Residual Strength and Fatigue Lifetime of ... - Solid Mechanics

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Load (kN) 250 200 150 100 50 250 300 (a) (b) (c) Panel 1 Panel 2 Load (kN) 200 150 100 50 Panel 1 Panel 2 0 0 0 0 2 4 6 0 2 4 6 0 2 4 6 8 Displacement (mm) Displacement (mm) Displacement (mm) Figure B.2: Displacement vs. load for panels with H130 core and a debond diameter of (a) 100 mm, (b) 200 mm and (c) 300 mm. 250 (a) 250 (b) 250 (c) Load (kN) 200 150 100 50 Panel 1 Panel 2 Load (kN) 200 150 100 50 Panel 1 Panel 2 0 0 0 0 2 4 6 8 0 2 4 6 0 2 4 6 Displacement (mm) Displacement (mm) Displacement (mm) Figure B.3: Displacement vs. load for panels with H250 core and a debond diameter of (a) 100 mm, (b) 200 mm and (c) 300 mm. 350 (a) 400 (b) 400 (c) Load (kN) 300 250 200 150 100 50 Panel 1 Panel 2 Panel 3 Load (kN) 300 200 100 Panel 1 Panel 2 Panel 3 0 0 0 0 2 4 6 0 2 4 6 8 10 0 2 4 6 8 10 Displacement (mm) Displacement (mm) Displacement (mm) Figure B.4: Displacement vs. load for the intact panels with (a) PMI, (b) H130 and (c) H250 core. 156 Load (kN) Load (kN) Load (kN) 250 200 150 100 50 200 150 100 50 300 200 100 Panel 1 Panel 2 Panel 1 Panel 2 Panel 1 Panel 2 Panel 3
B.2 Out-of-plane Deflection vs. Load Curves In this section out-of-plane displacement vs. load curves of the tested panels are presented. The out-of-plane deflection refers to the centre of the debond. Displacement (mm) Displacement (mm) 8 6 4 2 0 6 6 (a) (b) (c) Panel 1 Panel 2 Panel 3 0 30 60 90 120 Load (kN) Displacement (mm) 4 2 0 Panel 1 Panel 2 Panel 3 0 20 40 Load (kN) 60 80 Figure B.5: Load vs. out-of-plane displacement for the panels with PMI core and a debond diameter of (a) 100 mm, (b) 200 mm and (c) 300 mm. 8 6 4 2 0 8 8 (a) (b) (c) Panel 1 Panel 2 0 50 100 150 200 Load (kN) Displacement (mm) 6 4 2 0 Panel 1 Panel 2 0 30 60 90 120 Load (kN) Figure B.6: Load vs. out-of-plane displacement for the panels with H130 core and a debond diameter of (a) 100 mm, (b) 200 mm and (c) 300 mm. 157 Displacement (mm) Displacement (mm) 4 2 0 6 4 2 0 Panel 1 Panel 2 Panel 3 0 20 40 60 Load (kN) Panel 1 Panel 2 0 25 50 75 100 Load (kN)
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Residual Strength and Fatigue Lifet
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Published in Denmark by Technical U
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method to accelerate the simulation
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Synopsis Sandwich kompositter er i
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Contents Preface Executive Summary
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5 Face/core Interface Fatigue Crack
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H11 bimaterial constant H22 bimater
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These peculiar damage modes often r
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1.2 Overview of the Thesis In this
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Figure 1.3: Fracture modes, from Be
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In Equations (1.5) and (1.6) H11, H
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Figure 1.6: Schematic illustration
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The compact tension specimen (CT) i
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A Figure 1.10: CSB, DCB, TSD, DCB-U
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Chapter 2 Buckling Driven Face/Core
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(DIC) measurement system (ARAMIS 2M
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corresponds to the onset of debond
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Figure 2.7: Crack kinking into the
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(2.2) where and for plane str
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A modified version of the tilted sa
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previous observations of crack path
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of contact elements (CONTACT173 and
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the debond opening initially increa
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Table 2.4: Instability loads determ
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G (J/m2) 600 400 200 0 H100 IMP=0.1
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Hayman (2007) has described a damag
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Table 3.1: Panel test specimens. La
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sheet and the core thickness, respe
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Load (N) 250 200 150 100 50 0 H130
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Table 3.4: Parameters in the face/c
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was used to monitor 3D surface disp
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arising due to the junction between
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(a) Debonded face sheet Figure 3.16
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Figure 3.19 shows the determined en
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H130 MMB H130 Panel H250 MMB Interf
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3.6 Conclusion In this chapter the
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composite laminates under thermal c
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S S y( t ) y( t ) ( t ) 2 1 12 2
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listed in Table 4.1. The length and
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The strain energy release rate, G,
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high growth rate of G (see Figure 4
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4.4 Face/Core Fatigue Crack Growth
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Debond 310 mm Symmetry B. C. a Figu
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B 2 1/ 2 ( S44 S55 S45) (4.17) wh
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75), which illustrates possible ina
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Figure 4.18 (a) presents the deflec
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Debond radius (mm) 100 90 80 70 60
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using the cycle jump method, more t
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Chapter 5 Face/Core Interface Fatig
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of this chapter, sandwich panels wi
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H250 Specimen H100 Specimen H45 Spe
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Figure 5.5: Test setup. Initially,
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H100 Specimen Fibre bridging Figure
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propagation, the crack continues to
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Figure 5.14: Kinking of the crack i
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Crack length [mm] Crack length [mm]
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mode-mixity phase angle was chosen
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Page 146 and 147: 110 q=qG=0.4 Test #1 100 Test #2 Te
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Page 160 and 161: Bezazi A., Mahi A. E., Berthelot J.
Page 162 and 163: Kanny K. and Mahfuz H. (2005), Flex
Page 164 and 165: Ratcliffe J. and Cantwell W. J. (20
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Page 168 and 169: Out-of-plane displacement (mm) 1 0.
Page 170 and 171: Out-of-plane displacement (mm) 3 2
Page 172 and 173: A.5 Out-of-plane deflection of Debo
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Page 176 and 177: (a) (b) Figure A.18: Out-of-plane d
Page 180 and 181: Displacement (mm) 4 3 2 1 0 8 9 (a)
Page 182 and 183: (a) (b) Figure B.11: Out-of-plane d
Page 184 and 185: (a) (b) Figure B.15: Out-of-plane d
Page 188: DTU Mechanical Engineering Section
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Residual Strength and Fatigue Lifetime of ... - Solid Mechanics

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