Thermo-Mechanical Analysis of 1U CubeSat Structures using ANSYS: Insights for Mobility Applications

Particularly for small satellites like CubeSats, the growing commercialization and downsizing of space technology have brought both new opportunities and problems in the areas of heat management and structural design. A Single Unit (1U) CubeSat structure's design and simulation analysis are presented in this work, with an emphasis on the structure's mechanical and thermal performance during launch and orbit. The CubeSat platform, which is frequently constructed using commercial off-the-shelf (COTS) components, needs robust and lightweight structures that can handle mechanical loads and high temperature changes. In order to conduct mechanical stress loading (MSL) and thermal analysis (TA) on a 3D CubeSat model, this work uses ANSYS in a simulation-driven manner. Geometry modeling, meshing, boundary condition application, and simulation of important space environment elements including microgravity, solar radiation, and launch-induced stresses are all part of the process. The findings provide light on the combined thermo-mechanical behavior of CubeSat structures and draw attention to important design factors that maintain thermal stability and structural integrity. These results contribute to the larger discussion on materials optimization, thermal protection systems, and vehicle structural design in the automotive mobility areas. Through the application of simulation methods from aerospace applications to mobility engineering, this study provides cross-domain insights into effective heat management approaches and lightweight structural design.