Patent ID: 7874526
Filing Date: 2011-01-25
Classification: B64C,Y02T,Y10T

Abstract:
1. 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.