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The trajectory design for the Dark Ages Radio Explorer (DARE) missioncon-cept involves launching the DARE spacecraft into a geosynchronous transferorbit (GTO) as a secondary payload. From GTO, the spacecraft then transfers toa lunar orbit that is stable (i.e., no station-keeping maneuvers are requiredwith minimum perilune altitude always above 40 km) and allows for more than1,000 cumulative hours for science measurements in the radio-quiet regionlocated on the lunar farside.

Trajectory Design From GTO To Lunar Equatorial Orbit For The Dark Ages Radio Explorer (DARE) Spacecraft