Energy Absorbing Properties Analysis of Layers Structure of Titanium Alloy Ti6Al4V during Dynamic Impact Loading Tests

This paper presents the testing methodology of specimens made of layers of titanium alloy Ti6Al4V in dynamic impact loading conditions. Tests were carried out using a drop-weight impact tower. The test methodology allowed us to record parameters as displacement or force. Based on recorded data, force and absorbed energy curves during plastic deformation and sheet perforation were created. The characteristics of the fractures were also analyzed. The impact test simulation was carried out in the ABAQUS/Explicit environment. Results for one, two, and three layers of titanium alloy were compared. The increase in force required to initialize the damage and the absorbed energy during plastic deformation can be observed with an increase in the number of layers. The increase in absorbed energy is close to linear. In the simulation process, parameters such as Huber–Mises–Hencky stress value, equivalent plastic strain, temperature increase, and stress triaxiality were analyzed.


Introduction
Titanium and its alloys are common materials that have been used since the 1960s. Their desirable properties, which include low density, high mechanical strength, heat resistance, low-temperature fracture toughness, low thermal expansion, resistance to in-service corrosion processes, and biocompatibility, allow for wide applications in biomedical, automotive, aviation, and military engineering. An example is the modern method of joining parts using the electromagnetic riveting process (EMR), a high-speed impact connection technology with the advantages of fast loading speed, large impact force, and stable rivet deformation [1]. However, a high friction coefficient, poor resistance to abrasive wear, and a low hardness limit the possible areas of application of titanium alloys. Therefore, the proper use of these materials requires knowledge of their characteristics and properties [2][3][4].
There are many publications on the behavior of titanium alloys under static loading [5,6]. However, dynamic loading has not been sufficiently defined. Some papers concerning the high strain rate properties of titanium alloys are available [7][8][9][10], but much work must still be undertaken, especially in the areas of experimental techniques, microstructural analysis, and modeling, to fully define the constitutive properties of these materials. Invoking a variable load over a short time period can cause a change in the behavior of titanium alloys [11]. In some areas, such as aviation and the military, the level of dissipation or absorption of impact energy in a material is also important. However, detailed information on this, such as the energy absorption level related to mass, is often absent [12].
The aim of this study was to determine the energy-absorbing properties of layered structures of titanium Ti6Al4V alloy under dynamic impact conditions using a drop-weight impact tester, as well as to determine the basic material properties for high strain rate deformation for numerical simulation. The analysis allowed us to estimate the energy required to break a single sheet and the layered structure sheets to determine the puncture characteristics and the influence of layered structures on the amount of energy required.
A visual assessment of the mechanism of developing damage and absorbed energy value during experimentation depending on the number of layers was performed. In addition, a force value analysis of failure initiation was performed. For this purpose, appropriate sheet metal specimens of 1 mm thickness were prepared to perform dynamic impact tests on a drop-weight tester. The mechanical and physical properties of titanium alloy Ti6Al4V have been broadly described in the literature. These alloys can be widely applied in many fields, such as 3D printing of ultralight sandwich structures with corrugated cores in aerospace [13] and medical [14] applications.
The innovative approach in this paper is based on a multi-layer analysis of energy absorption by layered structures of titanium alloy during dynamic impact loading tests. This paper presents experimental data together with the numerical solution of a given impact load. The multi-layer structures are more effective in terms of strength and energy absorption compared to monolithic layers.
Using a drop-weight impact method allowed us to determine the energy-absorbing properties of a Ti6Al4V titanium alloy sheet. Further research could be used to analyze the behavior of polymer-titanium and polymer-glass-titanium composites.

Properties and Structure of the Titanium Alloy Ti6Al4V
Titanium Ti6Al4V is a dual-phase alloy composed of α and β phases. Stabilization of the phases corresponds to the principal alloying elements, aluminum stabilizing alpha, and vanadium beta phase [15][16][17]. Chemical compositions of the Ti6Al4V were used according to ISO 5832/3 [18]. The selected titanium alloy exhibits very good mechanical properties [19], which is why Ti6Al4V is commonly used in technology, especially in the aerospace industry. Depending on the manufacturing process, titanium alloys are characterized by anisotropy, low density, a Young's modulus of 115 GPa (comparable to steel: 205-210 GPa), high strength with good ductility, and a high melting point. The main mechanical properties are presented in Table 1 and Figure 1. Another characteristic advantage of titanium alloys is corrosion resistance at ambient temperatures, e.g., in the air or an industrial atmosphere. Compared to pure titanium, Ti6Al4V alloy has greater strength with the same stiffness and thermal properties [20]. However, Ti6Al4V also has the notable disadvantage of easily reacting with other materials at higher temperatures. This entails a number of obstacles, such as the need for using unconventional methods in the melting and casting processes, which leads to an increase in production and processing costs.

Specimens
Specimens were made from a cold-rolled metal sheet of Ti6Al4V of 1 mm th For the experiments, 18 plates of 80 mm × 80 mm were cut from the sheet. Each sp was described and marked with an arrow showing the rolling direction, accordin anisotropic material properties. A specimen is shown in Figure 2. Non-standard impact tests were used. There is no possibility to measure th impact strength on a sheet of 1 mm thickness, but it is possible to determine the absorbed by the puncture process. In this case, the state of the stress test changed dimensional. The chemical and physical properties that might occur during a given process type in Ti6Al4V titanium alloy processing must be considered due to chemical reactivity, low modulus of elasticity, and high strength. Ti6Al4V can be submitted to processes including casting, welding, cutting, and plastic processing. The variety of manufacturing methods and process parameters significantly affects the anisotropy of the material and its mechanical properties, which should always be considered in the design process.

Specimens
Specimens were made from a cold-rolled metal sheet of Ti6Al4V of 1 mm thickness. For the experiments, 18 plates of 80 mm × 80 mm were cut from the sheet. Each specimen was described and marked with an arrow showing the rolling direction, according to the anisotropic material properties. A specimen is shown in Figure 2.

Specimens
Specimens were made from a cold-rolled metal sheet of Ti6Al4V of 1 mm thicknes For the experiments, 18 plates of 80 mm × 80 mm were cut from the sheet. Each specime was described and marked with an arrow showing the rolling direction, according to th anisotropic material properties. A specimen is shown in Figure 2. Non-standard impact tests were used. There is no possibility to measure the direc impact strength on a sheet of 1 mm thickness, but it is possible to determine the energ absorbed by the puncture process. In this case, the state of the stress test changed to two dimensional. Non-standard impact tests were used. There is no possibility to measure the direct impact strength on a sheet of 1 mm thickness, but it is possible to determine the energy absorbed by the puncture process. In this case, the state of the stress test changed to two-dimensional.

Drop-Weight Impact Tester
Dynamic impact tests were carried out on a drop-weight impact tester INSTRON with Dynatup 9250 HV (Instron, Norwood, MA, USA) column equipped with an Impulse control and data processing system ( Figure 3). The INSTRON machine offers 20 m/s speed (forced drive), simulation of discharge height of 20.4 m, and impact energy from 4.5 to 1600 J. The use of this post enabled the impact test to record parameters such as impact velocity, energy change, load, yield strength, deformation, and time.

Drop-Weight Impact Tester
Dynamic impact tests were carried out on a drop-weight impact tester INSTRON with Dynatup 9250 HV (Instron, Norwood, MA, USA) column equipped with an Impulse control and data processing system ( Figure 3). The INSTRON machine offers 20 m/s speed (forced drive), simulation of discharge height of 20.4 m, and impact energy from 4.5 to 1600 J. The use of this post enabled the impact test to record parameters such as impact velocity, energy change, load, yield strength, deformation, and time.  The striker is made of NC3 tool steel with a hardness of 48 HRC ( Figure 4). It has a diameter of 10 mm, a cone-shaped blade with a tip angle of 30° ± 1°, and a radius of curvature of 2 mm. The striker is shown in Figure 4. It is easily seen that, apart from the cylindrical shape of the striker, the geometric dimensions fit Charpy's standards. The recorded results of impact tests were graphs of absorbed energy (impact work) (J) and load (kN) as a function of the recorded displacement (mm) of the specimen material and in the form of the numerical values, which were recorded automatically. The arrays for individual trials collected the values of the most important parameters measured and recorded during the tests by the Impulse control and the data processing system used. The striker is made of NC3 tool steel with a hardness of 48 HRC ( Figure 4). It has a diameter of 10 mm, a cone-shaped blade with a tip angle of 30 • ± 1 • , and a radius of curvature of 2 mm. The striker is shown in Figure 4. It is easily seen that, apart from the cylindrical shape of the striker, the geometric dimensions fit Charpy's standards.

Drop-Weight Impact Tester
Dynamic impact tests were carried out on a drop-weight impact tester INSTRON with Dynatup 9250 HV (Instron, Norwood, MA, USA) column equipped with an Impuls control and data processing system ( Figure 3). The INSTRON machine offers 20 m/s spee (forced drive), simulation of discharge height of 20.4 m, and impact energy from 4.5 t 1600 J. The use of this post enabled the impact test to record parameters such as impac velocity, energy change, load, yield strength, deformation, and time.  The striker is made of NC3 tool steel with a hardness of 48 HRC ( Figure 4). It has diameter of 10 mm, a cone-shaped blade with a tip angle of 30° ± 1°, and a radius of cu vature of 2 mm. The striker is shown in Figure 4. It is easily seen that, apart from th cylindrical shape of the striker, the geometric dimensions fit Charpy's standards. The recorded results of impact tests were graphs of absorbed energy (impact work (J) and load (kN) as a function of the recorded displacement (mm) of the specimen mate rial and in the form of the numerical values, which were recorded automatically. The a rays for individual trials collected the values of the most important parameters measure and recorded during the tests by the Impulse control and the data processing system used The recorded results of impact tests were graphs of absorbed energy (impact work) (J) and load (kN) as a function of the recorded displacement (mm) of the specimen material and in the form of the numerical values, which were recorded automatically. The arrays for individual trials collected the values of the most important parameters measured and recorded during the tests by the Impulse control and the data processing system used.

Calibration of Johnson-Cook Model for FE Simulation
The Johnson-Cook (JC) model was calibrated for the simulation because a reliable material model was required for numerical simulation at high deformation rates.
FEM analysis was performed using the ABAQUS/Explicit environment (ABAQUS Inc. Providence, MA, USA). The Johnson-Cook model [23,24] was used for the simulation. The JC is a constitutive model describing the plastic behavior of the material at high strain, strain rate, and temperature. The JC Equation (1) describes the empirical stress relationship of the Huber-Mises-Hencky (HMH) equation.
where Q = T−T 0 T melt −T 0 . There are different methods of calibrating the JC model. The method used in this study was calibrated according to the commonly used scheme: determination of constants (A, B, and n) based on isothermal tensile (or torsion) tests; determination of C constant under quasi-static or dynamic conditions at different deformation rates; and m coefficient in dynamic conditions for different temperature values (in this case, due to no possibility of testing under different temperature conditions, the m coefficient was selected from the literature [25]).
Due to the obtained mechanical characteristics of the titanium alloy, it was possible to calibrate the Johnson-Cook model as presented in Equation (2).
Calibration was made for two cases: for specimens with a gauge length (L) of 18 mm, and for specimens with a gauge length of 30 mm ( Figure 5). In the first step to determine the coefficients A, B, and n for the strain rate 0.0001/s, the stress-strain characteristic curve was approximated by the power function. The results are shown in Figure 6. The results shown in Figure 6 for strain value ε = 0.02 were recorded for three different strain velocities. Figure 7 shows the results for two specimens (18 and 30 mm), where the normalized yield strength is shown on the vertical axis. The value of the coefficient m was chosen based on the literature [25]. The values of the Johnson-Cook coefficients are set forth in Table 2. The real stress-strain characteristics were derived from the engineering values obtained in the tensile tests using the logarithmic function in Equations (2) and (3).
The JC is a constitutive model describing the plastic behavior of th strain rate, and temperature. The JC Equation (1) describes the e ship of the Huber-Mises-Hencky (HMH) equation.
There are different methods of calibrating the JC model. T study was calibrated according to the commonly used scheme: de (A, B, and n) based on isothermal tensile (or torsion) tests; dete under quasi-static or dynamic conditions at different deformatio in dynamic conditions for different temperature values (in this c of testing under different temperature conditions, the m coefficie literature [25]).
Due to the obtained mechanical characteristics of the titaniu to calibrate the Johnson-Cook model as presented in Equation (2 Calibration was made for two cases: for specimens with a ga and for specimens with a gauge length of 30 mm ( Figure 5). In th the coefficients A, B, and n for the strain rate 0.0001/s, the stress-s was approximated by the power function. The results are shown shown in Figure 6 for strain value ε = 0.02 were recorded for thre ties. Figure 7 shows the results for two specimens (18 and 30 mm yield strength is shown on the vertical axis. The value of the c based on the literature [25]. The values of the Johnson-Cook co Table 2. The real stress-strain characteristics were derived from obtained in the tensile tests using the logarithmic function in Equ    Based on the obtained results, stress-strain characteristics for 18 mm and 30 mm gauge lengths were developed for three different strain rates. Using Johnson-Cook coefficients, similar value characteristics for this model were obtained. The comparative characteristics are presented in Figure 8. It is easy to observe that as the strain rate increases, the difference between real and computational values rises. However, received values are within the limits of acceptability.   Based on the obtained results, stress-strain characteristics for 18 mm and 30 mm gauge lengths were developed for three different strain rates. Using Johnson-Cook coefficients, similar value characteristics for this model were obtained. The comparative characteristics are presented in Figure 8. It is easy to observe that as the strain rate increases, the difference between real and computational values rises. However, received values are within the limits of acceptability.  Table 2. Johnson Cook constitutive model coefficients. Based on the obtained results, stress-strain characteristics for 18 mm and 30 mm gauge lengths were developed for three different strain rates. Using Johnson-Cook coefficients, similar value characteristics for this model were obtained. The comparative characteristics are presented in Figure 8. It is easy to observe that as the strain rate increases, the difference between real and computational values rises. However, received values are within the limits of acceptability.
To verify the correctness of our methodology for determining the energy-absorbing properties of titanium alloy, numerical simulations of the sheet metal impact test were made using the above material models.
The model of sheet metal and mesh is shown in Figure 9. The sheet metal model was divided into 14,995 finite elements (element type: C3D8R) for the analysis. The mesh was compacted at the puncture area due to high displacement values and to precisely visualize the material deformation. The striker was modeled as a rigid body for simulation purposes. The plate was fixed at its edges and the striker was given a starting value of 12.3 m/s, which corresponds to the value measured during the experiment. A friction interaction of 0.1 was introduced between the surface of the striker and the mesh of the plate. The value of the friction coefficient was determined based on the successive simulations to achieve results most closely related to the experimental values.

Results and Discussion
During experiments, nine dynamic impact tests were carried out at room temperature (296.15 K). A total of three attempts were made for the individual case to obtain statistical data. Specimens were punctured separately (specimens 1, 2, and 3); specimens from 4-9 were layered in pairs (4-5, 6-7, and 8-9); specimens from 10-18 were layered in threes (10-11-12, 13-14-15, and 16-17-18). To verify the correctness of our methodology for determining the energy-absorbing properties of titanium alloy, numerical simulations of the sheet metal impact test were made using the above material models.
The model of sheet metal and mesh is shown in Figure 9. The sheet metal model was divided into 14,995 finite elements (element type: C3D8R) for the analysis. The mesh was compacted at the puncture area due to high displacement values and to precisely visualize the material deformation. The striker was modeled as a rigid body for simulation purposes. The plate was fixed at its edges and the striker was given a starting value of 12.3 m/s, which corresponds to the value measured during the experiment. A friction interaction of 0.1 was introduced between the surface of the striker and the mesh of the plate. The value of the friction coefficient was determined based on the successive simulations to achieve results most closely related to the experimental values. The remaining material data used in the simulation were: density 4510 kg/m 3 ; Young's modulus 115 GPa; Poisson ratio 0.31; Taylor-Quinney coefficient 0.9; specific heat 523 J/(kg•K).
To verify the correctness of our methodology for determining the energy-absorbing properties of titanium alloy, numerical simulations of the sheet metal impact test were made using the above material models.
The model of sheet metal and mesh is shown in Figure 9. The sheet metal model was divided into 14,995 finite elements (element type: C3D8R) for the analysis. The mesh was compacted at the puncture area due to high displacement values and to precisely visualize the material deformation. The striker was modeled as a rigid body for simulation purposes. The plate was fixed at its edges and the striker was given a starting value of 12.3 m/s, which corresponds to the value measured during the experiment. A friction interaction of 0.1 was introduced between the surface of the striker and the mesh of the plate. The value of the friction coefficient was determined based on the successive simulations to achieve results most closely related to the experimental values.
As a result of the study, graphs of force during puncture in the displacement function, as well as energy during puncture, were obtained. The results for individual cases shown in Figure 10 and averaged in Figure 11 are also a comparison of results for each case, as can be observed. It clearly shows an increase in strength during puncture relative to the number of layers. The energy needed to puncture double-plate (205 J) is greater than twice the energy required to puncture a single plate (84 J × 2 = 168 J). Similarly, three-layer structure energy (325 J) is greater than three times the energy required for a single plate (3 × 84 J = 252 J). That might be due to the fact that the striker energy is dispersed not only by the deformation of the material and the energy required to destroy it but also by friction between each layer. The coefficient of friction between each layer is correlated with the roughness of the samples, as shown in Figure 12. A comparison of the value obtained from the experiment and the energy value calculated based on a single-sheet puncture is shown in Figure 13. It is easy to see that this relationship shows characteristics similar to a linear one. The study of sheet metal multi-layer structures, consisting of sheet metal packaging, can be an introduction to the analysis of polymer-titanium and polymer-glass-titanium composites' behavior.
As a result of the study, graphs of force during puncture in the displacement function, as well as energy during puncture, were obtained. The results for individual cases shown in Figure 10 and averaged in Figure 11 are also a comparison of results for each case, as can be observed. It clearly shows an increase in strength during puncture relative to the number of layers. The energy needed to puncture double-plate (205 J) is greater than twice the energy required to puncture a single plate (84 J × 2 = 168 J). Similarly, threelayer structure energy (325 J) is greater than three times the energy required for a single plate (3 × 84 J = 252 J). That might be due to the fact that the striker energy is dispersed not only by the deformation of the material and the energy required to destroy it but also by friction between each layer. The coefficient of friction between each layer is correlated with the roughness of the samples, as shown in Figure 12. A comparison of the value obtained from the experiment and the energy value calculated based on a single-sheet puncture is shown in Figure 13. It is easy to see that this relationship shows characteristics similar to a linear one. The study of sheet metal multi-layer structures, consisting of sheet metal packaging, can be an introduction to the analysis of polymer-titanium and polymerglass-titanium composites' behavior.               Figures 14-16 show the results of the impact tests with a comparison to the finite element simulation. The form of material failure (bursting) has a petaling character. In titanium structure sheet tests, the first layers are most crushed, grated by contact between the plate and the striker. The last layers show the greatest deformation.

Calculation of Specific Energy Absorption W EA
The energy-consuming structures used in the aerospace industry should be of the lowest possible weight, but also of high strength and stiffness to specific mass ratio. One of the parameters describing the energy consumption is the total impact energy absorption EA (kJ), equivalent to the area under the load-displacement curve calculated up to points P 1 , P 2 , and P 3 of the sudden curve fall (Figure 11a).

Calculation of Specific Energy Absorption WEA
The energy-consuming structures used in the aerospace industry should be of the lowest possible weight, but also of high strength and stiffness to specific mass ratio. One of the parameters describing the energy consumption is the total impact energy absorption EA (kJ), equivalent to the area under the load-displacement curve calculated up to points P1, P2, and P3 of the sudden curve fall (Figure 11a).
In order for energy-absorbing structures to best absorb the impact energy, the destruction of these structures must not be carried out in an abrupt manner, as in beam damage during global buckling. Instead, the destruction should be carried out progressively, so that each volume of the specimen is crushed (destroyed) into the smallest particles.
The process of progressive destruction depends mainly on the mechanical properties of the material, its structure, shape, and the geometry of the specimens.
The specific energy absorption capability (4) WEA of a composite material is defined as the energy absorbed per unit mass of material as In order for energy-absorbing structures to best absorb the impact energy, the destruction of these structures must not be carried out in an abrupt manner, as in beam damage during global buckling. Instead, the destruction should be carried out progressively, so that each volume of the specimen is crushed (destroyed) into the smallest particles.
The process of progressive destruction depends mainly on the mechanical properties of the material, its structure, shape, and the geometry of the specimens.
The specific energy absorption capability (4) W EA of a composite material is defined as the energy absorbed per unit mass of material as where m is the mass of the composite material. Examples of the values for the highest relative absorption energy W EA for several types of materials are given in Figure 17.
where m is the mass of the composite material. Examples of the values for the highest relative absorption energy WEA for several types of materials are given in Figure 17.

FE Simulation Results
Simulations were created to develop a material model of Ti6Al4V matched to high strain rate tests, to compare the results with those of the experiments, and to define properties that could not be tested by experiments such as temperature and stress state during

FE Simulation Results
Simulations were created to develop a material model of Ti6Al4V matched to high strain rate tests, to compare the results with those of the experiments, and to define properties that could not be tested by experiments such as temperature and stress state during puncture. The Johnson-Cook coefficients in Table 2 were used in the simulation. The Huber-Mises-Hencky stress characteristic (HMH) during the puncture process was obtained in the simulation, as shown in Figure 18. As a result of the simulation, the maximum stress was approximately 1300 MPa, which can be considered to be in line with experimental data. Material crumbling and the formation of characteristic flakes comparable to the experiment can be observed during damage propagation. The highest value of reduced stress (1.3 × 10 9 Pa) was recorded for a step of 0.6 µs. At this point, the material undergoes progressive decohesion. At the next step (t = 0.8 µs), spring relief of the material can be observed by comparing the stress areas. At the time of decohesion, reduced stress greater than or equal to 2.8 × 10 8 Pa is present across the majority of the specimen area. However, in the next step (t = 0.8 µs), the reduced stress importantly decreases over a significant area below the value of 1.4 × 10 8 Pa, only to increase again in the next simulation step (t = 1.0 µs). This increase continues until the punch fully passes through the specimen. Figure  19 shows the strain visualization of equivalent plastic strain (PEEQ) during sheet metal Material crumbling and the formation of characteristic flakes comparable to the experiment can be observed during damage propagation. The highest value of reduced stress (1.3 × 10 9 Pa) was recorded for a step of 0.6 µs. At this point, the material undergoes progressive decohesion. At the next step (t = 0.8 µs), spring relief of the material can be observed by comparing the stress areas. At the time of decohesion, reduced stress greater than or equal to 2.8 × 10 8 Pa is present across the majority of the specimen area. However, in the next step (t = 0.8 µs), the reduced stress importantly decreases over a significant area below the value of 1.4 × 10 8 Pa, only to increase again in the next simulation step (t = 1.0 µs). This increase continues until the punch fully passes through the specimen. Figure 19 shows the strain visualization of equivalent plastic strain (PEEQ) during sheet metal puncturing. The maximum strain value was 0.532. This value is greater than that available in the literature [27]. of the sheet at the point where the striker contacted the sheet. When the sheet is bent b puncturing, at the point of contact with the striker the compressive stress undergoes ten sile stress, and the stress changes into compression with the development of the defor mation. The maximum triaxiality stress value is 1.9, which is higher than that in the liter ature [27].    In the ABAQUS simulation process, tests such as temperature increase, stress triaxiality, and force at failure initiation were carried out. Figure 20 shows the sheet metal temperature increase at the puncture area where the maximum increase from the initial temperature was 287.3 K. Taking into account the initial conditions (initial temperature 296.15 K) the sheet was heated to 583.45 K. Figure 21 shows the stress during the puncture of the specimen. Compressive stress occurred when there was tensile stress on the opposite side of the sheet at the point where the striker contacted the sheet. When the sheet is bent by puncturing, at the point of contact with the striker the compressive stress undergoes tensile stress, and the stress changes into compression with the development of the deformation. The maximum triaxiality stress value is 1.9, which is higher than that in the literature [27].
Materials 2021, 14, x FOR PEER REVIEW 14 of the sheet at the point where the striker contacted the sheet. When the sheet is ben puncturing, at the point of contact with the striker the compressive stress undergoes sile stress, and the stress changes into compression with the development of the de mation. The maximum triaxiality stress value is 1.9, which is higher than that in the l ature [27].      Figure 24 indicates a temperature increase of 385 K. This is 99 K more than for a single layer. Such a difference may be due to the interaction between the surfaces. The nature of the stress triaxiality condition can be considered analogous to the first simulation ( Figure 25). temperature increase at the puncture point in Figure 24 indicates a temperature increase of 385 K. This is 99 K more than for a single layer. Such a difference may be due to the interaction between the surfaces. The nature of the stress triaxiality condition can be considered analogous to the first simulation ( Figure 25).   temperature increase at the puncture point in Figure 24 indicates a temperature increase of 385 K. This is 99 K more than for a single layer. Such a difference may be due to the interaction between the surfaces. The nature of the stress triaxiality condition can be considered analogous to the first simulation ( Figure 25).           Analogous simulations were performed on three layers of Ti6Al4V titanium alloy sheet. The results of this simulation are also presented in the form of visualization of HMH stress, PEEQ strain, temperature increase, and stress triaxiality in individual layers. The maximum values in this simulation were an HMH stress of 1263 MPa, a PEEQ of 0.5306, and a sheet temperature increase of 393 K. All visualizations are shown in Figures 26-29. It can be observed that the temperature change can affect some mechanical parameters of the considered titanium alloy [28]. It can be observed that the temperature change can affect some mechanical parameters of the considered titanium alloy [28].   In the next step, the forces obtained from the INSTRON machine were compared with the results of the FE simulation, which made it possible to compare the accuracy of the applied material model. The results of the analysis were filtered using the Butterworth filter (available in ABAQUS) at a 20,000 Hz cut-off frequency (COF). The Butterworth filter is one of the most commonly used filters, with maximum flat amplitude in the passband bandwidth. The Butterworth filter was used to eliminate numerical noise. The COF, set at 20 kHz, was selected over the course of subsequent analyses using COF values from 5 to 30 kHz. The selected frequency had the least interference with the achieved maximum values and with the waveform. The approximate maximum forces at the initiation of damage were obtained. For a single plate experiment, the force was 5.33 kN, while the simulation obtained 5.41 kN; for two layers, the maximum force was 11.85 kN for the experiment and 11.32 kN for the simulation. Force values for three layers were found as 21.2 kN for the experiment and 19.7 kN for the simulation. Force diagrams are shown in Figure 30, which is a comparison of all obtained results related to force at damage initiation. The difference in results might be due to a too simple friction model between the striker and the sheet, incorrect selection of coefficient of friction, the approximate fracture locus, or the imperfection of the constitutive model. Since the titanium alloy was supplied in the form of a rolled sheet, it is characterized by an anisotropy that was not included in the calculation. stress, PEEQ strain, temperature increase, and stress triaxiality in individual layers. The maximum values in this simulation were an HMH stress of 1263 MPa, a PEEQ of 0.5306 and a sheet temperature increase of 393 K. All visualizations are shown in Figures 26-29 It can be observed that the temperature change can affect some mechanical parameters o the considered titanium alloy [28].    In the next step, the forces obtained from the INSTRON machine were compared with the results of the FE simulation, which made it possible to compare the accuracy o the applied material model. The results of the analysis were filtered using the Butterworth maximum values in this simulation were an HMH stress of 1263 MPa, a PEEQ of 0.5306 and a sheet temperature increase of 393 K. All visualizations are shown in Figures 26-29 It can be observed that the temperature change can affect some mechanical parameters o the considered titanium alloy [28].    In the next step, the forces obtained from the INSTRON machine were compare with the results of the FE simulation, which made it possible to compare the accuracy o the applied material model. The results of the analysis were filtered using the Butterwort and a sheet temperature increase of 393 K. All visualizations are shown in Figures 26-29. It can be observed that the temperature change can affect some mechanical parameters of the considered titanium alloy [28].    In the next step, the forces obtained from the INSTRON machine were compared with the results of the FE simulation, which made it possible to compare the accuracy of the applied material model. The results of the analysis were filtered using the Butterworth The use of high-impact velocities caused difficulties in modeling the observed phenomenon, which exhibited a rapidly varying character. The obtained calculation results have an oscillatory character, resulting from the specificity of the numerical model and requiring filtering.
Due to the fact that the material used for experimental research was only in the form of metal sheets, the standard impact strength for the Charpy standard U-notched specimen was determined in the simulation using the JC model. The velocity of the striker was given a value of 12.3 m/s, as in the simulation above. The impact strength was KC = 122 J/cm 2 . The model of this simulation is shown in Figure 31. form of a rolled sheet, it is characterized by an anisotropy that was not included in the calculation.
The use of high-impact velocities caused difficulties in modeling the observed phenomenon, which exhibited a rapidly varying character. The obtained calculation results have an oscillatory character, resulting from the specificity of the numerical model and requiring filtering. Due to the fact that the material used for experimental research was only in the form of metal sheets, the standard impact strength for the Charpy standard U-notched specimen was determined in the simulation using the JC model. The velocity of the striker was given a value of 12.3 m/s, as in the simulation above. The impact strength was KC = 122 J/cm 2 . The model of this simulation is shown in Figure 31.

Conclusions
The application of a drop-weight tester equipped with a conical striker allowed evaluation of the energy-absorbing properties of Ti6al4V titanium alloy sheets and allowed us to analyze phenomena occurring during the initiation and development of material damage. The study and analysis of the energy-absorbing properties of the titanium alloy Ti6Al4V layer structure under dynamic impact loading using a drop-weight impact tester revealed that:

•
The character of the resulting damage takes the form of petaling; a similar mechanism was achieved by simulation.

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The maximum values of absorbed energy are 84 J for a single plate, 205 J for two plates, and 325 J for three plates.

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The absorbed energy increase during the puncture of two or three layers of titanium sheets is not an exact multiple of the energy measured for a single sheet. It is probable the cause of the discrepancy is the friction between the layers of material.

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The temperature values obtained from the puncture simulation of the titanium alloy samples are 287.3 K for one layer, 385.7 K for two layers, and 393 K for three layers. A slight difference in the maximum temperature between two and three layers can be seen. Despite this, the value continues to rise.

•
The maximum force values for damage initiation are 5.33 kN for a single plate, 11.85 kN for two plates, and 21.2 kN for three plates.
The study of simple multi-layer structures of Ti6Al4V titanium alloy consisting of sheet metal is an introduction to the behavior of polymer-titanium and polymeric-glass-

Conclusions
The application of a drop-weight tester equipped with a conical striker allowed evaluation of the energy-absorbing properties of Ti6al4V titanium alloy sheets and allowed us to analyze phenomena occurring during the initiation and development of material damage. The study and analysis of the energy-absorbing properties of the titanium alloy Ti6Al4V layer structure under dynamic impact loading using a drop-weight impact tester revealed that:

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The character of the resulting damage takes the form of petaling; a similar mechanism was achieved by simulation.

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The maximum values of absorbed energy are 84 J for a single plate, 205 J for two plates, and 325 J for three plates.

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The absorbed energy increase during the puncture of two or three layers of titanium sheets is not an exact multiple of the energy measured for a single sheet. It is probable the cause of the discrepancy is the friction between the layers of material.

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The temperature values obtained from the puncture simulation of the titanium alloy samples are 287.3 K for one layer, 385.7 K for two layers, and 393 K for three layers. A slight difference in the maximum temperature between two and three layers can be seen. Despite this, the value continues to rise.

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The maximum force values for damage initiation are 5.33 kN for a single plate, 11.85 kN for two plates, and 21.2 kN for three plates.
The study of simple multi-layer structures of Ti6Al4V titanium alloy consisting of sheet metal is an introduction to the behavior of polymer-titanium and polymeric-glasstitanium composites. In further analyses, titanium alloy glue connection can be tested, using reinforcement in the form of glass or carbon fiber.