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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
WHULANZA2,*
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
Received: 7 July 2023/Accepted: 15 February 2024
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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*Corresponding author; email: yudan.whulanza@ui.ac.id
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