System and method for displaying critical aeronautical information on an uncertified display

• US 10,338,337 B1
• Filed: 03/08/2018
• Issued: 07/02/2019
• Est. Priority Date: 12/07/2017
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Berckefeldt, Richard, True, Willard R., Sarma, Kalluri R.
• Primary Examiner(s): Wu, Jerry
• Application Number:
  US15/915,503
• Publication Number:
  US 20190179097A1
• Time in Patent Office: 481 Days
• CPC Class Codes: B64D 2045/0075 Adaptations for use of electronic flight bags in aircraft; Supports therefor in the cockpit
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: B64D 43/02 for indicating aircraft speed or stalling conditions
• CPC Class Codes: B64D 47/02 Arrangements or adaptations of signal or lighting devices
• CPC Class Codes: G01C 23/00 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 Class Codes: G02B 26/001 based on interference in an adjustable optical cavity interference filters G02B5/28; devices or arrangements using multiple reflections in spectrometry or monochromators G01J3/26
• CPC Class Codes: G02B 27/0012 Optical design, e.g. procedures, algorithms, optimisation routines
• CPC Class Codes: G02B 27/0093 with means for monitoring data relating to the user, e.g. head-tracking, eye-tracking
• CPC Class Codes: G02B 7/005 Motorised alignment
• CPC Class Codes: G06F 11/0751 Error or fault detection not based on redundancy power supply failures G06F1/30; network fault management H04L41/06
• CPC Class Codes: G06F 11/0796 Safety measures, i.e. ensuring safe condition in the event of error, e.g. for controlling element
• CPC Class Codes: G06F 21/57 Certifying or maintaining trusted computer platforms, e.g. secure boots or power-downs, version controls, system software checks, secure updates or assessing vulnerabilities
• CPC Class Codes: G06F 21/84 output devices, e.g. displays or monitors
• CPC Class Codes: G06F 3/1415 with means for detecting differences between the image stored in the host and the images displayed on the displays
• CPC Class Codes: G09G 2300/023 Display panel composed of stacked panels
• CPC Class Codes: G09G 2380/12 Avionics applications

Abstract

A display system configured for displaying critical aeronautical information on an aircraft display that is not certified for displaying critical aeronautical information comprises a mounting adapter and an application server. The mounting adapter is configured to mount, in an aircraft cockpit, a personal electronic device (PED) wherein the PED is not certified to display critical aeronautical information. The mounting adapter further comprises a surface with an actuatable covering that is configured to be overlaid on a PED display and an actuation source configured to actuate the covering. The application server is configured to execute a module that generates critical aeronautical information, transmit the generated critical aeronautical information to the PED for display, determine whether a problem exists with the image displayed on the PED display, and enable the actuation source to cause the covering to annunciate a message indicating a problem with the image displayed on the PED display.

Claims

1. A display system configured for displaying critical aeronautical information on an aircraft display that is not certified for displaying critical aeronautical information, the display system comprising:

a mounting adapter configured to mount, in an aircraft cockpit, a personal electronic device (PED) having a PED display wherein the PED is not certified to display critical aeronautical information, the mounting adapter comprising a surface with an actuatable covering that is configured to be overlaid on the PED display, wherein the surface with an actuatable covering is optically active in the presence of an excitation source, and an actuation source configured to actuate the covering; and

an application server comprising one or more processors, the application server configured to execute one or more modules that generate critical aeronautical information, transmit the generated critical aeronautical information to the PED for display on the PED display, determine from an image of the PED display captured by an imaging device whether a problem exists with the image displayed on the PED display, and enable the actuation source to cause the covering to annunciate a message indicating that a problem exists with the image displayed on the PED display.

2. The system of claim 1, wherein:

the mounting adapter further comprises the imaging device which is configured to capture an image of the PED display;

the mounting adapter is further configured to transmit the image of the PED display to the application server; and

the application server is further configured to review the image from the PED display to determine whether a problem exists with the image displayed on the PED display.

3. The system of claim 2, wherein the imaging device comprises a camera.

4. The system of claim 1, wherein the surface with an actuatable covering comprises a film configured to be overlaid on the PED display wherein the film includes a coating that is optically active in the presence of the excitation source.

5. The system of claim 4, wherein the actuation source comprises the excitation source that is configured to activate the optically active coating.

6. The system of claim 5, wherein the coating when activated is configured to display a visible symbol that indicates that a problem exists with the image displayed on the PED display.

7. The system of claim 6 wherein the coating when activated is configured to display the visible symbol in a color that indicates that a problem exists with the image displayed on the PED display.

8. The system of claim 7, wherein the color is red and the symbol is an X.

9. The system of claim 5, wherein the coating when activated is configured to display text that indicates that a problem exists with the image displayed on the PED display.

10. The system of claim 5, wherein the excitation source comprises an optically emissive device.

11. The system of claim 10 wherein the optically emissive device comprises an LED (light-emitting diode) operating in a non-visible light band and configured to illuminate the coating on the film and activate optical qualities of the film.

12. The system of claim 5, wherein the excitation source comprises an electrical source configured to deliver an electrical signal to the coating on the film to activate optical qualities of the film.

13. The system of claim 2, wherein the application server is configured to review the image from the PED display to assess the integrity, continuity, and availability (ICA) of the generated critical aeronautical information displayed on the PED display.

14. The system of claim 13, wherein the application server is further configured to enable the actuation source to actuate the covering when a loss of ICA of the generated critical aeronautical information displayed on the PED display is detected, the activation of the covering resulting in the annunciation of the loss of ICA on the surface overlaid on the PED display.

15. The system of claim 1, wherein the PED comprises a general-purpose tablet computer or a smartphone.

16. A computer-implemented method in an aircraft for displaying critical aeronautical information on an aircraft display that is not certified for displaying critical aeronautical information, the method comprising:

transmitting, by a computing device in the aircraft, critical aeronautical information to a personal electronic device (PED) mounted in an aircraft cockpit for display on a PED display of the PED, wherein the PED is not certified to display critical aeronautical information, wherein the PED display is overlaid with a surface having an actuatable covering on the surface, and wherein the surface with the actuatable covering is optically active in the presence of an excitation source;

determining, from an image of the PED display captured by an imaging device by the computing device, whether a problem exists with the image displayed on the PED display; and

enabling, by the computing device, an actuation source to cause the covering to annunciate a message indicating that a problem exists with the image displayed on the PED display when it is determined that a problem exists.

17. The method of claim 16, wherein determining whether a problem exists with the image displayed on the PED display comprises reviewing the imaging device generated image of the PED display to determine whether a problem exists with the image displayed on the PED display.

18. The method of claim 17, wherein:

reviewing the imaging device generated image of the PED display comprises reviewing the imaging device generated image of the PED display to assess the integrity, continuity, and availability (ICA) of the generated critical aeronautical information displayed on the PED display; and

enabling the actuation source comprises enabling the actuation source to actuate the covering when a loss of ICA of the critical aeronautical information displayed on the PED display is detected to annunciate the loss of ICA on the surface overlaid on the PED display.

19. The method of claim 16, wherein:

the surface with an actuatable covering comprises a film configured to be overlaid on the PED display wherein the film includes a coating that is optically active in the presence of the excitation source;

the actuation source comprises the excitation source that is configured to activate the optically active coating;

the excitation source comprises an optically emissive device; and

enabling an actuation source to cause the covering to annunciate a message comprises enabling the optically emissive device to cause the optically active coating to annunciate a message that indicates that a problem exists with the image displayed on the PED display.

20. A display system configured for displaying critical aeronautical information on an aircraft display that is not certified for displaying critical aeronautical information, the display system comprising:

a mounting adapter configured to mount, in an aircraft cockpit, a personal electronic device (PED) having a PED display wherein the PED is not certified to display critical aeronautical information, the mounting adapter including a film configured to be overlaid on the PED display and that includes a coating that is optically active in the presence of an excitation source, an excitation source configured to activate the coating, and a camera configured to take an image of the PED display; and

an application server mounted in the aircraft and comprising one or more processors, the application server configured to execute one or more modules that generate critical aeronautical information and configured to transmit the generated critical aeronautical information to the PED for display on the PED display, the application server configured to monitor the integrity, continuity, and availability (ICA) of the generated critical aeronautical information displayed on the PED display using the camera image and to enable the excitation source to activate the coating when a loss of ICA of the generated critical aeronautical information displayed on the PED display is detected, the activation of the coating resulting in the annunciation of the loss of ICA on the film overlaid on the PED display.