直升机旋翼不平衡复合故障对机体振动的影响  

Influence of Helicopter Rotor Multiple Imbalance Faults on Fuselage Vibrations

作　　者：高亚东[1] 邓升平[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学重点实验室,南京210016

出　　处：《振动．测试与诊断》2011年第6期763-766,815,共4页Journal of Vibration,Measurement & Diagnosis

基　　金：直升机旋翼动力学重点实验室基金资助项目(编号:9140C4004010805)

摘　　要：在直升机旋翼不平衡单一故障试验研究的基础上,设计了桨叶后缘调整片不平衡、桨距不平衡和桨叶配重不平衡3种故障同时发生的复合故障试验,采用最大熵法估计了所采集的台体振动信号的功率谱。仿真测试表明,采用最大熵法进行功率谱估计,当与其等价的自回归模型阶数为100时,功率谱估计能充分反映台体振动信号的特征。利用正交设计方法进行复合故障试验设计并进行了风洞试验,选用L9(34)正交表,选取10m/s风速下的横向振动1Ω分量所对应的功率谱作为分析对象。分析结果表明,上述3种不平衡故障之间存在交互作用,其中桨距不平衡故障对机体振动水平的影响最为显著。Based on the single imbalance fault study on the helicopter rotor,three types of conventional blade faults,trim tab imbalance,pitch imbalance and mass imbalance,are simulated on a three-bladed rotor simultaneously.The power spectrum of vibration signals from fuselage is estimated by using the maximum entropy spectrum estimation.Simulation tests show that when the exponent of autoregression model equivalent to the maximum entropy method is 100,vibration signal features are clearly reflected by the power spectrum.Experiments on the helicopter rotor multiple imbalance faults are designed using the orthogonal experimental design method and are conducted in a wind tunnel.TheL9(34) orthogonal table is employed by selecting the fuselage vibrations corresponding to the weight of the lateral 1/rev vibration at the wind speed 10m/s.The results of orthogonal analysis show that the interaction among helicopter rotor multiple imbalance faults exists,of which the blade pitch imbalance has the chief effect on the fuselage vibrations.

关 键 词：直升机旋翼 复合故障 最大熵法 正交试验设计 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程] V216.21