Accurate determination and prediction of the vehicle angular momentum vector is crucial to many satellite programs, particularly those that require the interpretation of satellite imagery. A geostationary operational satellite program that services customers in near real time requires a spacecraft navigation capability that minimizes the number and/or magnitude of control perturbations to the orbit and attitude states. The accuracy of one's attitude determination and prediction process will profoundly affect this requirement. The satellite mission may require that the vehicle be controlled to within some tolerance about a preferred attitude, i.e., orbit normal, ecliptic normal, or equatorial normal. Based on regular measurements of the angular momentum vector, a mechanism will be described for making attitude predictions and for optimizing the selection of attitude control targets for a geostationary satellite.
An Attitude Predictor/Target Selector
1981
25 pages
Report
No indication
English
Unmanned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Artificial satellites , Satellite attitude , Attitude(Inclination) , Coordinates , Solar radiation , Transformations , Vector analysis , Mathematical models , Angular momentum , Predictions , Geostationary satellites , Mercator projections , NTISCOMNOA