Method and apparatus for configuring screen displays

Abstract

Controlling and reconfiguring a display system that includes at least two screens that are installed in a cockpit of an aircraft in case of a failure of one of the screens. For example, a control unit of the display system may detect occurrence of a screen failure. In response to detecting the screen failure, the control unit may determine whether a critical flight relevant information has not been displayed on an operational screen during a predetermined period of time, and in response to determining that the critical flight relevant information has not been displayed on the operational screen during the predetermined period of time, command display of a message on the operational screen that suggests displaying the critical flight relevant information on the operational screen.

Claims

1. A method for operating, in an aircraft, a display system that comprises a control unit and at least a first and a second screen that are installed in a cockpit of the aircraft, comprising: using the control unit to monitor the at least first and second screens and control display of the flight relevant information on the at least first and second screens in a first mode and in a second mode, wherein in the first mode the first and second screens are operational; if failure of the first screen occurs, detecting occurrence of the failure of the first screen with the control unit; in response to detecting occurrence of the failure of the first screen, entering the second mode with the control unit; wherein in the second mode, determining with the control unit whether a critical flight relevant information of the flight relevant information has not been displayed on the second screen during a predetermined period of time; and in response to determining with the control unit that the critical flight relevant information has not been displayed on the second screen during the predetermined period of time, using the control unit to command display of a message on the second screen that suggests displaying the critical flight relevant information on the second screen; wherein determining whether the critical flight relevant information has not been displayed on the second screen during the predetermined period of the time further comprises: initializing a timer; and running the timer for the predetermined period of time and, during the predetermined period of time, detecting whether the control unit has entered the first mode or whether the critical flight relevant information has been displayed on a screen of the at least first and second screens; and upon expiry of the predetermined period of time and in response to detecting that the control unit has not entered the first mode and that the critical flight relevant information has not been displayed on a screen of the at least first and second screens, generating a status signal indication that the critical flight relevant information has not been displayed during the predetermined period of time.

2. The method of claim 1, wherein in the second mode only the second screen is operational and all other screens of the at least first and second screens are non-operational.

3. A method for operating, in an aircraft, a display system that comprises a control unit and at least a first and a second screen that are installed in a cockpit of the aircraft, comprising: using the control unit to monitor the at least first and second screens and control display of the flight relevant information on the at least first and second screens in a first mode and in a second mode, wherein in the first mode the first and second screens are operational; if failure of the first screen occurs, detecting occurrence of the failure of the first screen with the control unit; in response to detecting occurrence of the failure of the first screen, entering the second mode with the control unit; wherein in the second mode, determining with the control unit whether a critical flight relevant information of the flight relevant information has not been displayed on the second screen during a predetermined period of time; and in response to determining with the control unit that the critical flight relevant information has not been displayed on the second screen during the predetermined period of time, using the control unit to command display of a message on the second screen that suggests displaying the critical flight relevant information on the second screen; with the control unit, receiving an information signal indicating an armed or coupled predetermined navigation mode; determining whether information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during another predetermined period of time; and in response to determining that the information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during the other predetermined period of time, using the control unit to command display of the information related to the armed or coupled predetermined navigation mode on the second screen; wherein determining whether the information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during the other predetermined period of time further comprises initializing an additional timer; running the additional timer for the other predetermined period of time and, during the other predetermined period of time, detecting whether the information related to the armed or coupled predetermined navigation mode has been displayed on a screen of the at least first and second screens; upon expiry of the other predetermined period of time and in response to detecting that the information related to the armed or coupled predetermined navigation mode has not been displayed on a screen of the at least first and second screens, generating a status signal indicating that the information related to the armed or coupled predetermined navigation mode has not been displayed during the other predetermined period of time; and in response to receiving the status signal with the control unit, using the control unit to automatically command display of the information related to the armed or coupled predetermined navigation mode on the second screen.

4. The method of claim 3, wherein in the second mode only the second screen is operational and all other screens of the at least first and second screens are non-operational.

5. The method of claim 3, further comprising: with the control unit, receiving an alert signal indicating an occurrence of a flight safety-critical event; and in response to receiving the alert signal, displaying information related to the flight safety-critical event on the second screen.

6. The method of claim 1, further comprising: in response to determining that the control unit is no longer in the second mode or that the critical flight relevant information has already been displayed on a screen of the at least first and second screens, before the timer has run for the predetermined period of time, generating a status signal indicating that the critical flight relevant information has been displayed on the second screen during the predetermined period of time.

7. The method of claim 1, further comprising: with the control unit, receiving an alert signal indicating an occurrence of a flight safety-critical event; and in response to receiving the alert signal, displaying information related to the flight safety-critical event on the second screen.

8. The method of claim 7, wherein the flight safety-critical event includes at least one of a first event that represents an immediate hazard to the safe operation of the aircraft or a second event that represents a potential future hazard to the safe operation of the aircraft.

9. The method of claim 1, further comprising: with the control unit, receiving an information signal indicating an armed or coupled predetermined navigation mode; determining whether information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during another predetermined period of time; and in response to determining that the information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during the other predetermined period of time, using the control unit to command display of the information related to the armed or coupled predetermined navigation mode on the second screen.

10. The method of claim 9, wherein the armed or coupled predetermined navigation mode comprises at least one of an armed or coupled automatic flight control system, an armed or coupled flight management system, an armed or coupled very high frequency omni-directional range system, or an armed or coupled instrument landing system.

11. The method of claim 9, wherein determining whether the information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during the other predetermined period of time further comprises: initializing an additional timer.

12. The method of claim 11, further comprising: running the additional timer for the other predetermined period of time and, during the other predetermined period of time, detecting whether the information related to the armed or coupled predetermined navigation mode has been displayed on a screen of the at least first and second screens; upon expiry of the other predetermined period of time and in response to detecting that the information related to the armed or coupled predetermined navigation mode has not been displayed on a screen of the at least first and second screens, generating a status signal indicating that the information related to the armed or coupled predetermined navigation mode has not been displayed during the other predetermined period of time; and in response to receiving the status signal with the control unit, using the control unit to automatically command display of the information related to the armed or coupled predetermined navigation mode on the second screen.

13. The method of claim 11, further comprising: running the additional timer; determining that the information related to the armed or coupled predetermined navigation mode has already been displayed on a screen of the at least first and second screens, before the additional timer has run for the other predetermined period of time; and generating a status signal indicating that the information related to the armed or coupled predetermined navigation mode has been displayed on the second screen during the other predetermined period of time.

14. The method of claim 1, further comprising: commanding display of information related to either one of two redundant instrument landing systems on the second screen.

15. A display system in an aircraft adapted to perform the method of claim 1, comprising: at least a first and a second screen that are installed in a cockpit of the aircraft; and a control unit that monitors the at least first and second screens and controls display of the flight relevant information on the at least first and second screens in a first mode and in a second mode, wherein in the first mode the first and second screens are operational, and wherein the control unit enters the second mode upon detecting occurrence of a failure of the first screen, wherein in the second mode, the control unit commands the second screen to display a message that suggests a switch from displaying a first non-critical flight relevant information of the flight relevant information on the second screen to displaying a first critical flight relevant information of the flight relevant information on the second screen, if the first critical flight relevant information has not been displayed on the second screen during a predetermined period of time.

16. A method for operating, in an aircraft, a display system that comprises a control unit and at least a first and a second screen that are installed in a cockpit of the aircraft, comprising: using the control unit to monitor the at least first and second screens and control display of the flight relevant information on the at least first and second screens in a first mode and in a second mode, wherein in the first mode the first and second screens are operational; if failure of the first screen occurs, detecting occurrence of the failure of the first screen with the control unit; in response to detecting occurrence of the failure of the first screen, entering the second mode with the control unit; wherein in the second mode, determining with the control unit whether a critical flight relevant information of the flight relevant information has not been displayed on the second screen during a predetermined period of time; and in response to determining with the control unit that the critical flight relevant information has not been displayed on the second screen during the predetermined period of time, using the control unit to command display of a message on the second screen that suggests displaying the critical flight relevant information on the second screen; wherein determining whether the critical flight relevant information has not been displayed on the second screen during the predetermined period of time further comprises initializing a timer; running the timer; determining whether the control unit is no longer in the second mode or whether the critical flight relevant information has already been displayed on a screen of the at least first and second screens, before the timer has run for the predetermined period of time; and in response to determining that the control unit is no longer in the second mode or that the critical flight relevant information has already been displayed on a screen of the at least first and second screens, before the timer has run for the predetermined period of time, generating a status signal indicating that the critical flight relevant information has been displayed on the second screen during the predetermined period of time.

17. The method of claim 16, wherein in the second mode only the second screen is operational and all other screens of the at least first and second screens are non-operational.

18. The method of claim 16, further comprising: with the control unit, receiving an alert signal indicating an occurrence of a flight safety-critical event; and in response to receiving the alert signal, displaying information related to the flight safety-critical event on the second screen.

19. The method of claim 18, wherein the flight safety-critical event includes at least one of a first event that represents an immediate hazard to the safe operation of the aircraft or a second event that represents a potential future hazard to the safe operation of the aircraft.

20. The method of claim 5, wherein the flight safety-critical event includes at least one of a first event that represents an immediate hazard to the safe operation of the aircraft or a second event that represents a potential future hazard to the safe operation of the aircraft.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Embodiments are outlined by way of example in the following description with reference to the attached drawings. In these attached drawings, identical or identically functioning components and elements are labeled with identical reference numbers and characters and are, consequently, only described once, in the following description.

(2) FIG. 1 is a diagram of an illustrative aircraft with a cockpit in accordance with some embodiments,

(3) FIG. 2 is a diagram of an illustrative display system in accordance with some embodiments,

(4) FIG. 3A is a diagram of an illustrative screen of a display system in accordance with some embodiments,

(5) FIG. 3B is a diagram of an illustrative screen of a display system showing a message in accordance with some embodiments,

(6) FIG. 4A is a diagram of an illustrative display system with two screens at a left, crew station and two screens at a right crew station in accordance with some embodiments,

(7) FIG. 4B is a diagram of an illustrative display system with one screen at a left crew station and two screens at a right crew station in accordance with some embodiments,

(8) FIG. 4C is a diagram of an illustrative display system with two screens for a single pilot configuration in accordance with some embodiments,

(9) FIG. 5 is a diagram of an exemplary flowchart showing illustrative operations for operating, in an aircraft, a display system that comprises a control unit and at least a first and a second screen that are installed in a cockpit of the aircraft in accordance with some embodiments,

(10) FIG. 6A is a diagram of a first exemplary flowchart showing illustrative operations for determining whether, after failure of a first screen has occurred, critical flight relevant information has not been displayed on a second screen during a predetermined period of time in accordance with some embodiments,

(11) FIG. 6B is a diagram of a second exemplary flowchart showing illustrative operations for determining whether, after failure of a first, screen has occurred, critical flight, relevant information has not been displayed on a second screen during a predetermined period of time in accordance with some embodiments,

(12) FIG. 7 is a diagram of an exemplary flowchart showing illustrative operations for commanding display of information related to an armed or coupled predetermined navigation mode on one screen after failure of at least one other screen in accordance with some embodiments, and

(13) FIG. 8 is a diagram of an exemplary flowchart showing illustrative operations for determining whether, after failure of a first screen has occurred, information related to an armed or coupled predetermined navigation mode has not been displayed on a second screen during a predetermined period of time in accordance with some embodiments.

DETAILED DESCRIPTION OF THE INVENTION

(14) Exemplary embodiments may be included in any aircraft with a cockpit in which a multi-screen display system is installed, and in which the multi-screen display system provides information that is relevant for the operation of the aircraft.

(15) FIG. 1 shows an example of an aircraft 1. An aircraft may be an airplane, a multicopter, a helicopter, or any other flying vehicle with a cockpit in which a multi-screen display system is installed. As shown in FIG. 1, aircraft 1 may be an airplane.

(16) Aircraft 1 is exemplarily embodied with fuselage 2 that includes compartments 2a and 2b. In some embodiments, compartments 2a, 2b may include the cockpit, the cabin, the cargo compartment, etc. If desired, compartments 2a, 2b may be spatially separated, for example, by a wall or a door 3. Cockpit 2a of aircraft 1 may have a display system. The display system may have a control unit and at least two screens that are installed in cockpit 2a.

(17) FIG. 2 shows illustrative display system 20 in accordance with some embodiments. Display system 20 may include display management system 28, human-machine interface (HMI) 14, and a warning management system of flight warning system (FWS) type 16.

(18) Display management system 28 may include control unit 12 and a plurality of display screens 18, which are sometimes also referred to as display units (DU) 18 or screens 18. In particular, display management system 28 may include at least a first and a second screen 18. Screens 18 may be located in the cockpit of an aircraft (e.g., in cockpit 2a of aircraft 1 of FIG. 1). If desired, connections 22 may connect screens 18 to control unit 12.

(19) In some embodiments, connection 24 may connect control unit 12 with human-machine interface (HMI) 14. Various variants are possible for human-machine interface 14. Human-machine interface 14 may, for example, include a push-button, a joystick, a pointing device such as a trackball, a touchscreen, etc. or any combination thereof.

(20) If desired, control unit 12 may be connected to a set of avionics computers. For example, connection 26 may connect control unit 12 to warning management system of flight warning system (FWS) type 16.

(21) In operation, control unit 12 may command the display on screens 18 according to information that it receives, in particular from the avionics computers including warning management system 16, and according to interactions with members of the aircraft's crew on the human-machine interface 14.

(22) In some embodiments, control unit 12 may monitor the proper operation of screens 18 via connections 22. For example, control unit 12 may monitor the at least first and second screens 18 and control display of flight relevant information on the at least first and second screens 18 in a first mode and in a second mode, wherein in the first mode the first and second screens 18 are operational.

(23) If desired, control unit 12 may be able to detect failure of one or more screens 18. To this end, control unit 12 may be configured to receive information about the state of screens 18 via connections 22 and to detect failure of a screen 13 according to the state information.

(24) In the absence of screen failure, control unit 12 may command the display on screens 18 according to the first mode, which is sometimes also referred to as “normal display mode”. In the event of failure of at least one screen of screens 18, the control unit 12 may command the display on another, functioning, screen of screens 18 according to the second mode, which is sometimes also referred to as “reconfigured display mode”.

(25) As an example, consider the scenario in which control unit 12 operates in the first mode. Consider further that failure of a first screen 18 occurs. In this scenario, control unit 12 may detect occurrence of the failure of the first screen 18. In response to detecting occurrence of the failure of the first screen, control unit 12 may enter the second mode.

(26) In the normal display mode, control unit 12 may command the display of at least one display window on each screen 18. In some embodiments, screen 18 may include more than one display area. For example, screen 18 may include a first and a second display area. In this example, control unit 12 may commands the display of at least one display window in the first display area and the display of at least one other display window in the second display area.

(27) A display window may include any display that locally regroups information on a screen. Optionally, the display window may be delimited by a frame.

(28) When the warning management system 16 detects the occurrence of an event on board the aircraft, if the flight procedures dictate that this event must be signaled to the members of the aircraft's crew and requires an action on the part of a crew member, then the warning management system 16 sends information relating to this event to the control unit 12 via the connection 26. The control unit 12 then commands the display of an interactive element in an interaction window and it commands the display of the interaction window on one of the screens 18, at least while an action by an operator is required on the interactive element.

(29) Thus, a crew member, such as a pilot of the aircraft, may use the human-machine interface 14 in order to act on the interactive element so as to carry out the required action. As the interaction window is displayed on one of screens 18, the pilot may act on the interactive element in this window subsequent to the occurrence of an event, without having to carry out any action to bring about the display of the interaction window.

(30) In the reconfigured display mode, control unit 12 may be configured to command on an operational screen 18 (e.g., a second screen) the display of a display window that is normally displayed on the no longer operational screen 18 (e.g., a first screen) in the normal display mode. This display window is then displayed on the second screen instead of another display window that is displayed on the second screen in normal display mode.

(31) According to one embodiment, control unit 12 may automatically command the display of the display window on the second screen following the failure of the first screen. For example, the display window may be parameterized in control unit 12 as having priority with respect to the other display window that is displayed on the second screen in normal display mode.

(32) According to one embodiment, control unit 12 may command the display of the display window on the second screen following an action by an operator on human-machine interface 14 after the failure of the first screen. For example, the display window may be parameterized in the control unit 12 as having lower priority with respect to the other display window that is displayed on the second screen in normal display mode.

(33) As an example, the display windows of Engine Display (ED), System Display (SD), MailBox (MB), Warning Display (WD), and Multi-Function Display (MFD) types may be parameterized in control unit 12 as having a lower priority, and the display windows of Flight and Navigation Display (FND), Vertical Display (VD), Primary Flight Display (PFD), Slat Flaps and Trim Indicator (SFT), Instrument Landing System (ILS), Automatic Flight Control System (AFCS), Flight Management System (FMS), Very High Frequency (VHF) Omni-Directional Range (VOR) types may be parameterized in control unit 12 as having higher priority.

(34) The display windows of display types that are parameterized in control unit 12 as having lower priority are sometimes associated with non-critical flight relevant information, while the display windows of display types that are parameterized in control unit 12 as having higher priority are sometimes associated with critical flight relevant information.

(35) When control unit 12 receives, via connection 24, information originating from human-machine interface 14 relating to an action by an operator on human-machine interface 14, the control unit 12 may command a change of the display window displayed on the second screen.

(36) For example, consider the scenario in which control unit 12 is in the reconfigured display mode, and a display window of a type having a higher priority parameter in control unit 12 (e.g., a display window of ND and/or VD type) is displayed on the second screen before an action by the operator on human-machine interface 14. Consider further that the effect of an action on human-machine interface 14 replaces the display window of the type having the higher priority parameter in control unit 12 with another display window of a type having a lower priority parameter in control unit 12 (e.g., a display window of ED and/or SD type).

(37) In other words, the second screen displays a display window that is associated with critical flight relevant information and the effect of an action on human-machine interface 14 replaces the display window that is associated with critical flight relevant information with a display window that is associated with non-critical flight relevant information.

(38) In this scenario, control unit 12 may determine that the critical flight relevant information is no longer displayed on the second screen. If desired, control unit 12 may be configured to allow that critical flight relevant information is not being displayed on the second screen for a predetermined period of time.

(39) Thus, control unit 12 may initialize a timer in response to detecting that the critical flight relevant information has not been displayed on the second screen. Control unit 12 may run the timer for the predetermined period of time and, during the predetermined period of time, detect whether control unit 12 has returned to the normal display mode or whether the critical flight relevant information has been displayed on the second screen.

(40) Upon expiry of the predetermined period of time and in response to detecting that control unit 12 has not returned to the normal display mode and that the critical flight relevant information has not been displayed on the second screen, control unit 12 may generate a status signal indicating that the critical flight relevant information has not been displayed during the predetermined period of time.

(41) In response to the status signal, control unit 12 may command display of a message on the second screen that suggests displaying the critical flight relevant information on the second screen. The message may be designed to draw the attention of the operator. For example, control unit 12 may display any combination of a display window with a different color than the remainder of the screen, a display window that flashes, a display window with text that blinks, a display window that is placed in the center of the screen or in any other highly visible area, etc.

(42) The operator, in particular a pilot of the aircraft, is thereby informed that he or she should change the display window on the second screen from displaying non-critical flight relevant information to displaying critical flight relevant information. For example, an action by the operator on the human-machine interface 14 may then direct control unit 12 to command display of the display window with the critical flight relevant information on the second screen, instead of the display window with the non-critical flight relevant information.

(43) In some scenarios, control unit 12 may determine that the control unit 12 is no longer in the reconfigured display mode or that the critical flight relevant information has already been displayed on the second screen, before the timer has run for the predetermined period of time.

(44) Thus, control unit 12 may generate a status signal indicating that the critical flight relevant Information has been displayed on the second screen during the predetermined period of time. In response to the status signal, control unit 12 may restrain from commanding display of a message on the second screen.

(45) As another example, consider the scenario in which control unit 12 is in the reconfigured display mode with a first screen being non-operational and a second screen being operational. Consider further that control unit 12 receives an information signal (e.g., from warning management system 16 via connection 26) indicating an armed or coupled predetermined navigation mode. For example, control unit 12 may receive an information signal indicating that the automatic flight control system (AFCS), the flight management system (FMS), the VHF omni-directional range (VOR), the instrument landing system (ILS), and/or any other predetermined navigation mode is armed (i.e., turned on) and/or coupled (i.e., in connection with a device that is not on board the aircraft, such as a terrestrial antenna).

(46) In such a scenario, flight regulations may require that a display window associated with the predetermined navigation mode displays information related to the armed or coupled predetermined navigation mode. Consider further that the effect of an action on human-machine interface 14 replaces the display window associated with the predetermined navigation mode with another display window of a type having a lower priority parameter in control unit 12 (e.g., a display window of ED and/or SD type).

(47) In other words, the second screen displays a display window that is associated with the predetermined navigation mode and the effect of an action on human-machine interface 14 replaces the display window that is associated with the predetermined navigation mode with a display window that is associated with non-critical flight relevant information.

(48) In this scenario, control unit 12 may determine that the information that is associated with the armed or coupled predetermined navigation mode is no longer displayed on the second screen. If desired, control unit 12 may be configured to allow that the information that is associated with the armed or coupled predetermined navigation mode is not being displayed on the second screen for a predetermined period of time before the armed or coupled predetermined navigation mode needs to be disarmed and/or decoupled.

(49) For example, control unit 12 may initialise a timer, run the timer for a first predetermined period of time, which may be shorter than a second predetermined period of time, upon expiry of which, the armed or coupled predetermined navigation mode needs to be disarmed and/or decoupled. Control unit 12 may, during the first predetermined period of time, detect whether the information related to the armed or coupled predetermined navigation mode has been displayed on the second screen. Upon expiry of the first predetermined period of time and in response to detecting that the information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen, control unit 12 may generate a status signal indicating that the information related to the armed or coupled predetermined navigation mode has not been displayed during the first predetermined period of time.

(50) In response to determining that the information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during the first; predetermined period of time (e.g., based on the status signal), control unit 12 may command display of the information related to the armed or coupled predetermined navigation mode on the second screen.

(51) In other words, before expiry of the period of time before the armed or coupled predetermined navigation mode needs to be disarmed and/or decoupled, control unit 12 may automatically command display of the information related to the armed or coupled predetermined navigation mode on the second screen, thereby overriding the operator's choice of displaying a display window that is associated with non-critical flight relevant information and avoiding disarmament and/or decoupling of the predetermined navigation mode.

(52) As another example, control unit 12 may initialize a timer, run the timer, and determine that the information related to the armed or coupled predetermined navigation mode has already been displayed on the second screen before expiry of the first predetermined period of time.

(53) If desired, control unit 12 may generate a status signal indicating that the information related to the armed or coupled predetermined navigation mode has been displayed on the second screen during the first predetermined period of time. In response to the status signal, control unit 12 may restrain from commanding a change of display windows on the second screen.

(54) In some scenarios, flight regulations may require the monitoring of redundant information on different screens of a display system. For example, flight regulations may require that information related to a first of two redundant instrument landing systems (ILS) is monitored on a first screen and that information related to a second of the two redundant instrument landing systems is monitored on a second screen.

(55) In some embodiments, when control unit 12 is operating in the reconfigured display mode with the first screen being non-operational and the second screen being operational, control unit 12 may command display of information related to either one of two redundant instrument landing systems (ILS) on the second screen.

(56) In some embodiments, control unit 12 may command display of information related to either one of two redundant instrument landing systems (ILS) on either one of the first and second screens when control unit 12 is operating in the normal display mode and both screens are operational.

(57) In some embodiments, control unit 12 may receive an alert signal. For example, control unit 12 may receive an alert signal from warning management system 16 via connection 26. The alert signal may indicate an occurrence of a flight safety-critical event. For example, the flight safety-critical event may include one or more events that represent an immediate hazard to the safe operation of the aircraft and/or one or more events that represent a potential future hazard to the safe operation of the aircraft.

(58) In response to receiving the alert signal, control unit 12 may command display of information related to the flight safety-critical event on the second screen. For example, control unit 12 may display the information related to the flight safety-critical event in form of any combination of a display window with a different color than the remainder of the screen, a display window that flashes, a display window with text that blinks, a display window that is placed in the center of the screen or in any other highly visible area, etc.

(59) In some embodiments, display attributes of the information related to the flight safety-critical event, such as its color or the display type (fixed or flashing, etc.) may depend on the importance of the event parameterized in the control unit 12. For example, the indicator may be displayed in red for the most important events and in yellow for less important events.

(60) In some embodiments, the plurality of display screens 13 of display system 20 may include at least a first and a second screen 18. According to one embodiment, at least the second screen may include display surface 30 in which the display is shared between display area 31 and signaling area 35, as shown in FIG. 3A.

(61) As shown in FIG. 3A, display area 31 may be arranged above signaling area 35. However, display area 31 and signaling area 35 may be arranged differently on display surface 30. For example, display area 31 may be arranged left of signaling area 35, right of signaling area 35, below signaling area 35, etc. In some embodiments, display area 31 may be split info left and right display areas and signaling area 35 may be arranged between the left and right display areas.

(62) As an example, subsequent to the occurrence of a flight safety-critical event on board the aircraft, control unit 12 may display the information related to the flight safety-critical event on the second screen by commanding the display of an indicator in signaling area 35 of display surface 30.

(63) The operator may then take note of the occurrence of a flight safety-critical event and carry out the required action by acting on the human-machine interface 14, if desired. The action may include, for example, an acknowledgment of a warning or a modification in the state of a system of the aircraft (e.g., the shutdown of an engine, the opening or closing of a valve, etc.).

(64) In some embodiments, signaling area 35 may include an interactive element that is actionable using the human-machine interface. For example, when the human-machine interface corresponds to a pointing device, the interactive element may correspond to a portion of the signaling area in which an operator may click. As another example, when the human-machine interface corresponds to a touchscreen, the interactive element may correspond to a sensitive surface of the touchscreen, this sensitive surface being defined in the signaling area.

(65) FIG. 3B shows a screen with display surface 30 on which display area 31 may be arranged above signaling area 35. If desired, display area 31 and signaling area 35 may be arranged differently on display surface 30. For example, display area 31 may be arranged left of signaling area 35, right of signaling area 35, below signaling area 35, etc. In some embodiments, display area 31 may be split into left and right display areas and signaling area 35 may be arranged between the left and right display areas.

(66) As shown in FIG. 3B, display area 31 may include message area 33. If desired, message, area 33 may be arranged differently on display area 31. For example, message area 33 may be placed on top, on the bottom, in the center, on the right, on the left, or in a corner of display area 31, just to name a few alternatives.

(67) If desired, message area 33 may take more or less space on display area 31. As an example, message area 33 may cover the entire display area 31. As another, example, message area 33 may cover only a small portion of display area 31. In some embodiments, message area 33 may be placed inside signaling area 35.

(68) As an example, message area 33 may display the message that suggests displaying critical flight relevant, information on the second screen. In some embodiments, signaling area 35 may display the message that suggests displaying critical flight relevant information on the second screen. If desired, message area 33 and signaling area 35 may both display the message that suggests displaying critical flight relevant information on the second screen. If desired, message area 33 and/or signaling area 35 may display the information related to a flight safety-critical event after occurrence of such an event.

(69) Message area 33 and/or signaling area 35 may display the message and/or the information related to the flight safety-critical event so as to draw the attention of the operator. For example, message area 33 may have a different color than the remainder of the screen, may flash or blink, may include text that blinks, etc.

(70) FIGS. 4A, 4B, and 4C show different display screen arrangements that may be installed in a cockpit of an aircraft. In some embodiments, a display system may include a single screen with different display surfaces that are controlled individually by a control unit (e.g., control unit 12 of FIG. 2 that controls several display units that all may be on the same screen).

(71) If desired, every display surface may be on a separate screen. In some embodiments, two or more display surfaces may be grouped on one screen. For example, two screens may be installed in the cockpit, and every screen of the two screens may have two display surfaces for a total of four display surfaces.

(72) However, for simplicity and clarity, we assume that one screen has one display surface. In other words, different display surfaces are on separate screens or each screen has exactly one display surface. Thus, as shown in FIGS. 4A, 4B, and 4C, each display system may include at least a first screen and a second screen.

(73) For example, FIG. 4A shows a right crew station 36 with two screens 30a, 30b and a left crew station 37 with two screens 30c, 30d. FIG. 4B shows a right crew station 36 with two screens 30a, 30b and a left crew station 37 with one screen 30c, and FIG. 4C shows a right crew station 36 with two screens 30a, 30b.

(74) During normal operation, all screens 30 are operational and connected to a control unit (e.g., via connections 22 to control unit 12 of FIG. 2). The control unit may monitor screens 30 and have two different modes. The control unit may be in a first mode or normal display mode when all screens 30 are operational.

(75) If failure of a first screen of screens 30 occurs, the control unit may detect the occurrence of the failure of the first screen. In response to detecting occurrence of the failure of the first screen, the control unit may enter a second mode which is sometimes also referred to as a reconfigured display mode.

(76) For example, screens 30a and 30c of FIG. 4B may fail. In this example, only screen 30b is operational and all other screens 30a, 30c are non-operational. As another example, screen 30b of FIG. 4C may fail and only screen 30a remains operational.

(77) If the first screen starts working again and the control unit detects that ail screens 30 are operational, the control unit may return to the first mode or normal display mode.

(78) FIG. 5 is a diagram of an illustrative flowchart showing exemplary operations for operating, in an aircraft, a display system that comprises a control unit and at least a first and a second screen that are installed in a cockpit of the aircraft in accordance with some embodiments. As an example, a display system such as display system 20 with control unit 12 of FIG. 2 may perform operations 51, 52, 53, 55, 56, and 57 of method 50.

(79) During operation 51, the display system may use the control unit to monitor the at least first and second screens and control display of the flight relevant information on the at least first and second screens in a first mode and in a second mode, wherein in the first mode the first and second screens are operational.

(80) For example, control unit 12 of display system 20 of FIG. 2 may monitor screens 18 via connections 22. If desired, control unit 12 may control display of the flight relevant information on screens 16. If the monitored screens 18 are operational, control unit 12 operates in a first mode which is sometimes also referred to as a normal display mode.

(81) During operation 52, the display system may observe whether failure of the first screen occurs. If no failure of the first screen occurs, the display system returns to operation 51.

(82) If failure of the first screen occurs, the display system may detect occurrence of the failure of the first screen with the control unit during operation 53.

(83) During operation 55, in response to detecting occurrence of the failure of the first screen, the display system may enter the second mode with the control unit. For example, control unit 12 of display system 20 of FIG. 2 may, upon detecting occurrence of a failure of a screen of screens 13, enter a second mode which is sometimes also referred to as a reconfigured display mode.

(84) During operation 56, the display system may monitor whether critical flight relevant information of the flight relevant information has not been displayed on the second screen during a predetermined period of time.

(85) If critical flight relevant information of the flight relevant information has not been displayed on the second screen during the predetermined period of time, the display system may use the control unit to command display of a message on the second screen that suggests displaying the critical flight relevant information on the second screen during operation 57.

(86) For example, control unit 12 of display system 20 of FIG. 2 may run a timer for the predetermined period of time and detect whether control unit 12 has returned to the normal display mode or whether the critical flight relevant information has been displayed on the second screen during that time. If this is not the case, control, unit 12 may command display of a message on the second screen.

(87) The message may be designed to draw the attention of the operator. For example, control unit 12 may display any combination of a display window with a different color than the remainder of the screen, a display window with text that has a different color than the text in other display windows, a display window that flashes, a display window with text that blinks, a display window that is placed in the center of the screen or in any other highly visible area, etc.

(88) The operator, in particular a pilot of the aircraft, is thereby informed that he or she should change the display window on the second screen from displaying non-critical flight relevant information to displaying critical flight relevant information.

(89) FIG. 6A is a diagram of a first exemplary flowchart showing illustrative operations for determining whether, after failure of the first screen has occurred, critical flight relevant information has not been displayed on the second screen during a predetermined period of time in accordance with some embodiments. As an example, a display system such as display system 20 with control unit 12 of FIG. 2 may perform operations 61, 63, and 64 of method 60.

(90) During operation 61, the display system may initialize a timer. For example, control unit 12 of display system 20 of FIG. 2 may include a timer. The timer may be a countdown timer that is initialized at the predetermined period of time and counts down until reaching zero. If desired, the timer may be a stopwatch that starts at zero and counts up until reaching the predetermined period of time.

(91) During operation 63, the display system may run the timer for the predetermined period of time and, during the predetermined period of time, detect whether the control unit has returned to the first mode or whether the critical flight relevant information has been displayed on a screen of the at least first and second screens.

(92) For example, control unit 12 of display system 20 of FIG. 2 may monitor screens 18 via connections 22 while the timer is running. In particular, control unit 12 may monitor screens 18 to detect whether all screens have become operational again and, as a result, the control unit has returned to the first mode. Control unit 12 may also monitor screens 18 to detect whether the critical flight relevant information has been displayed on one of the still operating screens 18.

(93) During operation 64, the display system may, upon expiry of the predetermined period of time and in response to detecting that the control unit has not returned to the first mode and that the critical flight relevant information has not been displayed on a screen of the at least first and second screens, generate a status signal indicating that the critical flight relevant information has not been displayed during the predetermined period of time.

(94) For example, control unit 12 of display system 20 of FIG. 2 may not have detected during the predetermined period of time that all screens have become operational and may not have detected that the critical flight relevant information has been displayed on one of the still operating screens 18. If desired, display system 20 may generate a status signal that is indicative of a non-display of critical flight relevant information on any screen of the still operating screens 18.

(95) In some embodiments, control unit 12 may command display of a message on the second screen that suggests displaying the critical flight relevant information on the second screen in response to the status signal.

(96) FIG. 6B is a diagram of a second exemplary flowchart showing illustrative operations for determining whether, after failure of the first screen has occurred, critical flight relevant information has not been displayed on the second screen during a predetermined period of time in accordance with some embodiments. As an example, a display system such as display system 20 with control unit 12 of FIG. 2 may perform operations 66, 67, 68, and 69 of method 65.

(97) During operation 66, the display system may initialize a timer. For example, control unit 12 of display system 20 of FIG. 2 may include a timer. The timer may be a countdown timer that is initialized at the predetermined period of time and counts down until reaching zero. If desired, the timer may be a stopwatch that starts at zero and counts up until reaching the predetermined period of time.

(98) During operation 67, the display system may run the timer. For example, control unit 12 of display system 20 of FIG. 2 may count down until reaching zero if the timer is a countdown timer or count up if the timer is a stopwatch.

(99) During operation 68, the display system may determine that the control unit is no longer in the second mode or that the critical flight relevant information has already been displayed on a screen of the at least first and second screens, before the timer has run for the predetermined period of time.

(100) For example, while control unit 12 of display system 20 of FIG. 2 counts up or down, control unit 12 may detect that all screens have become operational again or that the critical flight relevant information has been displayed on one of the still operating screens 18.

(101) During operation 69, the display system may generate a status signal indicating that the critical flight relevant information has been displayed on the second screen during the predetermined period of time. If desired, display system 20 of FIG. 2 may generate a status signal that is indicative of a display of critical flight relevant information on any screen of the still operating screens 18.

(102) Optionally the timer may be stopped as soon as the control unit detects a display of critical flight relevant information on any screen of the still operating screens.

(103) FIG. 7 is a diagram of an exemplary flowchart showing illustrative operations for commanding display of information related to an armed or coupled predetermined navigation mode on one screen after failure of at least one other screen in accordance with some embodiments. As an example, a display system such as display system 20 with control unit 12 of FIG. 2 may perform operations 71, 72, and 73 of method 70.

(104) During operation 71, the display system may receive an information signal indicating an armed or coupled predetermined navigation mode. For example, control unit 12 of display system 20 of FIG. 2 may receive a status signal from warning management system 16 over connection 26 that is indicative of an armed or coupled predetermined navigation mode.

(105) Such a status signal may indicate that the automatic flight control system (AFCS), the flight management system (FMS), the VHF omni-directional range (VOR), the instrument landing system (ILS), and/or any other predetermined navigation mode is armed (i.e., turned on) and/or coupled (i.e., in connection with, a device that is not on board the aircraft, such as a terrestrial antenna).

(106) During operation 72, the display system may determine whether information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during another predetermined period of time.

(107) For example, flight regulations may impose that a display window associated with the predetermined navigation mode displays information related to the armed or coupled predetermined navigation mode on a screen of the display system. Consider further that in display system 20 of FIG. 2, the effect of an action on human-machine interface 14 replaces the display window associated with, the predetermined navigation mode that is displayed on a screen 18 of display system 20 with another display window of a type having a lower priority parameter in control unit 12 on that screen 18.

(108) In other words, the second screen displays a display window that is associated with the predetermined navigation mode and the effect of an action on human-machine interface 14 replaces the display window that is associated with the predetermined navigation mode with a display window that is associated with non-critical flight relevant information on the second screen.

(109) For example, control unit 12 of display system 20 of FIG. 2 may determine that the information that is associated with the armed or coupled predetermined navigation mode is no longer displayed on the second screen. If desired, control unit 12 may be configured to allow that the information that is associated with the armed or coupled predetermined navigation mode is not being displayed on the second screen for a predetermined period of time before the armed or coupled predetermined navigation mode has to be disarmed and/or decoupled.

(110) During operation 73, the display system may, in response to determining that the information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during the other predetermined period of time, use the control unit to command display of the information related to the armed or coupled predetermined navigation mode on the second screen.

(111) For example, control unit 12 of display system 20 of FIG. 2 may command display of the information related to the armed or coupled predetermined navigation mode on one of the still functioning screens 18 to avoid disarmament and/or decoupling of the armed or coupled predetermined navigation mode.

(112) FIG. 8 is a diagram of an exemplary flowchart showing illustrative operations for determining whether, after failure of the first screen has occurred, the information related to the armed or coupled predetermined navigation mode has not been displayed on the second screen during another predetermined period of time in accordance with some embodiments. As an example, a display system such as display system 20 with control unit 12 of FIG. 2 may perform operations 81, 82, 83, 84, 85, 86, and 87 of method 80.

(113) During operation 81, the display system may initialize an additional timer. For example, control unit 12 of display system 20 of FIG. 2 may include an additional timer. The additional timer may be a countdown timer that is initialized at a predetermined period of time and counts down until reaching zero. If desired, the timer may be a stopwatch that starts at zero and counts up until reaching the predetermined period of time.

(114) During operation 82, the display system may run the additional timer for the other predetermined period of time and, during the additional period of time, detecting whether the information related to the armed or coupled predetermined navigation mode has been displayed on a screen of the at least first and second screens.

(115) For example, control unit 12 of display system 20 of FIG. 2 may monitor screens 18 via connections 22 and detect whether the information related to the armed or coupled predetermined navigation mode has been displayed on one of the operational screens 18.

(116) During operation 84, the display system may, upon expiry of the other predetermined period of time and in response to detecting that the information related to the armed or coupled predetermined navigation mode has not been displayed on a screen of the at least first and second screens, generate a status signal indicating that the information related to the armed or coupled predetermined navigation mode has not been displayed during the other predetermined period of time.

(117) During operation 86, the display system may, in response to receiving the status signal with the control unit, use the control unit to automatically command display of the information related to the armed or coupled predetermined navigation mode on the second screen.

(118) For example, control unit 12 of display system 20 of FIG. 2 may command display of the information related to the armed or coupled predetermined navigation mode on one of the operational screens 18.

(119) During operation 83, the display system may run the additional timer. The display system may determine that the information related to the armed or coupled predetermined navigation mode has already been displayed on a screen of the at least first and second screens, before the additional timer has run for the other predetermined period of time during operation 85.

(120) For example, control unit 12 of display system 20 of FIG. 2 may monitor screens 18 via connections 22 and determine that the information related to the armed or coupled predetermined navigation mode has already been displayed on one of the operational screens 18.

(121) During operation 87, the display system may generate a status signal indicating that the information related to the armed or coupled predetermined navigation mode has been displayed on the second screen during the predetermined period of time.

(122) It should be noted that the above described embodiments are merely described to illustrate possible realizations of the present invention, but not in order to restrict the present invention thereto. Instead, multiple modifications and variations of the described embodiments are possible and should, therefore, also be considered as being part of the invention.

(123) By way of example, right crew stations 36 and left crew stations 37 of FIGS. 4A to 4C are each shown to have up to two screens 30a, 30b and 30c, 30d. However, right crew stations 36 and left crew stations may include a different number of screens. As an example, right crew stations 36 may have three screens, four screens, etc. or only one screen. Furthermore, the distinction between right and left crew stations 36, 37 of FIGS. 4A and 4B is arbitrary. If desired, left crew stations may have two screens while right crew stations have one, two, or no screens.

(124) Furthermore, although the method operations were described in a specific order, it should be understood that other operations may be performed in between described operations, described operations may be adjusted so that they occur at slightly different times or described operations may be distributed in a system which allows the occurrence of the processing operations at various intervals associated with the processing.

REFERENCE LIST

(125) 1 aircraft

(126) 2 fuselage

(127) 2a compartment/cockpit

(128) 2b compartment/cabin, cargo compartment

(129) 3 door

(130) 12 control unit

(131) 14 human-machine interface

(132) 16 warning management system/flight warning system

(133) 18 display unit/screen

(134) 20 display system

(135) 22, 24, 26 connections

(136) 28 display management system, cockpit display system

(137) 30, 30a, 30b, 30c, 30d display surface

(138) 31 display area

(139) 33 message area

(140) 35 signaling area

(141) 36 right crew station

(142) 37 left crew station

(143) 50 flowchart

(144) 51, 53, 55, 57 operation

(145) 52, 54 decision

(146) 60, 65 flowchart

(147) 61, 63, 64, 66, 67, 68, 69 operation

(148) 70 flowchart

(149) 71, 72, 73 operation

(150) 80 flowchart

(151) 81, 82, 83, 84, 85, 86, 87 operation