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Research Papers

Computational Fluid Dynamics and Experimental Validations of the Direct Coupling Between Interior, Intermediate and Exterior Ballistics Using the Euler Equations

[+] Author and Article Information
Roxan Cayzac1

Head of Aerodynamics, Technical Direction, Nexter Munitions, 7 Route de Guerry, 18023 Bourges Cedex, France;  Associate Professor of the Universities, National School of Engineering at Bourges, 88 Boulevard Lahitolle, 18020 Bourges Cedexr.cayzac@nexter-group.fr

Eric Carette

Research Associate in Aerodynamics, Technical Direction, Nexter Munitions, 7 Route de Guerry, 18023 Bourges Cedex, Francee.carette@nexter-group.fr

Thierry Alziary de Roquefort

 Professor of the University of Poitiers, Expert Consulting in Fluid Mechanics, 129 Rue des Quatres Roues, 86000 Poitiers, Francethierry.alziary@club-internet.fr

François-Xavier Renard

Engineering Department, Nexter Systems, 7 Route de Guerry, 18023 Bourges Cedex, Francefx.renard@nexter-group.fr

Dominique Roux

Engineering Department, Nexter Systems, 7 Route de Guerry, 18023 Bourges Cedex, Franced.roux@nexter-group.fr

Patrick Balbo

Engineering Department, Nexter Systems, 7 Route de Guerry, 18023 Bourges Cedex, Francep.balbo@nexter-group.fr

Jean-Noël Patry

Product Development Manager, Engineering Department, Nexter Systems 13 Route de la Minière, 78034 Versailles Cedex, France e-mail: jn.patry@nexter-group.fr

1

Corresponding author.

J. Appl. Mech 78(6), 061006 (Aug 24, 2011) (11 pages) doi:10.1115/1.4003812 History: Received June 15, 2010; Revised January 03, 2011; Published August 24, 2011

For several years we have been working on the development of a computational fluid dynamics ballistics code called FREIN. This code is the result of a strong cooperation between Nexter Munitions and the University of Poitiers. In the last years, efforts have been carried out to improve the 3D modeling. In a fully unsteady way, the interior, intermediate and exterior ballistics were modeled as well as the weapon system environment. The complex phenomena encountered are investigated by an adapted numerical simulation approach using the Euler equations for two immiscible gases. The method involves moving bodies with respect to fixed Cartesian meshes and the aerodynamic forces are used to compute the trajectories. In this paper, theoretical developments and computations have been applied mainly to the simulation of the firing of an advanced 120 mm lightweight tank demonstrator. In comparison with firing experiments, first computation validation results concerning interior ballistics, muzzle brake flow, sabot discard and blast wave propagation and reflection are presented and are very satisfactory.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Sketch of the treatment of cut cells

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Figure 2

Example of grid embedding with three grids: grids 2 and 3 are shifted periodically to encompass the projectile

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Figure 3

Sketch of the recursive time integration scheme for a four level mesh

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Figure 4

Configuration for 1D tests in a 3D context

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Figure 5

TORO’s test 1 in a tube with D/L = 0.6 and α = 45 degrees computed wit CFL = 0.5

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Figure 6

Woodward-Colella blast wave problem in a tube with D/L = 0.06 and α = 0 degrees

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Figure 7

Woodward-Colella blast wave problem in a tube with D/L = 0.06 and α = 45 degrees

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Figure 8

120 mm lightweight tank demonstrator

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Figure 9

Lightweight tank demonstrator, example of grid with 6 levels

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Figure 10

Pressure distributions, every 0.2 ms, between the breech and the projectile, and between the projectile and the gun muzzle

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Figure 11

Experimental and theoretical pressure evolutions with time in the chamber at 2.46 calibers from the breech

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Figure 12

Firing of a 120 mm APFSDS through a muzzle brake, pressure field and u component of the velocity

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Figure 13

Pressure in the muzzle exit plane at 1.6 m from the tube axis

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Figure 14

44 mm gun - sabot discard for sabot type 1

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Figure 15

44 mm gun - sabot discard for sabot type 2

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Figure 16

44 mm gun - sabot discard for sabot type 3

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Figure 17

Experimental and numerical 3D unsteady sabot discard

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Figure 18

Time evolution of the sabot angle and of the x separation between penetrator and sabot

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Figure 19

Pressure measurement locations on the tank demonstrator

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Figure 20

Pressure contours on the tank demonstrator at different time levels

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Figure 21

Pressure versus time for measurement points N° 9, 10, 12 and 17

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Figure 22

Penetrator in flight after sabot discard at t = 16 ms

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