The Verification of Nanosatellites Solar Panels Automatic Deployment in Microgravity Conditions

AbstractThe solar panels installed on a CubeSat are considered the main energy source of a nanosatellites. The deployment mechanism of a solar panel must be analyzed and tested extensively. Any suggested solar panel design should present a low vibrating free spinning deployment mechanism. This paper examines various types of solar panels to reach a conclusion of the efficient design when deployed on a 1U or 2U unit. However, calculations, analysis, simulations do not always give an extensive picture of how the satellite shall behave during deployment. Thus, testing in a microgravity environment gives a more accurate answer of how the satellite shall behave. In our work, various solar panels mechanisms are developed and eventually tested in microgravity. The first accordion structure for a 1U structure is tested in a microgravity environment through a parabolic flight with the National Research Council Falcon 20 aircraft. The results are recorded and analyzed to optimize the next design. The second design is based on a drag-sail mechanism for a 2U structure. The design is improved upon the first experiment results for the next parabolic flight. The simulated amount of power generated in orbit is also a main factor in our evaluation.

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Iluminasi Panel Surya pada Satelit Orbit Rendah Ekuatorial

ELKOMIKA Jurnal Teknik Energi Elektrik Teknik Telekomunikasi & Teknik Elektronika ◽

10.26760/elkomika.v7i3.480 ◽

2019 ◽

Vol 7 (3) ◽

pp. 480

Author(s):

DESTI IKA SURYANTI ◽

SRI RAMAYANTI ◽

MOHAMMAD MUKHAYADI

Keyword(s):

Design Process ◽

Triple Junction ◽

Low Cost ◽

Solar Panel ◽

Satellite Orbits ◽

Small Satellite ◽

Solar Panels ◽

Efficient Design ◽

Small Satellites ◽

Satellite Design

ABSTRAKDesain satelit telah berkembang ke arah miniaturisasi untuk mengurangi biaya peluncuran. Satelit kecil menyediakan platform berbiaya rendah untuk misi luar angkasa. Salah satu permasalahan utama satelit kecil adalah terbatasnya ketersediaan daya. Karena ketersediaan daya diperlukan agar subsistem satelit dapat bekerja, maka pada proses desain satelit perlu dilakukan analisis dan estimasi ketersediaan daya selama satelit mengorbit dengan tetap mempertahankan kekompakan dan volume yang diberlakukan oleh standar. Penelitian ini bertujuan untuk mengetahui kondisi iluminasi matahari pada panel surya dari berbagai alternatif desain penempatan sehingga diperoleh sebuah desain yang efisien. Iluminasi maksimum sebuah panel surya triple junction yang terpasang secara body mounted pada satelit kurang lebih sebesar 60%. Berdasarkan hasil penelitian ini, kombinasi pemasangan 3 body mounted panel surya dan 2 simple deploy panel surya menghasilkan persentase iluminasi dua kali lipat dibandingkan 5 body mounted panel surya.Kata kunci: panel surya triple junction, iluminasi, body mounted, simple deploy, daya ABSTRACTSatellite design has envolved towards miniaturization to reduce launch costs. Small satellites provide a low-cost platform for space missions. One of the main problems with small satellites is the limited availability of power. Because the availability of power is needed so that the satellite subsystem can work, the satellite design process needs to analyze and estimated power availability as long as the satellite orbits while maintaining the compactness and volume imposed by the standard. This study aims to determine the conditions of solar illumination on solar panels from various alternative design placements in order to obtain an efficient design. Maximum illumination of triple junction solar panel mounted on a small satellite is approximately 60%. Based on the results of this study, the combination of installing 3 body mounted solar panels and 2 simple deploy solar panels produced twice the illumination percentage compared to 5 body mounted solar panels.Keywords: solar panel triple junction, illumination, body mounted, simple deploy, power

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