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Latin American Journal of Solids and Structures

Print version ISSN 1679-7817On-line version ISSN 1679-7825

Lat. Am. j. solids struct. vol.12 no.3 Rio de Janeiro Mar. 2015

http://dx.doi.org/10.1590/1679-78251202 

Articles

Performance of kevlar fibre-reinforced rubber composite armour against shaped-charge jet penetration

Xu-dong Zua 

Zheng-xiang Huanga 

Wen Zhaib 

aSchool of Mechanical Engineering, Nanjing University of Science and Technology, Xiaolingwei 200, Nanjing 210094, China. azuxudong9902@mail.njust.edu.cn, bhuangyue@mail.njust.edu.cn

bShandong Non-metallic Material Institute,NO.3 East road, Tianjiazhuang, Jinan 20031, China. cwenzhai53@163.com

Abstract

The protective capability of the Kevlar fibre-reinforced rubber composite armour (KFRRCA) at different obliquities is studied using depth-of-penetration experiments method against a 56 mm-diameter standard-shaped charge. Efficiency factors are calculated to evaluate the protection capability of the KFRRCA at different obliquities. Meanwhile, an X-ray experiment is used to observe the deformation, fracture, and scatter of the shaped-charge jet as it penetrates the composite armour. Finally, scanning electron microscopy (SEM) is used to analyse the effect of the Kevlar fibre-reinforced rubber for the composite armour to resist jet penetration. The results showed that the KFEECA can be used as additional armour, because it has excellent protection capability, and it can disturb the stability of the middle part of the shaped charge jet (SCJ) obviously especially when the armour at 30°and 68° obliquities.

Keywords: Impact dynamics; kevlar fibre; shaped-charge jet; penetration; efficiency factors

1 INTRODUCTION

Shaped-charge jet (SCJ) is one of the most important components in armour weaponry that exhibits excellent penetration performance and can damage armoured targets effectively. One common concern is protecting the armoured vehicles to reduce damage by SCJ. One effective protection method used at present is disturbance of the SCJ stabilities by additional armour to reduce the SCJ's penetration ability prior to attacking the main armour. Explosive reactive armours are widely used in tanks because of their excellent interference ability (Held, 1999, 2005; Yadav, 1988; Mayseless, 2011; Paik et al., 2007). However, the application of explosive reactive armour is subject to certain restrictions mainly because the explosion field of the explosive reactive armour can affect the normal operation of the vehicle parts and the explosion products may injure the soldiers around the armoured vehicles. According to the study, the bulging armour also can disturb the stability of the SCJ, and it has excellent resistance to penetration performance, so it has been widely used in the protective field of armoured vehicles, ships, and aerospace. Fibre-reinforced composite materials are widely used in the bulging armour as sandwich materials. Fibre-reinforced rubber base composite materials are materials containing fibre doped with a certain percentage of rubber to obtain specific material properties. Commonly used reinforcing fibres include Kevlar, glass, carbon and ultra-high molecular weight polyethylene. Kevlar and ultra-high molecular weight polyethylene have been introduced as base materials for ballistic protection. These high performance fibers are characterized by low density, high strength, and high energy absorption (Lee et al., 2003).

Current literature indicates that rubber base composite armour can disturb SCJ stability, turning the SCJ fracture and breakage as a kind of additional armour. The description of the mechanisms of these bulging systems was first proposed by (Gov et al., 1992). Yaziv compared rubber composite and explosive reactive armours, highlighting the former as superior in terms of safety and environmental effects (Yasiv et al., 1995). The study further described the process of interaction of the rubber composite armour with SCJ, but did not provide the theoretical model. Rosenberg studied the resistance capability of sandwich composite armours with different sandwich materials through two-dimensional (2D) simulation, and considered material strength, stress modulus, and density to be the relevant factors in the resistance of composite armour to SCJ (Rosenberg and Dekel, 1998). A layer of rubber that will gasify or possibly explode is regarded as an inert explosive. A mechanism for the interaction based on the theory of Kelvin-Helmholtz instabilities was discussed by (Helte and Lidén, 2010a, 2010b). The process of rubber composite armour protection against SCJ penetration is divided into four parts based on the jet deformation that occurs when the SCJ penetrates the rubber composite armour. Results of the interference speed interval, interference frequency, and surplus penetration capability of the SCJ with the rubber composite armour are derived based on the stress wave and Kelvin-Helmholtz instability theory. The effects of rubber layer thickness and obliquity of the armour for the composite armour anti-SCJ penetration were studied through theoretical, X-ray, and depth-of-penetration experiments by (Zu et al., 2013). The protection ability of woven fabric-reinforced rubber composite armour as subjected to SCJ was studied by (Jia et al., 2013) through experiments.

Research on the protective performance of KFRRCA, an important protective armour, against SCJ is crucial. The obliquity of the armour has substantial influence on protective performance. However, in the case of KFRRCA plates, the mechanism and simulation are significantly more complex because of the interaction of the fibre-reinforced rubber plate and the SCJ. Thus, in this paper, we study the protective performance of the KFRRCA in which the rubber base is doped with 15% Kevlar fibre at different obliquities through depth-of-penetration (DOP) experiments and X-ray experiment. The tip velocities of the SCJ after penetrating the composite were measured in the DOP experiments. The effect of the obliquity for the composite armour was investigated by the tip velocities of the SCJ, DOP, deformation of the armour, and the protection factors.

2 SHAPED CHARGE AND COMPOSITE ARMOUR CONDITIONS

2.1 Standard shaped-charge experiment

The standard shaped charge was used in this study for several reasons, such as increasing the universality of the study, simplifying the calculation of the protection, cost, and protection thickness coefficients, as well as considering that the standard shaped charge is often used in studies. The standard shaped charge (Figure 1, Figure 2) possessed the following characteristics: shaped-charge copper liner with 0.8 mm thickness and 56 mm diameter, as well as explosive weight of 203 g without a conical charge shell cover. The DOP experiments were set as Figure 3 to measure the standard shaped-charge jet parameters, with the 330 mm standoff and velocity sensors set at the top and the bottom of the standoff cylinder to measure the time of the shaped-charge jet tip through the standoff. A 8# flash detonator was used to detonate the SCJ. The results of the experiments are shown in the Table 1.

Figure 1 Photograph of the standard shaped charge with a diameter of 56 mm. 

Figure 2 Structure diagram photograph of the standard shaped charge with a diameter of 56 mm. 

Figure 3 DOP experimental setup with the velocity sensors to measure the velocity of the shaped-charge jet tip. 

Table 1 Results of the shaped-charge performance experiment. 

No. Standoff (mm) Time (μs) Velocity of jet tip (m/s) Depth of penetration (mm)
1 330 51 6470 161
2 330 51 6470 158
3 330 51 6470 160

The result showed the average depth of penetration to be 160 mm at the same standoff, with a relative error of approximately 5%. The depth of 160 mm was regarded as the datum plane, which is aimed at the condition of SCJ penetration of the semi-infinite steel target. The SCJ had good consistency, and the inlet diameter was almost the same as the outlet diameter. In the DOP experiments, the velocity of the shaped-charge jet tip was 6470 m/s.

The jet tip and tail velocities were simultaneously measured using a multi-channel X-ray system. The double flash X-ray exposures of the shaped-charge jet at 30 and 50 μs after initiation are shown in Figure 4. The magnification of the X-ray exposures was 2.0, so the jet tip velocity was 6453 m/s and that of the tail was 1179 m/s. Comparing the velocity of the shaped-charge jet tip obtained from the X-ray exposures with that measured from the DOP experiments, the relative error did not exceed 0.3%.

Figure 4 Double flash X-ray exposures of the shaped-charge jet at 30 and 50 µs after initiation (all dimensions in mm). 

2.2 KFRRCA construction

The KFRRCA configuration comprised the following layers: Q235 steel, rubber base material doped with 15% Kevlar fibre, and Q235 steel. The thicknesses of the Q235 steel plates and rubber base material sandwich plate were 3 and 5 mm, respectively. The KFRRCA had a geometric area of 300 mm×150 mm. The Q235 steel was sandblasted, and a premium-grade adhesive was used to bond the steel plates and the Kevlar fibre-reinforced rubber plate. The parameters of the rubber, Kevlar fibre, and Q235 steel are shown in Table 2. The details of the schematic of the KFRRCA are shown in Figure 5.

Figure 5 Schematic of the KFRRCA (all dimensions in mm). 

Table 2 Summary of rubber, Kevlar fibre and Q235 steel parameters. 

Material ρ (g/cm3) Shore hardness Yield strength (MPa) Tensile strength (MPa) Elongation at failure (%)
Rubber 1.3 75 - 20 400
Kevlar fibre 1.9 - - 134 3.5
Q235 1.785 - 235 375 26

3 DOP EXPERIMENT

3.1 DOP experiment setup

A DOP method was used in the experiment to investigate the protective capability of the KFRRCA against shaped charge at different obliquities. A schematic diagram of the sides of the DOP experiment configuration is shown in Figure 6. Given the velocity sensors after the KFRRCA and before the witness target along the shaped-charge jet direction of movement, the distance between the two velocity sensors, which were 250 mm apart (the real distance can be measured before experiment), and the velocity of the shaped-charge jet can be calculated. At the 330 mm distance standoff, the 45# steel witness targets were set to measure the depth of the residual penetration capability. The details of the DOP experiment are shown in Figure 7.

Figure 6 Schematic diagram of the experimental setup. 

Figure 7 DOP experimental setup with the velocity sensors to measure the velocity of the shaped-charge jet tip after penetrating the KFRRCA. 

3.2 Efficiency factors

The KFFRCA was placed at a certain distance from the main armour as additional armour to improve the protection performance. The surplus depth of penetration cannot evaluate the protection performance of the KFRRCA directly when the obliquity of the armour changed. Space protection coefficient (E s), quality protection coefficient (E m), and differential protection coefficient (Δec) are commonly used to describe the protection level of an armour with different states, providing information to an armour designer for armoured vehicle protection without a need to reveal details regarding the structure and mechanism of the armour systems (Zhang et al., 2000). Efficiency is always indicated in a standard or reference value.

The three factors were calculated to describe the protective performance of the armour systems. E s is the ratio between the spaces of the tested armour with that of the reference armour when they have the same protection ability and E m is the ratio between the quality of the tested armour with that of the reference armour when they have the same protection ability. Finally, Δec is the ratio between the protection ability of the sandwich material with that of the reference armour material.

where ρst denotes the density of steel, ϱ1 and ϱ3 denote the densities of the cover plates, ϱ2 denotes the density of the sandwich material, h 1 and h 3 denote the thickness of the cover plates respectively, h 2 denotes the thickness of the sandwich material, p 0 denotes the depth of penetration of the standard SCJ with the 330 mm standoff, pres denotes the surplus depth of penetration of the SCJ after the jet penetrated the composite armour, and υ denotes the angle between the normal direction of the plates and the axial direction of the SCJ.

3.3 Results and discussion

The shaped-charge jet affects the witness target and produces a large number of craters. The results of the impact are shown in Figure 8.

Figure 8 Craters caused by SCJ penetration of the witness target after penetrating the KFRRCA with various obliquities: a) 0°, b) 30°, c) 45°, d) 60°, e) 68°. 

The DOP experimental results on different obliquities are shown in Figure 9and Figure 10. The calculations of efficiency factors of different obliquities are shown in Figure 11, Figure 12 and Figure 13.

Figure 9 Relationship between velocity of jet tip and obliquity. 

Figure 10 Relationship between surplus depth of penetration and obliquity. 

Figure 11 Relationship between quality protection coefficient of penetration and obliquity. 

Figure 12 Relationship between space protection coefficient of penetration and obliquity. 

Figure 13 Relationship between differential protection coefficient of penetration and obliquity. 

Comparing the velocity of the SCJ tip, no significant speed change was observed to correspond to the obliquity of the KFRRCA change. The thickness of the composite armour change caused by the obliquity has slight effect on the velocity of the SCJ tip. However, large differences in the surplus depth of penetration and efficiency factor were observed with the change in obliquity. Comparing the craters caused by SCJ penetration of the witness target, the KFRRCA disturbed the shaped-charge jet stability, and part of the SCJ fragmented and scattered. More expanding craters were observed on the witness target with the obliquities at 30° and 68° than in other obliquities. This result indicates that when obliquity was at 30° and 68°, the KFRRCA disturbed the shaped-charge jet more apparently, which was proven by the surplus depth of penetration and the efficiency factors. The KFRRCA had excellent protection capability when the obliquity of the armour was at 30° and 68°.

Based on the theory models on the rubber composite armour disturbing the shaped-charge jet in the reference (Zu et al., 2013), the disturbed condition of shaped-charge jet was based on the deformation velocity of the front plate of the sandwich armour and the obliquity. The disturbance in the length of the shaped-charge jet increased as the obliquity and deformation velocity of the front plate increased. However, the deformation velocity of the front plate was reduced as the obliquity increased, which showed that the optimal obliquity of the KFRRCA was not the largest obliquity.

4 X-ray experiment

4.1 X-ray setup

To visualise the fracture and scatter of the shaped-charge jet, the X-ray experiment method was used. The shaped charge was vertically installed in a standoff 80 mm from the KFRRCA, and the obliquity of the armour was 60° of the shaped charge axis. The shaped charge and armour were elevated using a cotton rope. In the experiment, several 450 kV multi-channel X-ray systems set at 90° were used. The experimental setup is shown in Figure 14. Through a special setting, two radiographs were obtained for the same testing. Passive detonation technology was used in the experiment to observe the deformation of the jet accurately and to eliminate the errors attributable to the detonator. The image of the experimental setup is shown in Figure 15.

Figure 14 Schematic of the experiment setup of KFRRCA against a 56 mm shaped charge in front of double flash X-raytube. 

Figure 15 Image of the experiment setup with the charge on top of a KFRRCA panel. In the background are two protecting cassettes for the 860 mm-long FXR films. 

4.2 Results and discussion

The X-ray radiographs of the shaped-charge jet penetrating KFRRCA under 60° are shown in Figure 16.

Figure 16 Flash X-ray radiograph of a shaped-charge jet penetrating KFRRCA under 60° atapproximately 50 and 80 μs: a) 50.740 μs; b) 80.990 μs. The middle part of the shaped-charge jet was disturbed by the KFRRCA, and the middle part of the jet almost totally fragmented and scattered the jet, which drastically reduced the latter's penetration capability. 

5 SCANNING ELECTRON MICROSCOPY (SEM) ON THE KEVLAR FIBRE-REINFORCED RUBBER

When the SCJ penetrated the KFRRCA, numerous radial cracks appeared around the crater of the rubber base sandwich rubber (Figure 17), and numerous fractured fibres can be seen around the edge of the crater on the Kevlar fibre-reinforced rubber.

Figure 17 The cracks around the crater of the rubber base sandwich rubber. 

The rubber material will tear and shed under the impact, but with the Kevlar fibre, the rubber base material around the crater was still linked around the material (Figures 17 and 18.a ). The Kevlar fibres around the crater were separated with the rubber base material under the impact and shock wave (Figures 18.b and 18.c ). Therefore, Kevlar fibre can reinforce the strength of the rubber base material and absorb shock wave energy.

Figure 18 SEM images for the Kevlar fibre-reinforced rubber: a) magnification 70, b) magnification 200, c) magnification 500. 

6 CONCLUSIONS

A series of DOP and X-ray experiments were performed to evaluate the protection capability of the Kevlar fibre-reinforced rubber armour at different obliquities to resist Ф56 mm shaped-charge jet penetration. SEM was used to observe the deformation of the Kevlar fibre-reinforced rubber. The efficiency factors were used to evaluate the protection capability. Based on these findings, the following conclusions were drawn:

    1. ) The Kevlar fibre-reinforced rubber enhances the strength of the rubber base material, but because the Kevlar fibre reinforced rubber has excellent performance to absorb shock waves, the deformation of the front plate of the sandwich armour is reduced, so the length of the SCJ is disturbed.

    2. ) The Kevlar fibre-reinforced rubber armour has excellent protection capability, and can disturb the stability of the middle part of the SCJ.

    3. ) The KFRRCA has the best protection capability with obliquities at 30° and 68°.

Acknowledgements

This research was supported by the National Natural Science Foundation of China (Grant No.11402112).

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Received: February 16, 2014; Revised: June 24, 2014; Accepted: October 02, 2014

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