Accession Number:

ADA135603

Title:

Investigation of the Effect of Blade Sweep on Rotor Vibratory Loads.

Descriptive Note:

Contractor rept.,

Corporate Author:

BOEING VERTOL CO PHILADELPHIA PA

Personal Author(s):

Report Date:

1983-10-01

Pagination or Media Count:

134.0

Abstract:

The effect of helicopter rotor blade planform sweep on rotor vibratory hub, blade, and control system loads has been analytically investigated. The importance of sweep angle, sweep initiation radius, flap bending stiffness and torsion bending stiffness is discussed. The mechanism by which sweep influences the vibratory hub loads is investigated. Author

Subject Categories:

  • Helicopters
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE