Method and device for processing flight real-time dynamic data of aircraft

Abstract

The invention provides a method and device for processing flight real-time dynamic data of an aircraft, electronic equipment and a non-instantaneous computer readable storage medium, and the method comprises the steps: building a unified data model through employing the flight real-time dynamic data, the data model comprises aircraft real-time dynamic fusion result data and fusion dynamic analysis result data; and generating an aircraft dynamic data fusion analysis result message based on the data model. According to the embodiment of the invention, the flight real-time dynamic data of the aircraft is constructed into the uniform data model, and the dynamic data fusion analysis result message of the aircraft is generated based on the data model, so that the problem of low management efficiency of the aircraft caused by non-uniform issuing mechanism standards of an aircraft identification scheme in the prior art is solved.

Description

Technical Field

[0001] This application relates to the field of low-altitude flight management technology, and more specifically, to a method and apparatus for processing real-time dynamic flight data of an aircraft, an electronic device, and a non-transient computer-readable storage medium. Background Technology

[0002] With the increasing number of low-altitude aircraft, flight safety management faces increasingly challenging problems. The flight dynamic data actively reported by aircraft and reported by sensing devices come from diverse and heterogeneous sources, and traditional flight dynamic analysis methods often encounter the following issues when processing this data: Insufficient real-time performance and automation: Existing technologies cannot rely on continuous real-time active flight dynamics data and perceived flight dynamics data, and the data processing cycle is relatively long, which affects the ability to respond in real time and make rapid decisions.

[0003] Low standardization of problem abstraction and result description: The lack of a unified description and representation method for problem solutions makes it difficult to achieve data sharing and compatibility between different systems, and also makes it impossible to correctly utilize analysis results across platforms based on "consistent understanding", which affects the actual efficiency of full-domain awareness and black flight management.

[0004] Weak ability to continuously analyze events: Existing technologies are unable to continuously track, identify, and uniformly represent illegal flight events based on real-time flight dynamic data.

[0005] The lack of flexible and compatible four-dimensional spatiotemporal representation methods: Traditional data representation relies on two-dimensional or three-dimensional models and cannot support different coordinate reference frames, resulting in the representation of problem analysis results often not including continuous changes in the time dimension. In addition, data representation often only supports a single reference frame and cannot be understood and used by different aircraft, control platforms, and application systems that use different habitual reference frames. Summary of the Invention

[0006] This application proposes a method, apparatus, electronic device, and non-transient computer-readable storage medium for processing real-time dynamic flight data of aircraft, in order to solve the problem of low efficiency in aircraft management caused by inconsistent identification standards for aircraft in the prior art.

[0007] According to one aspect of this application, a method for processing real-time flight dynamic data of an aircraft is proposed, comprising: A unified data model is constructed using the real-time flight dynamic data, which includes real-time dynamic fusion result data of the aircraft and fusion dynamic analysis result data; The data model is used to generate a dynamic data fusion analysis result message for the aircraft.

[0008] According to some embodiments, the real-time flight dynamic data includes the real-time trajectory points of the aircraft. Before constructing a unified data model using the real-time flight dynamic data, the method further includes: The real-time trajectory points are described in a standardized manner based on a preset reference system and height benchmark. The preset reference system and height datum include WGS84, CGCS2000 or PZ90 coordinate systems and MSL, HAE or AGL elevation systems.

[0009] According to some embodiments, a unified data model is constructed using the real-time flight dynamic data, including: The real-time dynamic fusion result data of the flight is supplemented with standardized descriptions of real-time trajectory points, flight dynamic sampling time, cumulative flight duration, flight stage, reference coordinate system and / or reference altitude reference information.

[0010] According to some embodiments, before constructing a unified data model using the real-time flight dynamics data, the method further includes: The system identifies whether the aircraft corresponding to the real-time flight dynamic data is a legitimate aircraft based on the flight dynamic data.

[0011] According to some embodiments, identifying whether the aircraft is a legitimate aircraft based on the real-time flight dynamic data includes: Determine whether the real-time trajectory point belongs to the same flight activity as any actively reported real-time flight trajectory; If the real-time trajectory point and any actively reported real-time flight trajectory belong to the same flight activity, the real-time trajectory point and the actively reported real-time flight trajectory are fused and associated, and the aircraft is marked as a legitimate aircraft. Otherwise, the aircraft will be marked as an illegal aircraft.

[0012] According to some embodiments, before constructing a unified data model using the real-time flight dynamics data, the method further includes: Once the aircraft is determined to be an illegitimate aircraft, the event begins with the first acquisition of the aircraft's real-time flight dynamic data and ends with the last acquisition of the aircraft's real-time flight dynamic data, and the aircraft is continuously tracked.

[0013] According to some embodiments, a unified data model is constructed using the real-time flight dynamic data, including: The fusion probability, whether fusion has occurred, whether the aircraft is legitimate, and / or the fusion trajectory identifier corresponding to the real-time dynamic data of the aircraft are added to the fusion dynamic analysis result data.

[0014] According to some embodiments, the data model further includes aircraft information and sensing device information. Constructing a unified data model using the identification data also includes: Add the product information and / or operational information of the aircraft to the aircraft information, and add the product information, operational information, location information, attitude information and / or sensing device type information of the sensing device to the sensing device information.

[0015] According to some embodiments, a dynamic data fusion analysis result message for an aircraft is generated based on the data model, including: Based on the inertial reference frame and reference altitude benchmark of the receiver corresponding to the aircraft dynamic data fusion analysis result message, the aircraft dynamic data fusion analysis result message is generated using the data model.

[0016] According to one aspect of this application, an apparatus for processing real-time flight dynamic data of an aircraft is provided, comprising: The data model building unit is used to build a unified data model using the real-time flight dynamic data. The data model includes real-time dynamic fusion result data of the aircraft and fusion dynamic analysis result data. The aircraft dynamic data fusion analysis result message generation unit is used to generate an aircraft dynamic data fusion analysis result message based on the data model.

[0017] According to one aspect of this application, an electronic device is provided, characterized in that it includes: a processor; a memory for storing a computer program; and when the computer program is executed by the processor, causing the processor to perform the method as described in any of the preceding embodiments.

[0018] According to one aspect of this application, a non-transitory computer-readable storage medium is provided, having stored thereon computer-readable instructions that, when executed by a processor, cause the processor to perform the method as described in any of the preceding embodiments.

[0019] According to the example embodiments of this application, by constructing the real-time dynamic flight data of the aircraft into a unified data model, and generating the aircraft dynamic data fusion analysis result message based on the data model, the problem of low management efficiency of aircraft caused by the lack of unified standards in the aircraft identification scheme distribution mechanism in the prior art is solved. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below.

[0021] Figure 1A flowchart illustrating a method for processing real-time flight dynamics data of an aircraft according to an example embodiment of this application is shown.

[0022] Figure 2 A block diagram of an apparatus for processing real-time flight dynamic data of an aircraft according to an example embodiment of this application is shown.

[0023] Figure 3 An electronic device according to an exemplary embodiment of this application is shown. Detailed Implementation

[0024] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this application will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar parts, and therefore repeated descriptions of them will be omitted.

[0025] The described features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. Numerous specific details are provided in the following description to give a full understanding of embodiments of this disclosure. However, those skilled in the art will recognize that the technical solutions of this disclosure can be practiced without one or more of these specific details, or other methods, components, materials, apparatus, or operations may be employed. In these cases, well-known structures, methods, apparatuses, implementations, materials, or operations will not be shown or described in detail.

[0026] The flowcharts shown in the accompanying drawings are merely illustrative and do not necessarily include all content and operations / steps, nor do they necessarily have to be performed in the described order. For example, some operations / steps can be broken down, while others can be combined or partially combined; therefore, the actual execution order may change depending on the specific circumstances.

[0027] The terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish different objects, not to describe a specific order. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to these processes, methods, products, or apparatuses.

[0028] The specific embodiments according to this application will now be described in detail with reference to the accompanying drawings.

[0029] Figure 1A flowchart illustrating a method for processing real-time flight dynamic data of an aircraft according to an example embodiment of this application is shown, such as... Figure 1 The method described above includes steps S101 and S103. The following describes... Figure 1 Taking an example, a method for processing real-time flight dynamic data of an aircraft according to an example embodiment of this application will be described in detail.

[0030] like Figure 1 As shown, in step S101, a unified data model is constructed using the real-time flight dynamic data. The data model includes real-time dynamic fusion result data of the aircraft and fusion dynamic analysis result data.

[0031] It should be noted that the real-time flight dynamic data mentioned in this application can be either real-time dynamic data actively reported by the aircraft or data obtained through sensing devices.

[0032] According to embodiments of this application, the real-time flight dynamic data is continuous, real-time, actively reported flight dynamic data from different aircraft or flight dynamic data uploaded by different sensing devices. The flight dynamic data includes flight dynamic sampling time, flight position information, flight speed information, aircraft information, and / or sensing device information.

[0033] In a specific embodiment, when constructing a unified data model using the real-time flight dynamic data, the flight dynamic sampling time, cumulative flight duration, flight phase and / or reference coordinate system information, and reference altitude reference information are added to the real-time flight dynamic fusion result data. Specifically, the real-time flight dynamic sampling time is the sampling time of actively reported flight dynamics, or the actual sampling time of perceived and detected dynamics; the cumulative flight duration is the cumulative flight duration from the takeoff time of this flight activity to the current time, or the cumulative tracking duration from the detection of the first dynamic to the current time of this tracking activity; the flight phase includes flight start (the moment the aircraft begins flight, which is singular), takeoff (the phase after the aircraft begins flight, during which it continuously climbs to the predetermined route), cruise (the phase after the aircraft climbs to the predetermined route, during which it continuously and smoothly flies along the route, including brief hovering states)), descent (the phase after the aircraft begins to descend from the cruise altitude to the end of flight), and flight end (the moment the aircraft ends flight, which is singular); the coordinate system information includes supported reference coordinate systems and / or a unified coordinate reference system.

[0034] In the real-time example of this application, the aircraft dynamic data in the real-time flight dynamic data also includes the real-time trajectory points of the aircraft. Before constructing a unified data model using the real-time flight dynamic data, it is necessary to standardize the description of the position data of the real-time trajectory points of the aircraft according to a preset reference system and altitude datum. The preset reference system and altitude datum include WGS84, CGCS2000, or PZ90 coordinate systems and MSL, HAE, or AGL elevation systems. WGS84 corresponds to the WGS84 ellipsoid, CGCS2000 to the CGCS2000 ellipsoid, and PZ90 to the PZ90 ellipsoid. HAE is ellipsoidal height / geodetic height; elevations obtained directly from GNSS are usually HAE, with the reference ellipsoid corresponding to the coordinate system identified by CRS as the datum. MSL is altitude or average altitude, and the reference surface of MSL (which can be approximated by the geoid) is based on a geoid model. To facilitate obstacle avoidance and safe takeoff and landing for traditional civil aircraft during takeoff and landing phases and stable flight phases, in some embodiments, the geodetic height can be converted using an Earth gravity field model to obtain MSL, where AGL is the altitude above the ground. This method is suitable for obstacle avoidance and safe takeoff and landing for traditional civil aircraft during takeoff and landing phases and stable flight phases.

[0035] In a specific embodiment, the real-time trajectory points of the aircraft are represented using a 4D trajectory point representation method, which includes three-dimensional spatial coordinates (x, y, z) and time (t). Each trajectory point includes longitude, latitude, altitude, and the arrival time of the corresponding trajectory point. In this application, by using a unified standard to describe the real-time trajectory points of the aircraft, unified processing of multi-source heterogeneous flight real-time dynamic data is achieved, providing a data foundation for the legality identification of the aircraft.

[0036] According to embodiments of this application, before constructing a unified data model using the real-time flight dynamic data, Figure 1 The method also includes identifying whether the aircraft corresponding to the flight dynamic data is a legitimate aircraft based on the real-time flight dynamic data.

[0037] In constructing the data model, this application integrates flight dynamic data and known trajectory information from real-time flight dynamic data, standardizes the definition of issues such as whether an aircraft is legitimate, and abstracts the representation methods of the fusion and the analysis results of whether an aircraft is legitimate. This transforms the problem of multi-source flight dynamic data fusion and the analysis and processing of whether an aircraft is legitimate into a computable digital problem in 4-dimensional spacetime.

[0038] For example, in a specific embodiment, when identifying whether the aircraft is a legitimate aircraft, it is first determined whether the real-time trajectory point belongs to the same flight activity as any actively reported real-time flight trajectory; if the real-time trajectory point and any actively reported real-time flight trajectory belong to the same flight activity, the real-time trajectory point and the actively reported real-time flight trajectory are fused and associated, and the aircraft is marked as a legitimate aircraft; otherwise, the aircraft is marked as an illegitimate aircraft.

[0039] In order to continuously track illegal flights, in some other embodiments, once the aircraft is determined to be an illegal aircraft, the tracking of the aircraft is continuously performed from the first acquisition of the aircraft's real-time flight dynamic data to the last acquisition of the aircraft's real-time flight dynamic data.

[0040] After the fusion analysis of the aircraft is completed, according to the embodiments of this application, when constructing a unified data model using the real-time flight dynamic data in step 110, it is necessary to add fusion probability, whether fusion is performed, whether the aircraft is legal, and / or fusion trajectory identifiers corresponding to the real-time flight dynamic data to the fusion dynamic analysis result data. Here, the fusion trajectory identifier refers to the identifier corresponding to the real-time trajectory with the highest fusion probability of the perceived dynamic point; the real-time trajectory set refers to the trajectory set composed of all actively reported flight dynamic points; the fusion probability refers to the fusion probability of the flight trajectory of the perceived dynamic point and the fusion trajectory identifier; whether fusion is performed refers to whether it is recommended to fuse the perceived dynamic data into the flight trajectory of the fusion trajectory identifier; whether the aircraft is legal refers to whether it is recommended to determine the aircraft corresponding to the perceived dynamic data as an illegal aircraft, i.e., a black flight, which is an unregistered flight; and the continuous event identifier refers to the event identifier corresponding to continuous tracking of the aircraft.

[0041] In other embodiments, the data model also includes fused flight dynamic supplementary description data, specifically including but not limited to the plan trajectory number used to identify the planned trajectory corresponding to a specific flight activity, the plan trajectory version used to distinguish different versions of the planned trajectory reported multiple times for the same flight activity, the plan type (including general flight plan, emergency flight plan, special emergency flight plan, long-term operation plan, special flight plan), the flight mission type (referring to the flight purpose), and / or the current control mode (including manual remote control, automatic control, autonomous control, and combined control).

[0042] According to an embodiment of this application, the data model also includes aircraft information, and when constructing a unified data model in step S101, product information and / or operational information of the aircraft are added to the aircraft information to assist in identifying the aircraft.

[0043] In a specific embodiment, the product information of the aircraft includes the aircraft manufacturer, product serial number, and aircraft owner information.

[0044] In other embodiments, the data model also includes sensing device information, and when constructing a unified data model in step S101, the product information, operation information, location information, attitude information and / or sensing device type information of the sensing device are added to the sensing device information to assist in the location identification of the aircraft.

[0045] For example, taking the sensing device itself as the origin and the line of sight at the center of the detection field of view as the polar axis, the angle between the detection aircraft and the polar axis is measured on the radar's own horizontal plane, and increases counterclockwise, in order to determine the target azimuth angle of the aircraft.

[0046] For example, taking the sensing device itself as the origin and the line of sight at the center of the detection field of view as the polar axis, the angle between the detection aircraft and the polar axis is measured on the vertical plane of the radar itself, with the counterclockwise direction as positive, to determine the target pitch angle of the aircraft.

[0047] For example, the distance between the target and the sensing device (the origin of the polar coordinate system) can be detected to determine the distance between the sensing device and the aircraft.

[0048] In step S103, a dynamic data fusion analysis result message of the aircraft is generated based on the data model.

[0049] According to an embodiment of this application, in step S103, based on the inertial reference frame and reference altitude benchmark of the receiver corresponding to the aircraft message, the data model is used to generate the aircraft dynamic data fusion analysis result message, so as to send the aircraft's legality judgment result in real time. This ensures that even if the real-time flight dynamic data is a multi-source heterogeneous data structure, different receivers can understand, calculate, and utilize the fused dynamic and illegal aircraft alarm data, thereby realizing effective full-domain real-time detection capability, so that the message receiver can accurately grasp the flight status of legal and illegal aircraft in the air.

[0050] It should be noted that this application does not limit the real-time processing of flight dynamic data. Any real-time processing that can determine the legality of the aircraft is applicable to this application.

[0051] In some embodiments, a message queue mode is used to send out the aircraft dynamic data fusion analysis result messages, thereby realizing the real-time sending out of the aircraft legality judgment analysis results.

[0052] In specific embodiments, for each piece of active real-time flight dynamic data and / or perceived real-time flight dynamic data, a corresponding fused dynamic data is issued. For each latest piece of perceived real-time flight dynamic data, the fusion and unauthorized flight analysis results are updated based on the latest neighboring active real-time flight dynamic data and real-time perceived dynamic data. The analysis result description parameters are then sent along with the fused flight dynamic data to the event recipient (e.g., the aircraft's operating subscriber). Furthermore, the intelligent fused low-altitude system employs an automated fused dynamic and unauthorized flight alarm issuance mechanism to ensure the operator's real-time, full-domain awareness of alarms for illegal aircraft. Through this issuance mechanism, the visibility, identification, and location of a large number of aircraft across the entire domain can be effectively achieved, thereby enabling timely acquisition of the status information of all aircraft and improving flight safety management efficiency.

[0053] according to Figure 1 The embodiment shown solves the problem of low management efficiency of aircraft caused by the lack of standardized aircraft identification scheme distribution mechanisms in the prior art by constructing a unified data model from the real-time dynamic flight data of the aircraft and generating a dynamic data fusion analysis result message based on the data model.

[0054] According to the embodiments of this application, the received real-time flight dynamic data is the real-time dynamic data of the aircraft, and based on the real-time dynamic data, the legal judgment data of the aircraft is uniformly described using a preset standard. At the same time, it supports the distribution of legal judgment data according to the habitual reference system and altitude reference of different data recipients.

[0055] In other embodiments, the legality determination data includes continuous tracking data of illegitimate aircraft, thereby enabling continuous tracking and identification of illegitimate aircraft.

[0056] The above description primarily focuses on the methodological aspects of the embodiments of this application. Those skilled in the art should readily recognize that, based on the operations or steps described in conjunction with the embodiments disclosed herein, this application can be implemented in hardware or a combination of hardware and computer software. Those skilled in the art can implement the described functionality in different ways for each specific operation or method, and such implementations should not be considered beyond the scope of this application.

[0057] The apparatus embodiments of this application are described below. For details not described in the apparatus embodiments of this application, please refer to the method embodiments of this application.

[0058] Figure 2 A block diagram of an apparatus for processing real-time flight dynamic data of an aircraft according to an example embodiment of this application is shown, such as... Figure 2The apparatus shown includes a data model building unit 201 and an aircraft dynamic data fusion analysis result message generation unit 203. The data model building unit 201 is used to construct a unified data model using the real-time flight dynamic data. This data model includes real-time dynamic fusion result data and fusion dynamic analysis result data. The aircraft dynamic data fusion analysis result message generation unit 203 is used to generate an aircraft dynamic data fusion analysis result message based on the data model.

[0059] Figure 3 An electronic device according to an exemplary embodiment of this application is shown. Reference is made below. Figure 3 To describe an electronic device 200 according to this embodiment of the present application. Figure 3 The electronic device 200 shown is merely an example and should not impose any limitations on the functionality and scope of use of the embodiments of this application.

[0060] like Figure 3 As shown, the electronic device 200 is presented in the form of a general-purpose computing device. The components of the electronic device 200 may include, but are not limited to: at least one processing unit 210, at least one storage unit 220, a bus 230 connecting different system components (including storage unit 220 and processing unit 210), a display unit 240, etc.

[0061] The storage unit stores program code that can be executed by the processing unit 210, causing the processing unit 210 to perform the methods described in this specification according to various exemplary embodiments of this application. For example, the processing unit 210 can perform the methods described above.

[0062] Storage unit 220 may include readable media in the form of volatile storage units, such as random access memory (RAM) 2201 and / or cache memory 2202, and may further include read-only memory (ROM) 2203.

[0063] Storage unit 220 may also include a program / utility 2204 having a set (at least one) program module 2205, such program module 2205 including but not limited to: operating system, one or more application programs, other program modules and program data, each or some combination of these examples may include an implementation of a network environment.

[0064] Bus 230 can represent one or more of several types of bus structures, including a memory cell bus or memory cell controller, a peripheral bus, a graphics acceleration port, a processing unit, or a local bus using any of the various bus structures.

[0065] Electronic device 200 can also communicate with one or more external devices 300 (e.g., keyboard, pointing device, Bluetooth device, etc.), and with one or more devices that enable a user to interact with electronic device 200, and / or with any device that enables electronic device 200 to communicate with one or more other computing devices (e.g., router, modem, etc.). This communication can be performed via input / output (I / O) interface 250. Furthermore, electronic device 200 can also communicate with one or more networks (e.g., local area network (LAN), wide area network (WAN), and / or public networks, such as the Internet) via network adapter 260. Network adapter 260 can communicate with other modules of electronic device 200 via bus 230. It should be understood that, although not shown in the figures, other hardware and / or software modules can be used in conjunction with electronic device 200, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems.

[0066] Through the above description of the embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein can be implemented by software or by combining software with necessary hardware. The technical solutions according to the embodiments of this application can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (such as a CD-ROM, USB flash drive, external hard drive, etc.) or on a network, including several instructions to cause a computing device (such as a personal computer, server, or network device, etc.) to execute the methods described above according to the embodiments of this application.

[0067] Software products may employ any combination of one or more readable media. A readable medium may be a readable signal medium or a readable storage medium. A readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of readable storage media (a non-exhaustive list) include: electrical connections with one or more wires, portable disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0068] Computer-readable storage media may include data signals propagated in baseband or as part of a carrier wave, carrying readable program code. Such propagated data signals may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A readable storage medium may also be any readable medium other than a readable storage medium that can transmit, propagate, or transfer a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on the readable storage medium may be transmitted using any suitable medium, including but not limited to wireless, wired, optical fiber, RF, etc., or any suitable combination thereof.

[0069] Program code for performing the operations of this application can be written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Java and C++, and conventional procedural programming languages ​​such as C or similar languages. The program code can execute entirely on the user's computing device, partially on the user's computing device, as a standalone software package, partially on the user's computing device and partially on a remote computing device, or entirely on a remote computing device or server. In cases involving remote computing devices, the remote computing device can be connected to the user's computing device via any type of network, including a local area network (LAN) or a wide area network (WAN), or it can be connected to an external computing device (e.g., via the Internet using an Internet service provider).

[0070] The aforementioned computer-readable medium carries one or more programs, which, when executed by a device, cause the computer-readable medium to perform the aforementioned functions.

[0071] Those skilled in the art will understand that the above modules can be distributed in the device as described in the embodiments, or they can be modified accordingly and placed in one or more devices that are unique to this embodiment. The modules in the above embodiments can be combined into one module, or they can be further divided into multiple sub-modules.

[0072] According to an embodiment of this application, a computer program is proposed, including a computer program or instructions, which, when executed by a processor, can perform the methods described above.

[0073] The embodiments of this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core ideas of this application. Furthermore, any changes or modifications made by those skilled in the art based on the ideas of this application, and on the specific implementation methods and application scope of this application, are all within the scope of protection of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

[0074] Those skilled in the art will understand that the above modules can be distributed in the device as described in the embodiments, or they can be modified accordingly and placed in one or more devices that are unique to this embodiment. The modules in the above embodiments can be combined into one module, or they can be further divided into multiple sub-modules.

[0075] The embodiments of this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core ideas of this application. Furthermore, any changes or modifications made by those skilled in the art based on the ideas of this application, and on the specific implementation methods and application scope of this application, are all within the scope of protection of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A method for processing real-time dynamic flight data of an aircraft, characterized in that, include: A unified data model is constructed using the real-time flight dynamic data, which includes real-time dynamic fusion result data of the aircraft and fusion dynamic analysis result data; The data model is used to generate a dynamic data fusion analysis result message for the aircraft.

2. The method according to claim 1, characterized in that, The real-time flight dynamic data includes the real-time trajectory points of the aircraft. Before constructing a unified data model using the real-time flight dynamic data, the method further includes: The real-time trajectory points are described in a standardized manner based on a preset reference system and height benchmark. The preset reference system and height datum include WGS84, CGCS2000 or PZ90 coordinate systems and MSL, HAE or AGL elevation systems.

3. The method according to claim 2, characterized in that, Constructing a unified data model using the aforementioned real-time flight dynamic data includes: The real-time dynamic fusion result data of the flight is supplemented with standardized descriptions of real-time trajectory points, flight dynamic sampling time, cumulative flight duration, flight stage, reference coordinate system and / or reference altitude reference information.

4. The method according to claim 3, characterized in that, Before constructing a unified data model using the real-time flight dynamic data, the method further includes: The system identifies whether the aircraft corresponding to the real-time flight dynamic data is a legitimate aircraft based on the flight dynamic data.

5. The method according to claim 4, characterized in that, Identifying whether an aircraft is a legitimate aircraft based on the real-time flight dynamic data includes: Determine whether the real-time trajectory point belongs to the same flight activity as any actively reported real-time flight trajectory; If the real-time trajectory point and any actively reported real-time flight trajectory belong to the same flight activity, the real-time trajectory point and the actively reported real-time flight trajectory are fused and associated, and the aircraft is marked as a legitimate aircraft. Otherwise, the aircraft will be marked as an illegal aircraft.

6. The method according to claim 5, characterized in that, Before constructing a unified data model using the real-time flight dynamic data, the method further includes: Once the aircraft is determined to be an illegitimate aircraft, the event begins with the first acquisition of the aircraft's real-time flight dynamic data and ends with the last acquisition of the aircraft's real-time flight dynamic data, and the aircraft is continuously tracked.

7. The method according to claim 6, characterized in that, Constructing a unified data model using the aforementioned real-time flight dynamic data includes: The fusion probability, whether fusion has occurred, whether the aircraft is legitimate, and / or the fusion trajectory identifier corresponding to the real-time dynamic data of the aircraft are added to the fusion dynamic analysis result data.

8. An apparatus for processing real-time dynamic flight data of an aircraft, characterized in that, include: The data model building unit is used to build a unified data model using the real-time flight dynamic data. The data model includes real-time dynamic fusion result data of the aircraft and fusion dynamic analysis result data. The aircraft dynamic data fusion analysis result message generation unit is used to generate an aircraft dynamic data fusion analysis result message based on the data model.

9. An electronic device, characterized in that, include: processor; Memory, used to store computer programs; When the computer program is executed by the processor, the processor performs the method as described in any one of claims 1-7.

10. A non-transitory computer-readable storage medium having stored thereon computer-readable instructions that, when executed by a processor, cause the processor to perform the method as described in any one of claims 1-7.

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