扑翼非定常运动对平尾影响及俯仰力矩特性研究

为了研究微型扑翼飞行器尾流对其平尾设计、飞行器稳定性以及飞行控制的影响,选取微型扑翼飞行器ASN-211为原模型,采用将其简化为二维的前后串列翼模型进行具体计算和分析。首先以Fluent动网格技术为背景,在用户自定义函数控制扑翼的非定常运动条件下进行不可压、非定常二维流动的计算,并研究在扑翼非定常运动条件下的模型的俯仰力矩特性。然后通过计算不同来流攻角、扑翼扑动频率、扑翼与平尾间距以及不同力矩中心下扑翼、平尾及总的力矩系数,讨论各个参数对力矩特性的影响。最后得出不同的扑翼扑动频率以及扑翼与平尾间距将会对平尾与扑翼的俯仰力矩间的相位差产生影响,所得结论为扑翼飞机的重心布置设计提供参考。

Influences of Flapping Wing’s Unsteady Motion to the Horizontal Tail and Discussion of Pitching Moment Characters

In order to investigate the wake impact of flapping wing micro aerial vehicle on the design of its horizontal tail,stability and control system,the ASN211 model,which is a flapping wing micro aerial vehicle,is applied as the original model.The 2D simplified model with in-tandem airfoil of the ASN211 is computed and analyzed.Firstly,in the context of the dynamic mesh of Fluent,with the motion of the flapping wing controlled by the User-Defined Function（UDF）,computation is done on the 2D model under incompressible,unsteady conditions.The moment performance of the model is studied when the flapping wing is flapped unsteadily.Then total moment coefficient of the flapping wing and horizontal tail is computed with different angles of attack,flapping frequencies,distances from flapping wing to horizontal tail and centers of moment.The parameter effect on the moment performance of the model is discussed.Finally,It is concluded that different flapping frequencies and the distances from flapping wing to the horizontal tail will affect the phase displacement in the moment curve of the flapping wing and the horizontal tail.These conclusions would help to arrange the center of gravity in flapping wing micro aerial vehicle in the future.