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Experiment and analysis of mechanical properties of carbon fiber composite laminates under impact compression

  • Kang Yang , Li Yang , Peng Gong EMAIL logo , Liguo Zhang , Yumei Yue and Qunfang Li
Published/Copyright: March 16, 2022
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e-Polymers
From the journal e-Polymers Volume 22 Issue 1

Abstract

Composite materials are more and more widely used in aircraft structural design, and impact damage is the most serious defect/damage form of aviation composite structures in service. Therefore, it is of great significance to study the impact resistance of composites with different materials and structural forms for aircraft structural design. In this article, the damage of reinforced fiber/resin composite laminates with unidirectional carbon fiber prepreg (UIN23100), carbon fiber woven fabric (W-3021FF), and carbon fiber-aramid fiber blended fabric (W-38211) under the same impact energy were studied. The impact damage area was scanned and analyzed by ultrasonic C-scan, and the impact resistance of the three laminates were obtained. Finally, the compression bearing capacity of carbon fiber laminates after impact was tested, and the compression failure mode of each material has been analyzed. The results show that the impact resistance of carbon fiber unidirectional prepreg was stronger than that of carbon fiber woven fabric; the compression bearing capacity of carbon fiber laminate after impact was higher than that of carbon fiber unidirectional prepreg; the post impact bearing capacity of W-38211 was higher than that of W-3021FF.

Keywords: composite; impact; compression bearing; ultrasonic C-scan; mechanical properties

1 Introduction

With the gradual opening of domestic low airspace, the number of general aircrafts which used composite materials is increasing year by year (1). Due to the limitation of weight, in the process of structural lightweight design, the requirements for mechanical properties of materials are higher and higher, especially for the selection of carbon fiber composite materials (2,3,4). Carbon fiber reinforced polymers (CFRP) have been widely used in aerospace, automobile, wind power generation, and other fields due to its designability, high specific strength, and low production cost (5,6,7). Pengcheng (2) tested the tensile fracture interface shear strength and short beam shear properties of carbon fiber resin-based materials under electric heating. The results show that the tensile fracture interface shear strength of single fiber and short beam first increases and then decreases with the increase in the electric current strength. Xiaojun (3) studied the influence of different hygrothermal aging environment on the mechanical properties of carbon fiber/epoxy resin matrix composites, and proved that the mechanical properties of the composites decreased significantly after soaking in water at 80°C. The influence of medium components on the composites was not obvious at low temperature, and the static mechanical properties of the composites were destroyed significantly after soaking in water at 80°C. Xudong et al. (4) used the finite element software ABAQUS as the modeling and calculation platform and applied Python language programming to predict the mechanical properties of fiber-reinforced composites with different properties of fiber, matrix material, different fiber volume fraction contents, different fiber laying angles, and different loading directions.

In the process of flight and landing, the aircraft will inevitably be affected by dynamic loads such as impact and vibration. Under the action of dynamic loads, the composite structure may suffer some local damage. Delamination is the main damage mode of composite structures under low energy impact (8,9,10,11,12,13,14), so it has become the focus of relevant researchers to study the influence of local damage of composite materials on the mechanical properties of structural parts, and compression after impact (CAI) test is one of the main methods to evaluate the residual bearing capacity of composite materials. Chong et al. (15) designed a new test fixture in order to prevent the instability of the thin plate in the impact compression test. Yao et al. (16) studied the compression bearing capacity and failure mode of carbon fiber/epoxy resin matrix composites after three kinds of impact energy and measured the repair efficiency of single bolt on the compression bearing capacity of laminates. Amaro et al. (14) carried out compression experiments on orthotropic laminated plates with different damage degrees, and obtained three different failure modes, which were local buckling, global buckling, and the failure mode of coupling local buckling and global buckling. The compression failure of laminates usually appears from the local buckling in the delamination region, and then the delamination propagates along the vertical load direction until the structural failure. Sun and Hallett (17) used the three-dimensional digital image correlation technology to obtain the full field out of plane displacement information in the process of CAI test, described the detailed failure process of CAI laminates, and concluded that delamination buckling propagation eventually led to the failure of laminates. In this article, the impact resistance of three kinds of materials have been obtained by impact test and ultrasonic C-scan. Finally, the CAI test of CFRP laminates has been carried out, and the compression failure mode of each material was used for analysis. The test data and analysis results can provide some reference for the related composite structure designers.

2 Experimental method

2.1 Preparation of specimens

Specimens include three kinds of materials, reinforced fiber/resin composite laminates with unidirectional carbon fiber prepreg (UIN23100), carbon fiber woven fabric (W-3021FF), and carbon fiber-aramid fiber blended fabric (W-38211) (provided by Weihai Guangwei composite material Co., Ltd, china), which adopted resin transfer molding (RTM) and the thickness was about 5 mm. The curing process and lamination of each reinforcing fiber material are shown in Table 1. The formed composite laminates were cut into 150 mm × 100 mm standard specimens by water cutting machine (LTJ1613, Shanghai Shimai Technology Co., Ltd, china) for subsequent tests, as shown in Figure 1.

Table 1

Curing process parameters and lay

Reinforcing fiber Matrix Ply direction Curing process parameters Number of specimens
UIN23100 9,314 [0]s 80°C 1 h + 120°C 1.5 h 5
W-3021FF 285/287 [0/90]s 20°C 24 h + 80°C 15 h 6
W-38211 285/287 [0/90]s 20°C 24 h + 80°C 15 h 6

s: symmetrical paving.

Figure 1 Schematic diagram of standard test piece size and impact position.
Figure 1

Schematic diagram of standard test piece size and impact position.

2.2 Experimental procedure

The ASTM D7136 standard test (18) has been used for the drop weight impact test. The support window size of the specimen was 125 mm × 75 mm, the impact object was a steel hemispherical punch, the diameter of the punch was 16 mm, the weight of the hammer was 5.5 kg, the impact energy was 6.67 J·mm−1, and the test environment temperature/humidity was 25°C/40% RH. The composite material specimens were clamped by the chuck on the edge, and the impact energy reaches 32.5 J by manually adjusting the height of the hammer. Ultrasonic C-scan (SAM300 Basic, PVA TePla, Germany) was used to characterize the damage characteristics after impact, as shown in Figure 2a.

Figure 2 Test equipment: (a) the ultrasonic C-scan, (b) the post impact compression test fixture, and (c) the static universal testing machine.
Figure 2

Test equipment: (a) the ultrasonic C-scan, (b) the post impact compression test fixture, and (c) the static universal testing machine.

The standard of the compression after impact test was ASTM D7137 (19), the compression test fixture (ASTM D7137, Wyoming Test Fixture Inc.) is shown in Figure 2b. The compression test was carried out on a static universal testing machine (Instron 5982, American), as shown in Figure 2c. The compression rate was 0.5 mm·min−1, the load was stopped when the load drops by 20%, and the temperature/humidity of the test environment was 24°C/48% RH.

3 Results and discussion

3.1 Impact damage of composite laminates

The specimen after the test is shown in Figure 3. The impact caused impact dents on the front side of the laminate, and the typical impact damage indentation is shown in Figure 4. After the impact test, the three-material composite laminates were visually inspected, and no visible damage was found on the reverse side of the impact. Then, an ultrasonic C-scan was performed on the specimen after the impact to detect the damage of the specimen under the same impact condition. Figure 5a–c shows the typical results of ultrasonic C-scan after the impact. It can be seen from the figure that the image after the impact shows a failure morphology similar to the “top hat shape.” The typical damage characteristics obtained in this study are consistent with those reported in literature (9). In addition, the dent depth of the UIN23100/9314 specimen is smaller than that of the woven fabric specimen; therefore, the ability of UIN23100/9314 specimen to absorb and transfer impact energy is stronger than that of woven fabric specimen. It can be seen that the impact resistance of the UIN23100/9314 specimen is stronger than that of the woven fabric specimen. According to the ultrasonic C-scan results of the woven fabric specimen in Fig 5b and c, the dent diameter of the W-38211/285/287 specimen is larger and the ability of absorbing and transferring impact energy is improved compared with that of the W-3021FF/285/287 specimen.

Figure 3 Test piece after test: (a) UIN23100/9314, (b) W-3021FF/285/287, and (c) W-38211/285/287.
Figure 3

Test piece after test: (a) UIN23100/9314, (b) W-3021FF/285/287, and (c) W-38211/285/287.

Figure 4 Typical impact damage indentation.
Figure 4

Typical impact damage indentation.

Figure 5 Typical results of ultrasonic C-scan after impact: (a) UIN23100/9314, (b) W-3021FF/285/287, and (c) W-38211/285/287.
Figure 5

Typical results of ultrasonic C-scan after impact: (a) UIN23100/9314, (b) W-3021FF/285/287, and (c) W-38211/285/287.

3.2 Compression capacity after impact

Tables 2–4 show the ultimate compression bearing capacity of the three-material composite laminates after impact loading. The average compressive load of UIN23100/9314, W-3021FF/285/287, and W-38211/285/287 are 82, 85, and 100 kN, and the corresponding load-bearing compressive strength is 147, 175, and 191 MPa, respectively. The results show that the compression bearing capacity of the woven fabric specimen after impact is stronger than that of the carbon fiber unidirectional prepreg specimen, while for the resin-based woven fabric material, the compression bearing capacity of the W-38211/285/287 laminate is higher than that of the W-3021FF/285/287 laminate. Figure 6a–c shows the typical failure modes of three kinds of materials in compression after impact test. It can be seen from Figure 6 that the failure cracks of three kinds of materials extend along the width direction, but not along the length direction. Because the impact on the carbon fiber unidirectional prepreg specimen caused less damage, the damage modes of the front and back of the impact are consistent, and the damage of the specimen is caused mainly by the shear failure between the fibers (Figure 6a). It can be seen from Figure 6b and c that for the woven fabric laminates, the front of the impact presents a failure morphology characterized by shear failure, with less delamination failure. On the back of the impact, a large number of spalling occurred, and the local deformation presented a “C”-shaped bulge in the same direction as the dent.

Table 2

Compressive properties of UIN23100/9314 composite laminates after impact

No. Width (mm) Thickness (mm) Maximum load (kN) Compression strength (MPa)
3-1 99.83 5.59 80.62 144
3-2 99.76 5.57 86.81 156
3-3 99.85 5.58 78.25 140
3-4 99.80 5.63 85.67 152
3-5 99.86 5.66 78.64 139
Average 99.82 5.61 82 147
Table 3

Compressive properties of W-3021FF/285/287 composite laminates after impact

No. Width (mm) Thickness (mm) Maximum load (kN) Compression strength (MPa)
4-1 100.39 5.00 83.93 167
4-2 100.39 4.85 85.17 175
4-3 100.36 4.76 87.32 183
4-4 100.27 4.76 86.53 181
4-5 100.42 4.95 79.76 160
4-6 100.30 4.89 89.25 182
Average 100.35 4.87 85 175
Table 4

Compressive properties of W-38211/285/287 composite laminates after impact

No. Width (mm) Thickness (mm) Maximum load (kN) Compression strength (MPa)
5-1 100.23 5.15 90.71 176
5-2 100.20 5.20 98.21 188
5-3 100.16 5.19 102.63 197
5-4 100.21 5.30 102.11 192
5-5 100.16 5.32 102.07 192
5-6 100.12 5.27 104.45 198
Average 100.18 5.24 100 191
Figure 6 (continued)
Figure 6 (continued)
Figure 6

(continued)

From the compression failure mode of the specimen after impact, it can be seen that after the specimen is subjected to an impact load, the local impact damage changes the symmetry of the original structure, and the neutral plane of the specimen is shifted. Under the compression load, the whole structure tends to have C-type instability, which is the main reason that the ultimate interlayer failure extends along the width direction rather than along the length direction (loading direction). The depth of the dent after impact will determine the degree of neutral plane deviation, which directly affects the compression resistance of the test piece after impact. The more serious the neutral plane deviation was, the more obvious the C-type instability trend is; therefore, according to Tables 3 and 4, the compression bearing capacity of the W-38211/285/287 laminate after impact is higher than that of the W-3021FF/285/287 laminate, which indicates that the neutral plane offset of W-38211/285/287 laminate after impact is low. Therefore, the depth of the dent of the W-38211/285/287 laminate after impact is less than that of the W-3021FF/285/287 laminate.

4 Conclusion

In this study, the impact and the compression after impact test of carbon fiber/resin composite laminates made of UIN23100/9314, W-3021FF/285/287, and W-38211/285/287 were carried out under the same impact energy, and combined with the scanning results of ultrasonic C-scan on impact failure area and the compression failure mode, the following conclusions were arrived at:

  1. Under the same impact conditions (6.67 J·mm−1), the impact resistance of carbon fiber unidirectional prepreg (UIN23100) is stronger than that of carbon fiber woven fabric (W-3021FF) and carbon fiber-aramid fiber blended fabric (W-38211).

  2. The compression bearing capacity of woven fabric after impact is stronger than that of unidirectional prepreg at the same impact energy.

  3. After the impact, the deviation of neutral plane of the W-3021FF/285/287 composite laminate is more serious than that of the W-38211/285/287 composite laminate, resulting in poorer compression bearing capacity after impact.

These authors contributed equally to this work.

  1. Funding information: This work was supported by a grant from the project of Liaoning Provincial Department of Education (JYT2020141) and the key research and service local project of Liaoning Provincial Department of Education (JYT2020156).

  2. Author contributions: Kang Yang: writing – original draft, writing – review and editing, resources, and formal analysis; Li Yang: writing – original draft, formal analysis, visualization, and project administration; Peng Gong: data curation; Liguo Zhang: supervision; Yumei Yue: formal analysis; Qunfang Li: investigation.

  3. Conflict of interest: Authors state no conflict of interest.

  4. Data availability statement: The datasets generated during and/or analyzed during the current study are available from the corresponding author on reasonable request.

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Received: 2021-12-31
Revised: 2022-02-05
Accepted: 2022-02-08
Published Online: 2022-03-16

© 2022 Kang Yang et al., published by De Gruyter

This work is licensed under the Creative Commons Attribution 4.0 International License.

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https://doi.org/10.1515/epoly-2022-0033
Keywords for this article
composite; impact; compression bearing; ultrasonic C-scan; mechanical properties
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  21. Study on the interfacial interaction between ammonium perchlorate and hydroxyl-terminated polybutadiene in solid propellants by molecular dynamics simulation
  22. Study on the self-assembly of aromatic antimicrobial peptides based on different PAF26 peptide sequences
  23. Effects of high polyamic acid content and curing process on properties of epoxy resins
  24. Experiment and analysis of mechanical properties of carbon fiber composite laminates under impact compression
  25. A machine learning investigation of low-density polylactide batch foams
  26. A comparison study of hyaluronic acid hydrogel exquisite micropatterns with photolithography and light-cured inkjet printing methods
  27. Multifunctional nanoparticles for targeted delivery of apoptin plasmid in cancer treatment
  28. Thermal stability, mechanical, and optical properties of novel RTV silicone rubbers using octa(dimethylethoxysiloxy)-POSS as a cross-linker
  29. Preparation and applications of hydrophilic quaternary ammonium salt type polymeric antistatic agents
  30. Coefficient of thermal expansion and mechanical properties of modified fiber-reinforced boron phenolic composites
  31. Synergistic effects of PEG middle-blocks and talcum on crystallizability and thermomechanical properties of flexible PLLA-b-PEG-b-PLLA bioplastic
  32. A poly(amidoxime)-modified MOF macroporous membrane for high-efficient uranium extraction from seawater
  33. Simultaneously enhance the fire safety and mechanical properties of PLA by incorporating a cyclophosphazene-based flame retardant
  34. Fabrication of two multifunctional phosphorus–nitrogen flame retardants toward improving the fire safety of epoxy resin
  35. The role of natural rubber endogenous proteins in promoting the formation of vulcanization networks
  36. The impact of viscoelastic nanofluids on the oil droplet remobilization in porous media: An experimental approach
  37. A wood-mimetic porous MXene/gelatin hydrogel for electric field/sunlight bi-enhanced uranium adsorption
  38. Fabrication of functional polyester fibers by sputter deposition with stainless steel
  39. Facile synthesis of core–shell structured magnetic Fe3O4@SiO2@Au molecularly imprinted polymers for high effective extraction and determination of 4-methylmethcathinone in human urine samples
  40. Interfacial structure and properties of isotactic polybutene-1/polyethylene blends
  41. Toward long-live ceramic on ceramic hip joints: In vitro investigation of squeaking of coated hip joint with layer-by-layer reinforced PVA coatings
  42. Effect of post-compaction heating on characteristics of microcrystalline cellulose compacts
  43. Polyurethane-based retanning agents with antimicrobial properties
  44. Preparation of polyamide 12 powder for additive manufacturing applications via thermally induced phase separation
  45. Polyvinyl alcohol/gum Arabic hydrogel preparation and cytotoxicity for wound healing improvement
  46. Synthesis and properties of PI composite films using carbon quantum dots as fillers
  47. Effect of phenyltrimethoxysilane coupling agent (A153) on simultaneously improving mechanical, electrical, and processing properties of ultra-high-filled polypropylene composites
  48. High-temperature behavior of silicone rubber composite with boron oxide/calcium silicate
  49. Lipid nanodiscs of poly(styrene-alt-maleic acid) to enhance plant antioxidant extraction
  50. Study on composting and seawater degradation properties of diethylene glycol-modified poly(butylene succinate) copolyesters
  51. A ternary hybrid nucleating agent for isotropic polypropylene: Preparation, characterization, and application
  52. Facile synthesis of a triazine-based porous organic polymer containing thiophene units for effective loading and releasing of temozolomide
  53. Preparation and performance of retention and drainage aid made of cationic spherical polyelectrolyte brushes
  54. Preparation and properties of nano-TiO2-modified photosensitive materials for 3D printing
  55. Mechanical properties and thermal analysis of graphene nanoplatelets reinforced polyimine composites
  56. Preparation and in vitro biocompatibility of PBAT and chitosan composites for novel biodegradable cardiac occluders
  57. Fabrication of biodegradable nanofibers via melt extrusion of immiscible blends
  58. Epoxy/melamine polyphosphate modified silicon carbide composites: Thermal conductivity and flame retardancy analyses
  59. Effect of dispersibility of graphene nanoplatelets on the properties of natural rubber latex composites using sodium dodecyl sulfate
  60. Preparation of PEEK-NH2/graphene network structured nanocomposites with high electrical conductivity
  61. Preparation and evaluation of high-performance modified alkyd resins based on 1,3,5-tris-(2-hydroxyethyl)cyanuric acid and study of their anticorrosive properties for surface coating applications
  62. A novel defect generation model based on two-stage GAN
  63. Thermally conductive h-BN/EHTPB/epoxy composites with enhanced toughness for on-board traction transformers
  64. Conformations and dynamic behaviors of confined wormlike chains in a pressure-driven flow
  65. Mechanical properties of epoxy resin toughened with cornstarch
  66. Optoelectronic investigation and spectroscopic characteristics of polyamide-66 polymer
  67. Novel bridged polysilsesquioxane aerogels with great mechanical properties and hydrophobicity
  68. Zeolitic imidazolate frameworks dispersed in waterborne epoxy resin to improve the anticorrosion performance of the coatings
  69. Fabrication of silver ions aramid fibers and polyethylene composites with excellent antibacterial and mechanical properties
  70. Thermal stability and optical properties of radiation-induced grafting of methyl methacrylate onto low-density polyethylene in a solvent system containing pyridine
  71. Preparation and permeation recognition mechanism of Cr(vi) ion-imprinted composite membranes
  72. Oxidized hyaluronic acid/adipic acid dihydrazide hydrogel as cell microcarriers for tissue regeneration applications
  73. Study of the phase-transition behavior of (AB)3 type star polystyrene-block-poly(n-butylacrylate) copolymers by the combination of rheology and SAXS
  74. A new insight into the reaction mechanism in preparation of poly(phenylene sulfide)
  75. Modified kaolin hydrogel for Cu2+ adsorption
  76. Thyme/garlic essential oils loaded chitosan–alginate nanocomposite: Characterization and antibacterial activities
  77. Thermal and mechanical properties of poly(lactic acid)/poly(butylene adipate-co-terephthalate)/calcium carbonate composite with single continuous morphology
  78. Review Articles
  79. The use of chitosan as a skin-regeneration agent in burns injuries: A review
  80. State of the art of geopolymers: A review
  81. Mechanical, thermal, and tribological characterization of bio-polymeric composites: A comprehensive review
  82. The influence of ionic liquid pretreatment on the physicomechanical properties of polymer biocomposites: A mini-review
  83. Influence of filler material on properties of fiber-reinforced polymer composites: A review
  84. Rapid Communications
  85. Pressure-induced flow processing behind the superior mechanical properties and heat-resistance performance of poly(butylene succinate)
  86. RAFT polymerization-induced self-assembly of semifluorinated liquid-crystalline block copolymers
  87. RAFT polymerization-induced self-assembly of poly(ionic liquids) in ethanol
  88. Topical Issue: Recent advances in smart polymers and their composites: Fundamentals and applications (Guest Editors: Shaohua Jiang and Chunxin Ma)
  89. Fabrication of PANI-modified PVDF nanofibrous yarn for pH sensor
  90. Shape memory polymer/graphene nanocomposites: State-of-the-art
  91. Recent advances in dynamic covalent bond-based shape memory polymers
  92. Construction of esterase-responsive hyperbranched polyprodrug micelles and their antitumor activity in vitro
  93. Regenerable bacterial killing–releasing ultrathin smart hydrogel surfaces modified with zwitterionic polymer brushes
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