System and method for dynamically determining and indicating an aircraft bank limit on an aircraft instrument panel

Patent metadata

Field	Value
Publication number	US-10101173-B2
Application number	US-201615212015-A
Country	US
Kind code	B2
Filing date	Jul 15, 2016
Priority date	Jul 15, 2016
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

Systems and methods are provided for indicating a bank limit on an instrument display of an aircraft. In an example implementation, static air pressure measurements, impact air pressure measurements, an acceleration measurement, and an angle of attack may be received from corresponding sensors. A current airspeed and a stick shaker speed are determined. A minimum maneuver speed is determined from the current airspeed and the shaker stick speed. A bank limit indicator is provided on the flight display when the current airspeed is equal to or less than the minimum maneuver speed. A bank angle limit is displayed on the bank limit indicator based on the extent to which the current airspeed is equal to or less than the minimum maneuver speed.

First claim

What is claimed is:

1. A method for indicating a bank limit on an instrument display in an aircraft, the method comprising:
receiving a static air pressure measurement from a static air pressure sensor;
receiving an impact air pressure measurement from a pitot air pressure sensor;
receiving an acceleration measurement from an accelerometer;
receiving an angle of attack measurement from an angle of attack sensor;
determining a current airspeed based on the impact air pressure measurement and the static air pressure measurement;
determining a stick shaker speed based on the current airspeed, wherein the stick shaker speed is a speed at which a pilot is warned of an imminent stall of the aircraft and the stick shaker is a method of providing a warning of the imminent stall;
determining a minimum maneuver speed based on the current airspeed, the acceleration measurement and the stick shaker speed, wherein the minimum maneuver speed is a minimum airspeed that provides full maneuvering capability to the aircraft;
displaying a bank limit indicator on a flight display when the current airspeed is equal to or less than the minimum maneuver speed; and
displaying a bank angle limit on the bank limit indicator based on an extent to which the current airspeed is equal to or less than the minimum maneuver speed.

2. The method of claim 1 where the step of displaying the bank angle limit further includes:
determining the bank angle limit for display on the bank limit indicator to a maximum bank angle limit when the current airspeed is equal to the minimum maneuver speed, to a minimum bank angle limit when the current airspeed is equal to the stick shaker speed, and to a bank angle between the maximum bank angle limit and the minimum bank angle limit when the current airspeed is between the minimum maneuver speed and the stick shaker speed.

3. The method of claim 2 where the step of determining the bank angle limit includes:
selecting a bank angle value between the maximum bank angle limit and the minimum bank angle limit corresponding to the current airspeed where bank angle values between the maximum bank angle limit and the minimum bank angle limit correspond linearly with airspeed values between the minimum maneuver speed and the stick shaker speed.

4. The method of claim 1 further including:
displaying the current airspeed by positioning a pointing graphic element on the flight display to point to the current airspeed on a band of airspeeds displayed on the flight display.

5. The method of claim 4 further including:
indicating the stick shaker speed using a highlighting graphical element on the band of airspeeds displayed on the flight display.

6. The method of claim 4 further including:
indicating the minimum maneuver speed using a highlighting graphical element on the band of airspeeds displayed on the flight display.

7. The method of claim 1 where the step of displaying the bank limit indicator includes:
providing the flight display with data to indicate an arcuate band corresponding to a range of bank angles, the arcuate band including a first region indicating a range of safe bank angles between a zero bank position and the bank limit angle and a second region indicating a range of unsafe bank angles.

8. The method of claim 7 further including:
displaying a zero bank reference using a second pointing graphic element fixed on the flight display to the zero bank position on the arcuate band.

9. The method of claim 7 further including:
displaying a current bank angle pointer using a third pointing graphic element that moves along an arcuate path to point to a current bank angle on the range of bank angles as the bank angle of the aircraft changes.

10. The method of claim 9 where the third pointing graphic element is positioned at an upper end of a pitch scale indicating pitch angles, the method further including:
displaying a current pitch indicator marking a current pitch angle of the aircraft on the pitch scale.

11. The method of claim 10 further including:
determining a pitch limit angle based on a pitch margin to stick shaker; and
displaying a pitch limit indicator at the pitch limit angle on the pitch scale.

12. An aircraft control system for controlling an aircraft comprising:
an air data system including input connections to:
an angle of attack sensor to receive an angle of attack measurement;
a static air pressure sensor to receive a static air pressure measurement;
an accelerometer to receive an acceleration measurement; and
a pitot air pressure sensor to receive an impact air pressure measurement;
a flight display connected to receive flight data relating to the aircraft and to display the flight data; and
a flight control system including a processor and a non-transitory storage medium for storing machine-executable instructions that when executed by the processor perform:
a current airspeed function configured to determine a current airspeed based on the impact air pressure measurement and the static air pressure measurement;
a stick shaker speed function configured to determine a stick shaker speed based on the current airspeed, wherein the stick shaker speed is a speed at which a pilot is warned of an imminent stall of the aircraft and the stick shaker is a method of providing a warning of the imminent stall;
a minimum maneuver speed function configured to determine a minimum maneuver speed based on the current airspeed, the acceleration measurement and the shaker stick speed, wherein the minimum maneuver speed is a minimum airspeed that provides full maneuvering capability to the aircraft; and
a bank limit indicator function configured to generate a bank limit indicator for display on the flight display when the current airspeed is equal to or less than the minimum maneuver speed and to send the bank limit indicator to the flight display where the bank limit indicator displays a bank angle limit based on an extent to which the current airspeed is equal to or less than the minimum maneuver speed.

13. The aircraft control system of claim 12 where the bank limit indicator function is further configured to set the bank angle limit on the bank limit indicator to a maximum bank angle limit when the current airspeed is equal to the minimum maneuver speed, to a minimum bank angle limit when the current airspeed is equal to the stick shaker speed, and to a bank angle between the maximum bank angle limit and the minimum bank angle limit when the current airspeed is between the minimum maneuver speed and the stick shaker speed.

14. The aircraft control system of claim 13 where the bank limit indicator function is further configured to select a bank angle value between the maximum bank angle limit and the minimum bank angle limit corresponding to the current airspeed where bank angle values between the maximum bank angle limit and the minimum bank angle limit correspond linearly with airspeed values between the minimum maneuver speed and the stick shaker speed.

15. The aircraft control system of claim 12 where the non-transitory storage medium further includes machine-executable instructions that when executed by the processor are operable to:
display the current airspeed by positioning a pointing graphic element on the flight display to point to the current airspeed on a band of airspeeds displayed on the flight display.

16. The aircraft control system of claim 15 where the non-transitory storage medium further includes machine-executable instructions that when executed by the processor are operable to:
indicate the stick shaker speed using

Assignees

• Boeing Co

Inventors

• Ludtke Ii Frederick E

Classifications

• B64D43/02

  for indicating aircraft speed or stalling conditions · CPC title

• G01C23/005 Primary

  Flight directors (indicating arrangements specially adapted for rotary gyroscopes G01C19/32) · CPC title

• B64C13/10

  comprising warning devices · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G05D1/044

  during banks · CPC title