摘要
建立了空降车-气囊系统非线性有限元模型,并通过典型工况试验对模型进行了验证,空降车各测点的垂向冲击加速度的仿真结果与实测结果的高度一致性表明,文中所建立模型的精度能够满足工程分析的需要。针对缓冲气囊的复杂非线性模型计算规模大、难以通过迭代的方法进行优化的问题,研究采用建立等效响应模型方法进行缓冲气囊的参数优化,优化前后气囊缓冲特性的对比结果表明,气囊优化后空降车着陆冲击加速度最大值减小了19.81%,气囊的能量吸收能力提高了7.85%,气囊的缓冲性能有显著的提高。
An finite element（FE） model of airborne vehicle and its airbags was established and verified experimentally.The simulation results agree very well with the experimental results,which indicate that the established model is valid for further research.Airbags cushion system and the optimization of the design based on a complex nonlinear model is very difficult by traditional iterative approach method.Thus,equivalent response mode was employed to optimize the parameters of airbags.The optimization result shows that the maximal acceleration of airborne vehicle landing reduces 19.81%,while the energy absorption of airbags increases 7.85%.The performance of the airbags cushion system is largely improved through optimization.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2012年第12期1461-1466,共6页
Acta Armamentarii
基金
装甲兵工程学院科研创新基金项目(2011CJ019)
关键词
机械工程其他学科
空降车
缓冲气囊
非线性有限元法
特性验证
等效响应模型
other disciplines of mechanical engineering
airborne vehicle
airbag
nonlinear finite element method
verification
equivalent response model
