Analytical Thermal Modeling of Deployed and Body Mount Solar Panel and Its Comparison with Numerical Approaches for Small Satellite

2020 ◽  
pp. 509-521
Author(s):  
G. Ramu ◽  
Prateek Nagvanshi
Keyword(s):  
Thermal Modeling ◽  
Solar Panel ◽  
Small Satellite ◽  
Numerical Approaches

scholarly journals Thermal Modeling of the Mars Reconnaissance Orbiter 's Solar Panel and Instruments During Aerobraking

2007 ◽  
Author(s):  
John A. Dec ◽  
Joseph F. Gasbarre ◽  
Ruth M. Amundsen
Keyword(s):  
Thermal Modeling ◽  
Solar Panel

Thermal Modeling of an Induction Machine Through the Association of Two Numerical Approaches

2006 ◽  
Vol 21 (2) ◽  
pp. 314-323 ◽  
Author(s):  
J.-F. Trigeol ◽  
Y. Bertin ◽  
P. Lagonotte
Keyword(s):  
Thermal Modeling ◽  
Induction Machine ◽  
Numerical Approaches

Performance Evaluation of Fractal Array Antenna for Small Satellite Applications

2016 ◽  
Vol 3 (2) ◽  
pp. 356 ◽  
Author(s):  
Yemane Ghebremedhin Teklehaimanot ◽  
Sinshaw Bekelle ◽  
Mohammed Ismail
Keyword(s):  
Antenna Array ◽  
Solar Panel ◽  
Patch Antennas ◽  
Small Satellite ◽  
Radiation Characteristics ◽  
Small Satellites ◽  
Microstrip Patch Antennas ◽  
Compact Size ◽  
High Efficient ◽  
Satellite Applications

<p class="Default">The possible antenna which can be integrated with relatively large flat structure of solar panel of small satellites is patch antenna. The main problem of common Microstrip patch antennas is that they only operate at one or two frequencies, restricting the number of bands that equipment is capable of supporting. Another issue is that, due to the very strict space that a solar panel has, setting up more antenna array is very difficult. To reduce these problems, the use of fractal shaped antennas integrated on solar cells will be analyzed. The small satellite applications demand a high efficient multi-band antenna with a very compact size. A 2x2 Sierpinski Fractal antenna array is modeled and simulated using HFSS. The proposed work has resulted in multiband operation 10.2 GHz and 18.3GHz with increased bandwidth and radiation characteristics betterment, with added advantage of light weight and smaller dimension which is important where cost to payload is a constraint in satellites.</p>

scholarly journals Design & thermal modeling of solar panel module with embedded reconfigurable Air-Coil for micro-satellites

PLoS ONE ◽  
2018 ◽  
Vol 13 (7) ◽  
pp. e0199145 ◽  
Author(s):  
Anwar Ali ◽  
Shoaib Ahmed Khan ◽  
Musaib Aleem Dildar ◽  
Haider Ali ◽  
Nasim Ullah
Keyword(s):  
Thermal Modeling ◽  
Solar Panel

scholarly journals Iluminasi Panel Surya pada Satelit Orbit Rendah Ekuatorial

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

131 Development of Solar Panel Deployment Mechanisms for a Small Satellite ChubuSat

2015 ◽  
Vol 2015.64 (0) ◽  
pp. _131-1_-_131-2_
Author(s):  
Yasufumi ODA ◽  
Yasutaka NARUSAWA ◽  
Toshihiro IDEHARA ◽  
Masanobu MIZOGUCHI
Keyword(s):  
Solar Panel ◽  
Small Satellite
Sign in / Sign up

Export Citation Format

Share Document