Method and apparatus for turn coordination gain as function of flap position

A technology of flap and wing electronics, applied in the field of new system of turn coordination gain of aircraft yaw damper, which can solve the problem that the gain adjuster cannot optimally provide turn coordination, diverging or converging turns, etc.

Inactive Publication Date: 2003-10-15
THE BOEING CO
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  • Abstract
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AI Technical Summary

Problems solved by technology

It was found from Figure 1 that the gain adjuster shown does not provide optimal turn coordination, sometimes with diverging or converging turn characteristics

Method used

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  • Method and apparatus for turn coordination gain as function of flap position
  • Method and apparatus for turn coordination gain as function of flap position
  • Method and apparatus for turn coordination gain as function of flap position

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Embodiment Construction

[0017] Figure 2 shows a simplified state-of-the-art yaw damper 201 which is used to generate a yaw damping command, YDCMD, to control the deflection of the rudder during a turn. This YDCMD signal is typically provided to one or more yaw damping servos that drive the rudder of the aircraft. This particular yaw damper 201 has been used on Boeing 747-400 aircraft. The yaw damper 201 uses data input from an inertial reference unit on the aircraft to calculate a rudder command (YDCMD) corresponding to the actual aircraft conditions at the time. The yaw damping servo then converts the electrical signal from the yaw damper 201 to control turbulent flow to the actuator pistons that drive the aircraft's rudders.

[0018] The inputs to the yaw damper 201 include: N y , represents the lateral acceleration of the aircraft; R, represents the yaw rate of the aircraft; Φ, represents the roll angle of the aircraft; P, represents the roll rate of the aircraft. The above parameters are provi...

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PUM

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Abstract

An improved method and apparatus for determining the amount of turn coordination gain in an aircraft yaw damper during a turn maneuver is disclosed. The yaw damper includes inputs from the inertial reference units of the aircraft and also from the flight management computer of the aircraft. The flight management computer provides to the yaw damper a signal indicative of the position of the flaps of the aircraft. The yaw damper includes a turn coordination gain box that receives the flap position signal and outputs a turn coordination gain value, dependent upon the flap position. Generally, the turn coordination gain value increases as the flap position is more extended. The precise turn coordination gain value for each flap position is dependent upon the particular aerodynamic characteristics of the aircraft.

Description

technical field [0001] The present invention relates to aircraft turning control systems, and more particularly to a novel system capable of changing the turning coordination gain of an aircraft yaw damper as a function of aircraft flap position. Background technique [0002] During a maneuver in an aircraft in a fixed-wing configuration, turns are coordinated by various control units. For example, pilots make turns by manipulating the aircraft's ailerons, rudder, and elevators using joysticks in the cockpit of a fixed-wing aircraft. [0003] Computer-controlled rudder deflection has long been used to coordinate turns during aircraft bank maneuvers. It is well known that turn coordination is desirable because, for example, when an aircraft is banked to the left, the aircraft tends to yaw to the right due to the aileron-induced moment about the yaw axis. For a coordinated turn, the yaw axis moment induced during a left bank maneuver can be counteracted by a left rudder bias...

Claims

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Application Information

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IPC IPC(8): B64C13/18G05D1/08
CPCG05D1/085
Inventor 陈勃璋
Owner THE BOEING CO
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