Full authority fly-by-wire pedal system

• US 7,806,372 B2
• Filed: 12/01/2009
• Issued: 10/05/2010
• Est. Priority Date: 02/15/2006
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Boczar, Bruce, Witiak, Peter T., Stiles, Lorren
• Primary Examiner(s): Dinh; Tien
• Assistant Examiner(s): Sanderson; Joseph W
• Application Number:
  US12/628,269
• Publication Number:
  US 20100078524A1
• Time in Patent Office: 308 Days
• Field of Search: 244/220, 244/221, 244/223, 244/227, 244/228, 244/235, 244/236
• US Class Current: 244/223
• CPC Class Codes: B64C 13/044 operated by feet, e.g. pedals
• CPC Class Codes: B64C 13/507 with artificial feel
• CPC Class Codes: B64C 27/56 characterised by the control initiating means, e.g. manually actuated
• CPC Class Codes: B64C 27/68 using electrical energy, e.g. having electrical power amplification
• CPC Class Codes: B64C 27/78 in association with pitch adjustment of blades of anti-torque rotor
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 74/20528 Foot operated
• CPC Class Codes: Y10T 74/20888 Pedals
• CPC Class Codes: Y10T 74/209 Extension

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.

Claims

1. A method of controlling a yaw axis of a rotary-wing aircraft comprising the steps of:

(A) maintaining stability and coordination through a fly-by-wire flight control system; and

(B) receiving a pilot yaw control input only when a change in a yaw axis state is demanded, and providing the pilot yaw control input through a double gradient force feedback pedal dynamic for control of an anti-torque system.

2. The method as recited in claim 1, wherein said step (B) further comprises:

(a) providing the double gradient pedal dynamic through a pedal system having a compact travel.

3. The method as recited in claim 1, wherein said step (B) further comprises:

(a) providing a first resistance for a first travel of the pilot yaw control input; and

(b) providing a second resistance less than the first resistance for travel of the pilot yaw control input beyond the first travel.