ML19114A311
| ML19114A311 | |
| Person / Time | |
|---|---|
| Site: | 07103052 |
| Issue date: | 03/05/2019 |
| From: | Paris A TN Americas LLC, Orano USA |
| To: | Division of Spent Fuel Management |
| Shared Package | |
| ML19115A128 | List:
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| References | |
| Download: ML19114A311 (57) | |
Text
TN International CHAPTER 1 - APPENDIX 9-1 TN-MTR Names Signatures Date Prepared by A. PARIS Ref. DOS-18-011415-016-NPV Rev. 1.0 Form: PM04-3-MO-3 rev. 2 Page 1/57 NON PROPRIETARY VERSION FITTING OF THE OBLIQUE DROP OF THE MOCKUP OF THE TN-MTR PACKAGE TABLE OF CONTENTS REVISION STATUS
SUMMARY
- 1. INTRODUCTION
- 2. BASIC DATA
- 3. MODELLING
- 4. RESULTS
- 5. CONCLUSIONS
- 6. REFERENCES LIST OF TABLES LIST OF FIGURES LIST OF APPENDICES
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 2/57 NON PROPRIETARY VERSION REVISION STATUS Revision Date Modifications Prepared by /
Reviewed by Old reference: DOS-16-00173678-191 0
N/A Document first issue.
APA / ALC New reference: DOS-18-011415-016 1.0 N/A New reference due to new document management system software.
APA / ALC
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 3/57 NON PROPRIETARY VERSION
SUMMARY
The aim of this study is to fit the oblique drop on the corner of the shock absorbing cover of the 1/2 scale packaging mockup.
The next drop is studied (drop No. 4 described in Chapter 1-6):
9.25 m drop onto a cylindrical edge of the shock absorbing cover on the top of the mockup.
The packaging axis is at 47° from the horizontal. The mockup is oriented head-down and drops on the 90°-270° line.
The fitting of the numerical model of the mockup is based upon:
accelerometer readings for Drop No. 4 derived from Chapter 1-6; crushing of shock absorbing covers surveyed during real drops for drop No. 4 taken from Chapter 1 -6.
The purpose of this fitting is to obtain a numerical model that gives reliable compression and acceleration results. This calibrated model is then used for calculations to extrapolate the package model to -40°C and to the maximum temperature under normal transport conditions for oblique and top-down axial cases (see Appendices 1-9-2 and 1-9-3).
The fitting made to the iso-model with the fitting of the lateral drop presented in Chapter 1-9-4 gives satisfactory results.
The duration and the shape of the acceleration peaks obtained in the simulation are representative of the test. Therefore the fitting is satisfactory in terms of acceleration.
The crushed heights of the shock absorbing cover measured in the simulation are higher overall than those measured after the drop test. Therefore the numerical model is conservative in terms of crushing.
The numerical model used is representative of the behaviour of the 1/2 scale mockup of the TN-MTR packaging in oblique drop.
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 4/57 NON PROPRIETARY VERSION
- 1. INTRODUCTION The aim of this study is to fit the oblique drop on the corner of the shock absorbing cover of the 1/2 scale packaging mockup.
The next drop is studied (drop No. 4 described in Chapter 1-6):
9.25 m drop onto a cylindrical edge of the shock absorbing cover on the top of the mockup.
The packaging axis is 47° from the horizontal. The mockup is oriented head-down and drops on the 90°-270° line.
The fitting of the numerical model of the mockup is based upon:
accelerometer readings for Drop No. 4 derived from Chapter 1-6; crushing of shock absorbing covers measured during real drops for drop No. 4 taken from Chapter 1 -6).
The purpose of this fitting is to obtain a numerical model that gives reliable compression and acceleration results. This calibrated model is then used for calculations to extrapolate the package model to -40°C and to the maximum temperature under normal transport conditions for oblique and top-down axial cases (see Appendices 1-9-2 and 1-9-3).
The iso-model fitting with the lateral drop (see chapter 1-9-4) is made at ambient temperature (20°C). This fitting results in a numerical model that gives reliable compression and acceleration results.
- 2. BASIC DATA The input data for the fitting are as follows:
mockup geometry (see Chapter 1-4);
mockup mechanical properties presented in section 3.6; report of regulatory drop tests (chapter 1-6).
- 3. MODELLING 3.1. Computer codes used The geometry of the model is prepared with software <3>.
The calculations are made with<2 > in double precision.
The results presented below were processed with LS-PREPOST.2.2.
3.2. Geometry and meshing The geometry of the 1/2 scale mockup of the TN-MTR packaging is presented in figure 1 1.1. The fitting is made with iso-model with the lateral drop fitting (see Chapter 1-9-4).
The mesh of the model is presented in figure 1-9-1.2.
The orientation of the wood in the shock absorbing cover is shown in Figure 9-1.3.
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 5/57 NON PROPRIETARY VERSION 3.3. Calculation cases The calculation made to fit the oblique drop of the 1/2 scale mockup (drop No. 4 in Chapter 1-6) is presented in figure 1-9-1.7.
The fitting is made with a drop angle between the axis of the packaging and the horizontal equal to 47°. The centre of gravity of the mockup should initially be aligned with the point of impact (drop angle 50°), but an angle of 47° from the packaging axis was considered to obtain optimum fitting of accelerations. The line of impact of the mockup is at 90° and that of the basket is at 0°.
3.4. Modelling assumptions For reasons of symmetry, only a half-model is created.
3.4.1. Content The mass of the content is uniformly distributed on the lid over a diameter of 477.5 mm. This content is modelled by 5 mm thick shell elements with null material (zero stiffness in this material).
3.4.2. Lid
- The complete lid is modelled with the flange, the lead shielding enclosure, the stiffener shell, the outer shell and the inner disk.
- The shells (outer and stiffener) are modelled by 5 mm thick shell elements.
- The groove of the lid seal located close to the inside of the cavity is modelled.
- The class 8-8 M14 screws fastening the lid to the shell are modelled according to figure 1-9-1.1.
- The preload in each screw is applied using *MAT_ORTHOTROPIC_THERMAL in which a coefficient of thermal expansion is defined. The screw/shell interface is modelled by a sticking contact.
MAT_ORTHOTROPIC_THERMAL Sticking contact
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 6/57 NON PROPRIETARY VERSION 3.4.3. Shell
- The shell is divided into two parts, namely the flange and the shell body, they are both considered to be deformable.
- The resin is ignored: the volume that it occupies is filled by the lead shielding for which the density is reevaluated accordingly. The shell outside wall is modelled by shell elements with a common node with the lead. The inside wall is modelled by shell elements in contact with 3-d elements representing the lead.
- The trunnions are modelled by cylinders with a constant diameter of 60 mm "stuck" to the shell flange.
- Accelerations on the shell are filtered at 1 000 Hz as in the tests. Accelerations are filtered using an 8-order Butterworth filter. Accelerometers are placed as can be seen on photos of the drop mockup (see figure 1-9-1.6).
3.4.4. Shock absorbing cover
- The containment plate around the shock absorbing cover is modelled by shell elements.
- Lid screw passage tubes are modelled by shell type elements.
- The orifice located at the plywood is not modelled. Therefore the plywood is distributed over a 490 mm diameter.
- Gusset plate welds and the shock absorbing cover containment plate are represented to improve fitting. These welds are modelled by beam elements (2 mm diameter tubes) with a *MAT_SPOTWELD (see Appendix 1-9-1.1). An erosion criterion is defined, based on the maximum tensile force along one direction (centreline of beam) and the maximum shear force along the other two directions (see Appendix 1-9-1.1). The geometry of the welds is presented in figure 9-1.5.
- The shock absorbing cover M20 attachment screws are simplified and are modelled by17.5 mm diameter cylinders. Washers are not represented. The screw/shell interface is modelled by a sticking contact, and the screw/ring interface is modelled with a << surface to surface >> contact at the anti-puncture plate.
3.5. Boundary conditions and loads 3.5.1. Conditions of symmetry Nodes located in planes of symmetry have their translation degrees of freedom normal to these planes fixed, and their rotation degrees of freedom in these planes are also fixed (see figure 1-9-1.4).
Sticking contact
<< Surface to surface >> contact
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 7/57 NON PROPRIETARY VERSION 3.5.2. Loads Gravity is taken into account by the application of a downwards field equal to 9.81 ms-.
3.5.3. Initial speed The mockup was placed theoretically at 9.25 m above the ground. The velocity of the package at the moment of impact is calculated using the following formula:
25
,9 81
,9 2
2 0
h g
V
= 13.5 m.s-1 3.5.4. Coefficient of friction The coefficient of friction used is equal to 0.1 between all parts of the package.
The coefficient of friction used is equal to 0.1 between the mockup and the non-deformable target 3.5.5. Pre-loading of lid screws The maximum preload of M14 screws is taken to be equal to 73.8 kN, this value bounds the maximum preload of mockup lid screws equal to 61.8 kN determined in Chapter 1-5.
3.6. Materials The mechanical properties of the mockup used for the fitting calculations are presented in Table 1-9-1.1.
The properties of oak and balsa used for the model of the mockup are presented in Appendix 1-9-1.2.
The properties of plywood used for the model of the mockup are presented in Appendix 1-9-1.3.
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 8/57 NON PROPRIETARY VERSION 3.7. Masses The mass balance for the numerical model of the mockup is presented in the following table:
Mockup fitting Component Mockup (see Chapter 1-6) (kg)
Numerical model (kg)
Difference
(%)
Body (shell + bottom + resin +
outer enclosure + trunnions) 1,920 1,919.9
< 0.1 Lid 320 319.9
< 0.1 Shock absorbing cover 180 179.4 0.3 Content 359 359
< 0.1 Total 2,780 2,778.2
< 0.1 The masses of the numerical model used for the fitting are representative of the masses of the mockup.
- 4. RESULTS The results are archived in <1>.
4.1. Energy balance The energy balance of the drop is presented in figure 1-9-1.8. We see that Hourglass energies and sliding energies are very low, which demonstrates the validity of the calculations.
4.2. Maximum accelerations Maximum accelerations measured by the accelerometers are filtered with an 8-order Butterworth, at 1 000 Hz. These accelerations are shown on Figure 1-9-1.9.
Maximum accelerations measured by the 4AX, 4AY, 4BX and 4BY accelerometers are presented in the following table:
Case Maximum accelerations (g) 4AX 4AY 4BX 4BY Test (reference)
Simulation Difference (%)
+13.3
-7.2
-7.1
+4.9 Accelerations obtained for simulation of the mockup drop are used to fit the results obtained in simulation with the test results: 13.3% maximum difference between the test and the simulation. The amplitude of each signal obtained with the numerical model is very close to the test amplitude. Therefore the fitting is satisfactory in terms of acceleration.
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 9/57 NON PROPRIETARY VERSION 4.3. Shock absorbing cover strains Figures 1-9-1.10 and 1-9-1.11 show deformed shapes of the shock absorbing cover and maximum deformations.
Final distance after impact (mm)
Mark D D1 D2 D3 D4 D5 Test (reference)
Simulation Difference (%)
-2.6
+18.8
+5.4
+11.2
+4 The maximum difference between crushing distances obtained by simulation and during the test is 18.8%. In general, the calibrated model is conservative because it tends to maximise crushing. Therefore the fitting is satisfactory in terms of crushing.
- 5. CONCLUSIONS This study calibrated the 9.25m oblique drop No. 4 with an angle of 47° of the TN-MTR mockup.
The fitting made to the iso-model with the fitting of the lateral drop presented in Chapter 1-9-4 gives satisfactory results.
The duration and the shape of the acceleration peaks obtained in the simulation are representative of the test. Therefore the fitting is satisfactory in terms of acceleration.
The fitting of crushing distances of the shock absorbing cover is satisfactory. The crushed heights of the shock absorbing cover measured in the simulation are higher overall than those measured after the drop test. The numerical model is conservative in terms of crushing.
The numerical model used is representative of the behaviour of the 1/2 scale mockup of the TN--
MTR packaging in oblique drop.
- 6. REFERENCES
<1> File archiving: L\\Archivage\\08S.EMC001171T\\Dynamique\\CAL-10-00016264-002-00
<2> LS-DYNA software v971.7600.1224
<3> NX-IDEAS software m1
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 10/57 NON PROPRIETARY VERSION LIST OF TABLES Table Description Pages 1-9-1.1 Characteristics of materials used in the mockup model 1
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 11/57 NON PROPRIETARY VERSION LIST OF FIGURES Figure Description Pages 1-9-1.1 Geometry of the mockup half-model 23 1-9-1.2 Model meshing 1
1-9-1.3 Orientation of the wood in the shock absorbing cover 2
1-9-1.4 Conditions of symmetry 1
1-9-1.5 Model of shock absorbing cover welds 1
1-9-1.6 Position of accelerometers 1
1-9-1.7 Calculation case 1
1-9-1.8 Energy balance 1
1-9-1.9 Maximum accelerations 2
1-9-1.10 Deformed shape after impact 3
1-9-1.11 Measurement of deformations after impact 2
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 12/57 NON PROPRIETARY VERSION LIST OF APPENDICES Appendi x
Description Pages 1-9-1.1 Modelling welds 1
1-9-1.2 Modelling of the wood in LS-DYNA 4
1-9-1.3 Modelling of the plywood in LS-DYNA 1
TN International Ref.: DOS-06-00032593-191 Rev. 0 Page 13/57 NON PROPRIETARY VERSION TABLE 1-9-1.1 CHARACTERISTICS OF MATERIALS USED IN THE MOCKUP MODEL Component Re (MPa)
Rm (MPa)
E (GPa)
A (%)
Shell Flange 274 583 210 59.6 Bottom 555 728 210 48 Inner plate 303 568.5 210 56.5 Outer plate 275 565 210 66.9 Shell body (lead) 19 38.6 42.46 50 Lid Shielding enclosure (lead) 19 38.6 42.46 50 Flange 577.5 754 210 32 Outer shell 606 785 210 32 Stiffener shell 591.5 799 210 31.75 Inner disk 601 762 210 38 Shock absorbing cover M20 screw passage tubes 273.5 567 210 55.5 Containment plate Anti-puncture plate Gusset plates 277 570.2 210 50.8 Central disk 591 762 210 38 Intermediate disk Screws M20 screws 1080 1200 210 8
M14 screws 640 800 210 12
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 14/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (1/23)
GEOMETRY OF THE MOCKUP HALF-MODEL General overview of model Lid: overview
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 15/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (2/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Lid: view 1 Lid-seal groove: view 2 4.8
Ø = 555.8 9.074 3.7
Ø = 551.5 17.5
Ø = 550.5 32.5 52.5 80
Ø = 645
Ø = 540
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 16/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (3/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Lid: view 3
Ø = 545.5
Ø = 249 e= 5 e= 5
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 17/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (4/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Shell - flange: view 1 Shell - flange: view 2
Ø = 480
Ø = 551
Ø = 645.5 54.5 46.5 30 10 98 32.5
Ø = 740 37.5 140.5 30
Ø = 738.5 10
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 18/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (5/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Shell - trunnions
Ø = 60 42.5 37.6
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 19/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (6/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Shell body - lead FIGURE 1-9-1.1 (7/23) 69 69
Ø = 501 10x10 chamfer 658.5
Ø = 728
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 20/57 NON PROPRIETARY VERSION GEOMETRY OF THE MOCKUP HALF-MODEL Shell body - plates: view 1 69 69 658.5
Ø = 728 e= 12 e= 12
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 21/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (8/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Shell body - plates: view 2 527
Ø = 490 e= 10 e= 10
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 22/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (9/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Shell bottom: outer plate
Ø = 590 e= 12
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 23/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (10/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Shell bottom: inner plate View 1 Shell bottom: inner plate View 1
Ø = 490 10x10 chamfer
Ø = 470 e= 15
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 24/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (11/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Dimensions of the spacer and the content Angular distribution of the spacer and the content 45° Shim Content 360.5 179.5 e = 8 e = 8
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 25/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (12/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - positioning plate: view 1 Top shock absorbing cover - positioning plate: view 2 FIGURE 1-9-1.1 (13/23)
Ø = 760.5 10.65
Ø = 739.2 28 58 25 52.5
Ø = 740 5
10.25
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 26/57 NON PROPRIETARY VERSION GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - axial balsa 99 15x15
Ø = 50
Ø = 496.5
Ø = 737
Ø = 879.3
Ø = 691 65.9
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 27/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (14/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - radial balsa
Ø = 1035
Ø = 880.5 14.6x15 99
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 28/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (15/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover -upper radial oak 15x15.1 74.5
Ø = 50 28.2 14.7 88.25
Ø = 737
Ø = 496.5
Ø = 691
Ø = 1035 65.9
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 29/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (16/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover -lower radial oak
Ø = 751.3
Ø = 1035 133.8 15 8.08
Ø = 751.3
Ø = 767.45 116.5 81.5 35 15 111.3 15.5 15
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 30/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (17/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - plywood Top shock absorbing cover - containment plate at the plywood
Ø = 492 33 e = 5 e = 5
Ø = 488.9
Ø = 488.9 53.5 27 6
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 31/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (18/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - gusset plate Top shock absorbing cover - screw passage tube
Ø = 46.7 60° 60° Top view Side view Top view 193 99 145 88.8 191 122 12.5 136.5 5
131.1 90 100 271 325 e= 2 32.1 136.5
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 32/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (19/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - angular distribution of M20 screw holes and gusset plates 60° 30° 30° 60° 30° 30° 60° 60° 45° 45° 15° 15° 60° Gusset plates Top view Upper oak top view Axial balsa Top view
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 33/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (20/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - containment plate: view 1 Top shock absorbing cover - containment plate: view 2
Ø = 492
Ø = 645.6
Ø = 746
Ø = 1038
Ø = 740
Ø = 46.7
Ø = 46.7 59 134 91 102 124 76.8 59 100 327 e = 2
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 34/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (21/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - containment plate welds Top shock absorbing cover - details of gusset plate welds
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 35/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (22/23)
GEOMETRY OF THE MOCKUP HALF-MODEL Top shock absorbing cover - angular distribution of M20 screw holes for the containment plate:
view 3 M14 screws and M20 screws 30° 30° 60° 60° 63.5 17.5 M14 screws M20 screws 4.4 7
Ø = 12.1 14 7
Ø = 21
Ø = 12.6 16 1.5 5.5
Ø = 17.5 1.6
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 36/57 NON PROPRIETARY VERSION FIGURE 1-9-1.1 (23/23)
GEOMETRY OF THE MOCKUP HALF-MODEL M20 screws: angular distribution (top view)
M14 screws: angular distribution (top view) 30° 30° 60° 60° 5° 10°
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 37/57 NON PROPRIETARY VERSION FIGURE 1-9-1.2 MODEL MESH Half-model Model: overview
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 38/57 NON PROPRIETARY VERSION FIGURE 1-9-1.3 (1/2)
ORIENTATION OF THE WOOD IN THE SHOCK ABSORBING COVER Orientation of the wood: balsa Orientation of the wood: upper oak
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 39/57 NON PROPRIETARY VERSION FIGURE 1-9-1.3 (2/2)
ORIENTATION OF THE WOOD IN THE SHOCK ABSORBING COVER Orientation of the wood: lower oak and plywood
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 40/57 NON PROPRIETARY VERSION FIGURE 1-9-1.4 CONDITIONS OF SYMMETRY Nodes constrained in the plane of symmetry Dx=free Rx=0 Dy=free Ry=0 Dz=0 Rz=free
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 41/57 NON PROPRIETARY VERSION FIGURE 1-9-1.5 MODEL OF SHOCK ABSORBING COVER WELDS
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 42/57 NON PROPRIETARY VERSION FIGURE 1-9-1.6 POSITION OF ACCELEROMETERS 4AX 4AY Accelerometer No. 4551 4BY 4BX Accelerometer No. 1115944
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 43/57 NON PROPRIETARY VERSION FIGURE 1-9-1.7 CALCULATION CASE Calibration 47°
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 44/57 NON PROPRIETARY VERSION FIGURE 1-9-1.8 ENERGY BALANCE Overall energy balance
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 45/57 NON PROPRIETARY VERSION FIGURE 1-9-1.9 (1/2)
MAXIMUM ACCELERATIONS 1 000 Hz Butterworth Filter Accelerometer 4AX: comparison between test / simulation Accelerometer 4AY: comparison between test / simulation
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 46/57 NON PROPRIETARY VERSION FIGURE 1-9-1.9 (2/2)
MAXIMUM ACCELERATIONS 1 000 Hz Butterworth Filter Accelerometer 4BX: comparison between test / simulation Accelerometer 4BY: comparison between test / simulation
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 47/57 NON PROPRIETARY VERSION FIGURE 1-9-1.10 (1/3)
DEFORMED SHAPES AFTER IMPACT View 1 View 2
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 48/57 NON PROPRIETARY VERSION FIGURE 1-9-1.10 (2/3)
DEFORMED SHAPES AFTER IMPACT View 3 View 4
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 49/57 NON PROPRIETARY VERSION FIGURE 1-9-1.10 (3/3)
DEFORMED SHAPES AFTER IMPACT View 5
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 50/57 NON PROPRIETARY VERSION FIGURE 1-9-1.11 (1/2)
MEASUREMENT OF DEFORMATIONS AFTER IMPACT View 1: Distance D1 between node No. 1058845 and node No. 1108585 along the y direction in the local coordinate system CSYS1 View 2 Distance between node No. 293845 and node No. 406766 along the y direction in the local coordinate system CSYS1 D3=
D2=
D4=
D1=+2* =
- thickness of the plate
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 51/57 NON PROPRIETARY VERSION FIGURE 1-9-1.11 (2/2)
MEASUREMENT OF DEFORMATIONS AFTER IMPACT View 3 Distance D between node No. 406766 and node No. 166401 in the local coordinate system CSYS1 D5=
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 52/57 NON PROPRIETARY VERSION APPENDIX 1-9-1.1 MODELLING WELDS The figure below shows modelling of the welds.
The rule used to model them is presented below. This rule is based on *MAT_SPOTWELD:
Description Unit Value RO Density kg/m3 The directions R, S and T are defined as described above (No distinction is made between S and T)
E Young's modulus Pa (1)
PR Poisson's ratio SIGY Yield stress Pa (2)
ET Tangent modulus Pa NRR Maximum tensile force N
(3)
NRS Maximum shearing force following S in the plane perpendicular to R N
(3)
NRT Maximum shearing force following T in the plane perpendicular to R N
(3)
MRR Maximum moment following R N.m MSS Maximum moment following S N.m MTT Maximum moment following T N.m (1) The Young's Modulus in question is that of the steel, divided by 10 in order to avoid adding mass to these extremely short elements (~1mm long). This assumption has no impact on the results as the material is considered elastic and the size of the element is small. Thus, regardless of the force considered, the stretch will be low in comparison with the other elements making up the model.
(2) Values selected to ensure that the element remains elastic.
(3) 3 2
0 0
S rationnel R
NRS S
nel convention R
NRR m
m
where
élément tion S
sec 0
The other values are default values.
R T
S
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 53/57 NON PROPRIETARY VERSION APPENDIX 1-9-1.2 (1/4)
MODELLING OF THE WOOD IN LS-DYNA The modelling used to model the behaviour of wood is as follows:
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 54/57 NON PROPRIETARY VERSION APPENDIX 1-9-1.2 (2/4)
MODELLING OF THE WOOD IN LS-DYNA Scope Parameter Formula LS-Dyna parameter Unit Value for Oak Value for Balsa density RO kg/m3 630.8 130.2 Orthotropic elastic behaviour:
Young's modulus // to fibres L
E E
1,1
//
(1)
EAAU = E //
GPa 16.28 2.35 Young's modulus to fibres
L R
L T
L E
E E
E moy E
E 1,1 (1)
EBBU = ECCU =
E GPa 1.683 0.0355 Shear modulus //
to fibres
L LT L
LR E
G E
G moy E
G
//
//
(1)
GABU = GCAU =
G//
GPa 1.118 0.106 Shear modulus to fibres L
RT E
G E
G
//
(1) or if not available min min
/
/
//
(*)
G G
G G
GBCU = G GPa 0.2674 0.0118 Perfectly plastic orthotropic behaviour (tension +
compression):
Crushing stress // to fibres See the red curve above LCB (see the definition below)
Crushing stress // to fibres at start of plateau See the blue curve above LCC (see the definition below)
Compacted material: elastic isotropic behaviour -
perfectly plastic Maximum compression ratio cellulose bois c
1
cellulose bois VF
42 20(3)
Young's modulus Ec= 35 GPa for a load //
= 10 GPa for a load (taken from (2))
E = EC GPa 35 35 (radial wood) 10 (axial wood)
Poisson's ratio
= 0.3 (taken from (2))
PR =
0.3 0.3 Yield stress y = 120 MPa for a // load
= 150 MPa for a load (taken from (2))
SIGY = y (MPa) 120 120 (radial wood) 150 (axial wood)
Viscosity
= 0.05 (default value)
MU =
0.05 0.05 (1) Characteristics taken from the Wood Handbook (2) Thesis by C. ADALIAN: "The behaviour of wood during multi-axial dynamic compression - Applications to the simulation of container crashes".
(3) Value defined for the fitting.
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 55/57 NON PROPRIETARY VERSION APPENDIX 1-9-1.2 (3/4)
MODELLING OF THE WOOD IN LS-DYNA Scope Parameter Formula LS-Dyna parameter Value for Oak Value for the balsa Influence of crushing stress/angle To add a stress figure dependant on angle using the LCA curve.
Here the curve is zero - regardless of angle LCA = "nil" curve Shearing rupture Shearing rupture max = [200% - 1000%]
Very high values (such rates are far higher than those that the wood could reach)
SSEF = [2 - 10]
0 0
Shearing rupture //
for fibres
//
Damage defined subsequently LCAB=LCCA (see definition below)
Shear rupture to fibres No damage LCBC (unitary curve)
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 56/57 NON PROPRIETARY VERSION APPENDIX 1-9-1.2 (4/4)
MODELLING OF THE WOOD IN LS-DYNA The LCB curve is defined as follows:
Scope Formula Value for Oak Value for the balsa
(-)
(MPa)
(-)
(MPa)
(-)
(MPa)
Perfectly plastic orthotropic behaviour under tension
-1.00
Vf y
t (1)
//
-1.00 50.46
-1.00 24 (radial wood) 30 (axial wood)
-1e-4
-1e-4 50.46
-1e-4 24 (radial wood) 30 (axial wood)
Perfectly plastic orthotropic behaviour under compression 0.0
//
1
0.0 53 0.0 12
-ln(1-max //)
//
1
+ 0.5 0.53 54 1.43 12.5 For oak:
cellulose wood
ln For balsa:
vf ln y = 120 MPa for a // load
= 150 MPa for a load (taken from (2))
0.87 120 1.61 120 (radial wood) 150 (axial wood)
The LCC curve is defined as follows:
Formula Value for Oak Value for the balsa
(-)
(MPa)
(-)
(MPa)
(-)
(MPa)
Perfectly plastic orthotropic behaviour under tension
-1.00
1
t (1) or
1
t
(*) if not available in (1)
-1.00 5.5
-1.00 1.4
-1e-4
-1e-4 5.5
-1e-4 1.4 Perfectly plastic orthotropic behaviour under compression 0.0
1
0.0 11 0.0 1.4
-ln(1-max )
2
0.42 35 0.76 2.5 For oak:
cellulose wood
ln For balsa:
vf ln y = 120 MPa for a // load
= 150 MPa for a load 0.87 120 1.61 120 (radial wood) 150 (axial wood)
(1) Characteristics taken from the Wood Handbook (2) Thesis by C. ADALIAN: "The behaviour of wood during multi-axial dynamic compression - Applications to the simulation of container crashes".
The curves LCAB and LCCA are defined uniquely for all types of wood using the following curve:
Shear deformation (-)
Stress multiplier (-)
0.0 1.0 0.05 1.0 0.06 0.99
TN International Ref.: DOS-18-011415-016-NPV Rev. 1.0 Page 57/57 NON PROPRIETARY VERSION APPENDIX 1-9-1.3 MODELLING OF THE PLYWOOD IN LS-DYNA Plywood (*)
Density (kg/m3)
Young's modulus E of compacted material (MPa)
Poisson's ratio of compacted material Yield stress of compacted material (MPa)
Relative compacted volume VF = Vcompacted/ Vinitial
(%)
Young's modulus E // fibres of the non-compacted material (MPa)
Young's modulus E fibres of the non-compacted material (MPa)
Shear modulus G // fibres (MGPa)
Shear modulus G fibres (MPa)
Behaviour under crushing // fibres Volume deformation Crushing stress (MPa)
Crushing behaviour fibres Volume deformation Crushing stress (MPa)
Reference volume VREF LS-DYNA behavioural rule
- MAT_MODIFIED_HONEYCOMB (2) Values taken from NTC-07-00088449 Rev.0: "Sensitivity analysis on ply-wood properties in the top shock absorber of TN 81 1/3 scale model"