Manufacturing ZrB<sub>2</sub>–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element Model
This study presents a new ultra-high temperature composite fabricated by using zirconium diboride (ZrB<sub>2</sub>), silicon carbide (SiC), and tantalum carbide (TaC) with the volume ratios of 70%, 20%, and 10%, respectively. To attain this novel composite, an advanced processing techniq...
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doaj-d18b1a5917464985a1664ec555c202572020-11-25T02:31:33ZengMDPI AGMaterials1996-19442020-05-01132213221310.3390/ma13102213Manufacturing ZrB<sub>2</sub>–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element ModelBehzad Mohammadzadeh0Sunghoon Jung1Tae Hyung Lee2Quyet Van Le3Joo Hwan Cha4Ho Won Jang5Sea-Hoon Lee6Junsuk Kang7Mohammadreza Shokouhimehr8Department of Landscape Architecture and Rural Systems Engineering, Seoul National University, Seoul 08826, KoreaDepartment of Materials Science and Engineering, Research Institute of Advanced Materials, Seoul National University, Seoul 08826, KoreaDepartment of Materials Science and Engineering, Research Institute of Advanced Materials, Seoul National University, Seoul 08826, KoreaInstitute of Research and Development, Duy Tan University, Da Nang 550000, VietnamInnovative Enterprise Cooperation Center, Korea Institute of Science & Technology, Hwarangro 14-gil, Seongbuk-gu, Seoul, KoreaDepartment of Materials Science and Engineering, Research Institute of Advanced Materials, Seoul National University, Seoul 08826, KoreaDivision of Powder/Ceramics Research, Korea Institute of Materials Science, Changwon 51508, KoreaDepartment of Landscape Architecture and Rural Systems Engineering, Seoul National University, Seoul 08826, KoreaDepartment of Materials Science and Engineering, Research Institute of Advanced Materials, Seoul National University, Seoul 08826, KoreaThis study presents a new ultra-high temperature composite fabricated by using zirconium diboride (ZrB<sub>2</sub>), silicon carbide (SiC), and tantalum carbide (TaC) with the volume ratios of 70%, 20%, and 10%, respectively. To attain this novel composite, an advanced processing technique of spark plasma sintering (SPS) was applied to produce ZrB<sub>2</sub>–SiC–TaC. The SPS manufacturing process was achieved under pressure of 30 MPa, at 2000 °C for 5 min. The micro/nanostructure and mechanical characteristics of the composite were clarified using X-ray diffraction (XRD), field-emission scanning electron microscopy (FESEM), and nano-indentation. For further investigations of the product and its characteristics, X-ray fluorescence (XRF) analysis and X-ray photoelectron spectroscopy (XPS) were undertaken, and the main constituting components were provided. The composite was densified to obtain a fully-dense ternary; the oxide pollutions were wiped out. The mean values of 23,356; 403.5 GPa; and 3100 °C were obtained for the rigidity, elastic modulus, and thermal resistance of the ZrB<sub>2</sub>–SiC–TaC interface, respectively. To explore the practical application of the composite, the natural frequency of an aircraft wing considering three cases of materials: i) with a leading edge made of ZrB<sub>2</sub>–SiC–TaC; ii) the whole wing made of ZrB<sub>2</sub>–SiC–TaC; and iii) the whole wing made of aluminum 2024-T3 were investigated employing a numerical finite element model (FEM) tool ABAQUS and compared with that of a wing of traditional materials. The precision of the method was verified by performing static analysis to obtain the responses of the wing including total deformation, equivalent stress, and strain. A comparison study of the results of this study and published literature clarified the validity of the FEM analysis of the current research. The composite produced in this study significantly can improve the vibrational responses and structural behavior of the aircraft’s wings.https://www.mdpi.com/1996-1944/13/10/2213Ultra-high temperature ceramicspark plasma sinteringnano-indentationcompositevibration analysisFEM analysis |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Behzad Mohammadzadeh Sunghoon Jung Tae Hyung Lee Quyet Van Le Joo Hwan Cha Ho Won Jang Sea-Hoon Lee Junsuk Kang Mohammadreza Shokouhimehr |
spellingShingle |
Behzad Mohammadzadeh Sunghoon Jung Tae Hyung Lee Quyet Van Le Joo Hwan Cha Ho Won Jang Sea-Hoon Lee Junsuk Kang Mohammadreza Shokouhimehr Manufacturing ZrB<sub>2</sub>–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element Model Materials Ultra-high temperature ceramic spark plasma sintering nano-indentation composite vibration analysis FEM analysis |
author_facet |
Behzad Mohammadzadeh Sunghoon Jung Tae Hyung Lee Quyet Van Le Joo Hwan Cha Ho Won Jang Sea-Hoon Lee Junsuk Kang Mohammadreza Shokouhimehr |
author_sort |
Behzad Mohammadzadeh |
title |
Manufacturing ZrB<sub>2</sub>–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element Model |
title_short |
Manufacturing ZrB<sub>2</sub>–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element Model |
title_full |
Manufacturing ZrB<sub>2</sub>–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element Model |
title_fullStr |
Manufacturing ZrB<sub>2</sub>–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element Model |
title_full_unstemmed |
Manufacturing ZrB<sub>2</sub>–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element Model |
title_sort |
manufacturing zrb<sub>2</sub>–sic–tac composite: potential application for aircraft wing assessed by frequency analysis through finite element model |
publisher |
MDPI AG |
series |
Materials |
issn |
1996-1944 |
publishDate |
2020-05-01 |
description |
This study presents a new ultra-high temperature composite fabricated by using zirconium diboride (ZrB<sub>2</sub>), silicon carbide (SiC), and tantalum carbide (TaC) with the volume ratios of 70%, 20%, and 10%, respectively. To attain this novel composite, an advanced processing technique of spark plasma sintering (SPS) was applied to produce ZrB<sub>2</sub>–SiC–TaC. The SPS manufacturing process was achieved under pressure of 30 MPa, at 2000 °C for 5 min. The micro/nanostructure and mechanical characteristics of the composite were clarified using X-ray diffraction (XRD), field-emission scanning electron microscopy (FESEM), and nano-indentation. For further investigations of the product and its characteristics, X-ray fluorescence (XRF) analysis and X-ray photoelectron spectroscopy (XPS) were undertaken, and the main constituting components were provided. The composite was densified to obtain a fully-dense ternary; the oxide pollutions were wiped out. The mean values of 23,356; 403.5 GPa; and 3100 °C were obtained for the rigidity, elastic modulus, and thermal resistance of the ZrB<sub>2</sub>–SiC–TaC interface, respectively. To explore the practical application of the composite, the natural frequency of an aircraft wing considering three cases of materials: i) with a leading edge made of ZrB<sub>2</sub>–SiC–TaC; ii) the whole wing made of ZrB<sub>2</sub>–SiC–TaC; and iii) the whole wing made of aluminum 2024-T3 were investigated employing a numerical finite element model (FEM) tool ABAQUS and compared with that of a wing of traditional materials. The precision of the method was verified by performing static analysis to obtain the responses of the wing including total deformation, equivalent stress, and strain. A comparison study of the results of this study and published literature clarified the validity of the FEM analysis of the current research. The composite produced in this study significantly can improve the vibrational responses and structural behavior of the aircraft’s wings. |
topic |
Ultra-high temperature ceramic spark plasma sintering nano-indentation composite vibration analysis FEM analysis |
url |
https://www.mdpi.com/1996-1944/13/10/2213 |
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