CAJ | 학술논문

基于有限元法和控制体积法建立装备－气囊系统有限元模型，并采用试验数据对模型进行验证。复杂气囊系统着陆缓冲过程仿真计算资源消耗大，难以应用传统迭代方法进行参数优化。为克服这些问题，结合扩展拉丁超立方设计，以最大着陆冲击加速度和最大翻转角度为响应，采用径向基函数构建代理模型。在代理模型基础上，利用多目标遗传算法对主气囊高度、横向宽度及排气孔面积等气囊缓冲系统参数进行了多目标优化。优化结果表明：优化后最大冲击加速度减小了15．5％，最大翻转角度减小了70．3％，缓冲性能与横向稳定性均有所提高。
기우유한원법화공제체적법건립장비－기낭계통유한원모형，병채용시험수거대모형진행험증。복잡기낭계통착륙완충과정방진계산자원소모대，난이응용전통질대방법진행삼수우화。위극복저사문제，결합확전랍정초립방설계，이최대착륙충격가속도화최대번전각도위향응，채용경향기함수구건대리모형。재대리모형기출상，이용다목표유전산법대주기낭고도、횡향관도급배기공면적등기낭완충계통삼수진행료다목표우화。우화결과표명：우화후최대충격가속도감소료15．5％，최대번전각도감소료70．3％，완충성능여횡향은정성균유소제고。
Based on the finite element method and the control volume method,a finite element model of equipment and its airbag cushion system was established and verified with test data.The simulation of landing process of an airbag cushion system within one tenth of a second duration typically required ten hours of CPU time.As a result,the optimization of its design based on a nonlinear model was very difficult with the traditional iterative approach.In order to solve this problem to optimize the design of an airbag cushion system for airdropping equipment,surrogate models were employed instead of the complex finite element model based on extended Latin hypercube method and radial basis functions.Height of airbag,width of airbag and area of vent hole were chosen as design variables.Then,Pareto optimal solution sets based on response surfaces were obtained with the multi-objective genetic algorithm.The optimization results showed that the maximum impact acceleration reduces 19%,while the maximum attitude angle reduces 1%;the cushion performance and the lateral stability of the airbag cushion system are obviously improved.