基于LS-DYNA的折叠翼动力学分析方法

Dynamic Analysis Method of Folding Wing Based on LS-DYNA

折叠翼展开时间短,冲击载荷大,对折叠翼展开机构的定位、锁紧以及缓冲装置的要求都较高。通常采用的分模块设计方法对结构简化后不能完全反映真实的系统特性,文中根据折叠翼展开机构平面运动简图建立了数学模型,采用LS-DYNA软件建立了折叠翼展开机构的有限元模型,并考虑了系统结构弹性与摩擦力的影响,对折叠翼动力学与结构强度进行综合仿真。仿真结果表明,该方法能够模拟展开机构定位销剪断过程、锁紧销完成锁紧动作以及机翼完全展开的动态过程,得到各构件运动参数信息,并且在大冲击载荷作用下,结构弹性会使折叠翼展开到位后出现过冲及振动现象。因此,在折叠翼展开机构设计时,不仅要满足快速展开的运动要求,还要提高结构强度来抑制过冲及振动。文中方法可为折叠翼展开机构的工程设计提供参考。

The folding wing has a short deployment time and a large impact load,and it has high requirement for positioning,locking and buffering devices of the wing deployment mechanism.The commonly used modular design method needs to simplify the structure,thus it cannot fully reflect the real system characteristics.This paper establishes a mathematical model of folding wing based on the simplified plane motion,and then establishes a finite element model by the LS-DYNA software,in which the influences of structural elasticity and friction are considered.The folding wing’s dynamics and structural strength are simulated comprehensively.The results show that the present method can simulate the shearing process of the positioning pin,the locking action and the unfolding process of the wing.As a result,the data of motion parameters are obtained,and the phenomenon of overshoot and vibration of the folding wing caused by large impact load and the structural elasticity after the wing fully deploys is observed.Therefore,the engineering design of the folding wing must satisfy the requirement of rapid deployment movement,and need to increase the structural strength to suppress the overshoot and vibration.This study may provide a reference for engineering design of the folding wing deployment mechanism.