Design and Analysis of Subsystems for a CubeSat Mission

The project addresses the science payload and performs thermal and spacecraft charging analysis of a three-unit CubeSat under design. An infrared spectrometer and a magnetometer are selected for the circular 680-km polar CubeSat mission. Thermal analysis using SolidWorks provides the CubeSat temperature distribution under anticipated ambient and internal heat fluxes. To achieve the design temperatures thermal control is recommended with coatings and internal insulation. Charging analysis is performed using the Spacecraft Plasma Interaction System (SPIS) software under anticipated ambient plasma conditions and shows no adverse impacts. Electromagnetic interference due to the onboard propulsion solenoids is assessed using COMSOL. The analysis guides the design of a 10-cm magnetometer boom