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All Journal Transmisi: Jurnal Ilmiah Teknik Elektro Indonesian Journal of Aerospace
Budiantoro, Poki Agung
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Aerospace Engineering Astronomy Education

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RADIATOR THERMAL SEBAGAI SISTEM PENOLAK PANAS PADA SATELIT BENTUK SILINDER Fauzi, Ahmad; Budiantoro, Poki Agung
Transmisi: Jurnal Ilmiah Teknik Elektro Vol 22, No 3 Juli (2020): TRANSMISI
Publisher : Departemen Teknik Elektro, Universitas Diponegoro

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.14710/transmisi.22.3.67-72

Abstract

Panas terjadi pada satelit karena pengaruh lingkungan antariksa, khususnya sinar matahari sebagai sumber energi panel surya satelit. Panel surya menghasilkan energi yang disimpan oleh baterai satelit, yang dibutuhkan untuk operasional satelit dalam keadaan eclipse. Sinar matahari dapat menyebabkan menurunnya kinerja satelit jika energi yang dihasilkan melebihi batas kapasitas simpan daya baterai, sehingga mengancam keberlangsungan kinerja satelit. Jumlah energi yang dibutuhkan satelit dapat diatur, salah satunya dengan menganalisis bagian krusial sisi satelit. Makalah ini membahas penggunaan jumlah panas per satuan luas dari permukaaan panel satelit sebagai sistem penolak panas (radiator), yang berfungsi membuang panas berlebih yang dihasilkan oleh komponen elektronik dan radiasi dari eksternal satelit di ruang antariksa.  Kemampuan dari 4 jenis bahan sebagai termal radiator dievaluasi. Hasil studi memperlihatkan bahwa sistem penolak panas dengan bahan lapisan radiator jenis OSR Aluminium mempunyai kenaikan jumlah panas yang dibuang atau ditolak ke ruang hampa yang tinggi sebesar 143,90 W/m2 pada suhu -50°C dan 776,95 W/m2 pada suhu +50°C di musim panas (summer solstice), sedangkan jumlah panas yang dibuang ke ruang hampa dengan jumlah yang terendah terjadi pada bahan lapisan radiator jenis White Paint SG-121FD sebesar -170,68 W/m2 pada suhu -50°C dan 517,07 W/m2 pada suhu +50°C di musim dingin (winter solstice).
PRELIMINARY THERMAL CONTROL DESIGN ANALYSIS OF LAPAN SAR-MICROSATELLITE DEPLOYABLE SOLAR ARRAY PANEL USING ONE NODAL METHODE Budiantoro, Poki Agung; Fauzi, Ahmad
Indonesian Journal of Aerospace Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3155

Abstract

LAPAN SAR-Microsatellite is the first LAPAN micro satellite being developed and planned to carry a Synthetic Aperture Radar (SAR) payload. Different from optical satellites that have been developed, LAPAN SAR-Microsatellite requires a lot more power. Solar array panels are needed to generate solar radiation into electrical energy which is used by all of subsystem satellite as energy to turn on and turn off all of components. More larger the area of solar array panel, more greater to the energy obtanied. Therefore, the needed of deployable solar array panel is a must caused by the dimension of the main body structur (MBS) are not large enough. Solar cells will experience a decrease in efficiency if they experience excessive heat. If there is a decrease in efficiency in the solar cell, it will have an impact on the decrease in power produced. The purpose of this study is to conduct thermal design on solar panels to maintain temperature according to their working temperature. Calculations are carried out on the temperature of solar array panel with various optical properties in the upper and lower panel that best which will be use using one nodal analysis methode According to the calculation result from all of the designs passive thermal control system on this study show that Design-5 is the best thermal control design which can be used for LAPAN SAR-microsatellite deployable solar array panel which α=0.24 at the top and ε=0.9 at the bottom surface of solar array panel.
FINITE ELEMENT MODELING OF LAPAN-A5/CHIBASAT DEPLOYABLE SOLAR PANEL COMPOSITE PLATE Triharjjanto, Robertus Heru; Budiantoro, Poki Agung
Indonesian Journal of Aerospace Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a3065

Abstract

LAPAN-A5/ChibaSat, that will carry synthetic aperture radar payload, requires a lot more power generation capacity, compared to its predecessor. Therefore, its solar panel will be deployed in orbit to ensure maximum sun exposure. Since the deployable system requires solar panel plate that lightweight and strong, honeycomb composite material is selected. The selection of such material requires special treatment in the satellite structural stiffness calculation. The objective of the research is to find simple stiffness model of the plate, so that later it can be integrated with the total satellite structural model and used by launch authority in its total vehicle modal analysis. The modeling used finite element software, and the simplified honeycomb model is validated using standar plate stiffnes problem. After model validation, the boundary condition as in the LAPAN-A5/ChibaSat deployable system is imposed. The result shows that the stiffness of the deployable solar panel plate has met the launch requirement of PSLV’s auxiliary payload. Therefore, the design mode can be used in the development of LAPAN-A5/ChibaSat. Â
Co-Authors Fauzi Ahmad Muda Triharjjanto, Robertus Heru