缓冲支柱充气压力对机体模态特性影响分析  

Analysis of The Influence of Inflation Pressure of Buffer Pillar on The Modal Characteristics of Helicopter

作　　者：宋山松 胡国才 刘湘一 SONG Shan-song;HU Guo-cai;LIU Xiang-yi(Aeronautical Foundation College,Naval Aviation University,Yantai Shandong 264001,China)

机构地区：[1]海军航空大学航空基础学院,山东烟台264001

出　　处：《计算机仿真》2020年第2期66-71,共6页Computer Simulation

摘　　要：为研究双腔式缓冲支柱充气压力对直升机机体模态特性的影响,在缓冲支柱参数不完备的情况下,先通过利用已有的静力试验数据对缓冲支柱参数进行识别,根据缓冲支柱动刚度试验的原理进行动刚度仿真计算,并确定动刚度仿真计算时γ的取值应为1.4。改变缓冲支柱高低压腔的充气压力,并由仿真计算得到充气压力变化后缓冲支柱的静压缩力和动刚度,由此可进行机体模态特性的计算。结果表明,缓冲支柱充气压力变化时,机体侧向一阶模态频率在0.85Hz^1.00Hz范围内变化,而机体其它各阶模态频率的变化并不显著,说明缓冲支柱充气压力对机体模态特性的影响不大。In order to study the effect of the inflation pressure of double-cavity buffer pillar on helicopter modal characteristics,the parameters of the buffer pillar are identified by using the existing static data under the condition of incomplete parameters of the buffer pillar,and then the dynamic stiffness is simulated according to the principle of the dynamic stiffness test of the buffer pillar.The value of γ should be 1.4 when the stiffness is simulated.The static compressive force and dynamic stiffness of the buffer pillar can be obtained by changing the inflation pressure of the high and low pressure chambers of the buffer pillar.The results show that the first-order lateral modal frequency varies in the range of 0.85~1.00Hz with the change of the inflation pressure of buffer pillar,while the other modal frequencies do not change significantly,which indicats that the inflation pressure of buffer pillar has little effect on the modal characteristics of the helicopter.

关 键 词：双腔式缓冲支柱 充气压力 机体模态 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程] V275