On the UPMSat-2 attitude, control and determination subsystem’s design

Rodríguez-Rojo, Elena and Cubas Cano, Javier and Roibás-Millán, Elena and Pindado Carrion, Santiago (2019). On the UPMSat-2 attitude, control and determination subsystem’s design. In: "8th European Conference for Aeronautics and Space Sciences (EUCASS 2019)", 1-4 jul 2019, Madrid, España. https://doi.org/10.13009/EUCASS2019-736.

Description

Title: On the UPMSat-2 attitude, control and determination subsystem’s design
Author/s:
  • Rodríguez-Rojo, Elena
  • Cubas Cano, Javier
  • Roibás-Millán, Elena
  • Pindado Carrion, Santiago
Item Type: Presentation at Congress or Conference (Article)
Event Title: 8th European Conference for Aeronautics and Space Sciences (EUCASS 2019)
Event Dates: 1-4 jul 2019
Event Location: Madrid, España
Title of Book: 8th European Conference for Aeronautics and Space Sciences (EUCASS 2019)
Date: 2019
Subjects:
Faculty: Instituto de Microgravedad Ignacio Da Riva (UPM)
Department: Aeronaves y Vehículos Espaciales
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

In the present paper the work carried out in relation to the Attitude, Control and Determination Subsystem (ACDS) of the UPMSat-2 is summarized. This engineering project is integrated within the UPMSat-2 mission framework. This 50-kg satellite has been designed and manufactured by the Polytechnic University of Madrid (Universidad Politécnica de Madrid). The development of this ACDS comprises the selection of the different parts, sensors (magnetometers) and actuators (magnetorquers), the design of the control law, the testing campaigns of the different subsystem’s parts, and its verification. The magnetometers and magnetorquers were tested in the IDR/UPM Institute facilities at Montegancedo campus, in order to check its accuracy. Besides, the effect of their uncertainty levels on the satellite’s stabilization process once its normal attitude has been perturbed, were studied. The control law is based on B-dot, being thoroughly simulated by using Monte Carlo analysis. Finally, the last testing campaign, carried out during the final integration stages of the satellite is also summarized. The results obtained show a strong and reliable spacecraft control subsystem.

More information

Item ID: 64133
DC Identifier: http://oa.upm.es/64133/
OAI Identifier: oai:oa.upm.es:64133
DOI: 10.13009/EUCASS2019-736
Deposited by: Biblioteca ETSI Aeronauticos
Deposited on: 29 Sep 2020 06:10
Last Modified: 29 Sep 2020 06:10
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