A demonstration of dual spacecraft tracking conducted with the Viking spacecraft during the approach phase

Details A demonstration of dual spacecraft tracking conducted with the Viking spacecraft during the approach phase A demonstration of dual spacecraft tracking conducted with the Viking spacecraft during the approach phase

Sep 1977

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1977aiaa.confw....c&link_type=abstract

American Astronautical Society and American Institute of Aeronautics and Astronautics, Astrodynamics Specialist Conference, Jack

Other

Descent Trajectories, Space Navigation, Spacecraft Tracking, Viking Mars Program, Accuracy, Data Processing, Ephemeris Time, Error Analysis, Flyby Missions, Orbit Calculation, Trajectory Analysis, Viking Orbiter Spacecraft

Scientific paper

In the case of interplanetary space missions involving two spacecraft, such as Viking, significant navigation advantages may sometimes be achieved (at least for the trailing vehicle) by determining the orbit of one relative to the other, or otherwise combining the data from the two spacecraft. Dual spacecraft navigation concepts have been investigated by Chao et al. (1976). New analytical models for the dual spacecraft data types are presented and results are reported from a more recent demonstration conducted during the approach phase of the Viking mission. The demonstration was based on data taken two weeks before Mars orbit insertion of the second Viking spacecraft. The demonstration was designed to show that the approaching probe could be tied accurately to the planet through the orbiter. Attention is given to the geometry of the Viking B approach trajectory, the accuracy of the delivered estimates for midcourse maneuvers, and an algorithm of data processing.

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