动载荷下直升机的动特性分析  

THE DYNAMIC BEHAVIOUR ANALYSIS OF HELICOPTER UNDER DYNAMIC LOAD

作　　者：姚国凤[1] 李守魁[1] 高雪飞[1] 梁静文[1] 

机构地区：[1]吉林大学南岭校区机械科学与工程学院力学系,长春130025

出　　处：《固体力学学报》2008年第S1期85-89,共5页Chinese Journal of Solid Mechanics

基　　金：吉林大学"985工程"汽车工程科技创新平台资助;吉林省科技引导计划项目(20080540)资助

摘　　要：直升机机体的振动水平是评定直升机性能的一项重要指标,直升机的强烈振动会严重影响直升机的各种性能、安全、寿命等。本文针对直升飞机在空中停泊,人员在机内走动,上人下人,吊起重物或投递重物等重心的移动及质量的变化等因素,研究直升飞机在飞行过程中受到各种激励情况下,采取何种控制方法保证关键部位对应的频率和模态保持在安全变化范围之内。针对直升机的使用条件,对轴线载荷、边梁载荷、轴线对称载荷三种不同工况以及非对称结构下,移动质量载荷对机身结构的影响进行模拟计算。本文的分析结果为机身结构的动力学分析提供了经验,为直升机进行实机试验的测点分布提供参考。The vibration level of helicopter body is an important index to estimate the performance of the helicopter, and the fierce vibration will strictly influence the helicopter’s functions, safety and longevity. This paper has studied the vibration frequency and mode shape of the airframe in condition of the change of location and mass as well as the excitation of other exterior load.We establish the FEM model of the helicopter airframe and then calculate the eigenvalues and eigenvectors. The first 15 natural frequencies of the mainframe are picked up and the corresponding vibration mode shapes are analyzed. Finally, we make simulating computation for the load on axial line, side girder and positions of axial symmetry respectively.The analysis results of this paper provide experience for the dynamics analysis of the airframe structure, and provide conference for the distribution of the testing points when undertaking actual test for the helicopter.

关 键 词：直升机动态行为 模态分析 动载荷 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]