超声速降落伞作为提供气动阻力和稳定性的重要气动减速系统，其设计好坏直接影响着探测器着陆任务的成败。适应不同气动性能需求的降落伞结构参数通常是相互矛盾的，为了解决火星降落伞在外形设计时的结构参数矛盾，以及设计周期长、计算误差大的问题，本文提出了一种面向探测器-降落伞双体模型的融合代理优化策略。融合代理模型集成了插值型代理模型和回归型代理模型的优点，能够在相同样本的条件下具备更高的气动力系数预测精度。通过采用融合代理模型替代长耗时的计算流体力学（CFD）计算过程，能够缩短设计周期，提高设计效率。结合多目标遗传算法对探测器-盘缝带伞双体模型进行了优化设计，结果表明，采用融合代理优化策略能够平衡伞体的阻力性能及稳定性能，在满足结构及气动约束的前提下提升盘缝带伞的综合减速能力，具有良好的实用性和可行性。文章的研究结果可为未来新一代火星探测用超声速降落伞的设计研制提供一定的理论参考和技术储备。

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 performance requirements are often contradictory. To address the issues of structural parameter conflicts in the shape design of Mars parachutes， as well as the errors of lengthy design cycles and high calculation， this study proposes a fusion 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 prediction 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.