Multi-objective Optimization Design Framework and Flight Performance Prediction for Reentry Module Using a Rapid Analysis Program

In this study, we developed a multi-objective design optimization framework that integrates thermal, aerodynamic, trajectory, and structural analyses through the use of low-fidelity and rapid analysis tools. Using a sphere-cone-flare shape as the baseline, the optimization was aimed at minimizing the total heating load, maximizing the volumetric efficiency, and minimizing the ballistic coefficient, employing a genetic algorithm for optimization. The Pareto-front solutions revealed correlations between the total heating load, volumetric efficiency, and ballistic coefficient. Increasing the flare area effectively reduced the total heating load and ballistic coefficient by enhancing the drag and reducing the aerodynamic heating at through significant deceleration. However, this adjustment resulted in a reduction in volumetric efficiency. Conversely, reducing the flare and adopting a blunt hemispherical shape increased the volumetric efficiency yet resulted in higher ballistic coefficients and significant aerodynamic heating. Performance analysis of the proposed designs indicated improved thermal performance and ballistic coefficients compared to the baseline. Future research should focus on optimizing the entry modules for planetary exploration by considering diverse planetary characteristics.