Thermal Design and Analysis of a Low Earth Orbit Micro-Satellite

Document Type : Original Article

Authors

1 institute of aviation engineering and technology

2 Doctor engineer @STC

3 Institute 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.

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