This project presents design and analysis for a 6-unit CubeSat carrying a miniaturized mass spectrometer. The CubeSat is inserted at the International Space Station (ISS) altitude and uses the BET-300-P electrospray thruster to acquire an orbit with perigee at about 200 km and apogee at 440 km.Orbital analysis using the SystemsToolKit (STK) provides an orbital life of about 45 days. STK simulations estimate 17 W of available power and battery capacity of 40 Wh, STK simulations provide the downlink transfer periods with the Near Earth Network and the thermal fluxes onto the CubeSat. COMSOL Multiphysics simulations determine that the induced magnetic fields from the magnetorquers do not adversely affect electronics and sensors.Preliminary design of a thermal vacuum chamber is also presented
