Pitch control trimming system for canard design aircraft

Details Pitch control trimming system for canard design aircraft Pitch control trimming system for canard design aircraft

B - Operations, Transporting

64

C

244/40, 244/59

B64C 17/00 (2006.01) B64C 13/00 (2006.01) B64D 27/08 (2006.01)

Patent

CA 2013236

ABSTRACT A pitch control trimming system for a canard design aircraft has the ability to reposition the center of gravity of the aircraft along the longitudinal axis. The design permits trimming of the aircraft without external trim tabs and permits flaps to be used on a canard design aircraft without forward pitching moment occurring. The aircraft has a substantial mass associated with the aircraft preferably the engine, which is movable substantially along the longitudinal axis of the aircraft, and includes an actuator to move the mass forward and aft on the longitudinal axis to reposition the center of gravity of the aircraft.

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