Thermal and Structural Analysis of the MARMOTSat

CubeSat missions face stringent constraints on power, volume, and mass, often compounded by limited budgets and small teams whose expertise evolves from concept through launch. Accurately predicting MARMOTSat’s behavior under both launch level vibrations and in orbit thermal loads,including the resulting thermoelastic deformations,is therefore essential to ensure mission success. This thesis develops detailed finite element (FE) models to evaluate MARMOT- Sat’s structural, thermal, and coupled thermoelastic performance. In the structural study, modal analyses are performed in a stowed configuration (solar panels folded and antennas removed) using the Lanczos eigenvalue extraction method. Thermal simulations model MARMOTSat’s LEO orbit, incorporating solar flux, Earth infrared radiation, and internal heat dissipation. Both “hot case” and “cold case” scenarios are assessed. The resulting temperature distributions are then fed back into a thermoelastic analysis to quantify thermal induced deformations and stresses, ensuring the correct operability of the payload’s VHF antenna. Where margins are insufficient, passive thermal control elements are proposed to mitigate excessive thermal gradients and their mechanical effects. All FE models and simulation workflows are described in detail to serve as a reproducible guide for future team members. Results demonstrate that, with the recommended modal enhancements and thermoelastic control measures, MARMOTSat will both survive launch loads and maintain its structural and thermal stability throughout its operational lifetime.