Automatic shrink shock strut for an aircraft landing gear

Details Automatic shrink shock strut for an aircraft landing gear Automatic shrink shock strut for an aircraft landing gear

1997-11-01

1999-06-01

Barefoot, Galen

Aeronautics and astronautics

Landing gear

Retractable

B64C 2518

Patent

active

059081740

ABSTRACT:
An automatic shrink shock strut for use in conjunction with aircraft landing gear. The landing gear is of the type which includes a shock strut cylinder and a shock strut piston mounted coaxially therewith, and defining there between a shock strut shrink chamber filled with hydraulic fluid and a gas spring chamber filled with a pressurized gas. During retraction of the landing gear, the mechanism transfers the pressurized gas from the gas spring chamber to a transfer cylinder and therein drives a volume of hydraulic fluid from a hydraulic fluid supply in the transfer cylinder to the shock strut shrink chamber. The shock strut responds by shrinking to a shortened length. During extension of the landing gear the mechanism returns works in reverse and returns the pressurized gas to the gas spring chamber to drive the volume of hydraulic fluid from the shock strut shrink chamber back to the hydraulic fluid supply, thereby extending the landing gear to its normal length.

REFERENCES:
patent: 1918426 (1933-07-01), Randor
patent: 2186266 (1940-01-01), Onions
patent: 2390661 (1945-12-01), Parilla
patent: 4291850 (1981-09-01), Sharples

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