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Hingeless helicopter rotor with improved stability (1976)

Ormiston, R. A. ; Peters, D. A. ; Hodges, D. H. ; [et al.]

In: CASI

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Publication Date: 2019-06-27

Description: Improved stability was provided in a hingeless helicopter rotor by inclining the principal elastic flexural axes and coupling pitching of the rotor blade with the lead-lag bending of the blade. The primary elastic flex axes were inclined by constructing the blade of materials that display non-uniform stiffness, and the specification described various cross section distributions and the resulting inclined flex axes. Arrangements for varying the pitch of the rotor blade in a predetermined relationship with lead-lag bending of the blade, i.e., bending of the blade in a plane parallel to its plane of rotation were constructed.

Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE

Format: application/pdf

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