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Using mean orbit period in Mars Reconnaissance Orbiter maneuver design

Show simple item record Chung, Min-Kun J. Menon, Premkumar. R. Wagner, Sean V. Williams, Jessica L. 2016-06-06T19:40:39Z 2016-06-06T19:40:39Z 2014-08-05
dc.identifier.citation AIAA Space 2014, San Diego, California, August 5-7, 2014 en_US
dc.identifier.clearanceno 14-2855
dc.description.abstract Mars Reconnaissance Orbiter (MRO) has provided communication relays for a number of Mars spacecraft. In 2016 MRO is expected to support a relay for NASA’s Interior Exploration using Seismic Investigations, Geodesy and Heat Transport (InSight) spacecraft. In addition, support may be needed by another mission, ESA’s ExoMars EDL Demonstrator Module’s (EDM), only 21 days after the InSight coverage. The close proximity of these two events presents a unique challenge to a conventional orbit synchronization maneuver where one deterministic maneuver is executed prior to each relay. Since the two events are close together and the difference in required phasing between InSight and EDM may be up to half an orbit (yielding a large execution error), the downtrack timing error can increase rapidly at the EDM encounter. Thus, a new maneuver strategy that does not require a deterministic maneuver in-between the two events (with only a small statistical cleanup) is proposed in the paper. This proposed strategy rests heavily on the stability of the mean orbital period. The ability to search and set the specified mean period is fundamental in the proposed maneuver design as well as in understanding the scope of the problem. The proposed strategy is explained and its result is used to understand and solve the problem in the flight operations environment. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2014 en_US
dc.title Using mean orbit period in Mars Reconnaissance Orbiter maneuver design en_US
dc.type Preprint en_US

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