CN113815874A - Alarm information pushing method and system for aircraft - Google Patents
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
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Abstract
The invention discloses an alarm information pushing method for an aircraft, which comprises the following steps: when the aircraft is detected to be in an abnormal operation state, triggering the pushing of the alarm information associated with the abnormal operation state; determining whether there are one or more navigation map pages being displayed within the cockpit; if one or more navigation map pages are determined to exist, displaying the alarm information on one of the one or more navigation map pages; if it is determined that the navigation map page does not exist, the following operations are performed: selecting a multi-function display window available within the cockpit; switching the selected multifunctional display window from an original page to a navigation map page; and displaying the alarm information on the navigation map page of the selected multifunctional display window.
Description
Technical Field
The invention relates to the field of avionics systems, in particular to a warning information pushing method and system for an aircraft.
Background
Currently, the cockpit of a large civil aircraft usually includes a plurality of large-sized liquid crystal displays, and a part of the displays usually have a specific Display format, such as a Primary Flight Display (PFD) page. The display pages of the other displays are designed as Multi Function Windows (MFW), and the pilot can manually access the pages to be checked on the MFW as required, such as Flight Management (FMS), Checklist (CHKL), System summary page (SYS), navigation MAP (MAP), and Onboard Maintenance information (OMS). The navigation map page is used for displaying traffic information such as flight plans and waypoints of the airplane. When the monitoring System of the aircraft triggers an alarm, such as an alarm of a Weather Radar (WXR), a Terrain identification and alarm System (TAWS), and an air Traffic Warning and Collision Avoidance System (TCAS), the alarm information of these systems can be transmitted to the pilot through different overlay layers or alarm messages on a navigation map page, so as to help the pilot build situational Awareness and timely acquire the current abnormal operating state of the aircraft, which is very important for ensuring flight safety.
In the prior art, a pilot can manually set any of the multi-function display windows to a desired page during operation of the aircraft. If the pilot selects the navigation map page, whether the WXR, TAWS or TCAS information of the monitoring system needs to be superposed on the navigation map page or not can be set. When the monitoring system detects an abnormal operating condition that may threaten flight safety, relevant alarms, such as "WINDSHEAR", "TRAFFIC", etc., are triggered. If the navigation map page exists on the cockpit display at the moment, the navigation map page can automatically overlap key information corresponding to the alarm, so that the pilot can conveniently know the condition.
When the monitoring system triggers an alarm, the pilot needs to know the aircraft status as soon as possible and take action to resume normal flight. However, since the degree of automation of the cockpit is not high in the existing mainstream model, it is only possible to superimpose the display page of the monitoring system on the existing display page. If the pilot does not select the navigation map page to display, or the selected navigation map page is not allocated within the main field of view, the pilot may not be able to know the warning information in time. After the relevant monitoring alarm is triggered, if no navigation map page which is opened in the cockpit exists, the pilot needs to manually adjust a multifunctional display window to the navigation map page to acquire corresponding alarm information so as to process the alarm. The method has multiple operation steps, consumes long time in emergency, increases the workload of pilots, and is not favorable for flight safety.
In view of the deficiencies of the existing alert information pushing technology, it is desirable to provide an improved alert information pushing method and system for an aircraft.
Disclosure of Invention
The following presents a simplified summary of one or more aspects in order to provide a basic understanding of such aspects. This summary is not an extensive overview of all contemplated aspects, and is intended to neither identify key or critical elements of all aspects nor delineate the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that is presented later.
The invention provides an alarm information pushing method for an aircraft, which comprises the following steps: when the aircraft is detected to be in an abnormal operation state, triggering the pushing of the alarm information associated with the abnormal operation state; determining whether there are one or more navigation map pages being displayed within the cockpit; if one or more navigation map pages are determined to exist, displaying alarm information on one of the one or more navigation map pages; if it is determined that the navigation map page does not exist, the following operations are performed: selecting a multi-function display window available in the cockpit; switching the selected multifunctional display window from an original page to a navigation map page; and displaying the alarm information on the navigation map page of the selected multifunctional display window.
In some embodiments, determining whether there are one or more navigation map pages being displayed within the cockpit further comprises: it is determined whether one or more navigation map pages are present within the main field of view of the driver's seat being displayed.
In some embodiments, selecting one of the multi-function display windows available within the cockpit further comprises: identifying one or more multifunction display windows available within the cockpit; one of the one or more multi-function display windows is selected according to a predetermined criterion.
In some embodiments, the alert information includes associated layer information, and displaying the alert information on the navigation map page includes: and overlaying the map layer information onto a navigation map page.
In some embodiments, the alert information further includes associated text information, and displaying the alert information on the navigation map page further includes: and displaying the text information in a non-overlapped area on the navigation map page and the layer information.
In some embodiments, the method further comprises: and if the navigation map page displaying the alarm information is switched from the original page of the multifunctional display window, switching the multifunctional display window from the navigation map page back to the original page when detecting that the aircraft is in a normal operation state.
The invention also provides an alarm information pushing system for the aircraft, which comprises: the warning triggering module is used for triggering the pushing of the warning information associated with the abnormal operation state when the aircraft is detected to be in the abnormal operation state; a navigation map page detection module that determines whether there are one or more navigation map pages being displayed within the cockpit; a window selection module configured to: if the navigation map page is determined not to exist, selecting one multifunctional display window available in the cockpit; the page switching module switches the multifunctional display window selected by the window selection module from an original page to a navigation map page; an alert display module configured to: if one or more navigation map pages are determined to exist, displaying alarm information on one of the one or more navigation map pages; and if the navigation map page does not exist, displaying the alarm information on the navigation map page of the selected multifunctional display window.
In some embodiments, the navigation map page detection module is further configured to: it is determined whether one or more navigation map pages are present within the main field of view of the driver's seat being displayed.
In some embodiments, the window selection module is further configured to: identifying one or more multifunction display windows available within the cockpit; one of the one or more multi-function display windows is selected according to a predetermined criterion.
In some embodiments, the alert information includes associated layer information, and the alert display module is further configured to display the alert information on the navigational map page by: and overlaying the map layer information onto a navigation map page.
In some embodiments, the alert information further includes associated textual information, and the alert display module is further configured to display the alert information on the navigation map page by: and displaying the text information in a non-overlapped area on the navigation map page and the layer information.
In some embodiments, the page switching module is further configured to: and if the navigation map page displaying the alarm information is switched from the original page of the multifunctional display window, switching the multifunctional display window from the navigation map page back to the original page when detecting that the aircraft is in a normal operation state.
The present invention also provides a computer-readable medium storing a computer program for alert information push for an aircraft, the computer program being executable by a processor to perform the aforementioned alert information push method for an aircraft.
According to the technical scheme, when the aircraft is detected to be in an abnormal operation state, the related warning information can be displayed on the existing navigation map page or the switched navigation map page in time, the warning information is quickly presented to the pilot, the situational awareness of the pilot is increased, the workload of the pilot is reduced, and the flight safety is improved.
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The features, nature, and advantages of the present invention will become more apparent from the detailed description set forth below when taken in conjunction with the drawings. In the drawings, like reference numerals are used to designate corresponding parts throughout the several views. It is noted that the drawings described are only schematic and are non-limiting. In the drawings, the size of some of the elements may be exaggerated and not drawn on scale for illustrative purposes.
Fig. 1 shows a flowchart of an alarm information pushing method of the present invention.
Fig. 2 shows a flowchart of the warning information pushing method in the case that the navigation map page being displayed exists in the cockpit according to the present invention.
Fig. 3 shows a flowchart of the warning information pushing method in the case that there is no navigation map page being displayed in the cockpit according to the present invention.
Fig. 4 shows a block diagram of the warning information pushing system of the present invention.
Fig. 5 shows a block diagram of a device comprising the alert information push system of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with specific embodiments. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the described exemplary embodiments. It will be apparent, however, to one skilled in the art, that the described embodiments may be practiced without some or all of these specific details. In other exemplary embodiments, well-known structures have not been described in detail to avoid unnecessarily obscuring the concepts of the present disclosure. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. Meanwhile, the various aspects described in the embodiments may be arbitrarily combined without conflict.
In the existing warning information pushing, if the pilot does not select the navigation map page to display, or the selected navigation map page is not distributed in the main view field range, the situation that the pilot cannot acquire warning information in time may exist. After the relevant monitoring alarm is triggered, if no navigation map page which is opened in the cockpit exists, the pilot needs to manually adjust a multifunctional display window to the navigation map page to acquire corresponding alarm information so as to process the alarm. The method has more operation steps and consumes more time in emergency, thus increasing the workload of pilots and being not beneficial to flight safety.
The invention provides an improved alarm information pushing method and system for an aircraft, which overcome the defects of the existing alarm information pushing technology and realize quick and timely alarm information pushing.
Fig. 1 shows a flow chart of an alert information pushing method 100 of the present invention.
The method 100 begins at step 102, and at step 102, when an aircraft is detected in an abnormal operating condition, a push of alert information associated with the abnormal operating condition is triggered.
In the present invention, the abnormal operation state refers to an operation state that threatens the flight safety to some extent. In particular, an abnormal operating condition may refer to an operating condition that puts the aircraft at risk above a predetermined threshold. Conversely, a normal operating state may refer to an operating state that places the aircraft at risk of not exceeding a predetermined threshold.
For example, when an aircraft's surveillance system detects a potential collision hazard with a neighboring aircraft, the aircraft's air traffic warning and collision avoidance system (TCAS) may determine that the aircraft is in an abnormal operating state and trigger an alert while pushing associated alert information. In another example, when wind shear is detected by a weather radar (WXR) of the aircraft, it may be determined whether the aircraft is in an abnormal operating state based on a distance and an orientation of the wind shear relative to the aircraft (i.e., whether the risk of the wind shear for the aircraft is above a threshold value), and a wind shear alert may be triggered and associated alert information may be pushed when the aircraft is determined to be in the abnormal operating state.
At step 104, it is determined whether there are one or more navigation map pages being displayed within the cockpit.
In a preferred embodiment, determining whether there are one or more navigation pages being displayed within the cockpit may include: it is determined whether there are one or more navigation pages being displayed within a Primary Field of View (View) of the driver's seat. As is known in the art, the main field of view range is in terms of cockpit design eye position and is typically represented by a horizontal field of view and a vertical field of view. An (optimal) horizontal field of view of +/-15 ° and an (optimal) vertical field of view of +/-15 ° are defined in AC 25-11B of the FAA, as well as a (maximum) horizontal field of view of +/-35 ° and a (maximum) vertical field of view of +40 ° up and-20 ° down. In the present invention, the main field of view range may be represented by a maximum horizontal field of view and a maximum vertical field of view.
If it is determined that one or more navigation map pages exist within the cockpit ("yes" at 104), then alert information is displayed on one of the one or more navigation map pages (106).
If it is determined that no navigational map page exists within the cockpit ("NO" of 104), the method 100 proceeds to step 108. At step 108, one of the multi-function display windows available in the cockpit is selected.
Next, at step 110, the selected multifunction display window is switched from the original page to the navigation map page. For example, the selected multifunction display window may initially be displaying on-board maintenance information (OMS), and the multifunction display window may be switched from the OMS page to the navigation map page.
Finally, at step 112, the alert information is displayed on the navigation map page of the selected multi-function display window.
In some embodiments, the alert information may include associated layer information (e.g., weather layer information), and displaying the alert information on the navigation map page may include: and superposing the related layer information on the navigation map page.
In some embodiments, the alert information may also include associated text information (e.g., alert words), and displaying the alert information on the navigation map page may include: and displaying the text information in a region which is not overlapped with the layer information on the navigation map page.
The method 100 automatically determines whether a navigation map page exists in the cockpit when detecting that the aircraft is in an abnormal operation state, selects an available multifunctional display window and switches an original page of the multifunctional display window to the navigation map page under the condition that the navigation map page does not exist, and pushes associated warning information on the navigation map page. For example, in the flight phase of the aircraft, if a TERRAIN warning is triggered, the pilot will receive a "TERRAIN" warning message, and at this time, if there is no navigation map page in the cockpit (preferably, within the main field of view of the pilot), the aircraft automatically selects one of the multi-function display windows in the cockpit (for example, the multi-function display window closest to the pilot) and switches the page of the multi-function display window to the navigation map page, and superimposes the TAWS layer. This enables the warning information to be presented to the pilot quickly, increases the situational awareness of the pilot, reduces the workload of the pilot, and further improves flight safety.
Fig. 2 shows a flow chart of an alert information pushing method 200 of the present invention in the presence of a navigation map page being displayed within the cockpit.
The method 200 begins at step 202, and at step 202, when an aircraft is detected in an abnormal operating condition, a push of alert information associated with the abnormal operating condition is triggered. Step 202 corresponds to step 102 of fig. 1.
At step 204, it is determined that there are one or more navigation map pages being displayed within the cockpit.
In a preferred embodiment, determining that there are one or more navigation pages being displayed within the cockpit may include: it is determined that one or more navigation pages are present within the main field of view of the driver's seat being displayed.
In step 206, it is determined whether the number of navigation map pages is greater than 1.
If there are multiple navigation map pages within the cockpit ("yes" at 206), one of the navigation map pages is selected (210). In a preferred embodiment, the one of the navigation map pages closest to the pilot may be selected. In other embodiments, one of the navigation map pages may also be selected based on other criteria (e.g., based on priority, based on predetermined settings, etc.).
If only a single navigation map page exists within the cockpit ("no" at 206), the single navigation map page is selected (208).
Finally, at step 212, the alert information is displayed on the selected navigation map page.
After the warning information is displayed on the navigation map page, when it is detected that the aircraft is in a normal operation state, the navigation map page may be made to no longer display the warning information (not shown in the figure).
Fig. 3 shows a flow chart of an alert information pushing method 300 of the present invention in the case where there is no navigation map page being displayed in the cockpit. Where the steps in the dashed box may be optional.
The method 300 begins at step 302, and at step 302, when an aircraft is detected in an abnormal operating condition, a push of alert information associated with the abnormal operating condition is triggered. Step 302 corresponds to step 102 of fig. 1 and step 202 of fig. 2.
At 304, it is determined that there is no navigation map page being displayed within the cockpit.
In a preferred embodiment, determining that there is no navigation map page being displayed within the cockpit may include: and determining that the navigation map page being displayed does not exist in the main view field range of the driving position.
At 306, one or more multifunction display windows available within the cockpit are identified.
In a preferred embodiment, identifying one or more multifunction display windows available within the cockpit may include: one or more multi-function display windows available within a primary field of view of the driver's seat are identified. In the present invention, the "available" of the multi-function display window means that the multi-function display window can be switched from the currently displayed page to another page. In the cockpit, certain specific information needs to be displayed in a fixed location. In this case, even though there may be a multi-function display window at that location, the page of that multi-function display window cannot be switched to other pages, and thus such multi-function display windows need to be excluded when identifying the multi-function display windows at step 306.
At 308, one of the one or more multi-function display windows is selected according to a predetermined criterion. For example, one of the multi-function display windows closest to the pilot may be selected. Alternatively, the multi-function display window may be selected according to predetermined criteria such as a predetermined priority, a predetermined setting, user preference, etc.
At 310, the selected multifunction display window is switched from the original page to the navigation map page.
At 312, alert information is displayed on the navigation map page of the selected multifunction display window.
At 314, the selected multifunction display window is switched back from the navigation map page to the original page when the aircraft is detected to be in a normal operating state. For example, if the multifunction display window is displaying an OMS page before the aircraft triggers an alert, the aircraft may be restored to normal operation after the pilot has processed the alert information (e.g., cleared the fault), at which point the multifunction display window may be switched back from the navigation map page to the OMS page. In some embodiments, the original page may be automatically switched back upon detecting that the aircraft is in a normal operating state. In an alternative embodiment, the transition back to the original page may be performed manually by the pilot after detecting that the aircraft is in a normal operating state.
Fig. 4 shows a block diagram of the system 400 for pushing alarm information of the present invention.
Referring to FIG. 4, the system 400 may include an alert triggering module 402, a navigation map page detection module 404, a window selection module 406, a page switching module 408, and an alert display module 410. Each of these modules may be connected or communicate with each other, directly or indirectly, over one or more buses 412.
In embodiments of the present invention, the alert triggering module 402 may be configured to: when the aircraft is detected to be in an abnormal operation state, pushing of alarm information associated with the abnormal operation state is triggered.
The navigation map page detection module 404 may be configured to: it is determined whether there are one or more navigation map pages being displayed within the cockpit.
In a preferred embodiment, the navigation map page detection module 404 may be further configured to: it is determined whether one or more navigation map pages are present within the main field of view of the driver's seat being displayed.
The window selection module 406 may be configured to: if it is determined that the navigation map page does not exist, one of the multi-function display windows available in the cockpit is selected.
In some embodiments, the window selection module 406 may be further configured to: identifying one or more multifunction display windows available within the cockpit; one of the one or more multi-function display windows is selected according to a predetermined criterion.
The page switching module 408 may be configured to: and switching the multifunctional display window selected by the window selection module from the original page to the navigation map page.
The alert display module 410 may be configured to: if one or more navigation map pages are determined to exist, displaying alarm information on one of the one or more navigation map pages; and if the navigation map page does not exist, displaying the alarm information on the navigation map page of the selected multifunctional display window.
In some embodiments, the alert information includes associated layer information, and the alert display module 410 may be further configured to display the alert information on the navigation map page by: and overlaying the map layer information onto a navigation map page.
In some embodiments, the alert information also includes associated textual information, and the alert display module 410 may be further configured to display the alert information on the navigation map page by: and displaying the text information in a non-overlapped area on the navigation map page and the layer information.
In some embodiments, the page switch module 408 may be further configured to: and if the navigation map page displaying the alarm information is switched from the original page of the multifunctional display window, switching the multifunctional display window from the navigation map page back to the original page when detecting that the aircraft is in a normal operation state.
While specific modules of the system 400 are shown in FIG. 4, it should be understood that these modules are exemplary only and not limiting. In different implementations, one or more of the modules may be combined, split, removed, or additional modules added. For example, in some implementations, the window selection module 406 and the page switching module 408 may be combined into a single module.
Fig. 5 shows a block diagram of a device 500 comprising the alert information push system of the present invention.
The apparatus illustrates a general hardware environment in which the present invention may be applied in accordance with an exemplary embodiment of the present invention.
A device 500 will now be described with reference to fig. 5, which is an exemplary embodiment of a hardware device that may be applied to aspects of the present invention. Device 500 may be any machine configured to perform processing and/or computing, and may be, but is not limited to, a workstation, a server, a desktop computer, a laptop computer, a tablet computer, a Personal Digital Assistant (PDA), a smartphone, or any combination thereof. The above-described system may be implemented in whole or at least in part by the device 500 or a similar device or system.
The processor 502 may be any type of processor and may include, but is not limited to, a general purpose processor and/or a special purpose processor (e.g., a special purpose processing chip), an intelligent hardware device (e.g., a general purpose processor, a DSP, a CPU, a microcontroller, an ASIC, an FPGA, a programmable logic device, discrete gate or transistor logic components, discrete hardware components, or any combination thereof). In some cases, the processor 502 may be configured to operate a memory array using a memory controller. In other cases, a memory controller (not shown) may be integrated into the processor 502. The processor 502 may be responsible for managing the bus and general processing, including the execution of software stored on memory. The processor 502 may also be configured to perform various functions described herein related to alert information push for an aircraft. For example, the processor 502 may be configured to: when the aircraft is detected to be in an abnormal operation state, triggering the pushing of the alarm information associated with the abnormal operation state; determining whether there are one or more navigation map pages being displayed within the cockpit; if one or more navigation map pages are determined to exist, displaying alarm information on one of the one or more navigation map pages; if it is determined that the navigation map page does not exist, the following operations are performed: selecting a multi-function display window available in the cockpit; switching the selected multifunctional display window from an original page to a navigation map page; and displaying the alarm information on the navigation map page of the selected multifunctional display window.
The detailed description set forth above in connection with the appended drawings describes examples and is not intended to represent all examples that may be implemented or fall within the scope of the claims. The terms "example" and "exemplary" when used in this specification mean "serving as an example, instance, or illustration," and do not mean "superior or superior to other examples.
Reference throughout this specification to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. Thus, usage of such phrases may not refer to only one embodiment. Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
The previous description is provided to enable any person skilled in the art to practice the various aspects described herein. Various modifications to these aspects will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other aspects. Thus, the claims are not intended to be limited to the aspects shown herein, but is to be accorded the full scope consistent with the language claims, wherein reference to an element in the singular is not intended to mean "one and only one" unless specifically so stated, but rather "one or more. The term "some" means one or more unless specifically stated otherwise. All structural and functional equivalents to the elements of the various aspects described throughout this disclosure that are known or later come to be known to those of ordinary skill in the art are expressly incorporated herein by reference and are intended to be encompassed by the claims.
It is also noted that the embodiments may be described as a process which is depicted as a flowchart, a flow diagram, a structure diagram, or a block diagram. Although a flowchart may describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. In addition, the order of the operations may be rearranged.
While various embodiments have been illustrated and described, it is to be understood that the embodiments are not limited to the precise configuration and components described above. Various modifications, substitutions, and improvements apparent to those skilled in the art may be made in the arrangement, operation, and details of the devices disclosed herein without departing from the scope of the claims.
Claims (13)
1. An alert information pushing method for an aircraft, comprising:
when the aircraft is detected to be in an abnormal operation state, triggering the pushing of the alarm information associated with the abnormal operation state;
determining whether there are one or more navigation map pages being displayed within the cockpit;
if one or more navigation map pages are determined to exist, displaying the alarm information on one of the one or more navigation map pages;
if it is determined that the navigation map page does not exist, the following operations are performed:
selecting a multifunction display window available within said cockpit;
switching the selected multifunctional display window from an original page to a navigation map page;
and displaying the alarm information on the navigation map page of the selected multifunctional display window.
2. The method of claim 1, wherein determining whether one or more navigation map pages are being displayed within the cockpit further comprises: it is determined whether one or more navigation map pages are present within the main field of view of the driver's seat being displayed.
3. The method of claim 1, wherein selecting one of the plurality of multifunction display windows available within the cockpit further comprises:
identifying one or more multifunction display windows available within the cockpit;
selecting one of the one or more multi-function display windows according to a predetermined criterion.
4. The method of claim 1, wherein the alert information includes associated layer information, and wherein displaying the alert information on a navigational map page includes: and overlaying the layer information to the navigation map page.
5. The method of claim 4, wherein the alert information further comprises associated text information, and wherein displaying the alert information on the navigation map page further comprises: and displaying the text information in a region which is not overlapped with the layer information on the navigation map page.
6. The method of claim 1, further comprising:
and if the navigation map page displaying the alarm information is switched from the original page of the multifunctional display window, switching the multifunctional display window from the navigation map page back to the original page when the aircraft is detected to be in the normal operation state.
7. An alert information push system for an aircraft, comprising:
the warning triggering module is used for triggering the pushing of warning information associated with the abnormal operation state when the aircraft is detected to be in the abnormal operation state;
a navigation map page detection module that determines whether there are one or more navigation map pages being displayed within the cockpit;
a window selection module configured to: selecting one of the multiple function display windows available within the cockpit if it is determined that a navigation map page does not exist;
the page switching module is used for switching the multifunctional display window selected by the window selection module from an original page to a navigation map page;
an alert display module configured to:
if one or more navigation map pages are determined to exist, displaying the alarm information on one of the one or more navigation map pages;
and if the navigation map page does not exist, displaying the alarm information on the navigation map page of the selected multifunctional display window.
8. The system of claim 7, wherein the navigation map page detection module is further configured to: it is determined whether one or more navigation map pages are present within the main field of view of the driver's seat being displayed.
9. The system of claim 7, wherein the window selection module is further configured to:
identifying one or more multifunction display windows available within the cockpit;
selecting one of the one or more multi-function display windows according to a predetermined criterion.
10. The system of claim 7, wherein the alert information comprises associated layer information, and wherein the alert display module is further configured to display the alert information on a navigation map page by: and overlaying the layer information to the navigation map page.
11. The system of claim 10, wherein the alert information further comprises associated text information, and wherein the alert display module is further configured to display the alert information on the navigation map page by: and displaying the text information in a region which is not overlapped with the layer information on the navigation map page.
12. The system of claim 7, wherein the page switch module is further configured to:
and if the navigation map page displaying the alarm information is switched from the original page of the multifunctional display window, switching the multifunctional display window from the navigation map page back to the original page when the aircraft is detected to be in the normal operation state.
13. A computer-readable medium storing a computer program for alert information pushing for an aircraft, the computer program being executable by a processor to perform the method of any one of claims 1-7.
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| CN202111183400.7A CN113815874B (en) | 2021-10-11 | 2021-10-11 | Alarm information pushing method and system for aircraft |
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| CN202111183400.7A CN113815874B (en) | 2021-10-11 | 2021-10-11 | Alarm information pushing method and system for aircraft |
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| CN115033152A (en) * | 2022-06-22 | 2022-09-09 | 中国商用飞机有限责任公司 | Display interface control method and electronic equipment |
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| CN113815874B (en) | 2022-06-21 |
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