Publikationsdatum:
2006-01-16
Beschreibung:
The determination of the Mars-centered ephemerides of the Viking Orbiters and positions of the Landers from two way Doppler and range data is described. An overview of mission satellite orbit determination functions and methods is given. Topics covered include: postmaneuver orbit convergence, local orbit knowledge accuracies, the effects of interplanetary media, use of constrained solutions, and solving through trim burns. Procedure and results relevant to the determination of the planet gravity field are included. Results relative to sensing Mars' gravity field during the extended mission are presented along with a discussion of the Phobos Flyby Experiment conducted during February 1977.
Schlagwort(e):
LAUNCH VEHICLES AND SPACE VEHICLES
Materialart:
Viking Navigation; p 109-152
Format:
text
Permalink
