Automatic heading synchronization control system

摘要

The automatic heading retention mode of operation of a flight control system for a rotary wing aircraft is discontinued and reestablished through the use of logic circuitry responsive to the bank angle of the aircraft and to the force applied to a control stick by the pilot. When the bank angle of the aircraft exceeds a preselected minimum and the lateral force applied to the cyclic pitch stick also exceeds a predetermined minimum the logic circuit operates to isolate the heading hold control from heading error signals and the heading retention mode of operation is automatically resumed when both of the bank angle and stick force fall below the preselected minimum levels. The invention may also encompass the application to the control mechanism of signals which will cause the aircraft to perform coordinated turns above a preselected minimum airspeed.