The problem of determining helicopter proneness to fatigue on the basis of safe fatigue life experiments and with the aid of devices indicating crack initiation is considered. Problems resulting from resonance due to lack of blade stiffness are discussed, as well as problems of helicopter vibration and rotor transmission operation, and also problems resulting from failure of the hydraulic system.

  • Availability:
  • Corporate Authors:

    Royal Aeronautical Society

    4 Hamilton Place
    London S1V 0BQ,   England 
  • Authors:
    • Le Sueur, H E
  • Publication Date: 1978-10

Media Info

  • Pagination: p. 411-416
  • Serial:
    • Aeronautical Journal
    • Volume: 82
    • Issue Number: 814
    • Publisher: Royal Aeronautical Society
    • ISSN: 0001-9240

Subject/Index Terms

Filing Info

  • Accession Number: 00196058
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Files: TRIS
  • Created Date: Aug 15 1979 12:00AM