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Completed TRL 2 (started at 1, targeting 3)
This study will investigate the solution space in transferring from a geostationary transfer orbit to large-amplitude orbits about the Sun-Earth L1 or L2 Libration Points. The transfer will be accomplished by using excess capability from the frequently manifested geostationary missions.
Every year there are multiple missions to geosynchronous transfer orbit with commercial, civil, and Department of Defense customers as the prime payload. Oftentimes, the launch vehicle has significant excess payload that is wasted. Recently, efforts have been undertaken whereby a propulsive ESPA (EELV Secondary Payload Adapter) Ring device could be flown as a secondary payload to take advantage of this excess capability to orbit. Additionally, there is the possibility of a long-life package added to the Centaur upper stage of an Atlas V expendable launch vehicle. Such a package could enable excess Centaur capability to be used for an additional upper stage burn to allow a secondary payload to achieve a transfer to the Libration Points.
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