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Experimental Study on Drop-Weight Impact Response of Basalt Fiber Aluminum Laminates (BFMLs).

1. Introduction

Fiber-metal laminates were firstly designed for aircraft structures [1, 2]. High-velocity impact events are the main problems that FMLs mostly faced in aviation industry [1, 3]. Along with the expansion of applications of FMLs to land transportation from aviation industry, low-velocity impact response of FMLs has been increasingly attracted attention since it quite often happens to vehicles on road [4-7].

Many researchers have studied low-velocity impact behavior of FMLs such as GLARE, ARALL, CARALL, and hybrid FMLs using two kinds of fibers and/or particular metals like magnesium and titanium [8, 9]. From those studies, people gain more understanding on how FMLs react to impacting events. Therein, delamination is the distinctive feature of FMLs during low-velocity impact. The deflection stiffness and energy absorption are closely related to delamination of FMLs, which also contributes to the complexity in analyzing mechanical behavior of FMLs [10, 11].

There are few articles discussing the fabrication of fibermetal laminates [12], but it is the prerequisite step before conducting the experimental study. Surface treatment of the metal layer can have significant effects on the interlaminar properties and thus the overall properties of FMLs. Thus, Aghamohammadi et al. [13] investigated four different surface treatment methods on the aluminum layers and studied their effects on the flexural behavior of FMLs. The effect of metal layer distribution on FMLs was concerned by Khan and Sharma [14, 15] in experimental and simulation ways. Norman Jones [16] made some theoretical predictions for the deformation and denting of fiber-metal laminates when subjected to low-velocity impact loads. The rigid plastic material approximation with modifications to reflect the actual cross section of a fiber-metal laminate was used to produce simple formulae which gave reasonable agreement with the corresponding experimental data.

However, of fibers applied in all types of FMLs, basalt fiber is rarely reported. Continuous basalt fiber has been widely used in automotive industry due to its superior mechanical properties in comparison to E-glass fiber, which can be seen in Table 1 [17]. In addition, basalt fiber has flame retardancy and is able to maintain high performance at high and low temperatures [18, 19]. Basalt fiber also has high abrasive and corrosive resistance, which can be used in the detrimental environment [20, 21]. Also, basalt fiber is nontoxic to human body [22].

Since basalt fiber has so many advantages, it is a potential substitute of glass fiber in FMLs' fabrication that may be used in automobiles. Thus, basalt-based FMLs were studied in this paper.

2. Preparation of Specimens

2.1. Materials. 2A12-T4 aluminum alloy sheets with a thickness of 0.5 mm were supplied by Southwest Aluminum (Group) Co., Ltd (China). The basalt fiber-reinforced polymer (epoxy resin) with a thickness of 1.32 mm was supplied by Sichuan Aerospace Tuoxin Basalt Industrial Co., Ltd (China). The adhesive film made of modified polyethylene acrylate was supplied by Shanghai Zhenghuan Adhesive Product Co., Ltd (China). The chemical components and basic mechanical properties of 2A12-T4 aluminum alloy are listed in Table 2 and Table 3, whilst the parameters of continuous basalt fiber (CBF) and its composite are listed in Table 4. Table 5 gives material properties of BFRP.

2.2. Specimen Design. A simple methodology was used to prepare BFMLs, with five steps listed as follows:

(1) Materials were cut in the light of BFMLs' size in order to avoid direct clipping on BFMLs which may introduce damage in interfaces between aluminum alloy sheet and BFRP layer.

(2) Surface treatment was applied to both materials so as to improve bonding quality when using adhesive film. Polishing (abrasion) on BFRP surface aimed at increasing roughness which is beneficial to bonding quality, while chemical cleaning, including alkali wash, acid cleaning, and phosphoric acid anodizing of aluminum alloy sheet, was also applied for the same purpose.

(3) Adhesive film (AF) was laid between aluminum alloy sheet and BFRP layer to make them initially bonded through hot-rolling to form semifinished product of BFMLs.

(4) Semifinished product of BFMLs was placed into moulds, with the applied pressure of 5 MPa and heat of 160[degrees]C, followed by a curing period of 60 minutes.

(5) The specimen was air-cooled.

3. Drop-Weight Impact Tests

The drop-weight tests were conducted in the INSTON 9520HV testing machine, as shown in Figure 1. The acceleration transducer was mounted in the drop hammer to record the history of acceleration. Optical grating was mounted at underpart of a stand column to record the initial impact velocity of the projectile. After once and twice integrals of acceleration, the history of velocity and displacement of the projectile can be obtained. The reaction force between the projectile and the BFML specimen can be calculated by Newton's second law. Moreover, the history of load, energy, velocity, and deflection during impact can also be obtained.

Aluminum alloy sheet and BFRP and BFML plates were tested by drop-weight impact. The specimens were clamped between two square steel plates with a circular opening at the center, as shown in Figure 1. The opening of steel plates has two diameters, i.e., 70 mm and 100 mm. The projectile is of hemisphere with the diameters of 10 mm or 20 mm and masses of the projectile of 5.666 kg, 14.353 kg, or 17.493 kg. The heights of the drop weight were set as 0.36 m, 0.48 m, or 0.76 m.

4. Results and Discussion

4.1. Strain-Rate Effect. In most cases, stiffness and strength of a material may increase with strain rate. The strain-rate effect during impact on a composite plate has a contribution to enhancing the bending stiffness and/or strength. While, if the load-deflection curve of a material under impact is similar to that under static loading, there is no strain-rate effect for such dynamic loading.

In order to investigate the strain-rate effects of the aluminum alloy sheet, BFRP layer, and BFML plate, drop-weight impact tests were conducted on the three types of materials, and the test results of drop-weight impact are listed in Table 6.

4.1.1. 2A12-T4 Aluminum Alloy Sheet. According to Damith [23], aluminum alloy shows hardly any strain-rate effect when the strain rate is less than 800 [s.sup.-1]. As the strain rate on the aluminum alloy sheet by a drop-weight impact in the present study is no more than 110 [s.sup.-1,] the strain-rate effect on the 2A12-T4 aluminum alloy sheet was therefore ignored. Figure 2 shows the load-deflection curves of 2A12-T4 aluminum alloy sheets under drop-weight impact. It can be seen that, in moderate strain-rate regime, there was no significant difference between curves in the impact velocity regime of 2.63-3.70 m/s. As for the deviation of the static result from impact curves, difference of the corresponding global deflection may attribute to it. Response of the 2A12-T4 aluminum alloy sheet under static loading is always global, while that under impact loading gave rise to more localized indentation in the vicinity of the impact region so that the stiffness of 2A12-T4 aluminum alloy sheet bending under impact is somewhat higher than that under static loading during early stage, say, deflections less than 2 mm. Afterwards, the bending stiffness showed no difference between static and impact curves considering slope and peak load.

4.1.2. BFRP. The strain rate of the BFRP plate can be estimated by means of average impact velocity being divided by radius [24]. Although BFRP plates do show some strain-rate effect, such effect in the range of 25-97 [s.sup.-1] seems minimal, which almost covers the strain rate range in the present study, as shown in Figure 3. The bending stiffness and ultimate load carrying capacity of BFRP plates under impact are nearly twice of that under static loading. However, the peak load of BFRP plates under impact was independent of projectile's diameter.

4.1.3. BFMLs. BFMLs showed no strain-rate effect. Similar to the 2A12 aluminum alloy sheet, localized indentation is responsible for the higher initial bending stiffness, which explains why the initial segment (where deflection is less than 2 mm) of the load-deflection curve of impact is steeper than that of static, as shown in Figure 4. Therefore, no strain-rate effect of BFMLs is considered in prediction of impact behavior of BFMLs plates in Section 4.2.

4.2. Loading-Deformation Relationship of BFML Plates. When the loading rate was not high, such as drop-weight impact, the analysis of dynamic behavior of structures may be converted to that of quasi-static process based on the modal analysis method [25].

2A12 aluminum alloy is an elastic-plastic ductile material, while BFRP is a linear elastic brittle material. In order to obtain analytical expressions for the load-deflection response of BFMLs, 2A12 aluminum is idealized as a rigid plastic material with linear strain hardening and BFRP is idealized as a linear elastic material, as shown in Figure 5.

4.2.1. Thin Plate. The principle of minimum potential energy was applied to derive the load-deflection relation of thin BFML plates (type of 2/1 BFML plate).

The total strain energy of the BFML panel consists of bending and membrane energy. Since the in-plane deformations are negligible compared to the transverse deflections, the strain energy can be expressed in terms of transverse deflections only.

For the symmetric BFML plate, the strain energies of aluminum alloy sheets and BFRP panels due to bending are given by

[mathematical expression not reproducible] (1)

[mathematical expression not reproducible] (2)

where S is the integral area, [M.sub.x0] and [M.sub.y0] are the fully plastic bending moments in x and y directions, [M.sub.xy0] is the twisting moment in the x-y plane, and [D.sub.ij] is the bending stiffness. The plastic bending and twisting moments can be derived by taking moments about the neutral surface of the plate which are expressed in the following equation:

[mathematical expression not reproducible], (3)

where m is the number of aluminum sheets, [z.sub.k] is the distance of neutral surface of the aluminum sheet from that of the BFML plate, and [h.sub.Al] is the thickness of the aluminum alloy sheet.

The membrane strain energies of aluminum alloy sheets and BFRP plates can be expressed by the von Karman strain-displacement relations:

[mathematical expression not reproducible], (4)

[mathematical expression not reproducible], (5)

where [N.sub.x0] = [N.sub.y0] and [N.sub.xy0] are fully plastic membrane and in-plane shear forces and [A.sub.ij] is the membrane stiffness. The membrane and in-plane shear forces can be obtained by taking stress resultants about the neutral surface of the plates which are expressed in the following equation:

[N.sub.x0] = [N.sub.y0] = [[n + 1]/2] [[sigma].sub.0][h.sub.Al], [N.sub.xy0] = [[n + 1]/2[square root of 3]][[sigma].sub.0][h.sub.al], (6)

where [[sigma].sub.0] is the yield strength of the aluminum alloy sheet.

The deformation profile of BFMLs needs to be considered when applying the principle of minimum potential energy. Tsamasphyros and Bikakis [26] proposed a velocity profile of GLARE panels under low-velocity impact as

[??](r) = [[??].sub.0] (1 - sin[[pi]r/2a]), 0 [less than or equal to] r [less than or equal to] a. (7)

The deformation profile of BFMLs can be obtained by integrating the above equation:

w(r) = [w.sub.0] (1 - sin[[pi]r/2a]), 0 [less than or equal to] r [less than or equal to] a. (8)

where a is the radius of the BFML plate. Under symmetrical loading conditions, the in-plane shear force and twisting moment are zero. By substituting Equation (8) into Equations (1), (2), (4), and (5), we can get the bending strain energy and membrane energy as follows:

[U.sup.Al.sub.b] = 4[M.sub.xy][w.sub.0] = [K.sup.Al.sub.b][w.sub.0], (9)

[mathematical expression not reproducible], (10)

[U.sup.Al.sub.m] = (0.288[N.sub.x] + 0.288[N.sub.y])[w.sup.2.sub.0] = [K.sup.Al.sub.m][w.sup.2.sub.0], (11)

[U.sup.BF.sub.m] = [0.155[A.sub.11] + 0.155[A.sub.22] + 0.103[A.sub.12]] [w.sup.4.sub.0]/[a.sup.2] = [K.sup.BF.sub.m][w.sup.4.sub.0], (12)

The work of external load is

W = P[w.sub.0]. (13)

By calculating the minimal value of the potential energy,

[PI] = [U.sub.b] + [U.sub.m] - W = [U.sup.Al.sub.b] + [U.sup.BF.sub.b] + [U.sup.Al.sub.m] + [U.sup.BF.sub.m] - W, (14)

there is

P = [K,sup.Al.sub.b] + (2[K.sup.Al.sub.m] + 2[K.sup.BF.sub.b])[w.sub.0] + 4[K.sup.BF.sub.m][w.sup.3.sub.0], (15)

where

[mathematical expression not reproducible]. (16)

The deflection of the thin BFML plate (type of 2/1) was several times the thickness of the BFML plate, and thus membrane force is dominant in responding to external loading. By ignoring the bending force, the following expression can be obtained:

P = 2[K.sup.Al.sub.m][w.sup.0] + 4[K.sup.BF.sub.m] [w.sup.3.sub.0]. (17)

The theoretical prediction by Equation (17) is in a good agreement with the related test results, which is shown in Figure 6.

4.2.2. Thick Plate. The small deflection profile of the clamped circular plate under lateral loading was given by the classical theory of plates:

w = P/16[pi]D ((2[r.sup.2] ln r/a + [a.sup.2] - [r.sup.2]), (18)

where P is the load, a is the radius of the plate, and D is the bending stiffness which is

D = E[h.sup.3]/12(1 - [v.sup.2]). (19)

The deflection at the center of loading can be obtained through Equation (18):

[w.sub.0] = P[a.sup.2]/16[pi]D. (20)

Therefore, the peak load is

P = [16[pi]D/[a.sup.2]] [w.sub.0]. (21)

The average elastic modulus of the BFML plate can be calculated by

E = [[E.sub.Al][h.sub.Al] + [E.sub.BF][h.sub.BF]]/[[h.sub.Al] + [h.sub.BF]] (22)

where [E.sub.Al] is the hardening slope of 2A12 aluminum alloy and [E.sub.BF] is the static elastic modulus of BFRP.

Figure 7 shows the predicted load-deflection curves compared with the test results of 4/3 BFMLs. The test results began to deviate from the predicted curve which did not take debonding (dashed line) into account when the deflection was more than 1 mm. Debonding may occur even when the impact load on the BFML plate is well below the peak load, as shown in Figure 8, which reduces the bending stiffness of the BFML plate. Therefore, the effect of debonding on the BFML plate stiffness must be considered during drop-weight impact. The debonding radius [R.sub.del] can be given in terms of the lateral load ([P.sub.d]) and the interlaminar shear strength (ILSS) between aluminum alloy sheet and BFRP [26]:

[R.sub.del] = [P.sub.d]/2[pi]hILSS. (23)

The bending stiffness of debonding area, as shown in Figure 9, can be calculated by

[R.suib.del] = [SIGMA](i[D.sub.Al] + J[D.sub.BF]), (24)

where

[D.sub.Al] = [E.sub.Al][h.sup.3.sub.Al]/12 (1 - [v.sup.2.sub.Al]), [D.sub.BF] = [E.sub.BF][h.sup.3.sub.BF]/12 (1 - [v.sup.2.sub.BF]). (25)

where i and j are the numbers of the aluminum alloy sheet and BFRP plate, respectively. The stiffness of bonding area is calculated by Equations (19) and (22). Then, the deflection composes of two parts ([w.sub.1] and [w.sub.2]) that are formed in bonding and debonding areas (Figure 9).

Figure 9 shows that the predicted load-deflection curve after considering debonding is in a good agreement with the test results, which demonstrates that the behavior of the thick BFML plate is closely related to the debonding phenomenon. It was further analyzed in the case that there was no debonding occurred, as shown in Figure 10. When the debonding is not dominated in the BFML plate after dropweight impact, the predicted load-deflection curve without considering debonding is more accurate than that considering debonding. It is worth pointing out that, in Figure 10, the initial bending stiffness of the load-deflection curve (less than 0.5 mm of deflection) should be calculated based on the elastic modulus of 2A12 aluminum alloy rather than the hardening slope (E : [E.sub.p] = 70.1 GPa : 1.5 GPa).

4.3. Failure Mode. The failure modes of the 2A12 aluminum alloy sheet and BFRP plate were both different on whether they are impacted alone or as components of BFMLs. The monolithic aluminum alloy sheet tends to form a plug during impact but petals during quasi-static loading as shown in Figure 11. The evident cross crack lines can be seen in loading area of the BFRP plate after static indentation while serious breakage was formed after impact as shown in Figure 12. As components of BFMLs, 2A12 aluminum alloy sheet and BFRP layer failed under impact were more like the way that both materials failed under static indentation, as shown in Figure 13. This means that the calculated energy based on static tests should be preferred in energy analysis of failure.

4.4. Energy Partition. The kinetic energy of the projectile was absorbed by global deformation of the BFML plate, debonding, fiber breakage, and plastic deformation and damage of 2A12 aluminum alloy during perforation. The energy balance equation is as follows:

[E.sub.abs] = [E.sub.deb] + [E.sub.tensile] + ([E.sub.m] + [E.sub.petal]), (26)

where [E.sub.abs] is the total absorbed energy and [E.sub.deb], [E.sub.tensile], [E.sub.m] and [E.sub.petal], are energies absorbed in debonding, tensile fracture of BFRP, deformation, and petaling of the 2A12 aluminum alloy sheet, respectively.

4.4.1. Energy Absorbed in Debonding. Debonding will propagate in mode II at a critical force [27]:

[P.sub.d] = [(8[[pi].sup.2] [E.sub.av] [h.sup.3][G.sub.IIC]/9 (1 - [v.sup.2)).sup.1/2], (27)

where v is Poisson's ratio, [E.sub.av] is the plate stiffness, and [G.sub.IIC] is the mode II critical interlaminar shear fracture toughness. The radius of debonding area is

[R.sub.deb] = [P.sub.d]/2[pi]hILSS, (28)

where ILSS is the shear strength of interface which was obtained by conducting tensile shearing tests on bonding surface between aluminum alloy sheet and BFRP plate. In the present study, ILSS = 30.0 MPa.

Energy absorbed in debonding is

[E.sub.deb] = [pi][R.sup.2.sub.deb][G.sub.IIC]. (29)

Combining Equations (27)-(29) gives

[E.sub.deb] = 2[pi][E.sub.av]h[G.sup.2.sub.IIC]/9(1 - [v.sup.2])ILS[S.sup.2]. (30)

4.4.2. Energy Absorbed by BFRP. The fracture energy density of BFRP can be obtained based on the area under strainstress curve of the tension test, which is [E.sub.t] - 2.85 x [10.sup.6] J/[m.sup.3]. The fracture energy of the BFRP plate under static indentation can be calculated by making the product of energy density to tensile failure by the volume of primary fiber region, shown in Figure 14. The calculated fracture energy is nearly equal to the test results, as shown in Table 7. Therefore, the energy absorbed in tensile fracture of BFRP in BFMLs during impacting perforation is given by

[E.sub.t] - 8[n.sub.BF][e.sub.t][r.sub.0]a[h.sub.BF], (31)

where [n.sub.BF] is the number of BFRP layers, [r.sub.0] is the radius of projectile, a is the radius of BFML plate, and [h.sub.BF] is the thickness of the single BFRP layer.

The membrane energy absorbed by the secondary fiber area where no fiber breakage occurred was calculated by Equation (12).

4.4.3. Energy Absorbed by 2A12 Aluminum Alloy Sheet. Based on the previous analysis, the membrane strain energy of the aluminum alloy sheet in BFMLs can be expressed as

[U.sup.Al.sub.m] = (0.288[N.sub.x] + 0.288[N.sub.y])[w.sup.2.sub.0] = [K.sup.Al.sub.m][w.sup.2.sub.0]. (32)

Taking [w.sub.0] as the maximum deflection of BFMLs, the plastic strain energy of the single aluminum alloy sheet can be obtained by

[E.sub.m] = [K.sup.Al.sub.m][w.sup.2.sub.max]. (33)

Furthermore, as the projectile perforating specimen, aluminum sheet bends back around projectile's periphery. The plastic work in petaling of n layers is

[E.sub.p] = [1/4][n.sub.Al][[pi].sup.2][r.sub.0][[sigma].sub.0][h.sup.2.sub.Al], (34)

where [n.sub.Al] is the number of aluminum alloy sheets and [r.sub.0] is the radius of the projectile.

Therefore, the energy partition of BFMLs is now clear, which is summarized in Table 8. The proportions of energy absorbed by constituent materials are shown in Figure 15. It can be seen that the energy absorbed by BFRP accounts for more than 75% of the total energy absorbed. The calculated total energy absorption is compared with the test results in Figure 16. Most of the calculated energies are in a good agreement with the test results. The reason for the discrepancies in the second and last ones may be due to the dispersiveness of ductility of the 2A12 aluminum alloy sheet as shown in Table 3.

If the total energy absorbed is divided by area density of the BFML plate, the specific energy absorption can be obtained. Figure 17 shows the specific energy absorption varies with metal volume fraction (MVF). The curves of MVF represent only the trends it varies. The two lines of MVF originate from two series of BFMLs, as shown in Figure 18. Series I was generated from numerical simulation using the commercial code ABAQUS (the corresponding properties such as absorbed energy were necessarily obtained from simulation in ABAQUS), while series II consisted of the specimens in the test. Both series of BFMLs (Figure 17) show that decreasing the MVF brings the higher specific energy absorption. However, the ductility of BFMLs is inevitably weakened with a low amount of ductile aluminum alloy.

5. Conclusions

Load-deflection relationships of 2A12 aluminum alloy sheets, BFRP plates, and BFML plates under drop-weight impact were obtained. The strain rate was calculated as impact velocity divided by specimen diameter, which was the averaged result over specimen span. It was used as an indicator in strain-rate effect analysis. Its accuracy is not high, but it is a convenient way to qualitatively inspect strain rate-related properties. Only BFRP plates showed strain-rate effect. As a result, drop-weight impact behavior of BFML plates was analyzed based on the static indentation. Moreover, the failure modes of 2A12 aluminum alloy sheets and BFRP layers in BFML plates were more or less similar to those of both monolithic materials failed in static indentation. Therefore, the fracture energies of each material in BFML plates were calculated based on properties obtained in static tests.

Thin and thick BFML plates under impact behaved quite differently. The behavior of thin BFML plates is controlled by membrane stress, while the bending stiffness of thick BFML plates is dependent on debonding between aluminum alloy sheet and BFRP layer.

The energy absorbed by BFRP layers in BFML plates accounts for more than 75% of total absorbed energy, indicating that BFRP is the main energy absorbing material. Decreasing MVF can raise the specific energy absorption of BFML plates. However, there must be a limit of MVF for the guarantee of the necessary ductility.

https://doi.org/10.1155/2018/1478951

Data Availability

The data used to support the findings of this study are included within the article.

Conflicts of Interest

The authors declare no conflict of interest.

Authors' Contributions

Dongliang Zhang and Qingyuan Wang were responsible for the conceptualization. Dongliang Zhang and Yunrong Luo were responsible for the methodology. Xiaoyan Zhang was responsible for the software. Qingyuan Wang and Yunrong Luo were responsible for the funding acquisition.

Acknowledgments

This research was funded by the Changjiang Scholars and Innovative Research Team (IRT14R37), National Natural Science Foundation of China under Grant No.11572057, Talent Introduction Project of Sichuan University of Science and Engineering (2015RC34), and the Project of Key Laboratory of Material Corrosion and Protection of Sichuan Province (2016CL17).

References

[1] C. A. J. R. Vermeeren, "An historic overview of the development of fibre metal laminates," Applied Composite Materials, vol. 10, no. 4-5, pp. 189-205, 2003.

[2] L. B. Vogelesang and A. Vlot, "Development of fibre metal laminates for advanced aerospace structures," Journal of Materials Processing Technology, vol. 103, no. 1, pp. 1-5, 2000.

[3] G. H. Majzoobi, H. Morshedi, and K. Farhadi, "The effect of aluminum and titanium sequence on ballistic limit of bi-metal 2/1 FMLs," Thin-Walled Structuers, vol. 122, pp. 1-7, 2018.

[4] Z. Asaee and F. Taheri, "Experimental and numerical investigation into the influence of stacking sequence on the low-velocity impact response of new 3D FMLs," Composite Structures, vol. 140, pp. 136-146, 2015.

[5] J. Bienias, P. Jakubczak, and K. Dadej, "Low-velocity impact resistance of aluminium glass laminates--experimental and numerical investigation," Composite Structures, vol. 152, pp. 339-348, 2016.

[6] J. Fan, W. Cantwell, and Z. Guan, "The low-velocity impact response of fiber-metal laminates," Journal of Reinforced Plastics and Composites, vol. 30, no. 1, pp. 26-35, 2011.

[7] M. Sadighi, M. Y. Tooski, and R. C. Alderliesten, "An experimental study on the low velocity impact resistance of fibre metal laminates under successive impacts with reduced energies," Aerospace Science and Technology, vol. 67, pp. 54-61, 2017.

[8] S. M. R. Khalili, A. Shokuhfar, K. Malekzadeh, and F. Ashenai Ghasemi, "Low-velocity impact response of active thin-walled hybrid composite structures embedded with SMA wires," Thin-Walled Structures, vol. 45, no. 9, pp. 799-808, 2007.

[9] S. Zhu and G. B. Chai, "Low-velocity impact response of fibremetal laminates-experimental and finite element analysis," Composites Science and Technology, vol. 72, no. 15, pp. 1793-1802, 2012.

[10] S. J. L. Curiel and N. Karapurath, "Delamination modelling of GLARE using the extended finite element method," Composites Science and Technology, vol. 72, no. 7, pp. 788-91, 2012.

[11] M. Kharazan, M. H. Sadr, and M. Kiani, "Delamination growth analysis in composite laminates subjected to low velocity impact," Steel and Composite Structures, vol. 17, no. 4, pp. 387-403, 2014.

[12] D. W. Lee, B. J. Park, S. Y. Park, C. H. Choi, and J. I. Song, "Fabrication of high-stiffness fiber-metal laminates and study of their behavior under low-velocity impact loadings," Composite Structures, vol. 189, pp. 61-69, 2018.

[13] H. Aghamohammadi, S. Navid Hosseini Abbandanak, R. Eslami-Farsani, and S. M. Hossein Siadati, "Effects of various aluminum surface treatments on the basalt fiber metal laminates interlaminar adhesion," International Journal of Adhesion and Adhesives, vol. 84, pp. 184-193, 2018.

[14] S. H. Khan, A. P. Sharma, R. Kitey, and V. Parameswaran, "Effect of metal layer placement on the damage and energy absorption mechanisms in aluminium/glass fibre laminate," International Journal of Impact Enginnering, vol. 119, pp. 14-25, 2018.

[15] A. P. Sharma, S. H. Khan, R. Kitey, and V. Parameswaran, "Effect of through thickness metal layer distribution on the low velocity impact responds of fiber metal laminates," Polymer Testing, vol. 65, pp. 301-312, 2018.

[16] N. Jones, "Note on the impact behavior of fibre-metal lamiantes," International Journal of Impact Engineering, vol. 108, pp. 147-152, 2017.

[17] T. Deak and T. Czigany, "Chemical composition and mechanical properties of basalt and glass fibers: a comparison," Textile Research Journal, vol. 79, no. 7, pp. 645-651, 2009.

[18] Q. Liu, M. T. Shaw, R. S. Parnas, and A. M. McDonnell, "Investigation of basalt fiber composite mechanical properties for applications in transportation," Polymer Composites, vol. 27, no. 1, pp. 41-8, 2006.

[19] A. Ross, "Basalt fibers: alternative to glass?," Composite Technology, vol. 12, pp. 44-8, 2006.

[20] B. Ozturk, F. Arslan, and S. Oztiirk, "Hot wear properties of ceramic and basalt fibre reinforced hybrid friction materials," Tribology International, vol. 40, no. 1, pp. 37-48, 2007.

[21] F. Rabinovich, V. Zueva, and L. Makeeva, "Stability of basalt fibres in a medium of hydrating cement," Glass and Ceramics, vol. 58, no. 11/12, pp. 431-4, 2001.

[22] F. M. Kogan and O. V. Nikitina, "Solubility of chrysotile asbestos and basalt fibres in relation to their fibrogenic and carcinogenic action," Environmental Health Perspectives, vol. 102, pp. 205-6, 1994.

[23] M. Damith, A. Muneeb, and N. Tuan, "Out-of-plane impact resistance of aluminum plates subjected to low velocity impacts," Materials and Design, vol. 50, pp. 413-426, 2013.

[24] M. S. Mahmood and J. O. Majid, "Investigating the transverse behavior of glass-epoxy composites under intermediate strain rates," Composite Structures, vol. 93, no. 2, pp. 690-696, 2011.

[25] X. Yu, Shock Mechanics, Tsinghua University Press, Beijing, China, 2011.

[26] G. J. Tsamasphyros and G. S. Bikakis, "Dynamic response of circular GLARE fibre-metal laminates subjected to low velocity impact," Journal of Reinforced Plastics and Composites, vol. 30, no. 11, pp. 978-987, 2011.

[27] S. H. F. Michelle, C. Lin, M. R. Duane Jr., and D. A. Hopkins, "Ballistic impact of GLARE fiber-metal laminates," Composite Structures, vol. 61, no. 1-2, pp. 73-88, 2003.

Dongliang Zhang [ID], (1) Xiaoyan Zhang [ID], (2) Yunrong Luo, (3) and Qingyuan Wang [ID] (4,5)

(1) Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China

(2) Sichuan University Jinjiang College, Pengshan 620860, China

(3) Sichuan University of Science and Engineering, Zigong 643000, China

(4) College of Architecture and Environment, Sichuan University, Chengdu 610065, China

(5) Chengdu University, Chengdu 610106, China

Correspondence should be addressed to Qingyuan Wang; wangqy@scu.edu.cn

Received 6 July 2018; Revised 31 August 2018; Accepted 4 September 2018; Published 30 September 2018

Academic Editor: Fabrizio Sarasini

Caption: Figure 1: INSTON 9520HV testing machine.

Caption: Figure 2: Load-deflection curves from static and drop-weight impact tests on the 2A12-T4 aluminum alloy sheet with a diameter of 100 mm loaded by the hemispherical projectile with a diameter of 20 mm.

Caption: Figure 3: Load-deflection curves of the BFRP plate under drop-weight impact: (a) 100 mm specimen and (b) 70 mm specimen.

Caption: Figure 4: Load-deflection curves of 2/1 BFMLs.

Caption: Figure 5: Idealized material behavior for 2A12 aluminum alloy and BFRP.

Caption: Figure 6: Load-deflection relation of the thin BFML plate controlled by membrane force.

Caption: Figure 7: Load-deflection relation of the thick BFML plate controlled by bending force.

Caption: Figure 8: Debonding of the thick BFML plate under low energy impact.

Caption: Figure 9: Illustration of deflection components of the BFML plate under drop-weight impact.

Caption: Figure 10: Load-deflection relation of the thick BFML plate without debonding.

Caption: Figure 11: Failure modes of the 2A12 aluminum alloy sheet: (a) petaling under static indentation; (b) pluging under drop-weight impact.

Caption: Figure 12: Failure modes of the BFRP plate under two sizes of projectile: (a) static indentation; (b) drop- weight impact.

Caption: Figure 13: Failure modes of the BFML plate: (a) impacted face; (b) nonimpacted face.

Caption: Figure 14: Subarea of the BFRP plate under impact.

Caption: Figure 15: Energy partition upon materials of BFML plates under drop-weight impact.

Caption: Figure 16: Comparison of calculated impact energy with the test results of BFML plates under drop-weight impact.

Caption: Figure 17: Absorbed energy and specific energy of BFML plates under drop-weight impact.

Caption: Figure 18: Two series of area density generated.
Table 1: Mechanical properties of E-glass fiber and basalt fiber.

                                          E-glass    Basalt
                                           fiber     fiber

Density (g/[cm.sup.3])                     2.56       2.8
Elastic modulus (GPa)                       76         89
Tensile strength (GPa)                    1.4-2.5      2.8
Elongation (%)                            1.8-3.2      3.15
Specific modulus (GPa * [cm.sup.3]/g)        30       31.78
Specific strength (GPa * [cm.sup.3]/g)      0.5-1       1

Table 2: Chemical components of 2A12-T4 aluminum alloy (%).

Element               Cu        Mg      Si      Fe       Mn

Standard value     3.8-4.9   1.2-1.8   <0.5    <0.5    0.3-0.9
Measured value       4.57      1.6      0.09    0.25     0.53

Element               Ni      Zn       Ti       Al

Standard value       <0.1    <0.3    <0.15   Remainder
Measured value       0.01     0.06    0.02

Table 3: Mechanical properties of 2A12-T4 aluminum alloy.

Elastic modulus        Hardening        Yield     Ultimate
(GPa)                 slope (GPa)      strength   strength
                                         (MPa)     (MPa)

70.1 [+ or -] 5.8   1.5 [+ or -] 0.3       325      470

Elastic modulus      Elongation
(GPa)                   (%)

70.1 [+ or -] 5.8   10 [+ or -]4

Table 4: Parameters of continuous basalt fiber and its composite.

             Diameter         Density/linear        Elastic
             ([micro]m)           density           modulus
                                                     (GPa)

CBF              13              600(Tex)             105
BFRP             --         1730 kg/[m.sup.3]         15.0

              Tensile         Elongation
              strength           (%)
               (MPa)

CBF             2100             2.6
BFRP            290              2.0

Table 5: Engineering constants of BFRP.

Parameter    [E.sub.1]   [E.sub.2]   [G.sub.12]
               (GPa)      (GPa)        (Gpa)

Value           15.0       15.0           3.27

Parameter    X = Y (MPa)          S (MPa)      [v.sub.12]

Value        290 [+ or -] 22   68 [+ or -] 7      0.28

Table 6: Test results of the drop-weight impact.

                   Peak load     Maximum      Impact
                      (kN)      Deflection    velocity
                                  (mm)          (m/s)

20-Al-70-1 (1)         3.41        6.95         2.630
20-Al-70-2             3.00        5.07         3.268
20-Al-100-1            3.31        8.50         1.644
20-Al-100-2            3.20        7.81         2.529
20-Al-100-3            4.22       10.35         2.654
20-FML2/1-70-1         6.92        5.24         3.542
20-FML2/1-100-2        8.78        9.56         3.229
20-FML3/2-70-1         7.22        4.18         3.309
20-FML3/2-100-3       13.14        8.89         3.117
20-BFRP-70-1           3.00        5.53          2.47
20-BFRP-70-2           3.37        5.85         3.328
20-BFRP-100-1          2.97        7.49         1.897
20-BFRP-100-2          3.46        8.90         2.244
20-BFRP-100-3          3.52        7.73         3.106
10-Al-70-1             2.35        4.99         3.686
10-Al-100-1            2.38        6.77         3.317
10-FML2/1-70-1         5.63        5.97         2.826
10-FML2/1-100-1        5.72        7.70         2.561
10-FML3/2-100-2        9.93        7.27         2.923
10-FML4/3-70-1        15.58        6.79         2.682
10-BFRP-70-1           2.05        5.16         0.864
10-BFRP-70-2           2.48        5.63         3.409
10-BFRP-100            2.40        5.46         3.458

                   Radius of     Strain
                    specimen       rate
                       (mm)     ([s.sup.-1])

20-Al-70-1 (1)          35           75
20-Al-70-2              35           93
20-Al-100-1             50           33
20-Al-100-2             50           51
20-Al-100-3             50           53
20-FML2/1-70-1          35          101
20-FML2/1-100-2         50           65
20-FML3/2-70-1          35           95
20-FML3/2-100-3         50           62
20-BFRP-70-1            35           71
20-BFRP-70-2            35           95
20-BFRP-100-1           50           38
20-BFRP-100-2           50           45
20-BFRP-100-3           50           62
10-Al-70-1              35          105
10-Al-100-1             50           66
10-FML2/1-70-1          35           81
10-FML2/1-100-1         50           51
10-FML3/2-100-2         50           58
10-FML4/3-70-1          35           77
10-BFRP-70-1            35           25
10-BFRP-70-2            35           97
10-BFRP-100             50           69

(1) 20-Al-70-1 represents the testing condition as follows: projectile
diameter is 20 mm, specimen material is aluminum sheet, specimen
diameter is 70 mm, and serial number of specimen is 1.

Table 7: Failure energy of the BFRP plate under static indentation.

Specimen diameter (mm)              70

Projectile diameter (mm)     20     10     5
Tested (J)                 14.42   5.90   2.92
Calculated (J)             10.53   5.27   2.63

Specimen diameter (mm)             100

Projectile diameter (mm)     20     10     5
Tested (J)                 16.39   6.61   3.53
Calculated (J)             15.05   7.52   3.76

Table 8: Energy partition of BFML plates under drop-weight impact.

Specimen          Debonding (J)        BFRP (J)

                                  Membrane   Breakage

20-FML2/1-70-1        0.58          13.49      10.53
20-FML2/1-100-2       0.58          72.95      15.05
20-FML3/2-70-1        2.28           5.46      21.07
20-FML3/2-100-3       2.28          54.55      30.10
10-FML2/1-70-1        0.58          22.60       5.27
10-FML2/1-100-1       0.58          30.81       7.52
10-FML3/2-100-2       2.28          24.40      15.05
10-FML4/3-70-1        5.10          37.91       15.80

Specimen           Aluminum alloy (J)         Total energy (J)

                  Membrane   Petaling   Calculated   Tested

20-FML2/1-70-1      5.16       4.02         33.78     36.11
20-FML2/1-100-2    17.15       4.02        109.75     71.27
20-FML3/2-70-1      4.93       6.03         39.77     31.57
20-FML3/2-100-3    22.25       6.03        115.20    122.48
10-FML2/1-70-1      6.68       2.01         37.14     32.55
10-FML2/1-100-1    11.15       2.01         52.07     32.22
10-FML3/2-100-2    14.88       3.01         59.62     67.08
10-FML4/3-70-1     17.31       4.02         80.14    125.46
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Title Annotation:Research Article
Author:Zhang, Dongliang; Zhang, Xiaoyan; Luo, Yunrong; Wang, Qingyuan
Publication:Advances in Materials Science and Engineering
Date:Jan 1, 2018
Words:6067
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