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Control Loads and Their Effects on Fuselage Vibrations

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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

More about this publication?
  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

    Journal subscribers who are AHS members log in here if you are not already logged in.

    Authors can find submission guidelines and related information on the AHS website.


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