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
收藏
页码：7 / 16
相关论文
共 50 条
  • [1] Helicopter aeroelastic analysis with spatially uncertain rotor blade properties
    Murugan, Senthil
    Chowdhury, R.
    Adhikari, S.
    Friswell, M. I.
    AEROSPACE SCIENCE AND TECHNOLOGY, 2012, 16 (01) : 29 - 39
  • [2] Aeroelastic stability analysis of helicopter rotor blade with swept tips
    Yang, Wei-Dong
    Deng, Jing-Hui
    Nanjing Hangkong Hangtian Daxue Xuebao/Journal of Nanjing University of Aeronautics and Astronautics, 2003, 35 (03): : 248 - 252
  • [3] PROGRESSIVE FAILURE ANALYSIS OF HELICOPTER ROTOR BLADE UNDER AEROELASTIC LOADING
    Ahmad, Kamran
    Baig, Yasir
    Rahman, Hammad
    Hasham, Hassan Junaid
    AVIATION, 2020, 24 (01) : 33 - 41
  • [4] Aeroelastic analysis of a helicopter rotor in hover
    Sieradzki, A.
    XXIII FLUID MECHANICS CONFERENCE (KKMP 2018), 2018, 1101
  • [5] NUMERICAL OPTIMIZATION OF HELICOPTER ROTOR BLADE DESIGN FOR ACTIVE TWIST CONTROL
    Kovalovs, A.
    Barkanov, E.
    Gluhihs, S.
    AVIATION, 2007, 11 (03) : 3 - 9
  • [6] Induced shear actuation of helicopter rotor blade for active twist control
    Thakkar, Dipali
    Ganguli, Ranjan
    THIN-WALLED STRUCTURES, 2007, 45 (01) : 111 - 121
  • [7] Influence of Blade Geometric Parameters on Aeroelastic Response of a Helicopter Rotor System
    Laxman, Vaitla
    Venkatesan, C.
    Byun, Yung Hwan
    JOURNAL OF AEROSPACE ENGINEERING, 2013, 26 (03) : 555 - 570
  • [8] Stochastic Aeroelastic Analysis of Composite Helicopter Rotor
    Murugan, Senthil
    Ganguli, Ranjan
    Harursampath, Dinesh Kumar
    JOURNAL OF THE AMERICAN HELICOPTER SOCIETY, 2011, 56 (01)
  • [9] Aeroelastic analysis of a helicopter rotor in forward flight
    Buchtala, B
    Hierholz, KH
    Wagner, S
    HIGH PERFORMANCE COMPUTING IN SCIENCE AND ENGINEERING '99, 2000, : 327 - 330
  • [10] ACTIVE VIBRATION CONTROL OF A HELICOPTER ROTOR BLADE BY USING A LINEAR QUADRATIC REGULATOR
    Uddin, Md Mosleh
    Sarker, Pratik
    Theodore, Colin R.
    Chakravarty, Uttam K.
    PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION, 2018, VOL 1, 2019,
12345