Method and apparatus for aircraft pitch and thrust axes control

Claim 2

In combination in an aircraft: a pitch axis control system; an engine control system; means for providing a signal representative of a desired selected reference speed; means for providing logic command signals in response to desired climb, descend, or maintain altitude maneuvers of said aircraft; and, switching means responsive to said logic command signals for automatically selecting said pitch axis control system to control the aircraft to said selected reference speed when said aircraft is commanded to climb or descend, and for automatically selecting said engine control system to control the aircraft to said selected reference speed when said aircraft is commanded to maintain altitude.

Claim 3

In combination in an aircraft: an engine control system; means for providing an altitude error signal representative of the difference between a predetermined altitude and the actual altitude of said aircraft; means for providing climb or descend command logic signals in response to said altitude error signal representative of aircraft altitude more than a given distance below or above respectively said predetermined altitude; and, switching means for providing said engine control system with an increase thrust command in response to said climb command logic signal, and for providing said engine control system with a decrease thrust command in response to said descend command logic signal.

Claim 4

In combination in an aircraft: an engine control system; means for providing an altitude error signal representative of the difference between a predetermined altitude and the actual altitude of said aircraft; means for providing climb or descend command logic signals in response to said altitude error signal representative of aircraft altitude more than a given distance below or above respectively said predetermined altitude; and, switching means for providing said engine control system with an increase thrust command in response to said climb command logic signal, and for providing said engine control system with a decrease thrust command in response to said descend command logic signal.

Claim 5

In combination in an aircraft having a pitch axis control system and an engine control system: an aircraft air data system for providing a signal representative of aircraft altitude and a signal representative of aircraft speed; speed select means for providing a signal representative of selected speed; combining circuit means responsive to said signal representative of aircraft speed and said signal representative of selected speed for providing a signal representative of speed error; altitude select control means for providing a signal representative of selected altitude; combining circuit means responsive to said signal representative of altitude and said signal representative of selected altitude for providing a signal representative of altitude error; thrust rating select control and display means for providing a signal representative of desired thrust; engine sensor means for providing a signal representative of actual engine thrust; combining circuit means responsive to said signal representative of desired thrust and said signal representative of actual engine thrust for providing a signal representative of thrust error; flight level change mode request control means for providing a signal representative of flight level change mode requested; altitude logic circuit means responsive to said signal representative of altitude error for providing first, second, and third signals; a first AND gate responsive to said signal representative of flight level change mode requested and said second signal for providing a signal representative of flight level change mode engaged; a first relay means having a first input terminal, a second input terminal, and an energizing circuit; said first input terminal of said first relay means responsive to said signal representative of altitude error; said second input terminal of said first relay means responsive to said signal representative of speed error, said output terminal of said first relay means coupled to said pitch axis control system, and said first relay means energizing circuit responsive to said signal representative of flight level change mode engaged; a second relay means having a first input terminal, a second input terminal, an output terminal, and an energizing circuit; a second AND gate having a first input terminal, a second input terminal, and an output terminal; a third relay means having a first input terminal, a second input terminal, an output terminal, and an energizing circuit; and a third AND gate having a first input terminal, a second input terminal, and an output terminal; said first input terminal of said second AND gate responsive to said third signal, said second input terminal of said second AND gate responsive to said signal representative of flight level change mode requested, and said second input terminal of said second AND gate connected to said second input terminal of said third AND gate; said first input terminal of said third AND gate responsive to said first signal, and said output of said third AND gate coupled to said energizing circuit of said third relay means; said output terminal of said second AND gate coupled to said energizing circuit of said second relay means; said first input terminal of said second relay means responsive to said signal representative of speed error signal, said second input terminal of said second relay means responsive to said signal representative of thrust error, and said output terminal of said second relay means connected to said first input terminal of said third relay means; said second input terminal of said third relay means responsive to signal representative of command idle composition of said aircraft, and said output terminal of said third relay means coupled to said engine control system.

Claim 6

In combination in an aircraft having a pitch axis control system and an engine control system: an aircraft air data system for providing a signal representative of aircraft altitude and a signal representative of aircraft speed; speed select means for providing a signal representative of selected speed; combining circuit means responsive to said signal representative of aircraft speed and said signal representative of selected speed for providing a signal representative of speed error; altitude select control means for providing a signal representative of selected altitude; combining circuit means responsive to said signal representative of altitude and said signal representative of selected altitude for providing a signal representative of altitude error; thrust rating select control and display means for providing a signal representative of desired thrust; engine sensor means for providing a signal representative of actual engine thrust; combining circuit means responsive to said signal representative of desired thrust and said signal representative of actual engine thrust for providing a signal representative of thrust error; flight level change mode request control means for providing a signal representative of flight level change mode requested; altitude logic circuit means responsive to said signal representative of altitude error for providing first, second, and third signals; a first AND gate responsive to said signal representative of flight level change mode requested and said second signal for providing a signal representative of flight level change mode engaged; a first relay means having a first input terminal, a second input terminal, and an energizing circuit; said first input terminal of said first relay means responsive to said signal representative of altitude error; said second input terminal of said first relay means responsive to said signal representative of speed error, said output terminal of said first relay means coupled to said pitch axis control system, and said first relay means energizing circuit responsive to said signal representative of flight level change mode engaged; a second relay means having a first input terminal, a second input terminal, an output terminal, and an energizing circuit; a second AND gate having a first input terminal, a second input terminal, and an output terminal; a third relay means having a first input terminal, a second input terminal, an output terminal, and an energizing circuit; and a third AND gate having a first input terminal, a second input terminal, and an output terminal; said first input terminal of said second AND gate responsive to said third signal, said second input terminal of said second AND gate responsive to said signal representative of flight level change mode requested, and said second input terminal of said second AND gate connected to said second input terminal of said third AND gate; said first input terminal of said third AND gate responsive to said first signal, and said output of said third AND gate coupled to said energizing circuit of said third relay means; said output terminal of said second AND gate coupled to said energizing circuit of said second relay means; said first input terminal of said second relay means responsive to said signal representative of speed error signal, said second input terminal of said second relay means responsive to said signal representative of thrust error, and said output terminal of said second relay means connected to said first input terminal of said third relay means; said second input terminal of said third relay means responsive to signal representative of command idle composition of said aircraft, and said output terminal of said third relay means coupled to said engine control system.

Claim 7

In combination in an aircraft: means for providing a first signal representative of selected reference altitude; means for providing a second signal representative of the altitude of said aircraft; means for combining said first and second signals for providing an altitude select error signal; means responsive to said altitude select error signal for providing logic signals corresponding to desired climb to or descend to or maintain said selected reference altitude; a pitch axis control system; a thrust axis control system; and, means coupled in said pitch axis and thrust axis control systems and responsive to said logic signals for causing said aircraft to climb to, descend to or maintain said selected altitude.

Claim 8

In combination in an aircraft: means for providing a first signal representative of selected reference altitude; means for providing a second signal representative of the altitude of said aircraft; means for combining said first and second signals for providing an altitude select error signal; means responsive to said altitude select error signal for providing logic signals corresponding to desired climb to or descend to or maintain said selected reference altitude; a pitch axis control system; a thrust axis control system; and, means coupled in said pitch axis and thrust axis control systems and responsive to said logic signals for causing said aircraft to climb to, descend to or maintain said selected altitude.

Claim 9

In combination in an aircraft: a pitch axis control system; a thrust axis control system; means for providing a first signal representative of a selected reference altitude; means for providing a second signal representative of the altitude of said aircraft; means for combining said first and second signals to produce an altitude select error signal; means responsive to said altitude select error signal for providing logic signals corresponding to a desired climb, descend, or maintain altitude maneuver of said aircraft; means for providing a third signal representative of a selected reference airspeed; means for providing a fourth signal representative of the airspeed of said aircraft; means for combining said third signal and said fourth signal to provide an airspeed error signal; switching means responsive to said logic signals for transferring control of airspeed of said aircraft between said pitch axis control system and said thrust axis control system; and means connected between said pitch axis control system and said thrust axis control system and responsive to said airspeed error signal for airspeed control of said aircraft.

Claim 10

In combination in an aircraft: a pitch axis control system; a thrust axis control system; means for providing a first signal representative of a selected reference altitude; means for providing a second signal representative of the altitude of said aircraft; means for combining said first and second signals to produce an altitude select error signal; means responsive to said altitude select error signal for providing logic signals corresponding to a desired climb, descend, or maintain altitude maneuver of said aircraft; means for providing a third signal representative of a selected reference airspeed; means for providing a fourth signal representative of the airspeed of said aircraft; means for combining said third signal and said fourth signal to provide an airspeed error signal; switching means responsive to said logic signals for transferring control of airspeed of said aircraft between said pitch axis control system and said thrust axis control system; and means connected between said pitch axis control system and said thrust axis control system and responsive to said airspeed error signal for airspeed control of said aircraft.

Claim 11

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.

Claim 12

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.

Claim 13

The invention according to claim 6 further comprising a single mode select means for enabling said logic circuit means and said switching means.

Claim 14

The invention according to claim 6 further comprising a single control device for providing a desired selected speed for utilization when either said pitch axis control system or said engine control system is controlling the speed of said aircraft.