Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material
When building spacecraft structures, it is crucial to use lightweight and high-strength composite materials with the necessary characteristics. Aerospace applications benefit significantly from the exceptional properties of carbon/ epoxy composite materials. As part of a study on composite materials...
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Penerbit Universiti Kebangsaan Malaysia
2024
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my-ukm.journal.237552024-07-02T07:56:35Z http://journalarticle.ukm.my/23755/ Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material Ibadi, Mahfud Purnomo, Herry Vicarneltor, David Natanael Wibowo, Heri Budi Setianto, Muhamad Hananuputra Whulanza, Yudan When building spacecraft structures, it is crucial to use lightweight and high-strength composite materials with the necessary characteristics. Aerospace applications benefit significantly from the exceptional properties of carbon/ epoxy composite materials. As part of a study on composite materials, this work focuses on exploring the thermomechanical properties of carbon fiber. The matrix used in this research is LY-5052 epoxy, applied through a vacuum infusion technique. To achieve optimal composite properties, various tests are conducted to evaluate its thermomechanical behavior. These tests may include measuring Thermal Conductivity and performing thermogravimetric analysis (TGA). Most importantly, the composite is subjected to tensile testing at room temperature to 200 °C. This is done because most tensile tests on carbon/LY5052 composites are carried out at room temperature. The results obtained from the measurement of the thermal conductivity of the carbon/LY5052 composite were 0.419 W/mK; from the Thermogravimetric Analysis (TGA), the carbon/LY5052 composite began to decompose at a temperature of 365.63 °C and the tensile test was carried out simultaneously with variations in temperature from room temperature, 50 °C, 100 °C, 150 °C and 200 °C have tensile strengths of 553, 507, 340, 266, and 242 MPa, respectively. This trend confirms that strength decreases with higher temperature loads. Several image observations are also presented in this report to understand composite materials’ failure behavior at these various temperatures. Penerbit Universiti Kebangsaan Malaysia 2024 Article PeerReviewed application/pdf en http://journalarticle.ukm.my/23755/1/SMT%2016.pdf Ibadi, Mahfud and Purnomo, Herry and Vicarneltor, David Natanael and Wibowo, Heri Budi and Setianto, Muhamad Hananuputra and Whulanza, Yudan (2024) Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material. Sains Malaysiana, 53 (3). pp. 691-704. ISSN 0126-6039 https://www.ukm.my/jsm/english_journals/vol53num3_2024/contentsVol53num3_2024.html |
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When building spacecraft structures, it is crucial to use lightweight and high-strength composite materials with the necessary characteristics. Aerospace applications benefit significantly from the exceptional properties of carbon/ epoxy composite materials. As part of a study on composite materials, this work focuses on exploring the thermomechanical properties of carbon fiber. The matrix used in this research is LY-5052 epoxy, applied through a vacuum infusion technique. To achieve optimal composite properties, various tests are conducted to evaluate its thermomechanical behavior. These tests may include measuring Thermal Conductivity and performing thermogravimetric analysis (TGA). Most importantly, the composite is subjected to tensile testing at room temperature to 200 °C. This is done because most tensile tests on carbon/LY5052 composites are carried out at room temperature. The results obtained from the measurement of the thermal conductivity of the carbon/LY5052 composite were 0.419 W/mK; from the Thermogravimetric Analysis (TGA), the carbon/LY5052 composite began to decompose at a temperature of 365.63 °C and the tensile test was carried out simultaneously with variations in temperature from room temperature, 50 °C, 100 °C, 150 °C and 200 °C have tensile strengths of 553, 507, 340, 266, and 242 MPa, respectively. This trend confirms that strength decreases with higher temperature loads. Several image observations are also presented in this report to understand composite materials’ failure behavior at these various temperatures. |
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Ibadi, Mahfud Purnomo, Herry Vicarneltor, David Natanael Wibowo, Heri Budi Setianto, Muhamad Hananuputra Whulanza, Yudan |
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Ibadi, Mahfud Purnomo, Herry Vicarneltor, David Natanael Wibowo, Heri Budi Setianto, Muhamad Hananuputra Whulanza, Yudan Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material |
author_facet |
Ibadi, Mahfud Purnomo, Herry Vicarneltor, David Natanael Wibowo, Heri Budi Setianto, Muhamad Hananuputra Whulanza, Yudan |
author_sort |
Ibadi, Mahfud |
title |
Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material |
title_short |
Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material |
title_full |
Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material |
title_fullStr |
Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material |
title_full_unstemmed |
Investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material |
title_sort |
investigation of thermomechanical analysis of carbon/epoxy composite for spacecraft structure material |
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Penerbit Universiti Kebangsaan Malaysia |
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2024 |
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http://journalarticle.ukm.my/23755/1/SMT%2016.pdf http://journalarticle.ukm.my/23755/ https://www.ukm.my/jsm/english_journals/vol53num3_2024/contentsVol53num3_2024.html |
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