Shock absorber for an aircraft landing gear leg

Details Shock absorber for an aircraft landing gear leg Shock absorber for an aircraft landing gear leg

1993-02-01

1994-05-10

Barefoot, Galen L.

Aeronautics and astronautics

Landing gear

Wheel

267 6416, B64C 2510

Patent

active

053101405

ABSTRACT:
The invention relates to a shock absorber for a landing gear leg, the shock absorber being of the type comprising a cylinder and a sliding rod, and including a disk that delimits a lower hydraulic fluid chamber which communicates via a diaphragm with an upper hydraulic fluid chamber adjacent to a pressurized gas chamber formed in the top portion of the cylinder. According to the invention, the sliding rod 102 is implemented in telescopic form, having an outer rod 131 and an inner rod 132 which bears directly against an intermediate partition 112 constituting the above-mentioned disk when the shock absorber is relaxed or under static load. The shock absorber also includes a linear actuator 150.1 received in the inner rod 132, and which, when triggered, serves to extend the landing gear providing the airplane is stationary or is moving slowly on the ground. Two scissors linkages 124 and 127 are also provided for conveying structural twisting forces.

REFERENCES:
patent: 2735634 (1956-02-01), Fosness
patent: 2933271 (1960-04-01), Maltby
patent: 3826450 (1974-07-01), Currey
patent: 3954232 (1976-05-01), Harper

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