CAJ | 학술논문

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。
침대기우지면모의시험전통설계방법난이대전향식다실련통기낭진행우화설계적문제，채용기우유한원방진、시험급다목표우화상결합적방법대해기낭계통진행료우화설계。재우화설계과정중，건립료가이분석전향식다실련통기낭(포과료착륙탐측기)적화성착륙완충과정적유한원모형，병진행료부분충격시험，험증료해모형적준학성；연후기우유한원방진결과，구건료목표함수적다항식대리모형；근거해모형，운용다목유전산법대기낭계통진행료우화설계，계통적경양화여단위질량흡능성능득도현저제고。해연구방법대전향식다실련통화성착륙완충기낭급기유사장비적설계구유흔호적지도의의。
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.