无人直升机旋翼桨叶设计及动力学特性分析  

Rotor blade design and dynamic characteristics analysis of unmanned helicopter

作　　者：高洪波 邵天双 刘向楠 杨征 GAO Hongbo;SHAO Tianshuang;LIU Xiangnan;YANG Zheng(Low Speed High Reynolds Number Aeronautical Key Laboratory,AVIC Aerodynamics Research Institute,Harbin 150001,China;Aerodynamic Noise and Control Key Laboratory of Heilongjiang Province,AVIC Aerodynamics Research Institute,Harbin 150001,China)

机构地区：[1]航空工业空气动力研究院低速高雷诺数气动力航空科技重点实验室,哈尔滨150001 [2]航空工业空气动力研究院黑龙江省空气动力噪声及其控制重点试验室,哈尔滨150001

出　　处：《航空工程进展》2024年第3期151-156,190,共7页Advances in Aeronautical Science and Engineering

摘　　要：复合材料在桨叶上广泛应用的同时使桨叶的受力、刚度特性比传统的桨叶更为复杂。为了降低桨叶工作时动应力和旋翼的振动水平,有必要对旋翼桨叶进行动力学特性分析。对旋翼总体参数及桨叶气动参数进行设计,采用CFD方法对旋翼悬停状态进行气动特性分析,将桨叶三维非线性弹性模型分解为二维线性剖面模型和一维非线性梁模型进行动力学特性分析。结果表明:该旋翼能够成功拉起230 kg级无人直升机,悬停效率大于0.65,工作转速下桨叶的固有频率与8阶以下的气动激振力频率保持一定的范围,避开了转速共振区,满足桨叶动力学设计要求。The widespread application of composite materials in blades also makes the force and stiffness characteris⁃tics of blades more complex than traditional blades.In order to reduce the dynamic stress and vibration level of rotor blades,it is necessary to analyze the dynamic characteristics of rotor blades.The overall parameters of the rotor and the aerodynamic parameters of the blade are designed.The CFD method is used to analyze the aerodynamic charac⁃teristics of the rotor in hover.The three-dimensional nonlinear elastic model of the blade is decomposed into a twodimensional linear profile model and a one-dimensional nonlinear beam model for dynamic characteristics analysis.The results show that the rotor can successfully pull up the 230 kg unmanned helicopter,the hover efficiency is greater than 0.65,the natural frequency of the blade under the working speed keeps a certain range with the frequen⁃cy of the aerodynamic excitation force below the 8th order,avoid the speed resonance region and meet the require⁃ments of the blade dynamics design.

关 键 词：无人直升机 旋翼桨叶 悬停效率 气动特性 动力学特性 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]