  The advent of the modular CubeSat satellite architecture has heralded a
revolution in satellite missions, drastically lowering the technical and
financial barriers to space. Surface charging resulting from energetic electron
poses a direct risk to satellites in space, causing electric arcing and
breakdowns. This risk is exacerbated for small technology demonstration
CubeSats that are less resilient than larger satellites. An upcoming CubeSat
launch is the first CubeSat project originating from Honduras, the Moraz\'an
satellite (MRZ-SAT), due to launch in 2024. This will carry earth observational
payloads to detect natural disasters. This study conducts simulations using the
Electro-Magnetic Spacecraft Environment Simulator code to study absolute and
differential charging of the MRZ-SAT cube-sat in Low Earth Orbit (LEO). The
MRZ-SAT hosts four antennas, an architecture which lends itself well to
studying and understanding differential charging in LEO. The MRZ-SAT was first
simulated in a typical benign ionospheric plasma environment. Here the antenna
located in the ambient plasma wake displayed the maximum charging up to --0.9
V, 0.24 V biased to the main cube. An energetic electron population was then
included and the wake antenna subsequently charged to greater values of --2.73
V, now 1.56 V biased to the main cube. The anisotropy of the energetic
electrons was then varied, and this differential charging trend appeared
exacerbated with anisotropies of 0.5 to 0.05 inducing absolute wake antenna
voltages up to --4.5 V and differential voltage biases 50 and 100 \% greater
than when an isotropic population was considered. This study highlights the
importance of electron anisotropy in LEO to surface charging and identifies
this property in the energetic electron distribution functions as inducing
potentially greater risks to satellites of electrical arcing and breakdown.
