Airplane status system

Patent metadata

Field	Value
Publication number	US-10315778-B2
Application number	US-201514865794-A
Country	US
Kind code	B2
Filing date	Sep 25, 2015
Priority date	Sep 25, 2015
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

Abstract

A flight deck display that represents the overall health of the airplane by combining energy state, system state and configuration state into one integrated representation that is triggered by the on-board engine indication and crew alerting system. The computer system for controlling the display unit is configured to display an airplane status indicator in the form of a symbolic representation of the airplane that persists across displays. The status indicator shows the energy state of the airplane and how energy is being added or subtracted from it in terms of altitude, airspeed, thrust, wind, etc. As the airplane gains energy, there is a projection of excess energy shown in front of the airplane. As the airplane loses energy, an alerting indicator will appear around the airplane symbol if the performance of the airplane becomes is too low.

First claim

The invention claimed is:

1. A computer-implemented method for displaying airplane energy state information, comprising:
acquiring current values of engine operating parameters during operation of one or more engines on the airplane;
calculating a magnitude of thrust being produced by the engine(s) based on the current values of the engine operating parameters;
acquiring current values of wind speed and direction at a location of the airplane;
calculating a wind force vector relative to the airplane based on the current values of the wind speed and direction; and
displaying an airplane status indicator on a display screen, said airplane status indicator comprising first symbology representing the airplane, second symbology having a color indicative of a state of aircraft performance, third symbology representing the thrust vector, and fourth symbology representing the wind force vector relative to the airplane,
wherein the third symbology is located adjacent to the second symbology such that a radial line from a center of the second symbology to a midpoint of the third symbology indicates the thrust direction relative to the orientation of the airplane, and the magnitude of the thrust is indicated by different colors or different shades of the same color, with each thrust increment being represented by a respective band of color; and
wherein the fourth symbology is located adjacent to the second symbology such that a radial line from a center of the second symbology to a midpoint of the fourth symbology indicates the wind direction relative to the orientation of the airplane, and the wind velocity is indicated by different colors or different shades of the same color, with each velocity increment being represented by a respective band of color.

2. The computer-implemented method as recited in claim 1 , wherein the
second symbology is displayed when an amount of energy of the airplane reaches a first preset threshold, and wherein said second symbology surrounds at least a portion of said first symbology and has a first color.

3. The computer-implemented method as recited in claim 2 , wherein said second symbology comprises a circular band having a center located within said first symbology.

4. The computer-implemented method as recited in claim 2 , wherein said second symbology changes color from said first color to a second color different than said first color when the amount of energy of the airplane reaches a second preset threshold beyond said first preset threshold, said second preset threshold being set at a level corresponding to a caution state.

5. The computer-implemented method as recited in claim 4 , wherein said second symbology changes color from said second color to a third color different than said first and second colors when the amount of energy of the airplane reaches a third preset threshold beyond said second preset threshold, said third preset threshold being set at a level corresponding to a warning state.

6. The computer-implemented method as recited in claim 5 , wherein said second color is amber or orange and said third color is red.

7. The computer-implemented method as recited in claim 1 , further comprising:
monitoring the display screen to detect when a pressure is exerted on a portion of the display screen displaying a portion of said second symbology; and
displaying a window comprising a checklist and a synoptics diagram in response to detection of pressure on the portion of the display screen displaying a portion of said second symbology.

8. The computer-implemented method as recited in claim 1 , wherein said second symbology comprises a circular band, said third symbology comprises a first segment extending outward from an outer circumference of said circular band, and said fourth symbology comprises a second segment extending outward from the outer circumference of said circular band.

9. An onboard airplane system for displaying airplane status information, comprising:
a flight management system comprising at least one flight management computer configured to compute values for performance parameters of the airplane;
a display unit situated on a flight deck of the airplane, said display unit comprising a display screen; and
a computer system in communication with said flight management system and said display unit, and configured to be capable of performing the following operations:
causing said display unit to display first symbology representing the airplane on said display screen;
monitoring an energy state of the airplane during operation of the airplane, wherein contributing factors to the energy state of the airplane which are taken into account include at least wind speed, wind direction, current thrust, available thrust, flap settings, and landing gear status;
causing said display unit to display second symbology on said display screen when the energy state of the airplane reaches a first preset threshold, wherein said second symbology surrounds at least a portion of said first symbology and has a first color;
acquiring values of engine operating parameters during operation of one or more engines on the airplane;
calculating a magnitude of thrust being produced by the engine(s) based on the acquired values of the engine operating parameters;
acquiring values of wind speed and direction at a location of the airplane;
calculating a wind force vector relative to the airplane based on the acquired values of the wind speed and direction; and
causing said display unit to display third symbology representing the thrust vector and fourth symbology representing the wind force vector on said display screen relative to the airplane,
wherein the third symbology is located adjacent to the second symbology such that a radial line from a center of the second symbology to a midpoint of the third symbology indicates the thrust direction relative to the orientation of the airplane, and the magnitude of the thrust is indicated by different colors or different shades of the same color, with each thrust increment being represented by a respective band of color; and
wherein the fourth symbology is located adjacent to the second symbology such that a radial line from a center of the second symbology to a midpoint of the fourth symbology indicates the wind direction relative to the orientation of the airplane, and the wind velocity is indicated by different colors or different shades of the same color, with each velocity increment being represented by a respective band of color.

10. The system as recited in claim 9 , wherein said computer system is further configured to cause said display unit to change said second symbology from said first color to a second color different than said first color when the energy state of the airplane reaches a second preset threshold beyond said first preset threshold, said second preset threshold being set at a level corresponding to a caution state.

11. The system recited in claim 10 , wherein said computer system is further configured to cause said display unit to change said second symbology from said second color to a third color different than said first and second colors when the energy state of the airplane reaches a third preset threshold beyond said second preset threshold, said third preset threshold being set at a level corresponding to a warning state.

12. The system as recited in claim 9 , wherein said second symbology comprises a circular band, said third symbology comprises a first segment extending outward from an outer circumference of said circular band, and said fourth symbology comprises a second segment extending outward from the outer circumference of said circular band.

Assignees

• Boeing Co
• The Beoing Company

Inventors

• Holder Barbara E

Classifications

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• G01C23/005

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

• B64D45/00 Primary

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G01C23/00

  Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration · CPC title