Shock strut

Details Shock strut Shock strut

1990-05-14

1992-02-04

Graham, Matthew C.

Spring devices

Vehicle

Comprising compressible fluid

267 6413, 188269, B60G 1904

Patent

active

050854127

ABSTRACT:
A cylinder housing an oil chamber and a piston housing a pair of concentric gas chambers define a telescopingly compressible shock strut. Upon compression of the shock strut, oil under pressure flows from the oil chamber into a compartment defined in part by a floating piston of one of the gas chambers to urge translation of the floating piston if the pressure exerted is above a first threshold and to compress the gas within the chamber. When the oil under pressure exceeds a second threshold, a floating piston of the other of the gas chambers and forming a part of the compartment is urged to translate and to compress the gas in the other gas chamber. A relief valve associated with each gas chamber relieves pressure therein above a further threshold.

REFERENCES:
patent: 1179253 (1916-04-01), Westinghouse
patent: 1596444 (1926-08-01), Morinelli
patent: 1718700 (1929-06-01), Luoma
patent: 3056598 (1962-10-01), Conway et al.
patent: 3083000 (1963-03-01), Perdue
patent: 3888436 (1975-06-01), Sealey
patent: 4054311 (1977-10-01), Gute
"Final Report Active Control Landing Gear--Landing Gear Shock Strut Pressure Management Valve", James C. Warrick, U.S. Army Aviation Research and Technology Activity (AVSCOM), TR-86402, pp. 1-47).
"Military Standard Light Fixed and Rotary-Wing Aircraft Crash Resistance" Department of Defense, MIL-STD-1290A(AV), 26 Sep. 1974, pp. 1-39.
"Military Specification Tests, Impact, Shock Absorber Landing Gear, Aircraft", U.S. Air Force, MIL-T-6053C(USAF), 1 Mar. 1984, pp. 1-15.
"FIG. 1. UH-60A Main Landing Gear", United Technologies, Sikorsky Aircraft 28 Nov. 1978, Document No. SER 70174, pp. II-6.

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