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CubeSat standardized modular assembly method and design optimization
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DOI：10.1016/j.actaastro.2024.01.011.png)
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Abstract
En 中文
In order to solve the deficiencies of traditional board-level assembly CubeSat, such as low modularity, complex assembly process and poor scalability, a sandwich module assembly structure and method with no drive components is proposed, which can achieve quick connection and flexible assembly between modules. First, the proposed CubeSat standard module can be compatible with the standard interface of traditional CubeSat. The 4in-1 interface of Mechanical-Electrical-Thermal-Data does not occupy the internal space of the standard module, and the electrical and thermal interfaces meet the requirements of CubeSat in -orbit work. Secondly, in order to improve the reliability of the connection between the modules, a plug -in connection scheme of the mechanical interface was designed. Finally, a genetic algorithm was used to optimize the interface size, so that it has better plug -in performance. The simulation results show that the performance of the male interface of titanium alloy material is the best, and the error between the finite element analysis and genetic algorithm results is less than 4.8 %, which is consistent with the actual tensile test results of the optimized prototype, and meets the mechanical requirements of the launch process and space orbit operation for CubeSat. The test results can guide production and provide a reference for subsequent engineering applications of CubeSat modular assembly.
Keywords:
CubeSat
Standardization
Modularization
Parameter optimization
Finite element analysis
Journal
IF:
3.4
Papers:
1.2W
Citations:
2.1W
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Cited Papers
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ACTA ASTRONAUTICA
OAAI
ACTA ASTRONAUTICAIF3.4
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