Orbit Design of Multiple Lunar CubeSat Impactors Deployed from a Single Mothership: A Practical Approach for Mission Feasibility

Abstract This paper presents a practical and feasible orbit design for a lunar impactor mission utilizing multiple CubeSats deployed from a single mothership in lunar orbit. The mission aims to investigate magnetic field anomalies on the Moon, specifically lunar swirls near the equator. These CubeSats will perform low-altitude flyovers of the target swirls, collecting scientific data before impacting the lunar surface. A key aspect of this study is the discovery and utilization of a CubeSat Release Orbit (CRO), where the periapsis vector naturally varies due to perturbative forces, allowing for efficient CubeSat deployment without requiring significant additional delta-V. Four lunar swirls, Rima Sirsalis, Firsov, Dewar, and Reiner Gamma, were selected as case studies, demonstrating that the CRO provides sufficient deployment opportunities. These CubeSats are shown to perform flyovers at altitudes near or below 20 km over the target swirls, maximizing the scientific data collection. This approach not only reduces systemic complexity and operational risks for both the mothership and CubeSats, but also enhances the potential for comprehensive magnetic field measurements over diverse lunar swirls. The proposed mission concept offers an efficient and scalable solution for future lunar exploration, enabling multiple CubeSat deployments from a single mission with broader scientific observation opportunities.