Thermal Design and Analysis of a Low Earth Orbit Micro-Satellite | ||||
| Journal of Advanced Engineering Trends | ||||
| Article 9, Volume 41, Issue 2, July 2021, Page 101-112 PDF (1.56 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/jaet.2021.54010.1077 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
mohamed Elfarran   1; Mohamed khalifa1; Ahmed DeifAllah2; ahmed Farrag3
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| 1institute of aviation engineering and technology | ||||
| 2Doctor engineer @STC | ||||
| 3Institute of Aviation Engineering and Technology | ||||
| Abstract | ||||
| The need for space missions is ever growing with the complexity of problems encountered, requiring experiments at different physical conditions. The cost and other factors experienced in each of the space missions are soaring, irrespective of the entanglements of these missions. Micro and Nano satellites have paved way in this regard, as they are cheap, feasible and provide a platform for new technologies to be tested and validated in space which can then be extended to larger satellites for enhanced applications. Orbital harsh conditions make thermal system design very big challenge to satisfy the different operation conditions required per satellite components. Thermal Control system (TCS) analysis of Hyper-Spectral Remote Sensing Micro-Satellite is crucial in its conceptual design phase. The thermal system design concept of the Micro-Satellite may be passive or active system working on a non-hermetic platform. Satellite thermal system shall provide suitable temperature envelop allow components to work in full performance. It consumes daily average power about 45 W. Battery is the most critical component because of its capacity sensitivity to temperature changes. | ||||
| Keywords | ||||
| Micro-satellite; thermal design; passive thermal control; orbital | ||||
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