Shock absorbing method and apparatus

Aeronautics and astronautics – Landing gear – Wheel

Patent

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Details

188289, 188299, 267 64R, 267 65D, B64C 2558

Patent

active

040612953

ABSTRACT:
The damping coefficient and spring constant of shock absorbing struts for commercial jet aircraft landing gears are selected to allow optimum absorption of forces on the landing gears at touchdown for an aircraft that has been descending at the maximum permissible "sinkrate" (descent rate immediately prior to touchdown). When so selected, the shock absorbing struts are unable to effectively dampen vertical oscillations of the aircraft body ensuing from a downward plunging of the weight of the aircraft due to the deployment of lift spoilers immediately after touchdown. To rapidly attenuate these post-touchdown vertical oscillations (for more efficient braking and ground handling), while still affording the proper spring constant and damping coefficient necessary for absorbing touchdown impact forces at maximum "sinkrate", the damping of each shock strut is substantially increased after the first cycle of strut compression and re-extension by automatically sensing the occurrence of touchdown, and after a predetermined time delay therefrom, actuating a damping control within each shock strut, to change the damping coefficient to an increased level.

REFERENCES:
patent: 3039566 (1962-06-01), Rumsey
patent: 3458016 (1969-07-01), Keech
patent: 3653613 (1972-04-01), Palmer et al.
patent: 3743222 (1973-07-01), Smith

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