Aircraft rudder thermal compensation linkage

Details Aircraft rudder thermal compensation linkage Aircraft rudder thermal compensation linkage

1987-06-24

1989-09-05

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft control

Pilot operated

244230, 745015R, 74469, B64C 1338

Patent

active

048631221

ABSTRACT:
A rudder control linkage having thermal compensation features employs a stationary thermal compensation rod, a lever with a fixed pivot, a reversing link with a movable pivot, a summing link, pilot and yaw damper input rods, and output rods. In an airplane having a fin and a rudder, the linkage is utilized to cancel undesired yaw inputs to the rudder caused by fin bending and differential thermal expansion which, if not corrected, would deleteriously affect airplane trim.

REFERENCES:
patent: 2395261 (1946-02-01), Findley
patent: 2899152 (1959-08-01), Wieland
patent: 3236478 (1966-02-01), Adams et al.
patent: 3327552 (1967-06-01), Broders et al.
patent: 3396597 (1968-08-01), Dean
patent: 3478990 (1969-11-01), Kaniuka
patent: 4243189 (1981-01-01), Ohgi

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