Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Mathematical model of a maneuvering nanosatellite with a heliothermal propulsion system and a flywheel orientation and stabilization system

Published: 18.05.2021

Authors: Zhumaev Z.S.

Published in issue: #5(113)/2021

DOI: 10.18698/2308-6033-2021-5-2078

Category: Aviation and Rocket-Space Engineering | Chapter: Design, construction and production of aircraft

The paper considers a possibility of using a heliothermal propulsion system for constructing constellations of nanosatellites in the CubeSat format. Such a propulsion system implies direct heating of the working fluid by focused solar radiation. In comparison with electric jet engines, the proposed propulsion has orders of magnitude higher thrust, which makes it possible to build a constellation of nanosatellites in low Earth orbit in less than 6 days. In comparison with electrothermal motors, the presented solution achieves higher efficiency of converting the energy of solar radiation into the thermal energy of the working fluid. The spacecraft motion was simulated taking into account the mutual influence of the propulsion system, the orientation and stabilization system, the power supply system, as well as the passage of the shadow sections of the orbit in which there is a loss of electrical and thermal energy.

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