The type of control system to be designed is highly dependent upon the vehicle configuration and the mission functions. In cases where high pointing accuracy is required an active control system is necessary. This system consists of some attitude sensing device, a torque producing device, and the associated electronics. This paper is primarily concerned with the design of an active control system for holding the desired vehicle angular rates during small disturbances. (Author)
Spacecraft Attitude Control Using Feedback Parameter Optimization
1968
49 pages
Report
Keine Angabe
Englisch
Single step optimization of feedback-decoupled spacecraft attitude maneuvers
Tema Archiv | 1985
|