Vertical navigation steering control system for aircraft

Claim 2

In combination in a system for generating pitch attitude command signals for controlling the flight path of an aircraft: means for generating a signal representative of navigation path error; means for providing a signal representative of calibrated airspeed; means for generating a speed reference signa; means for combining said signal representative of calibrated airspeed with said speed reference signal to provide an output error signal; means for providing a further signal responsive to pitch rate, angle of attack, and flap information signals; and, mid value signal selecting circuit means responsive to said signal representative of navigation path error, said output error signal, and said further signal for selecting the mid value of the aforesaid signals and providing said pitch attitude command signals.

Claim 3

The combination according to claim 1 wherein said speed reference signal is representative of the maximum permissible speed of the aircraft.

Claim 4

A flight control system for an aircraft comprising in combination: means for providing an angle of attack error signal; means for providing a navigation path error signal; means for providing a calibrated airspeed error signal; means responsive to each of said aforementioned means for selecting the mid value amplitude of the aforementioned signals for path command control of the aircraft.

Claim 5

A flight control system for an aircraft comprising in combination: means for providing an angle of attack error signal; means for providing a navigation path error signal; means for providing a calibrated airspeed error signal; means responsive to each of said aforementioned means for selecting the mid value amplitude of the aforementioned signals for path command control of the aircraft.

Claim 6

The flight control system according to claim 3 further including profile mode selecting means for providing a speed reference signal for path command control of the aircraft.

Claim 7

In combination in a flight control system for an aircraft: means for providing a signal representative of groundspeed; means for providing a signal representative of required flight path angle; means for providing a signal representative of distance from effective waypoint; means for providing a signal representative of altitude of the next waypoint; means for providing a signal representative of barometric altitude; first multiplier circuit means responsive to said signal representative of grounspeed and said signal representative of required flight path angle for providing a first output signal; second multiplier circuit means responsive to said signal representative of required flight path angle and said signal representative of distance from effective waypoint for providing a second output signal; first adder circuit means responsive to said second output signal and said signal representative of altitude of the next waypoint for providing a third output signal; second adder circuit means responsive to said third output signal and said signal representative of barometric altitude for providing a fourth output signal; third adder circuit means responsive to said first and fourth output signals for providing a fifth output signal, said fifth output signal representative of h C .

Claim 8

In combination in a flight control system for an aircraft: means for providing a signal representative of groundspeed; means for providing a signal representative of required flight path angle; means for providing a signal representative of distance from effective waypoint; means for providing a signal representative of altitude of the next waypoint; means for providing a signal representative of barometric altitude; first multiplier circuit means responsive to said signal representative of grounspeed and said signal representative of required flight path angle for providing a first output signal; second multiplier circuit means responsive to said signal representative of required flight path angle and said signal representative of distance from effective waypoint for providing a second output signal; first adder circuit means responsive to said second output signal and said signal representative of altitude of the next waypoint for providing a third output signal; second adder circuit means responsive to said third output signal and said signal representative of barometric altitude for providing a fourth output signal; third adder circuit means responsive to said first and fourth output signals for providing a fifth output signal, said fifth output signal representative of h C .

Claim 9

The combination in a flight control system for an aircraft according to claim 5 further including: means for providing a signal representative of vertical acceleration; means for providing a signal representative of barometric altitude rate; fourth adder circuit means responsive to said signal representative of vertical acceleration and said signal representative of barometric altitude rate for providing a sixth output signal; first lag filter circuit means responsive to said sixth output signal for providing a seventh output signal; and, fifth adder circuit means responsive to said fifth and seventh output signals for providing an eighth output signal, and said eighth output signal representative of flight path error.

Claim 10

The combination in a flight control system for an aircraft according to claim 6 further including: means for providing a signal representative of airspeed; gain scheduling circuit means responsive to said signal representative of airspeed for providing a further output signal; and, means for combining said eight output signal and said further output signal for providing another output signal.

Claim 11

The combination in a flight control system for an aircraft according to claim 6 further including: means for providing an angle of attack error signal; means for providing a calibrated airspeed error signal; mid value signal selection means responsive to said fifth output signal, said angle of attack error signal, and said calibrated error signal for providing a ninth output signal; and, utilization means responsive to said ninth output signal for providing path command control of the aircraft.

Claim 12

The combination in a flight control system for an aircraft according to claim 8 wherein said means for providing an angle of attack error signal comprises: means for providing a signal representative of aircraft flap position; first combining means having first and second input terminals and an output terminal; gain scheduling means responsive to said signal representative of flap position for providing a signal coupled to said first input terminal of said first combining means; means for providing a signal representative of angle of attack coupled to said second input terminal of said first combining means; second combining means having first and second input terminals and an output terminal; means for providing a signal representative of pitch rate, said pitch rate signal coupled to said first input terminal of said second combining means, and said second input terminal of said second combining means coupled to said output terminal of said first combining means, said output terminal of said second combining means providing said angle of attack error signal.