Patents by Inventor Peter T. Witiak

Peter T. Witiak has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Full authority fly-by-wire pedal system
    Patent number: 7874526
    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.
    Type: Grant
    Filed: December 1, 2009
    Date of Patent: January 25, 2011
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Bruce Boczar, Lorren Stiles, Peter T. Witiak
  • Full authority fly-by-wire pedal system
    Patent number: 7806372
    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.
    Type: Grant
    Filed: December 1, 2009
    Date of Patent: October 5, 2010
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Bruce Boczar, Lorren Stiles, Peter T. Witiak
  • FULL AUTHORITY FLY-BY-WIRE PEDAL SYSTEM
    Publication number: 20100078524
    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.
    Type: Application
    Filed: December 1, 2009
    Publication date: April 1, 2010
    Inventors: Bruce Boczar, Lorren Stiles, Peter T. Witiak
  • FULL AUTHORITY FLY-BY-WIRE PEDAL SYSTEM
    Publication number: 20100072322
    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.
    Type: Application
    Filed: December 1, 2009
    Publication date: March 25, 2010
    Inventors: Bruce Boczar, Lorren Stiles, Peter T. Witiak
  • Full authority fly-by-wire pedal system
    Patent number: 7644893
    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.
    Type: Grant
    Filed: February 15, 2006
    Date of Patent: January 12, 2010
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Bruce Boczar, Lorren Stiles, Peter T. Witiak