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

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(a) (b) Figure B.15: Out-of-plane deflection from DIC measurements of a panel with H250 core and a debond diameter of 200 mm, (a) prior to propagation and (b) after propagation. (a) (b) Figure B.16: Out-of-plane deflection from DIC measurements of a panel with H250 core and a debond diameter of 300 mm, (a) prior to propagation and (b) after propagation. 162
Appendix C Additional Results from the Tests on the STT Specimens In this appendix additional results from the static and fatigue tests performed on STT specimens studied in Chapter 5 are presented. C.1 Axial Displacement vs. Force Curves from the Static Tests In this section axial displacement vs. force curves for the STT specimens with H45, H100 and H250 are presented. Force (kN) 0.6 0.4 0.2 0 (a) 1.2 (b) 1.2 (c) Specimen 1 Specimen 2 0 0.5 1 1.5 Axial displacement (mm) Force (kN) 0.8 0.4 0 0 1 2 3 Axial displacement (mm) Figure C.1: Axial displacement vs. force for STT specimens with (a) H45, (b) H100 and (c) H250 core. 163 Specimen 1 Specimen 2 Force (kN) 0.8 0.4 0 Specimen 1 Specimen 2 0 1 2 3 Axial displacement (mm)
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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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should be taken into account for a
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Figure 5.25: Kinking of the crack i
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log (da/dN) (mm/cycle) 10 log G (J/
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Page 140 and 141: Load (kN) 2 1.5 1 0.5 0 Panel 1 Pan
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Page 146 and 147: 110 q=qG=0.4 Test #1 100 Test #2 Te
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Page 152 and 153: toughness using MMB fracture toughn
Page 154 and 155: For the specimens with H250 core th
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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
Page 174 and 175: (a) Figure A.14: Out-of-plane defle
Page 176 and 177: (a) (b) Figure A.18: Out-of-plane d
Page 178 and 179: Load (kN) 250 200 150 100 50 250 30
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 188: DTU Mechanical Engineering Section
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