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We show that it is possible to launch a satellite to Geostationary Equatorial orbit (GEO) from the non-equatorial launch site (Naro Space Center in South Korea) even though that is located in the mid-latitudes of the northern hemisphere. When launched from this site, the equatorial inclination after separation will be 80°. We use a lunar gravity assist (LGA) transfer to avoid the excessive ∆ V  costs of plane change maneuvers. There are eight possible paths for the LGA; there are four paths consisting of Earth departures and free-return types, and there are two nodes of the Moon’s orbit (ascending and descending). We analyze trajectories over five launch periods for each path using a high-fidelity orbit propagation model. We show that the LGA changes the orbital energy of the “cislunar” free-returns more than for the “circumlunar” free-returns, resulting in less geostationary insertion ∆ V  for the cislunar free-returns. We also show that the geometrical ∆ V  variation over the different paths is greater than the seasonal ∆ V  variation. Our results indicate that an ascending departure and cislunar free-return at the descending node have lower ∆ V  requirements than the other paths, and lower than described in several previous studies.

Geostationary Orbit Transfer with Lunar Gravity Assist from Non-equatorial Launch Site