Hydraulic nose landing gear steering actuator for an airplane

Details Hydraulic nose landing gear steering actuator for an airplane Hydraulic nose landing gear steering actuator for an airplane

1979-02-26

1981-05-05

Frankfort, Charles E.

Aeronautics and astronautics

Aircraft propulsion and steering on land or water

92122, B64C 2550

Patent

active

042654173

ABSTRACT:
A hydraulic aircraft nose landing gear steering actuator includes a coaxial stator and rotor ring assembly mounted on the fixed outer cylinder of a nose landing gear shock absorber strut. Hydraulic vanes protruding radially inwardly and outwardly from the rotor and stator, respectively, form semi-annular pressure chambers between the stator and rotor rings which may be selectively hydraulically pressurized. A torsion link connects the steering actuator to the landing gear wheels. The steering actuator is capable of providing a constant steering torque to the landing wheels over a total steering displacement angle of approximately 150.degree..

REFERENCES:
patent: 2550180 (1951-04-01), Allen
patent: 2854956 (1958-10-01), Hager
patent: 3052912 (1962-09-01), Bishop
patent: 3188023 (1965-06-01), Dowty et al.

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