The Boeing Vertol YUH‐61A tail rotor is a new, completely bearingless flexstrap design which uses fiberglass composite blades and straps to achieve significant gains in simplicity and survivability. This paper describes the design process by which such gains were made, with emphasis
an new approaches used to assure aeroelastic stability. The discussion covers theoretical methods, reduced‐scale model testing, full scale isolated rotor testing, and testing on the prototype aircraft.This rotor is unique in incorporating blade sweep and tip weight to achieve flap‐lag
stability in a “stiff inplane” design (first inplane modal frequency above one per rev). These features provide stability by improving flap‐lug couplings, making it unnecessary to separate the frequencies of the flap and inplane modes to avoid flap‐lag instability.
The resulting freedom of modal placement yields valuable design benefits.
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Document Type: Research Article
Boeing Vertol Company, Philadelphia, Pennsylvania
Publication date: 1978-04-01
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