THE OBJECTIVE OF THE PROPOSED WORK IS TO CREATE AN INTEGRATED MODELING FRAMEWORK TO SIMULATE THE OPERATION OF ELECTROSPRAY THRUSTER ARRAYS UNDER FLIGHT-LIKE CONDITIONS. THIS MODEL WILL CAPTURE THRUSTER PLUME PROPERTIES AND PROCESSES IN THE LOCAL VOLUME OF THESE THRUSTERS DEFINED HERE AS BOTH THE IMMEDIATE VICINITY OF THE ARRAYS AND THE FAR-FIELD REGIONS WHERE INTERACTIONS WITH OTHER ION BEAMS AND SPACECRAFT SURFACES OCCUR. THE MODEL WILL BE ABLE TO TRACK LONG TIME-SCALE PROCESSES THAT AFFECT THRUSTER PERFORMANCE SUCH AS MATERIALS EROSION AND SECONDARY EMISSION. ADDITIONALLY MODELS MUST ACCOUNT FOR AND TRACK THE EFFECTS OF FLIGHT CONDITIONS ON THRUSTER PERFORMANCE SUCH AS THERMAL TRANSIENTS AND SPACECRAFT CHARGING. THE PROPOSED SIMULATION FRAMEWORK WILL BE COMPRISED OF INTEGRATED SUB-MODELS THAT CAPTURE PROCESSES AT VARIOUS SPATIAL AND TEMPORAL SCALES. THE THRUSTER ITSELF HAS THREE KEY REGIONS OF INTEREST AND VARYING SCALES: THE INDIVIDUAL EMITTER (SUB-MICRON TO 1 MILLIMETER) EMITTER ARRAYS (SUB-MILLIMETER TO 1 CENTIMETER) AND THE PLUME (1 CENTIMETER TO SEVERAL METERS). A SUBMODULE THAT GIVES TEMPERATURE-DEPENDENT EMISSION PROPERTIES (CURRENT VS. VOLTAGE AND SPECIES) WILL BE DEVELOPED AND INFORMED BY MULTIPHYSICS MODELING OF FLUID MENISCI. PARTICLE-IN-CELL TECHNIQUES WILL BE USED TO MODEL THE POSITIVE AND NEGATIVE ION TRAJECTORIES FROM THE EXTRACTION REGION TO THE NEAR-FIELD PLUME (SMALL SPATIAL SCALES) AND IN THE FAR-FIELD REGION WHERE BEAMS OF OPPOSITE POLARITY IONS OVERLAP. MEMS ELECTROSPRAY THRUSTERS ARE SPECIFICALLY INCLUDED IN THE NASA IN-SPACE PROPULSION ROADMAP (ELEMENT 2.2.1.5) AND ARE IDENTIFIED AS A TECHNOLOGY THAT CAN BOTH REDUCE SYSTEM COST AND ENABLE SMALL SPACECRAFT MISSIONS TO NEW SCIENCE AND EXPLORATION TARGETS.