Patent ID: 8496199

Claim:
A rotary aircraft, comprising: a rotor blade; an actuator operably associated with the rotor blade, the actuator being configured to change the pitch of the rotor blade; a controller operably associated with the actuator; a flight control system, having: a first sensor associated with the controller, the sensor being configured to detect a displacement of the controller; a second sensor associated with the rotor, the second sensor being configured to detect a lateral flapping movement and a longitudinal flapping movement of the rotor blade; a third sensor associated with the rotary aircraft, the third sensor being configured to detect a flight parameter of the aircraft; a subsystem associated with the first sensor, the second sensor, and the third sensor, the subsystem having: a first loop associated with the first sensor and the second sensor, the first loop being configured to determine a longitudinal blowback value created by the rotor blade during flight; a second loop associated with the second sensor and the third sensor, the second loop being configured to determine a design maximum total flapping value and a lateral flapping value; wherein the squared value of the lateral flapping is subtracted from the squared value of the total flapping value to create a fight control limit; wherein the flight control limit is added to the longitudinal blowback value to create an upper longitudinal cyclic limit; and wherein the flight control limit is subtracted from the longitudinal blowback value to create a lower longitudinal cyclic limit; and a display configured to display a symbol identifying the displacement of the actuator relative to the upper longitudinal cyclic limit and the lower longitudinal cyclic limit.