The modular attitude control of a large space platform is studied using a three axis five body model of a flexible spacecraft. Three degree of freedom hinges are considered. A three axis four body model of a truss and a three axis ten body model of a space platform are presented. A state variable rotational dynamics model and a multilevel state variable model are shown. A decomposed performance index and decomposed Hamiltonian are also presented. A subproblem hierarchy for hybrid multilevel LQR attitude control of a three axis model is described.
Modular attitude control of a large space platform
1982-03-01
Conference paper
No indication
English
Space platform attitude control system
NTRS | 1983
|Modular design attitude control system
NTRS | 1982
|Modular Design Attitude Control System
NTIS | 1982
|Modular Design Attitude Control System
NTIS | 1983
|Modular design attitude control system
NTRS | 1983
|