Eventos Anais de eventos
COBEM 2023
27th International Congress of Mechanical Engineering
THERMAL ANALYSIS OF THE IMPACT OF SIX MONTHS IN A 1U CUBESAT IN LEO
Submission Author:
Damylle Donati , SC , Brazil
Co-Authors:
Rodrigo Cardozo, Talita Possamai, Damylle Donati, Renato Oba
Presenter: Rodrigo Cardozo
doi://10.26678/ABCM.COBEM2023.COB2023-0444
Abstract
Space projects, especially orbital platform projects, are comprised of high investment costs, requiring rigorous analysis in their development. The operating conditions of such devices include sudden changes in external temperature as a result of incident radiation during orbit, heat generation in electronic devices, and heat conduction for thermal control of subsystems. Nanosatellite development teams commonly have limited access to robust mission analysis and thermal analysis tools, such as environmental testing, numerical simulation software, and mission design software, due to low budgets when compared to large satellites. For this reason, simplified models of thermal analysis are used to define critical mission requirements. However, there is great difficulty in coupling thermal and orbit requirements, as they are independent complex phenomena. The present work aims to develop a thermal analysis module based on a lumped heat transfer model to be applied as an add-on module to an open-source orbital mission analysis code. The module is validated with the aid of literature data for fixed Beta angles comparing incident radiation on each face of the satellite. For a Beta angle of 0º and 72º, the incident solar, albedo, and infrared radiation on the six faces of a 1U CubeSat in LEO (Low Earth Orbit) are consistent with published data from different authors found in the literature. An analysis of the implications of the variation of the Beta angle in LEO for a 1U CubeSat in six months in orbit time is then presented indicating that without a propulsion system is expected that a 1U CubeSat variates its Beta angle between -72º to 72º in approximately 6 months in LEO. This variation results in an average total incident radiation of approximately 30% in the analyzed period. For the temperatures in each face, variations of more than 30 K can be seen for some faces while variations of 20 to 30 K can be seen for the internal electronic plates (PCD).
Keywords
Space Radiation, cubesat, nanosatellite, thermal transfer
