360 (perfect)
Length L, mm 100, 150, and 250
Yield stress �Y , MPa 240
Young modulus E, GPa 150
Poisson’s ratio 0.33
Fig. 2. Stress–strain diagram.
a b
Fig. 3. Fixtures for experimental test: (a) simply supported; (b) clamped.
3. Numerical Method. The numerical analysis has been performed with
Abaqus FE package. For this analysis, the nonlinear element S8R5 (which is an
eight-node element with six degrees of freedom per node, suitable for analysis of
thin shells) and the linear element S4R (which is a four-node element) were used
[18]. Part of a meshed specimen is shown in Fig. 4. Both linear and nonlinear
elements were used for the analysis of the shells and the results were compared
with each other.
The boundary conditions under study were clamped or simple (at arc edges)
and free (at straight edges). Eigenvalue analysis overestimates the value of
buckling load, because in this analysis the plastic properties of material play no
role in the analysis procedure. For buckling analysis, an eigenvalue analysis should
be perfomed initially for all specimens, to find the mode shapes and corresponding
eigenvalues. Primary modes have smaller eigenvalues and buckling usually occurs
in these mode shapes. For eigenvalues analysis the ‘‘Buckle step” was used in the
software. Three initial mode shapes and corresponding displacements of all
specimens were obtained. The effects of these mode shapes must be considered in
nonlinear buckling analysis (”Static Riks” step). Otherwise, the software would
choose the buckling mode in an arbitrary manner, resulting in unrealistic results of
nonlinear analysis. For ‘‘Buckle step”, the subspace solver method of the software
was used. It is noteworthy that, due to the presence of contact constraints between
rigid plates and the shell, the Lanczos solver method cannot be used for these
specimens [18]. In Fig. 5, two primary mode shapes are shown for the specimen
with L�100 mm, �� �90 . After completion of the buckle analysis, a nonlinear
analysis was performed to plot the load–displacement curve. The maximum value
attained by this curve is the buckling load.
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Experimental and Numerical Studies on Buckling ...
Fig. 4. Mesh pattern for a panel.
Fig. 5. Buckling mode shape for specimen with L �100 mm, � � �90 : (a) first mode, (b) second
mode, and (c) third mode.
a b c
This step, called ‘‘Static Riks’’ involves the arc length method for post-
buckling analysis. In this analysis, nonlinearity of both material properties and
geometry is taken into consideration. This analysis has been performed for
different panels (Table 1) for clamped and simple boundary conditions, and the
load–displacement diagram has been derived for each case.
4. Experimental Method. Some specimens with characteristics listed in
Table 1 were prepared and the compression test of panels was performed using a
servo-hydraulic machine. At first, for investigating the system reliability for
repeating the tests, three similar panels with L�100 mm and �� �120 were tested.
Figure 6 shows the load–displacement diagrams for these panels, which indicates
repeatability of the panel tests.
For different boundary conditions, the axial load was applied to the panels and
the load–axial displacement diagrams of panels have been drawn.
In all tests, the straight edges were free and the arc edges were clamped or
simply supported. To produce clamped and simple boundary conditions, some
appropriate fixtures were designed. Figure 7 shows the test setup.
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M. Shariati, J. Saemi, M. Sedighi, and H. R. Eipakchi
Fig. 6. Load–displacement diagrams for three similar panels with L �100 mm, � � �120 : (1) test 1,
(2) test 2, and (3) test 3.
Fig. 7. Experimental test setup.
5. Discussion of Results. Figure 8 shows the numerical and experimental
load–displacement diagrams for panels of different lengths. The peak values in
diagrams stand for the buckling load. It is seen that with increase in the length the
buckling load decreases. These variations are more pronounced for smaller lengths.
For higher lengths, the load–displacement diagram for the smallest sector angle,
i.e., �� �90 (Fig. 9) tends to the Euler buckling mode.
Figures 9 and 10 show the load–displacement diagrams for ��90 and 180� .
Figure 11 shows that with increase in the sector angle the buckling load
increases. When there is a narrow cut (�� �355 ), the buckling load drops noticeably.
The variations of the buckling load in terms of the sector angle (shown in Fig. 12)
are nearly linear and change considerably for a cylinder. Figure 13 shows the
deformed shape of a panel with a narrow cut.
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Experimental and Numerical Studies on Buckling ...
Fig. 8. Load–displacement diagrams for different lengths (� � �120 , simply supported). [Here and in
Figs. 9 and 10: (1) L �100 mm; (2) L �150 mm; (3) L � 250 mm.]
Fig. 9. Load–displacement diagrams for different lengths (� � �90 , simply supported).
Fig. 10. Load–displacement diagram for different lengths (� � �180 , simply supported).
The load–displacement diagrams and the first buckling modes for different
panels are shown in Table 2. The buckling modes are similar and there is a good
agreement between the load–displacement diagrams in the most cases.
The largest differences between the diagrams correspond to the post-buckling
region and the values for FE results are higher than the experimental values. It may
be due to approximated definition of the plastic part of stress–strain diagram and
no consideration of the specimens defects in FE model. The FE stress analysis
114 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2011, ¹ 2
M. Shariati, J. Saemi, M. Sedighi, and H. R. Eipakchi
Fig. 11. Buckling load in terms of the length for different sector angles: (�) perfect; (�) � � �355 ;
(�) � � �180 ; (�) � � �120 ; (�) � � �90 .
Fig. 12. Buckling load in terms of the sector angle for different sector angles (simply supported):
(�) L �100 mm; (�) L �150 mm; (�) L � 250 mm.
Fig 13. Deformed shaped of panel (� � �355 , L �100 mm, simply supported): (a) experimental;
(b) numerical.
a b
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Experimental and Numerical Studies on Buckling ...
T a b l e 2
Numerical and Experimental Load–Displacement Diagrams and Buckling Modes
for Different Lengths and Sector Angles
Numerical mode Experimental mode Load–displacement diagram
1 2 3
shows that in some cases, the von Mises stresses in panels are higher than the yield
stress or the panel is not elastic at buckling load. Figure 14 shows the von Mises
stresses of a panel under buckling load.
5.1. Effect of Boundary Conditions. To investigate the effects of different
boundary conditions, some tests were performed on panels with clamped and
simple supports. Table 3 shows the load–displacement diagrams for clamped and
simply supported boundary conditions. Results show that in all tests the clamped
boundary conditions can increase the buckling load capacity of the panels. This is
due to the fact that clamped boundaries can restrict the number of degrees of
freedom. The Euler buckling mode has been observed for L�250 mm and �� �90
in numerical and experimental results. The values of buckling loads for these
boundary conditions are listed in Table 4.
116 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2011, ¹ 2
M. Shariati, J. Saemi, M. Sedighi, and H. R. Eipakchi
continued Table 2
1 2 3
5.2. Effect of Linear and Nonlinear Elements. After comparing the curves in
Fig. 15, it can be noted that linear elements, in contrast to nonlinear elements, have
a better prediction power for the post-buckling behavior of mild steel cylindrical
shells with elliptical cutouts. In the prebuckling phase, both elements produce
similar results.
It can be seen that the slope of load vs. displacement curves prior to the
buckling is higher in numerical results than in the experimental ones. This
discrepancy is due to the presence of internal defects in the material which reduces
the stiffness of the specimens in the experimental method, while the materials are
assumed to be ideal in the numerical analysis.
The experimental results are compared with numerical findings in Table 5. It
is evident that there is a close correlation between experimental and numerical
results. For example, the biggest discrepancy between the two sets of results is
6.7% for S8R5 nonlinear element and 8.8% for S4R linear element. It is also
noteworthy that the greatest difference is observed for short specimens. This can be
attributed to the fact that the bending theory of shells is more suitable for lower t L
ratios, while and this theory is used by the software for calculations.
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Experimental and Numerical Studies on Buckling ...
a b c
Fig. 14. Von Mises stress distribution in panel due to different loads (simply supported): (a) applied
load is in the elastic region; (b, c) applied loads are in the post-buckling region.
T a b l e 3
Load–Displacement Diagrams for Clamped and Simply Supported Boundary Conditions
Numerical Experimental
118 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2011, ¹ 2
M. Shariati, J. Saemi, M. Sedighi, and H. R. Eipakchi
T a b l e 4
Buckling Load (kN) for Different Boundary Conditions
� � �90 L �100 mm L �150 mm L � 250 mm
Numerical Experimental Numerical Experimental Numerical Experimental
Simply
supported
8.40 7.06 7.04 6.61 4.80 4.66
clamped 8.45 7.92 7.67 6.99 5.19 5.05
Fig. 15. Comparison of the experimental and numerical results.
Conclusions. Increase in the panel length decreases the buckling load. This
effect is more critical for shorter panels. This can be attributed to the fact that the
bending theory of shells is more suitable for lower t L ratios, and this theory is
used by the software for calculations.
The existence of a narrow slot decreases the buckling load noticeably.
The clamped boundary conditions increase the panel load-bearing capacity,
i.e., increase the buckling load.
In the most cases, there is a good agreement between the numerical and
experimental results. FE analysis results show that the curves constructed using
linear elements predict the post-buckling region better than nonlinear elements,
while the nonlinear elements are more suitable for calculation of the buckling
load.
Acknowledgments. The authors regard the manager of the “Mechanical Properties
Laboratory” of Shahrood University of Technology for supporting the tests.
Ð å ç þ ì å
²ç âèêîðèñòàííÿì åêñïåðèìåíòàëüíèõ ³ ÷èñëîâèõ ðîçðàõóíêîâèõ ìåòîäèê
äîñë³äæåíî ïîâåä³íêó öèë³íäðè÷íèõ ïàíåëåé ï³ñëÿ âòðàòè ñò³éêîñò³. Ïðîàíà-
ë³çîâàíî âïëèâ äîâæèíè, êóòîâèõ ïàðàìåòð³â ñåêòîð³â ³ ð³çíèõ ãðàíè÷íèõ
ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2011, ¹ 2 119
Experimental and Numerical Studies on Buckling ...
T a b l e 5
Comparison of the Experimental and Numerical Results for Cylindrical Panels
Model
designation
Buckling load (kN) Error (%)
S4R S8R5 Experimental S4R S8R5
L100-�90 7.541 7.410 7.060 6.8 4.8
L100-�120 12.745 12.492 11.807 7.9 5.8
L100-�180 16.124 16.027 15.021 7.3 6.7
L100-�355 35.214 34.821 32.983 6.8 5.6
L100-perfect 43.245 43.038 40.934 5.6 5.1
L150-�90 7.202 7.039 6.611 8.8 6.5
L150-�120 11.459 11.265 11.048 3.7 2.0
L150-�180 14.601 14.303 13.634 7.1 4.9
L150-�355 32.249 31.029 29.652 8.7 4.6
L150-perfect 40.987 40.101 37.693 8.7 6.4
L250-�90 4.912 4.802 4.659 5.4 3.1
L250-�120 9.580 9.492 8.941 7.1 6.2
L250-�180 13.375 13.345 12.596 6.2 5.9
L250-�355 30.015 29.867 28.589 5.0 4.5
L250-perfect 38.012 37.436 36.223 4.9 3.4
óìîâ öèë³íäðè÷íèõ ïàíåëåé íà âåëè÷èíó íàâàíòàæåííÿ, çà ÿêîãî â³äáóâàºòüñÿ
âòðàòà ñò³éêîñò³. Åêñïåðèìåíòàëüí³ äîñë³äæåííÿ ïðîâîäèëè íà ñåðâîã³äðàâ-
ë³÷í³é âèïðîáóâàëüí³é ìàøèí³ Instron 8808, äëÿ ðîçðàõóíê³â âèêîðèñòîâóâàëè
ñê³í÷åííîåëåìåíòíèé ïàêåò ïðîãðàì Abaqus. Îòðèìàíî õîðîøó çá³æí³ñòü
ðîçðàõóíêîâèõ ðåçóëüòàò³â ç åêñïåðèìåíòàëüíèìè.
1. M. Farshad, Design and Analysis of Shell Structures, Kluwer Academic
Publishers, Dordrecht (1992).
2. B. Budiansky and J. W. Hutchinson (Eds.), Buckling of Circular Cylindrical
Shells under Axial Compression. Contributions to the Theory of Aircraft
Structures, Delft University Press (1972), pp. 239–260.
3. J. Arbocz and J. M. A. M. Hol, “Collapse of axially compressed cylindrical
shells with random imperfections,” AIAA J., 29, 2247–2256 (1991).
4. J. F. Jullien and A. Limam, “Effect of openings on the buckling of cylindrical
shells subjected to axial compression,” Thin-Walled Struct., 31, 187–202
(1998).
5. M. Farshad, Stability of Structures, Elsevier, Amsterdam (1994).
6. S. P. Timoshenko and J. M. Gere, Theory of Elastic Stability, McGraw-Hill,
NewYork (1961).
7. S. G. Lekhnitskii, Anisotropic Plates, Gordon and Breach, New York (1968).
8. M. El-Raheb, “Response of a thin cylindrical panel with constrained edges,”
Int. J. Solids Struct., 43, 7571–7592 (2006).
9. K. Magnucki and M. Mackiewicz, “Elastic buckling of an axially compressed
cylindrical panel with three edges simply supported and one edge free,”
Thin-Walled Struct., 44, 387–392 (2006).
10. S. N. Patel, P. K. Datta, and A. H. Sheikh, “Buckling and dynamic instability
analysis of stiffened shell panels,” Thin-Walled Struct., 44, 321–333 (2006).
11. P. Buermann, R. Rolfes, J. Tessmer, and M. Schagerl, “A semi-analytical
model for local post-buckling analysis of stringer- and frame-stiffened
cylindrical panels,” Thin-Walled Struct., 44, 102–114 (2006).
12. L. Lanzi and V. Giavotto, “Post-buckling optimization of composite stiffened
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ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2011, ¹ 2 121
Experimental and Numerical Studies on Buckling ...
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| id | nasplib_isofts_kiev_ua-123456789-112752 |
| institution | Digital Library of Periodicals of National Academy of Sciences of Ukraine |
| issn | 0556-171X |
| language | English |
| last_indexed | 2025-12-07T15:30:07Z |
| publishDate | 2011 |
| publisher | Інститут проблем міцності ім. Г.С. Писаренко НАН України |
| record_format | dspace |
| spelling | Shariati, M. Saemi, J. Sedighi, M. Eipakchi, H.R. 2017-01-27T09:15:51Z 2017-01-27T09:15:51Z 2011 Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load / M. Shariati, J. Saemi, M. Sedighi, H.R. Eipakchi // Проблемы прочности. — 2011. — № 2. — С. 108-121. — Бібліогр.: 18 назв. — англ. 0556-171X https://nasplib.isofts.kiev.ua/handle/123456789/112752 539.4 С использованием экспериментальных и численных расчетных методик исследовано поведение цилиндрических панелей после потери устойчивости. Проанализировано влияние длины, угловых параметров секторов и различных граничных условий цилиндрических панелей на величину нагрузки, при которой происходит потеря устойчивости. Экспериментальные исследования проводились на сервогидравлической испытательной машине Instron 8808, для расчетов использовался конечноэлементный пакет программ Abaqus. Получено хорошее соответствие расчетных результатов с экспериментальными. Із використанням експериментальних і числових розрахункових методик досліджено поведінку циліндричних панелей після втрати стійкості. Проаналізовано вплив довжини, кутових параметрів секторів і різних граничних умов циліндричних панелей на величину навантаження, за якого відбувається втрата стійкості. Експериментальні дослідження проводили на сервогідравлічній випробувальній машині Instron 8808, для розрахунків використовували скінченноелементний пакет програм Abaqus. Отримано хорошу збіжність розрахункових результатів з експериментальними. The authors regard the manager of the “Mechanical Properties Laboratory” of Shahrood University of Technology for supporting the tests. en Інститут проблем міцності ім. Г.С. Писаренко НАН України Проблемы прочности Научно-технический раздел Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load Экспериментальное исследование и численное моделирование потери устойчивости цилиндрических панелей при сжатии осевой нагрузкой Article published earlier |
| spellingShingle | Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load Shariati, M. Saemi, J. Sedighi, M. Eipakchi, H.R. Научно-технический раздел |
| title | Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load |
| title_alt | Экспериментальное исследование и численное моделирование потери устойчивости цилиндрических панелей при сжатии осевой нагрузкой |
| title_full | Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load |
| title_fullStr | Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load |
| title_full_unstemmed | Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load |
| title_short | Experimental and Numerical Studies on Buckling and Post-Buckling Behavior of Cylindrical Panels Subjected to Compressive Axial Load |
| title_sort | experimental and numerical studies on buckling and post-buckling behavior of cylindrical panels subjected to compressive axial load |
| topic | Научно-технический раздел |
| topic_facet | Научно-технический раздел |
| url | https://nasplib.isofts.kiev.ua/handle/123456789/112752 |
| work_keys_str_mv | AT shariatim experimentalandnumericalstudiesonbucklingandpostbucklingbehaviorofcylindricalpanelssubjectedtocompressiveaxialload AT saemij experimentalandnumericalstudiesonbucklingandpostbucklingbehaviorofcylindricalpanelssubjectedtocompressiveaxialload AT sedighim experimentalandnumericalstudiesonbucklingandpostbucklingbehaviorofcylindricalpanelssubjectedtocompressiveaxialload AT eipakchihr experimentalandnumericalstudiesonbucklingandpostbucklingbehaviorofcylindricalpanelssubjectedtocompressiveaxialload AT shariatim éksperimentalʹnoeissledovanieičislennoemodelirovaniepoteriustoičivosticilindričeskihpaneleiprisžatiiosevoinagruzkoi AT saemij éksperimentalʹnoeissledovanieičislennoemodelirovaniepoteriustoičivosticilindričeskihpaneleiprisžatiiosevoinagruzkoi AT sedighim éksperimentalʹnoeissledovanieičislennoemodelirovaniepoteriustoičivosticilindričeskihpaneleiprisžatiiosevoinagruzkoi AT eipakchihr éksperimentalʹnoeissledovanieičislennoemodelirovaniepoteriustoičivosticilindričeskihpaneleiprisžatiiosevoinagruzkoi |