Rotorcraft fuselage modal frequency placement using resilient mo

Details Rotorcraft fuselage modal frequency placement using resilient mo Rotorcraft fuselage modal frequency placement using resilient mo

1994-05-11

1997-06-24

Kashnikow, Andres

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

244117R, 244131, 267141, 248557, B64C 2735

Patent

active

056411332

ABSTRACT:
The present invention provides a desired design approach for retuning a rotorcraft airframe by utilizing resilient connections between major airframe components. In the preferred embodiment, the design employs resilient material, preferably elastomeric material, in the mounting system between the vertical tail and the tailboom of a helicopter as a method of providing dynamic detuning of the tailboom torsion/lateral mode. Other possibilities include similarly mounting the horizontal stabilator and the wing onto the airframe. Using elastomeric or similar devices to soft mount the vertical tail of a helicopter on the tailboom can efficiently and effectively alter the natural frequencies of the entire aircraft. By choosing the spring constant of this connection, the designer can place fuselage frequency at a desired value.

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