System and method for electronic pitch stability augmentation

A method for providing electronic pitch stability for an aircraft, the method comprising:

• receiving with compensation modules input from sensors mounted to the aircraft, wherein the sensors are configured for sensing one or more conditions experienced by the aircraft in real time;
• determining compensation commands via the compensation modules, wherein the compensation commands include instructions for at least one servo motor based upon the input from the sensors;
• and
• outputting the compensation commands to a servo control and dynamics system including the at least one servo motor, wherein the at least one servo motor is physically coupled to an aircraft control inceptor and is configured to, based on the compensation commands, provide reactive forces that work against the pilot or assists the pilot as the pilot manually manipulates the aircraft control inceptor.

A method for providing electronic pitch stability for an aircraft, the method comprising:

• receiving with compensation modules input from sensors mounted to the aircraft, wherein the sensors are configured for sensing one or more conditions experienced by the aircraft in real time;
• determining compensation commands via the compensation modules based on input from the sensors, wherein the compensation modules are configured to determine the compensation commands according to at least one of the following functions of the compensation modules:
• a. vertical acceleration augmentation based on aircraft control inceptor force,b. airspeed augmentation based on aircraft control inceptor force,c. aircraft center of gravity (CG) normalization based on aircraft control inceptor force,d. flap extension and retraction force bias,e. pitch damping, f. soft angle of attack (AOA) limit protection, andg. Mach trim offsetting of an elevator position versus stabilizer position at high Mach numbers to prevent Mach tuck;
• summing the compensation commands from a plurality of the compensation modules into a pitch stability compensation command, wherein the summing is performed in a weighted manner in accordance with flight control requirements;
• and
• outputting the pitch stability compensation command to a servo control and dynamics system including at least one servo motor, wherein the at least one servo motor is physically coupled to an aircraft control inceptor and configured to provide reactive forces that work against the pilot or assists the pilot as the pilot manually manipulates the aircraft control inceptor.