Control Loads and Their Effects on Fuselage Vibrations
Abstract:With the increasing forward velocities of advanced helicopter and compound designs, the magnitude of the rotor control feedback loads increases to the point where omission of these loads in helicopter vibration analyses is no longer justified. This subject is approached by first discussing the aerodynamic and dynamic sources of control loads. Two effects not previously considered are included in these discussions; namely (a) the effect of the tip vortex, and (b) the effect of airfoil contour deviations due to practical manufacturing tolerances. Methods for contour correction are also discussed.
Document Type: Research Article
Affiliations: Bell Helicopter Company, Fort Worth, Texas
Publication date: October 1, 1967
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