The three-spacecraft AMPTE mission set to be Delta-launched in August 1984 will become the first highly-elliptical Earth orbiters to be supported by the Deep Space Network. Orbit accuracies for the transponder-equipped CCE and IRM spacecraft are defined using coherent doppler and range, non-coherent doppler, and angles. Required navigation accuracies for both spacecraft are met using coherent doppler, and while the use of range enhances the achievable accuracy, it is not a required radio metric data type. Use of non-coherent doppler and angles shows that the IRM navigation accuracy requirements can also be met using listen-only antennas, although this requires an accurate estimate of the doppler bias.
Tracking and orbit determination strategies for the AMPTE mission set
Aerospace Sciences Meeting ; 1982 ; Orlando, FL
1982-01-01
Conference paper
No indication
English
NTRS | 1985
|AIAA | 1985
|AMPTE - IRM : Flugerfahrungen nach einjähriger Mission
TIBKAT | 1985
|AMPTE/IRM attitude determination
AIAA | 1985
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