Design and Analysis of the External Structure and Internal Configuration of ÆtherSat

Maintenance of a satellite's structural integrity through harsh space conditions is paramount. A satellite's integrity and stability are directly related to its design and configuration, and thus, it is essential to optimize the structure as per the expected conditions in space. This paper explores different design concepts for ÆtherSat and also deals with the stress-strain-displacement analyses for the same. ÆtherSat is a 1Ustudent CubeSat designed by MIT ADT University that incorporates an ingenious solar tracking mechanism for power generation in a circular Low Earth Orbit (LEO) at an altitude of 500 km. We thoroughly study the various nuances of the CubeSat architecture, including the material selection and validation, external structural designs, internal subsystem configurations, and the arrangement of payloads. ÆtherSat is designed so as to optimally accommodate the solar tracking mechanism and ensure that components are placed at befitting positions within the stipulated operating limitations. We scrutinize the different internal configurations and perform structural and material analyses to enhance the design and mechanical capabilities of ÆtherSat. ÆtherSat is designed and analyzed in Fusion 360.