Optimization shape design of capsule-supersonic parachute system based on fusion surrogate strategy
Supersonic parachutes,as crucial aerodynamic deceleration systems providing drag and stability,directly impact the success of lander missions.The structural parameters of parachutes that meet different aerodynamic per-formance requirements are often contradictory.To address the issues of structural parameter conflicts in the shape de-sign of Mars parachutes,as well as the errors of lengthy design cycles and high calculation,this study proposes a fu-sion surrogate optimization strategy for the two-body model of the canopy-capsule system.The fusion surrogate model integrates the advantages of interpolation-based and regression-based surrogate models,and achieves higher predic-tion accuracy of aerodynamic coefficients under the same sample conditions.By employing the fusion surrogate model to replace the time-consuming Computational Fluid Dynamics(CFD)calculation process,the design cycle can be shortened,and design efficiency can be improved.The two-body model of the capsule-DGB parachute is optimized using a multi-objective genetic algorithm.The results show that the fusion surrogate optimization strategy can balance the drag and stability performance of the canopy,and enhance the overall deceleration capability of the disk-gap-band parachute under structural parameters and aerodynamic constraints,demonstrating good practicality and feasibility.The research findings can provide theoretical reference and technical reserves for the design and development of a new generation of supersonic parachutes for future Mars exploration missions.
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