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Open AccessArticle

Thermal Numerical Analysis of the Primary Composite Structure of a CubeSat

by Saul Piedra 1,*,†, Mauricio Torres 1,† and Saul Ledesma 2,†
National Council of Science and Technology (CONACYT)—National Center for Aeronautics Technologies—Center for Engineering and Industrial Development (CENTA-CIDESI), Colón, Querétaro 76270, Mexico
National Center for Aeronautics Technologies (CENTA), Colón, Querétaro 76270, Mexico
Author to whom correspondence should be addressed.
These authors contributed equally to this work.
Aerospace 2019, 6(9), 97;
Received: 7 June 2019 / Revised: 12 August 2019 / Accepted: 26 August 2019 / Published: 4 September 2019
(This article belongs to the Special Issue Verification Approaches for Nano- and Micro-Satellites)
A thermal computational analysis for the composite structure of a CubeSat is presented. The main purpose of this investigation is to study the thermal performance of carbon fibre/epoxy resin composite materials with Zinc Oxide nanoparticles in order to be used in the panels of the primary structure of a CubeSat. The radiative heat fluxes over each composite panel are computed according to the orbit trajectory and they are utilized as boundary conditions for the analysis. The direct solar, albedo and Earth infrared radiation fluxes are considered in this study. The model implementation, including the computation of the orthotropic thermal conductivity of the composite material is presented. The thermal simulations were performed for three different orbit inclination angles: the selected mission ( β = 57 ), the worst hot ( β = 90 ) and the worst cold ( β = 0 ). The temperature ranges in the electronic boards are analyzed in order to show that are into the operating limits of each electronic component. View Full-Text
Keywords: CubeSat; composite structure; thermal analysis CubeSat; composite structure; thermal analysis
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Piedra, S.; Torres, M.; Ledesma, S. Thermal Numerical Analysis of the Primary Composite Structure of a CubeSat. Aerospace 2019, 6, 97.

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