Systems and methods are described for a satellite control system that exhibits improved stability and increased efficiency by implementing a non-linear dynamic inversion inner-loop control algorithm coupled with an eigen vector outer-loop control algorithm (225). Thus, the attitude determination and control system (ADACS) may operate using commands to rotate directly about an eigen vector. Additionally, the outer-loop control system (225) includes a feed-forward control element to enhance pointing accuracy when tracking moving targets.
SATELLITE ATTITUDE CONTROL SYSTEM USING EIGEN VECTOR, NON-LINEAR DYNAMIC INVERSION, AND FEEDFORWARD CONTROL
SATELLITENORIENTIERUNGSTEUERUNGSSYSTEM UNTER VERWENDUNG VON EIGEN-VEKTOR, NICHTLINEARER DYNAMISCHER INVERSION UND FEEDFORWARD-STEUERUNG
SYSTÈME DE COMMANDE D'ATTITUDE D'UN SATELLITE UTILISANT UN VECTEUR EIGEN, L'INVERSION DYNAMIQUE NON LINÉAIRE ET LA COMMANDE PRÉDICTIVE
2022-06-29
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS |
European Patent Office | 2022
|European Patent Office | 2022
|European Patent Office | 2020
|European Patent Office | 2021
|European Patent Office | 2020
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