post-buckling analysis in thin-web laminated … · 2019. 10. 26. · dissertation (master of...
TRANSCRIPT
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POST-BUCKLING ANALYSIS INTHIN-WEB LAMINATED
COMPOSITE BEAMS
AUTHORS: BRUNA LUIZA NOLLI
CARLOS ALBERTO CIMINI JÚNIOR
CRISTIANO ALVES PENA
Stockholm, Sweden, October 08th 2019Aerospace Technology Congress FT2019
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Agenda
• Introduction
• Objectives
• Methodology
• Results and Discussion
• Conclusion
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Agenda
• Introduction
• Objectives
• Methodology
• Results and Discussion
• Conclusion
3
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Introduction
Increase the efficiencyand reduce the costs
of the aircrafts
Post-buckling capacityof composite materials
reinforced panels
Panel’s buckling
Diagonal folds
Shear forces
Tension by the diagonal foldsCompression in the stiffeners
Lighter structure
Aeronautic Industry Main Goals
KUHN, P; PETERSON, J. P.; LEVIN L. R. A Summary of Diagonal Tension: Part I – Methods of Analysis. NACA Tech. Note 2661: may, 1952a. 4
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Agenda
• Introduction
• Objectives
• Methodology
• Results and Discussion
• Conclusion
5
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Objectives
JODOIN, A. et al. Diagonal tension in fibre-metal laminates. In: ICAS 2002, 23, 2002, Toronto. p. 7-8.
For the metallic reinforced panel there is a consolidated methodology developed by NASA to calculate thepanel’s diagonal tension, NACA TN2661. This semi-empiric method was developed based in several testsperformed with aluminum panels using different geometries and loads and is widely used by aircraftsmanufactures.
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For a method for the panel’s post-buckling behavior in composite reinforced panels is still indevelopment. There are some researches trying to adapt the NACA TN-2661 method for compositematerials making it account for the anisotropy of the material and corroborate the results with tests.Other studies were based in modeling the reinforced panel in finite elements and compared the resultswith tests data. Yet it was used a one bay panel with unidirectional load.
Objectives
HERRERO, J. Buckling, post-buckling, and progressive failure analysis of hybrid composite shear webs using a continuum damage mechanism model. 2007. 208 f.Dissertation (Master of Science in mechanical engineer) – Whichita State University, Orone, 2007. 7
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Objectives
• The first main goal is to develop a method to build a FEM to represents the post-buckling behavior of the composite reinforced panel in order to avoid having to useexperimental results in future projects.
KUHN, P.; PETERSON, J. P.; LEVIN L. Ross. A Summary of Diagonal Tension: Part II – Experimental Evidence. NACA Tech. Note 2662: may, 1952b. 8
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Objectives
Lay-up1 45°
Lay-up2 -45°
Lay-up3 0°
Lay-up4 90°
Lay-up1 0°
Lay-up2 90°
Lay-up3 45°
Lay-up4 -45°
Lay-up1 90°
Lay-up2 45°
Lay-up3 -45°
Lay-up4 0°
Lay-up1 -45°
Lay-up2 -0°
Lay-up3 90°
Lay-up4 45°
• The second main goal is to study the influence of stacking sequence in post-bucklingbehavior.
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Objectives
Metallic??? Composite???
• The third main goal was to choose the reinforced panel that have the best behaviorduring the post-buckling analysis: metallic or composite.
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Agenda
• Introduction
• Objectives
• Methodology
• Results and Discussion
• Conclusion
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Build FEM1 (metallicreinforced panel)
Compare FEM1 with NACATN2661 (Kuhn, 1952a)
Modify boundaryconditions
Build FEM2 and FEM3(composite reinforced panel)
Compare FEM2 with FEM3
Change materialor laminate
Build 6 models FEM4(composite reinforced panel)
Compare the 6 models FEM4
Choose the model with thelowest failure index
Compare the best modelwith the metallic one
Choose the best solution fordiagonal tension
NO
YESDifference < 5%?
NO
YESDifference < 5%?
NO
YES
Modify boundary conditions?
N
START
END
Methodology
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MethodologyStep 1Build FEM1 (metallic
reinforced panel)
Compare FEM1 with NACATN2661 (Kuhn, 1952a)
Modify boundaryconditions
Build FEM2 and FEM3(composite reinforced panel)
Compare FEM2 with FEM3
Change materialor laminate
Build 6 models FEM4(composite reinforced panel)
Compare the 6 models FEM4
Choose the model with thelowest failure index
Compare the best modelwith the metallic one
Choose the best solution fordiagonal tension
NO
YESDifference < 5%?
NO
YESDifference < 5%?
NO
YES
Modify boundary conditions?
N
START
END
Step 2
Step 3
Step 4
Step 5
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Agenda
• Introduction
• Objectives
• Methodology
• Results and Discussion
• Conclusion
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Results and Discussion
NO
YESDifference < 5%?
Difference < 5%?
NO
YES
Modify boundary conditions?
START
END
NO
YES
Build FEM1 (metallicreinforced panel)
Compare FEM1 with NACATN2661 (Kuhn, 1952a)
Modify boundaryconditions
Build FEM2 and FEM3(composite reinforced panel)
Compare FEM2 with FEM3
Change materialor laminate
Build 6 models FEM4(composite reinforced panel)
Compare the 6 models FEM4
Choose the model with thelowest failure index
Compare the best modelwith the metallic one
Choose the best solution fordiagonal tension
Step 1
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3D schematic model and material
Thickness
Width
He
igh
t
Thic
kne
ss
Web Thickness
Up
pe
rFlan
geTh
ickne
ss
He
igh
t
Upper Flange WidthWeb Thickness
Low
er
Flan
geTh
ickn
ess He
igh
t
Lower Flange Width Vertical Stiffener:
Horizontal Lower Stiffener:Horizontal Upper Stiffener:
All dimensions are in millimeter
VerticalStiffener Panel’s web
HorizontalUpper
Stiffener
HorizontalLower
Stiffener
Material
Web Aluminum 2024 T3
Horizontal Upper Stiffener Aluminum 7075-T3 Extruded
Horizontal Lower Stiffener Aluminum 7075-T3 Extruded
Vertical Stiffener Aluminum 7075-T3 Extruded
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Metallic reinforced panel FEM final model
It was performed:
• static analysis (SOL101) to evaluate thestress in the panel’s web;
• linear buckling analysis (SOL105) tocalculate the buckling load;
• non-linear analysis including largedisplacement and elastic materialproperties (SOL106) to evaluate thepost-buckling behavior of the structure.
Fixed nodes
Two times the thickness of web panel
Web thickness
Only Y displacementfree
Upper Stiffener Web Thickness +Panel Web thickness
Lower Stiffener Web Thickness +Panel Web thickness
17
Fixed nodes
Two times the thickness of web panel
Web thickness
Pre/Post processor: Femap 11.2®
Solver: NASTRAN®
CQUAD4CBAR
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Results and Discussion
NO
YESDifference < 5%?
Difference < 5%?
NO
YES
Modify boundary conditions?
START
END
NO
YES
Build FEM1 (metallicreinforced panel)
Compare FEM1 with NACATN2661 (Kuhn, 1952a)
Modify boundaryconditions
Build FEM2 and FEM3(composite reinforced panel)
Compare FEM2 with FEM3
Change materialor laminate
Build 6 models FEM4(composite reinforced panel)
Compare the 6 models FEM4
Choose the model with thelowest failure index
Compare the best modelwith the metallic one
Choose the best solution fordiagonal tension
Step 2
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FEM shearstress
NACA TN2661 (Kuhn, Peterson andLevin, 1952a) shear stress (�����)
Difference
137.58 MPa 134.21 MPa 2.51%
Linear Analysis (SOL101): Maximum stress in the middle of panel
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FEM shearstress
NACA TN2661 *Shear nominal stressin the web (��)
Difference
126.37 MPa 126.42 MPa 0.04%
Linear Analysis (SOL101): average shear stress in the web (regionof first eigenvalue buckling mode)
* (Kuhn, Peterson and Levin, 1952a) 20
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Buckling Load: 0.0227358 x 60075N = 1365.9N
Linear Buckling Analysis (SOL105) vs. Non-linear analysis (SOL106)
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Linear bucklinganalysis
Non-linearanalysis
Difference
1365.85 N 1324.36 N 3.13%
Linear Buckling Analysis (SOL105) vs. Non-linear analysis (SOL106)
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0.0606348 ∗ 60075� = 3642.64�
Non-linear analysis - diagonal tension initiation
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Non-linear analysis - diagonal tension initiation
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Non-linear analysis - diagonal tension initiation
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Results and Discussion
NO
YESDifference < 5%?
Difference < 5%?
NO
YES
Modify boundary conditions?
START
END
NO
YES
Build FEM1 (metallicreinforced panel)
Compare FEM1 with NACATN2661 (Kuhn, 1952a)
Modify boundaryconditions
Build FEM2 and FEM3(composite reinforced panel)
Compare FEM2 with FEM3
Change materialor laminate
Build 6 models FEM4(composite reinforced panel)
Compare the 6 models FEM4
Choose the model with thelowest failure index
Compare the best modelwith the metallic one
Choose the best solution fordiagonal tension
Step 3
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Carbon/epoxy [45/-45/0/90]S
Equivalent Properties
Ex = Ey = E 56675.5 [MPa]
Gxy 22039.8 [MPa]
nxy = nyx 0.286
Material
FEM2 Tape carbon/epoxy [45/-45/0/90]S
FEM3NA (it was used the Young’s modulus equal to the
composite model) E = 56675.5 MPaHorizontal Upper Stiffener Steel 4043Horizontal Lower Stiffener Steel 4043
Vertical Stiffener Steel 4043
Model 1: modeling each layer andentering tape’s material properties
Model 2: equivalent propertiesfor the layup selected
P.S.: the 0 angle ply is in X direction global coordinate system.
carbon/epoxy [45/-45/0/90]S
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Isotropic Model Laminate Model
Isotropic and Laminate models:First eigenvalue (linear buckling analysis) comparison
First Eigenvalue
Isotropic Equivalent Model 0.125621
Laminate Model 0.14315
Difference 1.75%
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Isotropic and Laminate models:Diagonal tension first occurrence (non-linear analysis) comparison
First occurrence of Diagonal Tension
Isotropic Equivalent Model 0.190313
Laminate Model 0.20751
Difference 1.72%
Isotropic Model Laminate Model
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Results and Discussion
NO
YESDifference < 5%?
Difference < 5%?
NO
YES
Modify boundary conditions?
START
END
NO
YES
Build FEM1 (metallicreinforced panel)
Compare FEM1 with NACATN2661 (Kuhn, 1952a)
Modify boundaryconditions
Build FEM2 and FEM3(composite reinforced panel)
Compare FEM2 with FEM3
Change materialor laminate
Build 6 models FEM4(composite reinforced panel)
Compare the 6 models FEM4
Choose the model with thelowest failure index
Compare the best modelwith the metallic one
Choose the best solution fordiagonal tension
Step 4
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Composite Reinforced Panel: FEM comparisonCondition
1 2 3 4 5 6 7
Tsai-Wu 5500 N 100000 N 160000 N 310000 N 500000 N 700000 N 800000 N
MaximumStrain
5500 N 100000 N 160000 N 310000 N 480000 N 700000 N 900000 N
Carbon/epoxy tape
Model 1 [0/90/45/-45]S
Model 2 [45/-45/0/90]S
Model 3 [45/0/90/-45]S
Model 4 [0/45/-45/90]S
Model 5 [0/45/90/-45]S
Model 6 [45/0/-45/90]S
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Carbon/epoxy tape
Model 1 [0/90/45/-45]S
Model 2 [45/-45/0/90]S
Model 3 [45/0/90/-45]S
Model 4 [0/45/-45/90]S
Model 5 [0/45/90/-45]S
Model 6 [45/0/-45/90]S
Composite Reinforced Panel: FEM comparisonCondition
1 2 3 4 5 6 7
Tsai-Wu 5500 N 100000 N 160000 N 310000 N 500000 N 700000 N 800000 N
MaximumStrain
5500 N 100000 N 160000 N 310000 N 480000 N 700000 N 900000 N
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Results and Discussion
NO
YESDifference < 5%?
Difference < 5%?
NO
YES
Modify boundary conditions?
START
END
NO
YES
Build FEM1 (metallicreinforced panel)
Compare FEM1 with NACATN2661 (Kuhn, 1952a)
Modify boundaryconditions
Build FEM2 and FEM3(composite reinforced panel)
Compare FEM2 with FEM3
Change materialor laminate
Build 6 models FEM4(composite reinforced panel)
Compare the 6 models FEM4
Choose the model with thelowest failure index
Compare the best modelwith the metallic one
Choose the best solution fordiagonal tension
Step 5
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Composite Reinforced Panel vs. Metallic Reinforced Panel
Composite Panel Metallic Panel Difference
Web’s thick 1.52 mm 0.701 mm -53.87%
Total Mass 14.330 kg 14.330 kg 0.00%
Carbon/epoxy tape [45/-45/0/90]S Aluminum 2524 T3
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Eigenvalue Diagonal Tension
Composite Model 0.114361 0.17001
Metallic Model 0.014123 0.04500
Composite Reinforced Panel vs. Metallic Reinforced PanelModel - Carbon/epoxy tape [45/-45/0/90]S
Model - Aluminum 2524 T3
Model - Carbon/epoxy tape [45/-45/0/90]S
Model - Aluminum 2524 T3
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Composite Reinforced Panel vs. Metallic Reinforced Panel
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Composite Reinforced Panel vs. Metallic Reinforced Panel
Eigenvalue Diagonal Tension
Composite Model 0.114361 0.17001
Metallic Model 0.114977 0.170166
Model - Carbon/epoxy tape [45/-45/0/90]S
Model - Aluminum 2524 T3
Model - Carbon/epoxy tape [45/-45/0/90]S
Model - Aluminum 2524 T3
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Composite Reinforced Panel vs. Metallic Reinforced Panel
Composite Panel Metallic Panel Difference
Web’s thick 1.52 mm 1.51 mm -0.82%
Total Mass 14.330 kg 17.368 kg 21.20%
Carbon/epoxy tape [45/-45/0/90]S Aluminum 2524 T3
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Agenda
• Introduction
• Objectives
• Methodology
• Results and Discussion
• Conclusion
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Conclusion1. To build a FEM to represents the post-buckling behavior of the composite reinforced
panel without having to use experimental results:a) The results have shown that it was possible to represent the behavior of the
composite reinforced panel during post-buckling using the FEM developed.
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Conclusion2. Study the influence of stacking sequence in post-buckling behavior:
b) The six lay-ups presented different failure index in the moment when first occurs thediagonal tension. And the conclusion was that the model that had better results, orlower failure index, was the one with +45 and -45 at the outside layers.
Carbon/epoxy tape
Model 1 [0/90/45/-45]S
Model 2 [45/-45/0/90]S
Model 3 [45/0/90/-45]S
Model 4 [0/45/-45/90]S
Model 5 [0/45/90/-45]S
Model 6 [45/0/-45/90]S
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Conclusion3. Choose the reinforced panel that have the best behavior during the post-buckling
analysis, metallic or composite:c) The comparison between buckling analysis and post-buckling behavior shown that the
web of the composite reinforced panel withstands to greater loads than the metallicone, and consequently redistributes less load for the stiffeners. Therefore, it is possibleto conclude that the composite reinforced panel presents the best behavior during thepost-buckling event.
CompositePanel
MetallicPanel
Difference
Web’sthick
1.52 mm 1.51 mm -0.82%
Mass 14.330 kg 17.368 kg 21.20%
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Thank you
Take the first step in faith.
You don't have to see the whole staircase, just take the first step.
Martin Luther King Jr
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