Hostname: page-component-cd9895bd7-gxg78 Total loading time: 0 Render date: 2024-12-22T15:32:28.991Z Has data issue: false hasContentIssue false
  • English
  • Français

The control of vibration in helicopters

Published online by Cambridge University Press:  04 July 2016

D. E. H. Balmford
D. E. H. Balmford*
Affiliation:
Westland Helicopters Limited
Get access Rights & Permissions [Opens in a new window]

Extract

The problems involving vibration which affect helicopters can be divided into two major categories:

  • (a)Forced vibration effects

  • (b)Aeroelastic and aeromechanical instabilities.

Forced vibration effects are subdivided into two categories.

  • (i)Effects due primarily to aerodynamic forcing; and

  • (ii)Effects due primarily to mechanical forcing.

Forced vibration effects have important repercussions in the area of:

  • (i)Crew comfort and efficiency

  • (ii)Fatigue strength of dynamic components and the airframe

  • (iii)Reliability of electronic equipment.

The most important forcing effect is aerodynamic in origin, and this will be considered first.

Type
Research Article
Information
The Aeronautical Journal , Volume 81 , Issue 794 , February 1977 , pp. 63 - 67
Copyright
Copyright © Royal Aeronautical Society 1977 

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.)