UPMSat-2 ACDS magnetic sensors test campaign

Rodríguez-Rojo, Elena ORCID: https://orcid.org/0000-0002-7193-4041, Pindado Carrion, Santiago ORCID: https://orcid.org/0000-0003-2073-8275, Cubas Cano, Javier ORCID: https://orcid.org/0000-0001-9787-3796 and Piqueras Carreño, Javier ORCID: https://orcid.org/0000-0002-3787-9640 (2019). UPMSat-2 ACDS magnetic sensors test campaign. "Measurement" ; ISSN 0263-2241. https://doi.org/10.1016/j.measurement.2018.08.069.


Title: UPMSat-2 ACDS magnetic sensors test campaign
Item Type: Article
Título de Revista/Publicación: Measurement
Date: September 2019
ISSN: 0263-2241
Freetext Keywords: UPMSat-2 ADCS Magnetic control. ADCS testing. ADCS integration. Space simulation
Faculty: E.T.S. de Ingeniería Aeronáutica y del Espacio (UPM)
Department: Sistemas Aeroespaciales, Transporte Aéreo y Aeropuertos
UPM's Research Group: Desarrollo y Ensayos Aeroespaciales DEA
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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The present paper summarizes the testing work carried out in relation to the UPMSat-2 Attitude, Control and Determination Subsystem (ADCS) sensors. The ACDS of this satellite is based on the magnetic interaction
with the Earth magnetic field, thus the selected sensors have been magnetometers. This test campaign
was carried out in order to check the performance and accuracy of the magnetometers (acceptance
tests) and to analyse its effect on the characteristic times of the satellite’s stabilization process once its
normal attitude has been perturbed (integration tests). Since the adequate calibration instruments were
not available in the institute, for the acceptance tests a simplified method was designed and performed.
The proposed methodology allows auto-calibrating the magnetometers, using the Earth magnetic field as reference and without a comparing with calibrated magnetometers. For the integration tests, the estimated errors were introduced in the simulator of the mission in order to analyse its effect on the stabilization time, once the satellite’s attitude is perturbed. The results of the simulations indicate a correct performance of the magnetometers, as the convergence of the satellite attitude to the target one was
reached within a reasonable period.

More information

Item ID: 52799
DC Identifier: https://oa.upm.es/52799/
OAI Identifier: oai:oa.upm.es:52799
DOI: 10.1016/j.measurement.2018.08.069
Official URL: https://www.sciencedirect.com/science/article/pii/...
Deposited by: Biblioteca ETSI Aeronauticos
Deposited on: 29 Oct 2018 06:58
Last Modified: 05 Jul 2023 15:14
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