直升机小速度前飞状态下的振动机理研究  

Research on the Mechanism of Vibration of the Helicopterin Low Advance Ratio

作　　者：余瑾 李建伟 金坤健[1] 黄珺[1] YU Jin;LI Jianwei;JIN Kunjian;HUANG Jun(China Helicopter Research and Development Institute,Jingdezhen 333001,China;Aviation and Military Representative Office in Jingdezhen District,Jingdezhen 333002,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]陆装驻景德镇地区航空军代室,江西景德镇333002

出　　处：《直升机技术》2024年第2期5-13,21,共10页Helicopter Technique

摘　　要：针对直升机在小速度前飞状态下振动偏大问题展开机理研究。采用自由尾迹模型计算小速度前飞状态下的旋翼桨涡干扰气动特征;推导了桨叶4自由度桨叶挥舞动力学结构有限元模型,以进行模态分析和结构参数影响分析;采用预定气动载荷法,建立桨叶挥舞动力学模型,分析桨叶结构动响应/载荷特征。研究结果表明,小速度状态下,气动载荷中桨涡干扰所致的频率为五倍旋翼转速的谐波成分是其振动问题的“外部”气动力源头;旋翼展向上根部大分布质量引起的惯性载荷是其振动问题的“内部”根源;两者的综合作用使得通过频率的旋翼动载荷高于基准旋翼,引起机体的异常振动。This paper addressed the mechanism of high vibration level of the helicopter in low advance ratio.The blade-vortex interaction characteristics of the blade aerodynamics were obtained by free wake model.This paper derived the 4-DOF element matrixes of the blade structure for the blade modal analysis and parametric study,the blade flap dynamics was established based on the prescribed air loads.The results showed that the blade-vortex interaction was the external source of the vibration,and concentrated mass near the blade root was the inner root of the vibration.

关 键 词：振动载荷 集中质量 桨涡干扰 旋翼 直升机 

分 类 号：V214.33[航空宇航科学与技术—航空宇航推进理论与工程]