Mechanical Design, Structural and Thermal Analysis for a 6U eLEO CubeSatPublic
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This project supports the design of a six-unit Cube Satellite (CubeSat) mission in an extreme Low Earth Orbit (eLEO). The goal is to perform Ionosphere experimentation using the NASA mini Ion Neutral Mass Spectrometer (mINMS). The CubeSat design addresses the mission and NanoRacks Deployer requirements. Mechanical design of the CubeSat is performed using SolidWorks. Vibration and stress analysis for expected launch conditions is performed using ANSYS, and thermal analysis in our desired orbit is performed with COMSOL software. Thermal characteristics are determined using the Systems Tool Kit (STK) software to model the CubeSat’s thermal environment throughout its orbit. All important documents and launch requirements are identified.
- This report represents the work of one or more WPI undergraduate students submitted to the faculty as evidence of completion of a degree requirement. WPI routinely publishes these reports on its website without editorial or peer review.
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