Aeroelastic analysis of a helicopter rotor blade with active impedance control at the root

被引：0

作者：

Nitzsche, F. ^{[1
]}

机构：

[1] Mechanical and Aerospace Engineering, Carleton University, 1125 Colonel By Drive, Ottawa, Ont. K1S 5B6, Canada

来源：

Canadian Aeronautics and Space Journal | 2001年 / 47卷 / 01期

关键词：

Acoustic impedance - Aerodynamic loads - Boundary conditions - Degrees of freedom (mechanics) - Dynamic response - Frequency domain analysis - Mathematical models - Turbomachine blades;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

In the present investigation, the helicopter blade is modelled as a rotating beam with two degrees of freedom, namely the elastic flatwise bending and torsion. A mathematical model in the frequency domain is developed, incorporating the incompressible unsteady aerodynamic loads associated with helicopters in forward flight. The effects of dynamic adaptation of the root boundary conditions on the beam aeroelastic response are studied. The results suggest that it is possible to control the local dynamic response at particular sections of the blade by varying the frequency and relative phase of the control signal.

引用

页码：7 / 16

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