Aircraft pitch control system with electronically geared elevator

An aircraft pitch control system comprising:

• a movable horizontal stabilizer;
• a first actuator for actuating the horizontal stabilizer;
• an elevator movably coupled to the horizontal stabilizer;
• a second actuator for actuating the elevator;
• and
• a computer configured to control the second actuator using an electronic gearing relationship between the horizontal stabilizer and the elevator to cause the elevator to be electronically geared to the horizontal stabilizer, wherein:
• the electronic gearing relationship is changeable based on one or more operating parameters of the aircraft, the one or more operating parameters of the aircraft including a flap angle;
• the electronic gearing relationship comprises:
• a first portion over a first range of stabilizer actuation amounts in which a first stabilizer actuation amount requires a corresponding first elevator actuation amount that is smaller than the first stabilizer actuation amount;
• a second portion defining a dead zone over a non-zero second range of stabilizer actuation amounts in which a non-zero second stabilizer actuation amount requires no corresponding second elevator actuation amount;
• and
• a third portion over a third range of stabilizer actuation amounts in which a third stabilizer actuation amount requires a corresponding third elevator actuation amount;
• and
• at least one of the first portion and third portion of the gearing relationship is linear.