Two-axis rudder trim for aircraft

Details Two-axis rudder trim for aircraft Two-axis rudder trim for aircraft

1982-09-29

1984-04-03

Blix, Trygve M.

Aeronautics and astronautics

Aircraft control

Rudders and empennage

244 91, B64C 510

Patent

active

044403623

ABSTRACT:
A swivel-mounted trim element of a predetermined configuration for use with aircraft for the purpose of providing additional control in flight. The trim element is mounted immediately to the rear of a channel-shaped stabilizer mounted externally or molded into the fuselage of an aircraft and is especially suited for small aircraft, particularly those having V-surface tail assemblies. The trim element configuration is generally right-angled with the base portion being additionally formed to have a downwardly-canted portion at the leading edge and an inwardly-canted portion at the trailing edge. In operation, the trim element provides two-axis rudder trim about both the pitch and yaw axis.

REFERENCES:
patent: 1883758 (1932-10-01), Brandt
patent: 2074765 (1937-03-01), Adams
patent: 2999657 (1961-09-01), Clark
patent: 3442472 (1969-05-01), Kalina
patent: 4264043 (1981-04-01), Walker
patent: 4373689 (1983-02-01), Walker

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