The fully coupled, systematically linearized equations of motion are used for attitude control system design of an early Space Station Freedom flight configuration. These equations are valid around any estimated spacecraft equilibrium point. A full state feedback controller, incorporating gain scheduled adaptation of the attitude gains, is developed for use during spacecraft on-orbit operations characterized by significant mass properties variations. Feasibility of the gain adaptation is demonstrated via a Space Station Freedom/Orbiter berthing operation scenario. The attitude controller transient performance during gain adaptation appear satisfactory.
Adaptive attitude stability and control for Space Station/Orbiter berthing operations
AIAA Guidance, Navigation and Control Conference ; 1992 ; Hilton Head Island, SC, United States
1992-01-01
Conference paper
No indication
English
Space Station Freedom Attitude Control During Orbiter Berthing
British Library Conference Proceedings | 1993
|Space Station ATCS Performance During Orbiter Berthing
SAE Technical Papers | 1993
|Berthing simulator for space station and orbiter
NTRS | 1991
|Berthing Simulator for Space Station and Orbiter
NTIS | 1991
|