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Notice

TECHNOLOGY TRANSFER OPPORTUNITY: Method for Transferring a Spacecraft from Geosynchronous Transfer Orbit to Lunar Orbit (TOP2-272)

NASA’s Technology Transfer Program solicits inquiries from companies interested in obtaining license rights to commercialize, manufacture and market the following technology. License rights may be issued on an exclusive or nonexclusive basis and may include specific fields of use.

Notice typeSpecial Notice: An announcement, such as an industry day or a request for information.
Who's buyingNASA Marshall Space Flight Center, National Aeronautics and Space Administration
WhereWork location not listed. The buying office is in Huntsville, Alabama.
DeadlineWed, Aug 11, 2027 at 4:00 PM EDT (292 days left)
Who can bidOpen to any business (no set-aside listed)
Solicitation #T2P-ARC-00125
PostedTue, Aug 11, 2026
ContactNASA’s Technology Transfer Program, [email protected]

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From the notice

NASA’s Technology Transfer Program solicits inquiries from companies interested in obtaining license rights to commercialize, manufacture and market the following technology. License rights may be issued on an exclusive or nonexclusive basis and may include specific fields of use. NASA provides no funding in conjunction with these potential licenses. THE TECHNOLOGY: This novel innovation from Ames Research Center allows spacecraft to share rides with larger spacecraft which are headed to Geosynchronous Earth Orbit (GEO). The secondary spacecraft is dropped off Geosynchronous Transfer Orbit (GTO) at any time during the day or year and will subsequently enter lunar orbit, with no constraint on the lunar orbit inclination. The secondary spacecraft can be relatively small, riding as a secondary payload with a larger primary spacecraft. The secondary spacecraft is intended to be controllable (i.e., maneuverable). The invention presents a trajectory design whereby a spacecraft can be launched as a secondary payload into a Geosynchronous Transfer Orbit (GTO) and through a series of maneuvers to reach lunar orbit. The trajectory analysis begins by identifying acceptable ranges of lunar orbit altitude and inclination values. The unique features of this method includes the use of either a leading or trailing edge lunar flyby to achieve an orbit inclination in the lunar orbit plane from a GTO launched at any time of day. This technique is applicable to secondary spacecraft that share a

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