摘要
文章基于显式有限元模型,采用控制体积法对缓冲气囊的展开及缓冲过程进行仿真分析。首先对单个球形气囊进行折叠展开过程模拟,之后依据NASA"猎户座"缓冲着陆器的缩比模型,建立了一个用以评估气囊着陆衰减系统的LS-DYNA有限元模型。分别研究了缓冲着陆器正碰和侧碰对缓冲气囊压力、着陆器的加速度和运动的影响。并与文献进行对比验证,计算结果表明数值模拟的正确性。
Inflatable deployment and cushion process of a landing vehicle play a key role during inflation of landing airbags and impaction with the ground.Based on explicit finite element model in this paper,deployment and buffer process were simulated using the control volume method.Firstly,the inflatable process of a folded spherical balloon was simulated.And then,according to the scale model of NASA Orion Crew Vechicle,a LS-DYNA finite element model was established to assess the landing airbag attenuation system.The pressure inside airbags were studied,as well as the acceleration and motion of the landing vechicle,when this vechicle had a central or lateral collision with the groud respectively.Comparing with the literature,the numerical simulation results show the correctness.
出处
《航天返回与遥感》
2010年第5期1-8,共8页
Spacecraft Recovery & Remote Sensing
基金
国家863计划资助项目(2008AA12A205)
关键词
缓冲着陆
气囊
充气展开
控制体积法
航天器
Cushion landing Airbags Inflatable deployment Control volume Spacecraft
