Thermal Analysis and Control Mechanism Using GHLP and Simulation of Space Environment for Small Satellites

Padmaja Kuruba and N.D. Dushyanth

The small satellites are gaining lot of interest in the current scenario especially for development by students and researchers at universities [3] [4]. The success of any satellite mission lies in the design of application functionality along with the reliability of the system in the space environment. One such important factor which determines the sustainability of the mission in space is thermal analysis for stability and relevant control mechanism. The development of small satellite system (SSM) is still possible by using commercially available off the shelf components based on the application mission [2]. But harsh environment and the radiation, earth albedo, internal heat developed by the components of SSM play a major role in design of SSM and also the deployment (orbital parameters).This is much more critical in small satellite (micro, nano and pico satellite) because of restricted capabilities due to compact size, mass, power limitation and volume etc. In this work we designed a has two objectives (1) Microcontroller based Thermal Analysis & Control System (MCBTACS), where Graphene Aerogel Loop-Heat Pipes (GALHP) is controlled by Micro-controller(MC). GHLP is mimicking the bee and small birds during summer. Graphene and aerogel has suitable thermal properties which has inspired from the work at Graphene Flagship work and by author in [9]. (2) Design a mathematical model to simulate the thermal flux observed by SSM in day and night for various orbital parameters. This is done facilitate students to determine the heat flux difficulty for actual testing of temperature during direct and eclipse condition at various altitude in low earth orbit.

Volume 11 | 12-Special Issue

Pages: 608-619

DOI: 10.5373/JARDCS/V11SP12/20193257