Full authority fly-by-wire pedal system
AssigneeSikorsky Aircraft Corporation
InventorsBruce Boczar, Lorren Stiles, Peter T. Witiak
Life of this patent
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Abstract
A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs.
Claims7
A pedal system for a rotary-wing aircraft comprising:
- a port pedal and a starboard pedal linked to a support structure through a crank assembly, said crank assembly pivotable relative said support structure about a support axis;
- a double gradient linkage assembly linked to said port pedal and said starboard pedal to provide a double gradient force feedback pedal dynamic for control of an anti-torque system;
- a pushrod attached between said crank assembly and a main pivot crank of said double gradient linkage assembly, said main pivot crank pivotable about a pivot axis non-parallel to said support axis;
- and
- a fly-by-wire input pivotally connected to an end segment of said main pivot crank at an input axis opposite said pushrod axis.
Dependencies are inferred from the claim text.