Numerical simulation of crashworthiness with an implicit finite element code

1999 ◽  
Vol 71 (1) ◽  
pp. 12-20 ◽  
Author(s):  
D. Graillet ◽  
J.‐P. Ponthot
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Finite Element Code

ON THE PROTECTION CAPABILITY OF THE FLYING PLATE AGAINST TO LONG-ROD PENETRATORS

2008 ◽  
Vol 22 (09n11) ◽  
pp. 1285-1290
Author(s):  
STANISLAV ROLC ◽  
JAROSLAV BUCHAR ◽  
ZBYNEK AKSTEIN
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Numerical Results ◽  
Finite Element Code ◽  
Plate Material ◽  
3D Finite Element ◽  
Plate Velocity ◽  
Long Rod ◽  
Protection Capability

The interaction of the flying plate with the Long-rod penetrator has been studied both experimentally and numerically using the LS DYNA 3D finite element code. The influence of the plate velocity and plate material on this interaction has been investigated in details. Numerical results show that there was a relatively large damage of the projectiles. The extent of this damage well agree with our experimental foundings. The numerical simulation of the damaged projectiles with some targets has been also performed

Optimization of Bulk Hgcdte Growth in a Directional Solidification Furnace by Numerical Simulation

1995 ◽  
Vol 398 ◽  
Author(s):  
A.V. Bune ◽  
D.C. Gillies ◽  
S.L. Lehoczky
Keyword(s):  
Heat Transfer ◽  
Numerical Simulation ◽  
Finite Element ◽  
Crystal Growth ◽  
Numerical Model ◽  
Directional Solidification ◽  
Growth Conditions ◽  
Finite Element Code ◽  
Interface Shape ◽  
Solidification Furnace

ABSTRACTA numerical model of heat transfer by combined conduction, radiation and convection was developed using the FIDAP finite element code for NASA's Advanced Automated Directional Solidification Furnace (AADSF). The prediction of the temperature gradient in an ampoule with HgCdTe is a necessity for the evaluation of whether or not the temperature set points for furnace heaters and the details of cartridge design ensure optimal crystal growth conditions for this material and size of crystal. A prediction of crystal/melt interface shape and the flow patterns in HgCdTe are available using a separate complementary model.

A Method of Improving Limiting Drawing Ratio：Differential Temperature Deep Drawing Based on Superplasticity

2011 ◽  
Vol 239-242 ◽  
pp. 392-397
Author(s):  
Xue Feng Xu ◽  
Ning Li ◽  
Gao Chao Wang ◽  
Hong Bo Dong
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Deep Drawing ◽  
Thickness Distribution ◽  
Coupled Analysis ◽  
Flowing Water ◽  
Finite Element Code ◽  
Uniform Thickness ◽  
Forming Process ◽  
Good Agreement

A thermal-mechanical coupled analysis of superplastic differential temperature deep drawing (SDTDD) with the MARC finite element code is performed in this paper. Initial drawing blank of an AA5083 bracket was calculated and adjusted according to the simulation result. During the SDTDD simulation, the power-law constitutive model of AA5083 was established as function of temperature and implanted in software MARC through new complied subroutine. Under the guide of the numerical simulation, the die was fabricated and the AA5083 bracket was successfully manufactured via superplastic differential temperature deep drawing. In forming practice, the temperature of female die was kept at 525°C, i.e. the optimal superplastic temperature of AA5083, and the punch was cooled by the flowing water throughout the forming process. The drawing velocity of punch was 0.1mm/s. Results revealed that the formed bracket had a sound uniform thickness distribution. Good agreement was obtained between the formed thickness profiles and the predicted ones.

Numerical Simulation of Aircraft Ditching Based on ALE Method

2014 ◽  
Vol 668-669 ◽  
pp. 490-493 ◽  
Author(s):  
Wei Hu ◽  
Yong Hu Wang ◽  
Cai Hua Chen
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Vertical Velocity ◽  
Field Model ◽  
Aviation Safety ◽  
Nonlinear Finite Element ◽  
Accident Analysis ◽  
Finite Element Code ◽  
Fluid Field ◽  
Simulation Results

Aircraft Ditching is related primarily with the aviation safety. Firstly, the full-scaled shape of Boeing 777-200 is modeled according to the lost MH370 aircraft on 8th March. And then an Arbitrary Lagrange-Euler (ALE) fluid-field model is created for water and air domain. Next some simulation cases are implemented related to different vertical velocities using LS-DYNA nonlinear finite-element code, with the same horizontal velocity and attack angle. At the same time, the variations of the velocity of the head and tail are discussed. Consequently, Ditching overload peak occurs at the highest vertical velocity. The simulation results can deeply be applied to accident analysis of aircraft impacting on water.

Experimental validation of a predictive model for numerical simulation of thermo-metallurgical phenomena during electron beam welding

2004 ◽  
Vol 120 ◽  
pp. 599-606
Author(s):  
M. Carin ◽  
Ph. Rogeon ◽  
D. Carron ◽  
Ph. Lemasson ◽  
D. Couedel ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Electron Beam ◽  
Heat Affected Zone ◽  
Experimental Validation ◽  
Electron Beam Welding ◽  
Welding Process ◽  
Experimental Measurements ◽  
Finite Element Code ◽  
Thermal Cycles

In the present work, thermal cycles measured with thermocouples embedded in specimens are employed to validate a numerical thermometallurgical model of an Electron Beam welding process. The implemented instrumentation techniques aim at reducing the perturbations induced by the sensors in place. A comparison between simulations performed on finite element code SYSWELD and the experimental measurements carried out on 16MnNiMo5 steel in the case of a partial penetration is achieved. This comparison is based on thermal cycles and also on microstructural evolutions, shapes of fusion zone (FZ) and heat affected zone (HAZ).

Numerical Simulation of Damage of Aluminium Plate Subjected to Underwater Explosion

2020 ◽  
Vol 12 (1) ◽  
Author(s):  
M. Vijay ◽  
R.P. Suryapraba ◽  
K. Ramajeyathilagam
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Equation Of State ◽  
Permanent Deformation ◽  
Underwater Explosion ◽  
Steel Plates ◽  
Finite Element Code ◽  
Fluid Structure Interactions ◽  
Test Plate ◽  
Model Setup

The numerical simulation performed on an aluminium plate of dimension 550*450*4 mm subjected to underwater explosion using finite element code LS-DYNA is presented in this paper. The box model setup along with the test plate is modelled using Lagrangian solid elements, the fluid and explosive are modelled using Eulerian solid elements with Gruneisan and Jones-Wilkins-Lee equation of state respectively. The fluid structure interactions are modelled using ALE coupling. Numerical simulation has been carried out for the aluminium plate under shock loads for various charge weights ranging from 30 to 60 g in steps of 10 g. The results of permanent deformation of aluminium plate for each shock factors are compared with the counterpart mild steel plates under the same conditions available in the literature.

Numerical Simulation of Blast Loadings on a Thick-Walled Cylindrical Vessel

2007 ◽  
Author(s):  
Guide Deng ◽  
Ping Xu ◽  
Jinyang Zheng ◽  
Yongjun Chen ◽  
Yongle Hu ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Dynamic Response ◽  
Rigid Wall ◽  
Cylindrical Vessel ◽  
Finite Element Code ◽  
Explicit Finite Element ◽  
Shell Deformation ◽  
Blast Loadings ◽  
Good Agreement

Determining blast loadings on an explosion containment vessel (ECV) is the foundation to design the ECV. Explosion of TNT centrally located in a thick-walled cylindrical vessel and its impact on the cylinder was simulated using the explicit finite element code LS-DYNA. Blast loadings on the cylinder computed are in good agreement with the corresponding experimental results. Then wall thickness and yield stress of the cylinder were changed in the following simulation to investigate effect of shell deformation on blast loadings. It is revealed that shell deformation during the primary pulses of blast loadings is so slight that it has little influence on the blast loadings. Though the deformation may increase greatly after the primary pulses, the dynamic response of an ECV is mainly affected by the primary pulses. Therefore, decoupled analyses are appropriate, in which the shell of an ECV is treated as a rigid wall when determining blast loadings on it.

Numerical simulation of the excitation and evolution of coherent vortices in hollow magnetized electron columns

1999 ◽  
Vol 77 (2) ◽  
pp. 105-112
Author(s):  
M Shoucri ◽  
R Marchand
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Nonlinear Evolution ◽  
Two Dimensional ◽  
Finite Element Code ◽  
Helmholtz Instability ◽  
Radial Transport ◽  
Subsequent Evolution ◽  
Azimuthal Mode ◽  
Coherent Vortices

We apply a finite-element code to study the excitation and nonlinear evolution of two-dimensional (2D) vortices in a hollow electron column using 2D guiding center equations. The perturbation (with m = 2) of the hollow column results in an instability (diocotron or Kelvin-Helmholtz instability) that evolves towards the formation of vortices (two vortices for the m = 2 perturbation). The subsequent evolution shows the nonlinear evolution of two vortices interacting to coalesce (cascading to lower azimuthal mode number), with a simultaneous radial transport toward the center of the column. PACS Nos.: 52.25.Wz, 52.65.Kj, 47.32.-y, 02.70.Dh

Numerical simulation of the excitation and evolution of high-azimuthal-mode-number coherent vortices in hollow magnetized electron columns

2001 ◽  
Vol 65 (2) ◽  
pp. 151-160 ◽  
Author(s):  
R. MARCHAND ◽  
M. SHOUCRI
Keyword(s):  
Numerical Simulation ◽  
Finite Element ◽  
Angular Momentum ◽  
Magnetized Plasma ◽  
Mode Number ◽  
Finite Element Code ◽  
Azimuthal Mode ◽  
Nonlinear Development ◽  
Coherent Vortices ◽  
Development And Evolution

A finite-element code is used to study the excitation of a perturbation with a range of azimuthal mode numbers in hollow magnetized plasma columns, and the subsequent nonlinear development and evolution of coherent vortices interacting to coalesce, while cascading to a lower azimuthal mode number. It is shown that, even for initially higher azimuthal mode numbers, the angular momentum remains a slowly varying ideal invariant, while the system cascades to lower azimuthal mode numbers. A detailed study of the evolution is presented for initially excited m = 3, m = 4, and m = 5 azimuthal modes, which underlines the physics of the inverse cascade of angular momentum.

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