Abstract: A control system having at least a first control loop and a second control loop for determining the upper and lower cyclic limit increments due to the contribution of collective pitch in rotorcraft based at least on nacelle angle and airspeed. The aircraft is more robustly controlled by generating flight control limits for the aircraft, modifying the flight control limits based upon impending hazardous flight conditions, and adjusting a size of a flight control envelope as the aircraft transitions between non-hazardous flight conditions and hazardous flight conditions.

Abstract: A control system having at least a first control loop and a second control loop for determining the upper and lower cyclic limit increments due to the contribution of collective pitch in rotorcraft based at least on nacelle angle and airspeed. The aircraft is more robustly controlled by generating flight control limits for the aircraft, modifying the flight control limits based upon impending hazardous flight conditions, and adjusting a size of a flight control envelope as the aircraft transitions between non-hazardous flight conditions and hazardous flight conditions.

Abstract: A control system having a series of control loops for determining the upper and lower cyclic limit increments due to the contribution of collective pitch in rotorcraft based at least on nacelle angle and airspeed.

Abstract: A method for operating an aircraft to prevent/recover from a stall condition includes the steps of detecting an actual vertical velocity of the aircraft, calculating vertical velocity error of the aircraft, the vertical velocity error being based upon a comparison between the actual vertical velocity of the aircraft and a commanded vertical velocity of the aircraft, and determining if the aircraft is in one of a near stalled condition and a stalled condition based upon at least the detected vertical velocity error and the polarity of the vertical velocity error. The method further includes the steps of taking control of the aircraft from an operator of the aircraft, reducing a bank angle of the aircraft, pitching the aircraft downward, and increasing the airspeed of the aircraft if the aircraft's airspeed is outside an airspeed window if the aircraft is in one of the near stalled condition and the stalled condition.

Abstract: A system to control flight of an aircraft includes a rotor blade, an actuator operably associated with the rotor blade, a controller operably associated with the actuator, and a flight control system. The flight control system having a subsystem adapted to modify a flight control limit of the aircraft based upon detection of an impending hazardous flight condition and a display showing available flight control limits provided by modification of design control limits based upon the detection of the impending hazardous flight condition. The method includes generating the control limits, modifying the control limits based upon the impending hazardous flight condition, and displaying the displacement of actuator position relative to the displayed control limits thus cueing the pilot as to the cyclic stick or pedal inputs required to increase the control margin from the impending hazardous condition.

Abstract: A control system having a series of control loops for determining the upper and lower cyclic limit increments due to the contribution of collective pitch in rotorcraft based at least on nacelle angle and airspeed.

Abstract: A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.

Abstract: A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.

Abstract: A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.

Abstract: A system to control flight of an aircraft includes a rotor blade, an actuator operably associated with the rotor blade, a controller operably associated with the actuator, and a flight control system. The flight control system having a subsystem adapted to modify a flight control limit of the aircraft based upon detection of an impending hazardous flight condition and a display showing available flight control limits provided by modification of design control limits based upon the detection of the impending hazardous flight condition.

Abstract: A method for operating an aircraft to prevent/recover from a stall condition includes the steps of detecting an actual vertical velocity of the aircraft, calculating vertical velocity error of the aircraft, the vertical velocity error being based upon a comparison between the actual vertical velocity of the aircraft and a commanded vertical velocity of the aircraft, and determining if the aircraft is in one of a near stalled condition and a stalled condition based upon at least the detected vertical velocity error and the polarity of the vertical velocity error. The method further includes the steps of taking control of the aircraft from an operator of the aircraft, reducing a bank angle of the aircraft, pitching the aircraft downward, and increasing the airspeed of the aircraft if the aircraft's airspeed is outside an airspeed window if the aircraft is in one of the near stalled condition and the stalled condition.

Abstract: A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.