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Article

The 3Cat-4 Spacecraft Thermal Analysis and Thermal Vacuum Test Campaign Results

by
Jeimmy Nataly Buitrago-Leiva
1,*,
Ines Terraza-Palanca
1,
Luis Contreras-Benito
1,3,
Lara Fernandez
1,2,3,
Guillem Gracia-Sola
1,
Cristina del Castillo Sancho
4,
Lily Ha
4,
David Palma
4,
Malgorzata Solyga
4 and
Adriano Camps
1,3,5
1
CommSensLab-UPC, Department of Signal Theory and Communications, Universitat Politecnica de Catalunya, Carrer de Jordi Girona 31, 08034 Barcelona, Spain
2
Department of Network Engineering, UPC BarcelonaTech, Carrer de Jordi Girona 31, 08034 Barcelona, Spain
3
Institut d’Estudis Espacials de Catalunya IEEC, Parc Mediterrani de la Tecnologia (PMT) Campus del Baix Llobregat, UPC, Castelldefels, 08860 Barcelona, Spain
4
European Space Agency, Keplerlaan 1, P.O. Box 299, NL-2200 AG Noordwijk, The Netherlands
5
College of Engineering, United Arab Emirates University, Al Ain P.O. Box 15551, United Arab Emirates
*
Author to whom correspondence should be addressed.
Aerospace 2024, 11(10), 805; https://doi.org/10.3390/aerospace11100805
Submission received: 14 August 2024 / Revised: 9 September 2024 / Accepted: 16 September 2024 / Published: 30 September 2024
(This article belongs to the Special Issue Small Satellite Missions)

Abstract

3Cat-4 is the fourth member of the CubeSat series of UPC’s NanoSat Lab, and it was selected by the ESA Academy’s Fly Your Satellite! program in 2017. This mission aims at demonstrating the capabilities of nano-satellites, and in particular those based in the 1-Unit CubeSat standard, for challenging Earth Observation (EO) using Global Navigation Satellite System - Reflectometry (GNSS-R) and L - band microwave radiometry, as well as for Automatic Identification Systems (AIS). The following study presents the results of the thermal analysis carried out for this mission, evaluating different scenarios, including the most critical cases at both high and low temperatures. The results consider different albedos and orbital parameters in order to establish the optimal temperatures to achieve the best mission performance within the nominal temperatures, and in all operational modes of the satellite. Simulation results are included considering the thermal performance of other materials, such as Kapton, as well as the redesign of the optical properties of the satellite’s solar panels. The correlation with the thermal model and the TVAC test campaign was conducted at the ESA ESEC-GALAXIA facilities in Belgium.
Keywords: CubeSat; thermal analysis; TVAC; deployment systems CubeSat; thermal analysis; TVAC; deployment systems

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MDPI and ACS Style

Buitrago-Leiva, J.N.; Terraza-Palanca, I.; Contreras-Benito, L.; Fernandez, L.; Gracia-Sola, G.; del Castillo Sancho, C.; Ha, L.; Palma, D.; Solyga, M.; Camps, A. The 3Cat-4 Spacecraft Thermal Analysis and Thermal Vacuum Test Campaign Results. Aerospace 2024, 11, 805. https://doi.org/10.3390/aerospace11100805

AMA Style

Buitrago-Leiva JN, Terraza-Palanca I, Contreras-Benito L, Fernandez L, Gracia-Sola G, del Castillo Sancho C, Ha L, Palma D, Solyga M, Camps A. The 3Cat-4 Spacecraft Thermal Analysis and Thermal Vacuum Test Campaign Results. Aerospace. 2024; 11(10):805. https://doi.org/10.3390/aerospace11100805

Chicago/Turabian Style

Buitrago-Leiva, Jeimmy Nataly, Ines Terraza-Palanca, Luis Contreras-Benito, Lara Fernandez, Guillem Gracia-Sola, Cristina del Castillo Sancho, Lily Ha, David Palma, Malgorzata Solyga, and Adriano Camps. 2024. "The 3Cat-4 Spacecraft Thermal Analysis and Thermal Vacuum Test Campaign Results" Aerospace 11, no. 10: 805. https://doi.org/10.3390/aerospace11100805

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