中文摘要：

针对基于地面模拟试验传统设计方法难以对全向式多室连通气囊进行优化设计的问题，采用基于有限元仿真、试验及多目标优化相结合的方法对该气囊系统进行了优化设计。在优化设计过程中，建立了可以分析全向式多室连通气囊（包裹了着陆探测器）的火星着陆缓冲过程的有限元模型，并进行了部分冲击试验，验证了该模型的准确性；然后基于有限元仿真结果，构建了目标函数的多项式代理模型；根据该模型，运用多目遗传算法对气囊系统进行了优化设计，系统的轻量化与单位质量吸能性能得到显著提高。该研究方法对全向式多室连通火星着陆缓冲气囊及其类似装备的设计具有很好的指导意义。

英文摘要：

Subject to the limitations of the traditional design method based on the experiments on the earth to solve the problem of the optimization design for omni-directional multi-chamber airbag for landing on Mars, a systemic methodology by jointly integrating the finite element simulation, experiment and multi-objective optimization method is used to optimize the airbag system. In the process of the optimization design, the finite element model which can simulate the landing process of the omni-directional multi-chamber airbag with the wrapped Mars lander is built. And then the impact physical experiments on the earth are implemented to validate the accuracy of the finite element model. Based on the results of finite element simulations, some polynomial metamodels of the objective function are obtained. According to these models, the airbag system is optimized by adopting multi-objective genetic optimization algorithm, and the optimized results show the obvious improvements of the lightweight and the specific energy absorption （SEA）. The proposed method has a great significance for the design of omni-directional multi-chamber airbag for landing on Mars or other similar equipment.