Optimal Structural Design of a Small-Scale Composite Satellite Including Parametric and Sensitivity Analyses

The objective of this study is to achieve the optimal structural design of a small-scale composite satellite, using an existing aluminum alloy satellite (SAT-00) as a reference for comparison. The research includes parametric and sensitivity analyses to refine the composite satellite structure, identifying the most effective panel configurations and input parameters for optimization. A novel finite element model, developed in accordance with European Cooperation for Space Standardization (ECSS) guidelines, is employed to conduct static, dynamic, random vibration, and thermal analyses using ANSYS and MATLAB software. A simplified model for the satellite's central plate is developed in MATLAB, while a full structural subsystem model is created in ANSYS. The primary goal is to minimize the satellite’s total weight while complying with ECSS specifications. A Genetic Algorithm is utilized to determine the optimal satellite design through three different optimization models. The study demonstrates a weight reduction of over 26% in the optimized composite satellite (SAT-02) compared to SAT-00. Additionally, dynamic and thermo-elastic analyses are performed to assess the satellite's performance under thermal loads in low Earth orbit (LEO) and to ensure its safety and reliability.