Hostname: page-component-7479d7b7d-68ccn Total loading time: 0 Render date: 2024-07-09T07:30:45.723Z Has data issue: false hasContentIssue false
  • English
  • Français

‘A Theoretical Approach to some Rotor Blade Flutter and Forced Vibration Problems’

Published online by Cambridge University Press:  26 October 2023

W E Hooper
W E Hooper*
Affiliation:
Bristol Aircraft Ltd
Get access

Extract

A method for predicting the flutter boundaries of a helicopter rotor blade is developed which is intended to provide

  1. (a) an illustration of the effects of fundamental characteristics of the blade on the flutter boundaries, e g, mass axis location, flexural axis location, stiffness of control circuit, etc

  2. (b) a basic approach which may be developed and expanded to provide more detailed representation of any particular blade problem For example, in addition to giving the flutter boundaries for the blade, the equations in the form presented could be used to determine the response of the rotor blade to force distributions which are simple harmonics of the rotor angular velocity Another example is given at the end of this report in which the familiar blade resonance diagram is obtained for the torsion and flapping modes considering dynamic and stiffness properties only, and then again for the blade including the effect of aerodynamic damping

Type
Cierva Memorial Essay Competition, 1957
Information
The Journal of the Helicopter Association of Great Britain , Volume 12 , Issue 6 , December 1958 , pp. 282 - 307
Copyright
Copyright © Royal Aeronautical Society 1958

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1 Yntema, R T “Simplified Procedures and Charts for the Rapid Estimation of Bending Frequencies of Rotating Beams”—Figs 25 and 26, NACA TN 3459Google Scholar
2 Scanlan, and Rosenbaum, “Introduction to the Study of Aircraft Vibration and Flutter” Macmillan Co, New York Page 133Google Scholar
3 Templeton, H “The Technique of Flutter Calculation” Royal Aircraft Establishment Report—Structures 142 1953Google Scholar
4 Broadbent, E G “Note on the preparation of Coefficients for the R A E Flutter Simulator” Royal Aircraft Establishment Internal Memorandum No Structures 200 1953Google Scholar
5 Payne, P R “A General Theory of Helicopter Rotor Dynamics” Aircraft Engineering, August, 1954CrossRefGoogle Scholar
6 Kennedy, C C and Pancu, C D P “Use of Vectors in Vibration Measurement and Analysis” Journal of the Aeronautical Sciences, Vol 14, No 11, November, 1947CrossRefGoogle Scholar
7 Broadbent, E G and Hartley, E V “Vectorial Analysis of Flight Flutter Test Results” R A E Technical Note No Structures 233 February, 1958Google Scholar
8 Gessow, A and Myers, G C “Aerodynamics of the Helicopter” Macmillan, New YorkGoogle Scholar