초록 ▼

An aircraft automatic or semiautomatic vertical path control system which coordinates operation of pitch and engine thrust control systems to transfer speed control from one system to the other depending on a requirement to climb, descend, or maintain altitude as determined by the polarity and magni

An aircraft automatic or semiautomatic vertical path control system which coordinates operation of pitch and engine thrust control systems to transfer speed control from one system to the other depending on a requirement to climb, descend, or maintain altitude as determined by the polarity and magnitude of the difference between a selectable desired altitude and current actual altitude.

대표청구항 ▼

In combination in an aircraft: a pitch axis control system; an engine control system; means for providing an altitude error signal representative of the difference between a desired selected altitude and the actual altitude of the aircraft; means for providing a speed error signal representative of

In combination in an aircraft: a pitch axis control system; an engine control system; means for providing an altitude error signal representative of the difference between a desired selected altitude and the actual altitude of the aircraft; means for providing a speed error signal representative of the difference between a desired selected speed and the actual speed of the aircraft; means for providing an increase thrust command signal; means for providing a decrease thrust command signal; logic circuit means responsive to said altitude error signal for providing a descend command logic signal when said actual altitude is more than a predetermined distance above said selected altitude, a climb command logic signal when said actual altitude is more than a predetermined distance below said selected altitude, and a maintain altitude command logic signal when said actual altitude is within a predetermined distance of said selected altitude; switching means responsive to said logic signals for coupling said speed error or said altitude error signal to said pitch axis control system and further coupling said speed error, or said increase thrust command signal, or said decrease thrust command signal to said engine control system for enabling said pitch axis control system to control said selected speed under both climb and descend command logic conditions and to control the aircraft to said selected altitude for the maintaining altitude command logic condition; and said engine control system providing control to said increase thrust command signal for said climb command logic condition, to said decrease thrust command signal for said descend command logic condition, and to said selected speed for said maintain altitude command logic condition.