Trajectory design for transfers from cislunar orbits to the retrograde geo-synchronous orbit
Peer-Reviewed Publication
Updates every hour. Last Updated: 20-Oct-2026 22:16 ET (21-Oct-2026 02:16 GMT/UTC)
Due to its unique orbital characteristics, the retrograde geosynchronous orbit (RGSO) has demonstrated substantial potential in the fields of space surveillance and space situational awareness. However, constrained by the direction of Earth's rotation and the tracking, telemetry, and control capabilities of launch sites, the direct launch of satellites into RGSO from Earth must overcome an additional velocity increment of more than approximately 4 km/s, entailing enormous fuel consumption and significant engineering difficulty. Conventional approaches employ lunar gravity assists to transfer from low Earth orbit or geosynchronous transfer orbit to RGSO, yet the velocity increment requirements remain relatively high and the transfer paths are limited. With the increasing development of cislunar space in recent years, an increasing number of spacecraft on cislunar orbits are being launched and deployed. If a spacecraft is placed on standby in cislunar orbits, whether the sensitive dynamical characteristics of the three-body problem in cislunar space can be exploited to achieve low-energy transfer to RGSO has become a key issue for expanding the utilization value of cislunar space assets.
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