Vibration damping arrangement for aircraft

Details Vibration damping arrangement for aircraft Vibration damping arrangement for aircraft

1991-08-01

1993-04-20

Focarino, Margaret A.

Aeronautics and astronautics

Aircraft control

244215, B64C 1316

Patent

active

052035247

ABSTRACT:
An arrangement and method for damping induced fundamental vibrations in an aircraft high lift device (3) are provided. The arrangement includes a wing (2), a high lift device (3) mounted upon and movable along a pre-determined path with respect to the wing between a stowed cruise position and an extended high lift position, a track beam (8) interconnecting the wing and the high lift device (3), and a damping device (15) interconnecting the track beam and said wing and the track beam (8) pivotally connected to the wing (2) and including a trackway (20) for sliding interconnection with the high-lift device (3) such that while the high lift device (15) operates within acceptable vibrational tolerances the damping device is isolated but induced fundamental vibrations will cause angular displacement of the track beam (8) inducing a reactive force in the the damping device (15) to substantially nullify the fundamental vibrations.

REFERENCES:
patent: 2332516 (1943-10-01), Kemmer
patent: 2342578 (1944-02-01), Giannini
patent: 2471857 (1949-05-01), Bleakney et al.
patent: 4651955 (1987-03-01), Krafka
patent: 4705236 (1987-11-01), Rudolph
patent: 4763862 (1988-08-01), Steinhauer et al.

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