Towards Standardization in Terminal Ballistics Testing: Velocity Representation

Lambert, Jack L.; Jonas, George H.

doi:10.21236/ada021389

Cited by 115 publications

(70 citation statements)

References 2 publications

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“…The residual velocity after penetration was plotted against the initial impact velocity of the projectile. A polynomial curve was fitted to the experimental results, based on the Lambert and Jonas relation [34], as given by:…”

Section: High-velocity Impact Testingmentioning

confidence: 99%

High-velocity impact deformation and perforation of fibre metal laminates

et al. 2017

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The quasi-static flexural and impact performance, up to projectile impact velocities of about 270 m s -1 , of fibre metal laminates (FMLs), which consist of relatively thin, alternately stacked, layers of an aluminium alloy and a thermoset glass fibre epoxy composite, have been investigated. The effects of varying (a) the yield strength, tensile strength and ductility of the aluminium alloy layer, (b) the surface treatment used for the aluminium alloy layers and (c) the number of layers present in the FML have been studied. It was found that increasing the strength of the aluminium alloy increases the quasi-static flexural strength of the FML, providing that good adhesion is achieved between the metal and the composite layers. Further, increasing the number of alternating layers of the aluminium alloy and fibre composite also somewhat increases the quasi-static flexural properties of the FML. In contrast, increasing the strength of the aluminium alloy had relatively little effect on the impact perforation resistance of the FML, but increasing the number of alternating layers of aluminium alloy and fibre composite did significantly increase the impact perforation resistance of the FML. The degree of adhesion achieved between the layers had only a negligible influence on the impact perforation resistance.

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Section: High-velocity Impact Testingmentioning

confidence: 99%

High-velocity impact deformation and perforation of fibre metal laminates

et al. 2017

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“…Tables 1 and 2 Note that the brass jacket and lead cap are completely stripped from the hard core by the target. and hard cores were curve-fit with the least squares method and the Lambert-Jonas empirical equation [9,10] ( )…”

Section: The 762mm Apm2 Bullet and Hard Steel Core Experimentsmentioning

confidence: 99%

Perforation of 6082-T651 Aluminum Plates with 7.62 mm APM2 Bullets at Normal and Oblique Impacts

Forrestal¹,

Warren²,

Chen³

2014

Conference Proceedings of the Society for Experimental Mechanics Series

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We conducted an experimental study to understand the mechanisms and dominant parameters for 7.62mm APM2 bullets that perforate 6082-T651 aluminum armor plates at oblique impacts. The 7.62-mm-diameter, 10.7g, APM2 bullet consists of a brass jacket, lead filler, and a 5.25g, ogive-nose, hard steel core. The brass and lead were stripped from the APM2 bullets by the targets, so we conducted ballistic experiments with both the APM2 bullets and only the hard steel cores. These projectiles were fired from a rifle to striking velocities between 400 and 1,000m/s into 20-mm-thick plates at normal impact (β=0 o ) and at oblique angles of . We also presented a scaling law for the bullet that showed the ballistic-limit velocities were proportional to the square root of the product of plate thickness and a material strength term.

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“…This approach requires a great number of tests around this velocity. In the present work the experimental perforation velocity was estimated, using a least-square method, by fitting the expression shown in the following equation proposed by Lambert and Jonas [27]. it is equivalent to that found assuming the conservation of momentum and energy during the perforation process with zero fragment ejected from the laminate [28].…”

Section: Experimental Testmentioning

confidence: 99%

Influence of shear plugging in the energy absorbed by thin carbon-fibre laminates subjected to high-velocity impacts

Buitrago

García-Castillo

Barbero

2013

Composites Part B: Engineering

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a b s t r a c tThis work examines the energy-absorption process in thin woven laminates made from carbon fibres, with the aim of analysing the energy employed in the formation of a shear plug. This study was conducted with a simplified model which considered five energy-absorption mechanisms. The model was validated with experimental tests and numerical simulations, with regard to the residual velocity of the projectile and perforation velocity. The model makes it possible to evaluate the influence of the shear plugging in laminates of different thickness. It has been demonstrated that this energy-absorption mechanism needs to be considered in the analysis. The main energy-absorption mechanisms for impact at low velocity (i.e. below the perforation velocity) are related to the elastic deformation of fibres and shear plugging, whereas when a higher impact velocity is considered (i.e. above the perforation velocity) such mechanisms are related to the acceleration field of the laminate and the shear plugging.

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Towards Standardization in Terminal Ballistics Testing: Velocity Representation

Cited by 115 publications

References 2 publications

High-velocity impact deformation and perforation of fibre metal laminates

High-velocity impact deformation and perforation of fibre metal laminates

Perforation of 6082-T651 Aluminum Plates with 7.62 mm APM2 Bullets at Normal and Oblique Impacts

Influence of shear plugging in the energy absorbed by thin carbon-fibre laminates subjected to high-velocity impacts

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