The current study designs the mission orbit of the lunar CubeSat spacecraft to
measure the lunar local magnetic anomaly. To perform this mission, the CubeSat will
impact the lunar surface over the Reiner Gamma swirl on the Moon. Orbit analyses are
conducted comprising ΔV and error propagation analysis for the CubeSat mission orbit.
First, three possible orbit scenarios are presented in terms of the CubeSat’s impacting
trajectories. For each scenario, it is important to achieve mission objectives with a
minimum ΔV since the CubeSat is limited in size and cost. Therefore, the ΔV needed for
the CubeSat to maneuver from the initial orbit toward the impacting trajectory is
analyzed for each orbit scenario. In addition, error propagation analysis is performed
for each scenario to evaluate how initial errors, such as position error, velocity
error, and maneuver error, that occur when the CubeSat is separated from the lunar
orbiter, eventually affect the final impact position. As a result, the current study
adopts a CubeSat release from the circular orbit at 100 km altitude and an impact slope
of 15°, among the possible impacting scenarios. For this scenario, the required ΔV is
calculated as the result of the ΔV analysis. It can be used to practically make an
estimate of this specific mission’s fuel budget. In addition, the current study suggests
error constraints for ΔV for the mission.