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. 2020 Feb 19;29:105306. doi: 10.1016/j.dib.2020.105306

Load-displacement experimental data from axial tensile loading of CFRP-SPCC hybrid laminates

Muhammad Akhsin Muflikhun a,∗, Alvin Y Chua b
PMCID: PMC7058899  PMID: 32154344

Abstract

The current paper shows a data set of load-displacement output from axial tensile loading of CFRP-SPCC hybrid laminates. The specimen geometries are cut based on standard procedure from ASTM D-3039. At least 3 positions in each specimen, we measured its width and thickness. Data of the load and displacement were repeated at least 3 samples in each combination of hybrid laminates. Tensile test was conducted with a 1 mm/min of loading rate. The data were recorded from unloading until failure of specimens. The data gives information about the highest load and the behavior of load-displacement in axial tensile loading. By using width and thickness, normalized data can be obtained, the load can be calculated into stress (MPa) unit. The data are useful for researchers and structural engineers that deals with CFRP, SPCC, and hybrid CFRP-SPCC laminates.

Keywords: Tensile loading, Hybrid laminate, CFRP, SPCC, Load-displacement

Specifications Table

Subject Engineering
Specific subject area Hybrid material, Mechanics of composite materials, Axial tensile loading, Material properties
Type of data 1. Tables
2. Figures
How data were acquired Data were acquired from Universal Testing Machine (UTM) and the output are load-displacement value.
Data format Raw and analyzed
Parameters for data collection Raw data from UTM output are Load in Newton (N) and displacement in millimeters (mm). Additional parameter added from sample measurement such as thickness, width, and length.
Description of data collection 1. Data were formed as load - displacement tables.
2. Specimen measurement (width and thickness) was measured before the specimen being tested.
3. Material properties that obtained from tensile loading can be transformed to stress and the information can give information about material strength.
Data source location Data were obtained from the Aoki-Yokozeki lab, department of Aeronautics and Astronautics, The University of Tokyo, Japan.
Data accessibility With the article
Related research article The data are related to two previous research papers:
1. https://doi.org/10.1016/j.compstruct.2019.03.094
2. https://doi.org/10.1016/j.compositesb.2019.05.049
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Value of the Data
  • •

    The data presented in the current study provide a complete material performance during axial tensile loading of CFRP laminates and hybrid laminates.

  • •

    The data can be used by designers, engineers, and scientists to predict the material strength, and maximum load of CFRP, SPCC, and CFRP-SPCC hybrid laminates.

  • •

    The data of CFRP-SPCC hybrid laminate can be used in several fields such as structural applications (buildings, bridges, towers) and automotive industries.

  • •

    Since load-displacement is raw data, data processing can be done with different purposes to obtain material strength, stiffness, and ABD matrixes of hybrid laminates.

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1. Data description

Comprehensive raw data of load-displacement values are available in the appendix. The data consist of specimens with several CFRPs and SPCCs can be seen in Table 1. Detailed dimension of all specimens can be seen in Table 2. Load-displacement of SPCC plate is shown in Fig. 1. Load-displacement of CFRP laminates with sequences of [0]4 can be seen in Fig. 2. Furthermore, for [0]2 CFRP laminate, load-displacement curves are illustrated in Fig. 3. The load-displacement performance of [90]4 and [±45]S CFRP laminates are displayed in Figs. 4 and 5, respectively.

Table 1.

List of specimens.

No. Layups Number of layers
CFRP SPCC
1 SPCC 0 1
2 [0]4 4 0
3 [0]2 2 0
4 [90]4 4 0
5 [±45]S 4 0
6 [SPCC/0]S 2 2
7 [SPCC/0/0]S 4 2
8 [0/0/SPCC/0/0] 4 1
9 [±45/0]S 6 0
10 [0/0/90/90]S 8 0
11 [SPCC/±45/0]S 6 2
12 [SPCC/0/±45]S 6 2
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Table 2.

Dimension of all specimens.

No. Specimen Width (mm) Mean Width (mm) Thickness (mm) Mean Thickness (mm)
1 SPCC-01 13.95 13.9667 0.804 0.8013
13.95 0.802
14 0.798
2 SPCC-02 14.15 14.2000 0.8 0.7990
14.25 0.798
14.2 0.799
3 SPCC-03 14.1 14.2167 0.802 0.8010
14.25 0.801
14.3 0.8
4 SPCC-04 14.2 14.0333 0.805 0.8043
14 0.804
13.9 0.804
5 SPCC-05 13.5 13.5333 0.802 0.8017
13.5 0.802
13.6 0.801
6 SPCC-06 15.1 15.1000 0.801 0.8023
15.1 0.805
15.1 0.801
7 [0]4-01 14.3 14.4500 0.667 0.6723
14.35 0.679
14.7 0.671
8 [0]4-02 13.85 13.9667 0.648 0.6467
13.95 0.65
14.1 0.642
9 [0]4-03 14.35 14.5000 0.664 0.6643
14.5 0.673
14.65 0.656
10 [0]4-04 14.4 14.3500 0.66 0.6697
14.35 0.698
14.3 0.651
11 [0]2-01 14.9 15.0000 0.32 0.3447
15 0.378
15.1 0.336
12 [0]2-02 13.4 13.4167 0.354 0.3563
13.55 0.345
13.3 0.37
13 [0]2-03 14.55 14.8667 0.34 0.3537
14.9 0.363
15.15 0.358
14 [90]4-01 15.25 15.2500 0.653 0.6623
15.4 0.676
15.1 0.658
15 [90]4-02 15.55 15.6667 0.657 0.6583
15.7 0.662
15.75 0.656
16 [90]4-03 15.05 15.1167 0.669 0.6670
15.1 0.663
15.2 0.669
17 [±45]S-01 14.1 14.1833 0.695 0.6850
14.2 0.687
14.25 0.673
18 [±45]S-02 15.5 15.4833 0.645 0.6320
15.5 0.642
15.45 0.609
19 [±45]S-03 15.65 15.9333 0.615 0.6230
16.6 0.625
15.55 0.629
20 [SPCC/0]S-01 15.2 15.0000 1.893 1.8933
15 1.9
14.8 1.887
21 [SPCC/0]S-02 14.8 14.5500 1.92 1.9010
14.6 1.899
14.25 1.884
22 [SPCC/0]S-03 14.55 14.6333 1.902 1.8850
14.65 1.881
14.7 1.872
23 [SPCC/0/0]S-01 15 14.8667 2.208 2.1810
14.9 2.168
14.7 2.167
24 [SPCC/0/0]S-02 15.05 14.8167 2.169 2.1823
14.85 2.176
14.55 2.202
25 [SPCC/0/0]S-03 15.5 15.2833 2.19 2.1973
15.35 2.197
15 2.205
26 [0/0/SPCC/0/0]-01 14.65 14.7500 1.442 1.4420
14.75 1.444
14.85 1.44
27 [0/0/SPCC/0/0]-02 14.8 14.9667 1.444 1.4473
14.95 1.457
15.15 1.441
28 [0/0/SPCC/0/0]-03 14.2 14.2500 1.443 1.4573
14.2 1.467
14.35 1.462
29 [±45/0]S-01 14 13.9167 0.957 0.9553
13.9 0.967
13.85 0.942
30 [±45/0]S-02 14.2 14.1833 0.943 0.9540
14.1 0.951
14.25 0.968
31 [±45/0]S-03 14 14.0000 0.957 0.9697
14 0.969
14 0.983
32 [±45/0]S-04 12.35 12.2833 0.975 0.9810
12.3 0.99
12.2 0.978
33 [0/0/90/90]S-01 14.2 14.2500 1.302 1.2990
14.25 1.303
14.3 1.292
34 [0/0/90/90]S-02 14.3 14.3167 1.308 1.3127
14.35 1.308
14.3 1.322
35 [0/0/90/90]S-03 14.35 14.3500 1.306 1.3097
14.35 1.315
14.35 1.308
36 [SPCC/±45/0]S-01 15.55 15.4500 2.59 2.5750
15.4 2.567
15.4 2.568
37 [SPCC/±45/0]S-02 13.65 13.5667 2.566 2.5813
13.55 2.597
13.5 2.581
38 [SPCC/±45/0]S-03 14.5 14.5000 2.557 2.5647
14.5 2.598
14.5 2.539
39 [SPCC/±45/0]S-04 14.05 14.5667 2.51 2.5033
15 2.501
14.65 2.499
40 [SPCC/0/±45]S-01 14.7 14.6667 2.583 2.5937
14.55 2.6
14.75 2.598
41 [SPCC/0/±45]S-02 12.75 12.7833 2.589 2.5940
12.85 2.593
12.75 2.6
42 [SPCC/0/±45]S-03 12.85 12.8667 2.617 2.5940
12.85 2.55
12.9 2.615
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Fig. 1.

Fig. 1

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Load-displacement of SPCC plates.

Fig. 2.

Fig. 2

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Load-displacement of [0]4 CFRP laminates.

Fig. 3.

Fig. 3

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Load-displacement of [0]2 CFRP laminates.

Fig. 4.

Fig. 4

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Load-displacement of [90]4 CFRP laminates.

Fig. 5.

Fig. 5

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Load-displacement of [±45]S CFRP laminates.

For hybrid laminates that consist of SPCC and 0°-layer of CFRP laminate are presented in Fig. 6, Fig. 7, Fig. 8 with the sequences of [SPCC/0]S, [SPCC/0/0]S, and [0/0/SPCC/0/0]. Moreover, for combination of 0°-layer and non 0°-layer of CFRP, Fig. 9 with 4 specimens, shows load-displacement curves of [±45/0]S. Fig. 10 shows the load-displacement performance of [0/0/90/90]S. For the last two different combinations, load-displacement curves can be seen in Figs. 11 and 12 with [SPCC/±45/0]S, and [SPCC/0/±45]S hybrid CFRP-SPCC laminates.

Fig. 6.

Fig. 6

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Load-displacement of [SPCC/0]S CFRP-SPCC hybrid laminates.

Fig. 7.

Fig. 7

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Load-displacement of [SPCC/0/0]S CFRP-SPCC hybrid laminates.

Fig. 8.

Fig. 8

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Load-displacement of [0/0/SPCC/0/0] CFRP-SPCC hybrid laminates.

Fig. 9.

Fig. 9

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Load-displacement of [±45/0]S CFRP laminates.

Fig. 10.

Fig. 10

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Load-displacement of [0/0/90/90]S CFRP laminates.

Fig. 11.

Fig. 11

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Load-displacement of [SPCC/±45/0]S CFRP-SPCC hybrid laminates.

Fig. 12.

Fig. 12

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Load-displacement of [SPCC/0/±45]S CFRP-SPCC hybrid laminates.

2. Experimental design, materials, and methods

2.1. Specimen preparation and test

The steel used in the research is called Steel Plate Cold Commercial (SPCC), or equivalent to JIS G 3141 with 0.8 mm of thickness. SPCC commonly used in structures applications and automobile parts [1]. Prepreg CFRP T800 from Toray Industries Inc. were manufactured alongside with SPCC directly by using hand lay-up technique. Curing process were used hot press machine with 130 °C for 3 h in room temperature condition (25 °C) to ensure all resin completely cured. The specimen then cut based on ASTM D3039 by using cutting machine. Fig. 13 show materials used in the study, hot press machine for curing process, and cutting machine to cut the specimens.

Fig. 13.

Fig. 13

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(a) SPCC plate, (b) Prepreg CFRP, (c) Hot press machine, and (d) Cutting machine.

The steel used in this research is called Steel Plate Cold Commercial (SPCC), or equivalent to JIS G 3141 with 0.8 mm of thickness. SPCC is commonly used in structures applications and automobile parts [1]. Prepreg CFRP T800 from Toray Industries, Inc. were manufactured alongside with SPCC directly by using hand lay-up technique. Curing process was done by using hot-press machine with 130 °C for 3 h to ensure all resin completely cured. After curing, cutting process, sample preparations and testing were done in the room temperature (25 °C). The specimens were then cut based on ASTM D3039 by using cutting machine. Fig. 13 show materials used in the study, hot press machine for curing process, and cutting machine to cut the specimens.

Before testing specimens, they were attached to 0.5 mm of aluminium tab with 40–50 mm length at both ends. The detailed specimen's dimension can be seen in Fig. 14 where t is the specimen thickness (mm), w is specimen width (mm), c is tab length (45 mm), l is total specimen length (200 mm). Data of specimen thickness and width are shown in Table 2. At least 3 different positions were required to measure specimen thickness and width. The detailed measurement method is illustrated in Fig. 15. Tensile test was conducted by using an Instron servo-hydraulic Universal Testing Machine (UTM) 8802. During tensile loading, load-displacement were recorded automatically until the failure of specimens. To investigate the condition of side surface of laminates during tensile loading, a Dino-Lite optical microscope was used. Detailed experimental setup is shown in Fig. 16.

Fig. 14.

Fig. 14

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Specimen dimension [2].

Fig. 15.

Fig. 15

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Specimen spots for thickness and width measurement.

Fig. 16.

Fig. 16

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Experimental setup.

2.2. Note from the experiment

  • •

    To increase the bonding strength between CFRP and SPCC, sandpaper P120 can be used to increase SPCC surface roughness.

  • •

    After sandpaper applied, ethanol was used with a clean tissue to remove all debris and SPCC tiny residual object from the SPCC surface. Make sure to clean all the surface and remove all the pollutants.

  • •

    To avoid pollutant attached on the material surface and hands, lab gloves can be used.

  • •

    Placed specimen in the hot press machine before the machine is started.

  • •

    Use heat resistance gloves to remove the specimen from hot press machine.

  • •

    Do not directly cut the sample while the sample is not properly cool and still in cooling process. At least wait 4 h to make sure the sample is properly cured and cool.

  • •

    Carefully to use cutting machine. Make sure to use gloves and lab glasses to protect the eyes.

  • •

    Keep distance during tensile loading is in progress since the delamination of CFRP may cause injury since it usually forms as sharp debris.

Acknowledgments

The authors would like to thank Prof. Takahira Aoki, and Prof. Tomohiro Yokozeki for the chance to conduct research in their lab and Ms. Kobayashi for helping and assist author during experimental process. Authors also thank Siwat Manomaisantiphap for reviewing manuscript and AUN SEED NET JICA scholarship for the funding.

Footnotes

Appendix A

Supplementary data to this article can be found online at https://doi.org/10.1016/j.dib.2020.105306.

Conflict of Interest

The authors declare that they have no known competing financial interests or personal relationships that could have appeared to influence the work reported in this paper.

Appendix A. Supplementary data

The following are the Supplementary data to this article:

Multimedia component 1
mmc1.xlsx (7.6MB, xlsx)
Multimedia component 2
mmc2.xml (307B, xml)

References

  • 1.Muflikhun M.A., Higuchi R., Yokozeki T., Aoki T. Failure mode analysis of CFRP-SPCC hybrid thin laminates under axial loading for structural applications : experimental research on strain performance. Compos. Part B. 2019;172:262–270. [Google Scholar]
  • 2.Muflikhun M.A., Yokozeki T., Aoki T. The strain performance of thin CFRP-SPCC hybrid laminates for automobile structures. Compos. Struct. 2019;220:11–18. [Google Scholar]

Associated Data

This section collects any data citations, data availability statements, or supplementary materials included in this article.

Supplementary Materials

Multimedia component 1
mmc1.xlsx (7.6MB, xlsx)
Multimedia component 2
mmc2.xml (307B, xml)

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