초록 ▼

In an aircraft automatic flight control system (FIG. 1) beeping of the reference voltage in attitude synchronizing and beeping circuits (70, FIG. 4; 70R, FIG. 6) is inhibited (196, 201; 278, 282) in response to proportional commands (54, 55; 54R, 55R) in excess of a predetermined magnitude (183-186,

In an aircraft automatic flight control system (FIG. 1) beeping of the reference voltage in attitude synchronizing and beeping circuits (70, FIG. 4; 70R, FIG. 6) is inhibited (196, 201; 278, 282) in response to proportional commands (54, 55; 54R, 55R) in excess of a predetermined magnitude (183-186, 283-286). Beeping is inhibited only in the direction of the high proportional command, but not in the other direction. In a dual system (FIG. 1) pitch attitude beeping is inhibited only if both channels of the system have excessive proportional commands (195, 200, FIG. 3) whereas roll attitude beeping is inhibited if either channel has excessive proportional command (294, 295).

대표청구항 ▼

1. A system for positioning attitude-controlling aerodynamic surfaces of an aircraft, comprising: attitude means for providing an actual attitude signal indicative of the actual attitude of the aircraft in a control axis thereof; beeper means selectively operable by the pilot of the aircraft to

1. A system for positioning attitude-controlling aerodynamic surfaces of an aircraft, comprising: attitude means for providing an actual attitude signal indicative of the actual attitude of the aircraft in a control axis thereof; beeper means selectively operable by the pilot of the aircraft to provide a beep signal indicative of a selected rotational direction about said control axis; actuator means responsive to a command input signal applied thereto for positioning said aerodynamic surfaces; and signal processing means, connected for response to said attitude means and said beeper means, for providing, during the presence of said beep signal, an attitude reference signal indicative of the attitude desired for the aircraft in said control axis which is adjusted at a substantially constant rate in a direction corresponding to the rotational direction indicated by said beep signal, for providing an attitude error signal indicative of the difference between said attitude reference signal and said actual attitude signal, and for providing to said actuator means an attitude command signal indicative of a desired change in aircraft attitude in response to said attitude error signal; characterized by said signal processing means comprising means for maintaining said attitude reference signal constant even in the presence of said beep signal in response to said attitude error signal being of a sense corresponding to the rotational direction indicated by said beep signal and in excess of a predetermined magnitude. 2. A system according to claim 1 characterized by said predetermined magnitude representing on the order of 5% of the full permissible range of positions to which said actuator means can position said aerodynamic surfaces.