作　　者： ; ;

机构地区： 西北工业大学

出　　处： 《西北工业大学学报》 1994年第4期509-513,共5页

摘　　要： 研究了飞机平尾结构模型存在失调时的振动模态局部化及频率曲线转向现象．运用常规摄动理论分析了两现象的产生机理及规律，提出了一个判断准则。计算实例验证了分析所得的结论。 In vibration analysis of aircraft horizontal tail there occur frequently mode localization and frequency loci veering. The necessary condition for such occurrences is the inevitable lack of completesymmetry of horizontal tail. UP to now, careful search by the authors has not discovered any studyin the open literature on the mechanism of such occurrences in aircraft horizontal tail. In this paper,such mechanism is studied and one criterion is given for predicting these occurrences.When ordinary perturbation method is applied to studying vibration of horizontal tail, it losescffcctivcncss under certain conditions. It is fortuitous that the criterion for determining its loss ofcffcctivcncss happens to be the criterion for predicting the occurrence of mode localization and frequency loci veering. Eq .(11), derived by the authors, is this criterion. It can be seen from Eq .(11) thatthe mechanism is: mode localization and frequency loci veering occur under the joint action of disorder (asymmetry) and weak coupling.For a specific aircraft horizontal tail, prediction of mode localization and frequency loci veeringby Eq.(11) is in good agreement with that obtained through numerica] calculation of characteristicsolutions of disordered system.

关 键 词： 局部化 曲线转向 飞机 平尾模型 模态分析 频率

领　　域： [航空宇航科学与技术] [航空宇航科学技术]