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

More documents

Recommendations

Info

Out-of-plane displacement (mm) 3 2 1 0 2 (a) (b) Column1 Column2 Column3 0 5 10 Load (kN) 15 Figure A.6: Load vs. out-of-plane displacement for the H200 columns with a debond length of (a) 38.1 mm and (b) 50.8 mm. A.4 Initial Imperfections in Debonded Columns In this section DIC images of initial out-of-plane imperfections in columns with H45, H100 and H200 core are shown. Figure A.7: Initial imperfections in columns with H45 core and a debond length of (a) 25.4 mm, (b) 38.1 mm and (c) 50.8 mm. 148 Out-of-plane displacement (mm) 1.5 1 0.5 (a) (b) 0 Column1 Column2 Column3 0 3 6 Load (KN) 9 (c)
(a) (b) (c) Figure A.8: Initial imperfections in columns with H100 core and a debond length of (a) 25.4 mm, (b) 38.1 mm and (c) 50.8 mm. (a) (b) (c) Figure A.9: Initial imperfections in columns with H200 core and a debond length of (a) 25.4 mm, (b) 38.1 mm and (c) 50.8 mm. 149
Page 1:
Residual Strength and Fatigue Lifet
Page 4 and 5:
Published in Denmark by Technical U
Page 6 and 7:
This page is intentionally left bla
Page 8 and 9:
method to accelerate the simulation
Page 10 and 11:
Synopsis Sandwich kompositter er i
Page 12 and 13:
Page 14 and 15:
Contents Preface Executive Summary
Page 16 and 17:
5 Face/core Interface Fatigue Crack
Page 18 and 19:
Page 20 and 21:
H11 bimaterial constant H22 bimater
Page 22 and 23:
Page 24 and 25:
These peculiar damage modes often r
Page 26 and 27:
1.2 Overview of the Thesis In this
Page 28 and 29:
Figure 1.3: Fracture modes, from Be
Page 30 and 31:
In Equations (1.5) and (1.6) H11, H
Page 32 and 33:
Figure 1.6: Schematic illustration
Page 34 and 35:
The compact tension specimen (CT) i
Page 36 and 37:
A Figure 1.10: CSB, DCB, TSD, DCB-U
Page 38 and 39:
Chapter 2 Buckling Driven Face/Core
Page 40 and 41:
(DIC) measurement system (ARAMIS 2M
Page 42 and 43:
corresponds to the onset of debond
Page 44 and 45:
Figure 2.7: Crack kinking into the
Page 46 and 47:
(2.2) where and for plane str
Page 48 and 49:
A modified version of the tilted sa
Page 50 and 51:
previous observations of crack path
Page 52 and 53:
of contact elements (CONTACT173 and
Page 54 and 55:
the debond opening initially increa
Page 56 and 57:
Table 2.4: Instability loads determ
Page 58 and 59:
G (J/m2) 600 400 200 0 H100 IMP=0.1
Page 60 and 61:
Page 62 and 63:
Hayman (2007) has described a damag
Page 64 and 65:
Table 3.1: Panel test specimens. La
Page 66 and 67:
sheet and the core thickness, respe
Page 68 and 69:
Load (N) 250 200 150 100 50 0 H130
Page 70 and 71:
Table 3.4: Parameters in the face/c
Page 72 and 73:
was used to monitor 3D surface disp
Page 74 and 75:
arising due to the junction between
Page 76 and 77:
(a) Debonded face sheet Figure 3.16
Page 78 and 79:
Figure 3.19 shows the determined en
Page 80 and 81:
H130 MMB H130 Panel H250 MMB Interf
Page 82 and 83:
3.6 Conclusion In this chapter the
Page 84 and 85:
Page 86 and 87:
composite laminates under thermal c
Page 88 and 89:
S S y( t ) y( t ) ( t ) 2 1 12 2
Page 90 and 91:
listed in Table 4.1. The length and
Page 92 and 93:
The strain energy release rate, G,
Page 94 and 95:
high growth rate of G (see Figure 4
Page 96 and 97:
4.4 Face/Core Fatigue Crack Growth
Page 98 and 99:
Debond 310 mm Symmetry B. C. a Figu
Page 100 and 101:
B 2 1/ 2 ( S44 S55 S45) (4.17) wh
Page 102 and 103:
75), which illustrates possible ina
Page 104 and 105:
Figure 4.18 (a) presents the deflec
Page 106 and 107:
Debond radius (mm) 100 90 80 70 60
Page 108 and 109:
using the cycle jump method, more t
Page 110 and 111:
Chapter 5 Face/Core Interface Fatig
Page 112 and 113:
of this chapter, sandwich panels wi
Page 114 and 115:
H250 Specimen H100 Specimen H45 Spe
Page 116 and 117:
Figure 5.5: Test setup. Initially,
Page 118 and 119:
H100 Specimen Fibre bridging Figure
Page 120 and 121: propagation, the crack continues to
Page 122 and 123: Figure 5.14: Kinking of the crack i
Page 124 and 125: Crack length [mm] Crack length [mm]
Page 126 and 127: mode-mixity phase angle was chosen
Page 128 and 129: should be taken into account for a
Page 130 and 131: Figure 5.25: Kinking of the crack i
Page 132 and 133: log (da/dN) (mm/cycle) 10 log G (J/
Page 134 and 135: erroneous extrapolations in the tra
Page 136 and 137: compared to the 65% efficiency obta
Page 138 and 139: the case of uneven debond growth, t
Page 140 and 141: Load (kN) 2 1.5 1 0.5 0 Panel 1 Pan
Page 142 and 143: Figure 5.42: Zero and ninety degree
Page 144 and 145: G(J/m 2 ) 180 150 210 120 150 100 5
Page 146 and 147: 110 q=qG=0.4 Test #1 100 Test #2 Te
Page 148 and 149: panels were determined for differen
Page 150 and 151: Chapter 6 Conclusion and Future Wor
Page 152 and 153: toughness using MMB fracture toughn
Page 154 and 155: For the specimens with H250 core th
Page 156 and 157: Development of testing methods for
Page 158 and 159: This page is intentionally left bla
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
Page 166 and 167: This page is intentionally left bla
Page 168 and 169: Out-of-plane displacement (mm) 1 0.
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 184 and 185: (a) (b) Figure B.15: Out-of-plane d
Page 188: DTU Mechanical Engineering Section
show all

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

Create successful ePaper yourself

Delete template?

Save as template?