Maneuver Design Techniques for Deploying and Maintaining the SunRISE Constellation
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http://dataverse.jpl.nasa.gov/citation?persistentId=doi:10.48577/jpl.GDGA8B
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The Sun Radio Interferometer Space Experiment (SunRISE) mission will employ a constellation of 6 CubeSats in an orbit 300 km above geostationary to study the transport and acceleration of solar energetic particles associated with coronal mass ejections. While the spacecraft are capable of executing maneuvers anywhere within the orbit, selecting the time of the OTM may minimize the DeltaV, ensure that DeltaV constraints are met, and minimize the chance of close approaches within the constellation during transfers. The present paper focuses on the maneuver design process for deploying and maintaining the constellation in a loose, repeating formation to create the first spaceborne imaging interferometer.
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Root
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2025-02-04
