无人机折叠尾翼机构性能分析及改进设计

Performance analysis and improved design of unmanned aerial vehicle folding empennage mechanism

为检验无人机折叠尾翼机构的性能,分别基于拉格朗日方程和有限元方法建立尾翼展开机构的运动微分方程和有限元数值仿真模型,两种方法求解得到的尾翼展开运动规律吻合较好。在此基础上,分析得出折叠尾翼原设计方案的展开时间满足设计要求,但冲击载荷超过了设计指标。最后从功能关系出发,改进了展开机构驱动转矩的加载方法,改进后的方案满足了设计要求。

In order to verify the performance of folding empennage mechanism of certain Unmanned Aerial Vehicle（UAV）,differential equation of motion and finite element numerical simulation model of the empennage unfolding mechanism were established based on Lagrange＇s Equation and Finite Element Method respectively.The results of folding empennage unfolding motion law solved by using these two methods agree well.On basis of this,it was found through analysis that empennage unfolding time of the original design can meet the design requirement,but the impact load exceeds the design index.Finally,starting from relationship between work and energy,the loading method of driving torque of the unfolding mechanism was improved,the improved scheme can satisfy the design requirements very well.