Sains Malaysiana 53(3)(2024): 691-704

http://doi.org/10.17576/jsm-2024-5303-16

Investigation of Thermomechanical Analysis of Carbon/Epoxy Composite for Spacecraft Structure Material

(Penelitian Analisis Termomekanik Komposit Karbon/Epoksi untuk Bahan Struktur Kapal Angkasa)

MAHFUD IBADI¹, HERRY PURNOMO¹, DAVID NATANAEL VICARNELTOR¹, HERI BUDI WIBOWO¹, MUHAMAD HANANUPUTRA SETIANTO¹ & YUDAN WHULANZA^2,*

¹Aeronautics and Spaces Research Organization, National Research and Innovation Agency (BRIN), West Java, Indonesia

²Department of Mechanical Engineering, Faculty of Engineering, Universitas Indonesia, West Java, Indonesia

Diserahkan: 7 Julai2023/Diterima: 15 Februari2024

Abstract

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 thermo-mechanical 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 thermo-mechanical 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.

Keywords: Carbon/epoxy composite; failure behavior; spacecraft structures; thermomechanical

Abstrak

Bahan komposit ringan dan berkekuatan tinggi adalah penting untuk struktur kapal angkasa yang memerlukan bahan dengan ciri yang dikehendaki. Bahan komposit karbon/epoksi mempamerkan sifat cemerlang untuk aplikasi ruang angkasa. Penelitian ini adalah sebahagian daripada kajian tentang sifat termo-mekanikal bahan komposit menggunakan gentian karbon, manakala matriks yang digunakan ialah epoksi LY-5052 yang dibuat melalui teknik infusi vakum. Untuk mendapatkan komposit terbaik dari segi sifat, tingkah laku termo-mekanikal dijalankan dengan melakukan beberapa ujian, antaranya pengukuran Kekonduksian Termal dan analisis termogravimetrik (TGA) dan yang paling penting ialah menjalankan ujian tegangan dengan variasi suhu daripada suhu bilik hingga 200 °C. Ini dilakukan kerana kebanyakan ujian tegangan pada komposit karbon/epoksi dijalankan pada keadaan suhu bilik. Keputusan yang diperoleh daripada pengukuran kekonduksian terma komposit karbon/epoksi ialah 0.419 W/mK daripada Analisis Termogravimetrik (TGA) komposit karbon/epoksi mula terurai pada suhu 365.63 °C dan ujian tegangan dijalankan, keluar serentak dengan variasi suhu daripada suhu bilik, 50 °C, 100 °C, 150 °C dan 200 °C masing-masing mempunyai kekuatan tegangan 553, 507, 340, 266 dan 242 MPa. Trend ini mengesahkan bahawa kekuatan berkurangan dengan beban suhu yang lebih tinggi. Beberapa pemerhatian imej juga dibentangkan dalam laporan ini untuk mendapatkan pemahaman tentang tingkah laku kegagalan bahan komposit pada pelbagai suhu ini.

Kata kunci: Komposit karbon/epoksi; struktur kapal angkasa; termomekanikal; tingkah laku kegagalan

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*Pengarang untuk surat-menyurat; email: yudan.whulanza@ui.ac.id