Attitude Control System for NANOSAT-1
- Paper number
IAC-06-B5.6.16
- Author
Mr. Pedro Vicente, Instituto Nacional de Tecnica Aerospacial (INTA), Spain
- Coauthor
Mr. Manuel Angulo, Instituto Nacional de Tecnica Aerospacial (INTA), Spain
- Year
2006
- Abstract
This paper present the overall characteristics of the Attitude Control System (ACS) developed for NANOSAT-1. The ACS shall retain two specific restrictions from Mission Requirements: The design is primarily based on new experimental sensors, fully designed integrated and qualified at INTA. Sun sensors are based on three AsGa miniature cells, and magnetometer is developed with four Honeywell HMC1201 sensors combined in cubic configuration. The second specific restriction is to actuate, in nominal mode, only once a week, in only one orbit, during a maximum of ten minutes. The control is based in general attitude determination routines and basic control maneuvers for spinning spacecrafts with magnetotorquer actuators devices. Specific software is developed for managing the special characteristics of the experimental sensors. All the ACS software (initial studies, simulators, etc) is developed in Matlab/Simulink(R), without specific toolboxes, and integrated with minimum but necessary changes in the general software of NANOSAT-1.
- Abstract document
- Manuscript document
IAC-06-B5.6.16.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.