MANY SMALL SATELLITE ELECTRIC PROPULSION (EP) SYSTEMS CREATE THRUST BY EXPELLING A CHARGED PARTICLE PLUME E.G. ELECTROSPRAY COLLOID FIELD-EMISSION EP ION HALL-EFFECT MICROCATHODE ARC VACUUM ARC THRUSTERS ALL EXPEL CHARGED PARTICLES. THE EFFECT OF THE PLUME CONTAMINATION ON SMALL SPACECRAFT SENSITIVE SURFACES PARTICULARLY FOR ELECTROSPRAY COLLOIDAL EP THRUSTERS IS POORLY KNOWN. FURTHERMORE OUR ABILITY TO PREDICTIVELY MODEL GROUND TESTING AND SPACE-BASED CONDITIONS IS KNOWN EVEN LESS. BASED ON OUR EXPERIENCE IN KINETIC MODELING OF ION ELECTRON AND NEUTRAL SPECIES USING PARTICLE APPROACHES FOR XENON-BASED EP DEVICES AND OUR BACKGROUND IN MOLECULAR DYNAMICS SIMULATIONS OF ROOM-TEMPERATURE IONIC LIQUID PROPELLANTS WE PROPOSE TO DEVELOP A CHARGED PARTICLE PLUME MODEL THAT WILL ALLOW US TO MODEL ELECTROSPRAY PLUME SPACECRAFT INTERACTIONS. THE MODEL WILL BE STRONGLY ASSISTED BY NEW IL SURFACE MEASUREMENTS OF SPUTTERING FROM DIFFERENT MATERIALS AND SIMULTANEOUSLY THE CHARACTERISTICS OF MATERIAL SECONDARY ELECTRON EMISSION.