Scenario-Based Surface Charging Guidance for CubeSat-Class Satellites in Low Earth Orbit

Spacecraft surface charging is one of the most common space environment effects and can pose significant risks to satellite operations through interactions with ambient plasma and space weather conditions. While spacecraft charging has been extensively investigated in high-altitude environments such as geostationary orbit (GEO), comparatively less attention has been given to low Earth orbit (LEO), where charging phenomena are often assumed to be less critical. However, the rapid expansion of the New Space sector and the increasing number of small satellites operating in LEO necessitate a renewed assessment of surface charging risks in this region. Despite this growing reliance on LEO, many small satellite manufacturers and operators still design and operate spacecraft with limited awareness of surface charging effects. In this study, we aim to provide scenario-based surface charging guidance applicable not only during the design phase of small satellite missions but, more importantly, for satellites already deployed and operating in LEO. Rather than performing precise, spacecraft-specific predictions, we construct a surface charging database based on generalized CubeSat-class geometries. The database is developed using the Spacecraft Plasma Interaction System (SPIS), a widely used numerical tool for spacecraft-plasma interaction analysis. Representative configurations commonly used in small satellite missions are considered, including 1U and 3U CubeSats, thin panel structures, and boom-equipped geometries. For each configuration, charging characteristics are evaluated across a range of surface material properties, latitude-dependent ionospheric plasma environments, and day–night illumination conditions.

The resulting database is not intended to deliver mission-specific absolute charging values. Instead, it provides qualitative and semi-quantitative information that enables satellite manufacturers and operators to assess whether an on-orbit spacecraft is likely operating under relatively benign charging conditions or exposed to potentially hazardous environments. This work helps bridge the gap between spacecraft charging physics and the practical operational needs of the CubeSat community, contributing to improved awareness of charging-related risks for small satellite missions in LEO.