摘要
为使后缘襟翼型智能旋翼达到最佳的减振效果,本文建立了两种模型方法对智能旋翼驱动机构的关键设计参数——驱动力臂进行了探讨。一方面基于CFD、CAMRADⅡ和ABAQUS联合仿真的方法,建立了机电耦合多体系统有限元模型;另一方面基于襟翼变形前后的几何关系分析,建立了更为简化的几何模型。最后通过对智能旋翼桨叶的驱动性能静态试验来验证模型。测试结果表明,有限元仿真结果与试验结果一致,几何模型与有限元模型得到的襟翼最大偏角的误差不超过6%。因此,本文所建立的有限元模型分析法和几何模型分析法可以为后缘襟翼型智能旋翼结构详细设计和初步设计中驱动力臂的参数选择提供有效参考。
In order to improve trailing edge flap rotor＇ s vibration reduction effect, two models were established to study driving arm which is the key parameter of smart rotor driving mechanism. On the one hand, a electromechanical coupling and multibody system FEM model of the driving mechanism was developed, which was based on co-simulation using CFD, CAMRADII and ABAQUS. On the other hand, a more simplified geometric model was built, which was based on analyzing the deformation contrast of trailing edge flap. Finally a simple smart rotor driving performance static test was conducted to confirm the model, the result of driving performance static test indicates that the FEM model result has better tally with test result. The result of two model contrastive analysis indicates that the relative error of the max flap deflection angle is not more than 6%.Thus the FEM model and the geometric model built in the paper can provide effective reference for driving arm parameter selection at the stage of smart rotor detail design and the stage of preliminary design.
作者
高乐
胡和平
宋彬
孟微
Gao Le;Hu Heping;Song Bin;Meng Wei(Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen 333001, China)
出处
《航空科学技术》
2018年第5期43-49,共7页
Aeronautical Science & Technology
