基于多体动力学的直升机桨叶特性仿真分析  

Simulation of helicopter blade characteristics based on multi-body dynamics

作　　者：贺继林[1,2] 谭耀[1] 马云荣[1] 徐雷[1] 

机构地区：[1]中南大学高性能复杂制造国家重点实验室,长沙410083 [2]山河智能装备股份有限公司国家级企业技术中心,长沙410100

出　　处：《科技导报》2015年第2期45-48,共4页Science & Technology Review

基　　金：湖南省重大科技成果转化项目(2012CK1003)

摘　　要：针对无人直升机旋翼桨叶性能改进升级的实际需求,以200 kg级无人机旋翼为原型建模,利用COMOSOL软件对直升机桨叶特性进行仿真分析研究。基于叶素法建立了桨叶升力的数学模型,克服了常规旋翼动力学仿真分析时气动载荷加载棘手的难题;通过研究直升机桨叶的空间旋转运动与其弹性变形间的耦合关系,得出了桨叶攻角、升力、桨尖位移随总距以及周期变距的变化曲线。将仿真结果与常规数值分析结果比较,验证了仿真结果的准确性。根据仿真结果提出了对桨叶迎角、桨叶前缘刚度等的具体改进建议,可为桨叶的改进设计提供参考依据。In view of the actual demand in upgrading performance improvements for unmanned aerial vehicle blade, the 200 kg unmanned aerial vehicle rotor is used as the prototype model, and with the COMOSOL software, the characteristics of helicopter blades are simulated. The mathematical model of the blade lift is based on the blade element approach, to overcome aerodynamic loading headaches in the conventional rotor dynamics simulation analysis. The blade attack angle and lift, and the tip displacement against the total distance and the cycle variable pitch are obtained through the coupling relationship between the space rotation movement of the helicopter rotor blade and the elastic deformation, and the results are compared with those of the conventional numerical analysis. The accuracy of the simulation results is verified. According to the simulation results, specific suggestions for improvement of the blade angle, the blade leading edge stiffness etc. are made, that provides a reference for improving the design of the blade.

关 键 词：多体动力学 桨叶特性 直升机 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]