Bell Helicopter Textron Inc.

Textron Innovations Inc.

John Joseph Schillings

Charles Eric Covington

Robert Earl Worsham, Ii

Ashok K Agnihotri

Shyhpyng Jack Shue

Robert L Fortenbaugh

Jimmy Charles Narramore

Helmuth Koelzer

Robert Fortenbaugh

Robert Earl Worsham

The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.

System and method for automation of rotorcraft entry into autorotation and maintenance of stabilized autorotation

Systems and method for automation of rotorcraft entry into autorotation and maintenance of stabilized autorotation

A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition.

Extension of three loop control laws for system uncertainties, calculation time delay and command quickness

One embodiment of the present invention is a main rotor helicopter blade for generating higher lift with less drag and delaying stall at high Mach numbers. A cross-section of this blade includes aft camber. The difference between a chord line of the cross-section and a camber line of the cross-section increases from a leading edge of the cross-section to a maximum between a trailing edge of the cross-section and a midpoint of the chord line and decreases to the trailing edge producing the aft camber of the blade. The aft camber generates higher lift with less drag and delays stall at high Mach numbers.

High performance low noise rotorcraft blade aerodynamic design

A method and system for optimizing rotor flapping utilizes the collective stick position and true airspeed to determine a commanded longitudinal stick position.

Method and apparatus for improving main rotor yoke fatigue life

Growing community of inventors

Fort Worth, TX, United States of America

John Joseph Schillings