Design, analysis and optimization of an 8U CubeSat having a spectrophotometer pay load for astrophysics applications
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Date
2026-10-07
Authors
Κατσιάδας, Γεώργιος
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Abstract
Τhis diploma thesis deals with the design, analysis, and optimization of an 8U CubeSatnanosatellite, which carries as its payload an optical telescope (80 mm in diameter, f/1.4) with a CMOS sensor, for the purpose of detecting exoplanets through transit photometry. The mission’s objective is to implement a hybrid observation strategy (combining radial velocity and extended monitoring data) using the defocused PSF technique, theoretically achieving photometric accuracy in the range of 200–400 ppm.From an engineering perspective, the system’s development was based on strict weight and volume constraints, while maintaining high structural rigidity. The main frame was designed using 7075-T6 aluminum alloys, while Al 6082-T651 and Al 5005-H14 alloys were selected for the deployable (DSPs) and mounted (MSPs) solar panels, respectively. Through this approach, the total estimated mass of the satellite was limited to 9.30 kg, fully satisfying the launch mass limit, with the center of mass (CoM) maintained within the permitted safety limits.To verify the structural integrity of the design against launch loads, a Finite Element Analysis (FEA) was performed using ABAQUS software. Initially, the quasi-static analysis showed that the maximum von Mises stresses remain significantly lower than the yield strength of the selected materials, ensuring a positive margin of safety (MOS) for all subsystems. The modal analysis revealed that the system’s first natural frequency is 100.4 Hz, clearly exceeding the critical threshold of 40 Hz (Rideshare specifications) and thus preventing the risk of resonance with the rocket. Finally, the random vibration (PSD) analysis based on the 3σ statistical criterion confirmed that all dynamic stresses remain strictly within the elastic range.In conclusion, the designed CubeSat meets all the required operational and mechanicalspecifications for flight certification. As future work, it is recommended to conduct an extensive thermal analysis, as well as to integrate a micro-propulsion system (thrusters) for the satellite’s controlled reentry into the atmosphere, with the aim of reducing space debris.
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Keywords
Satellite, CubeSat 8U, Photometry, Structural design, Finite element analysis