Bump detection method, apparatus, medium, and device for non-equidistant node trajectories

Abstract

The application relates to the field of data processing, and in particular to a method and device for bump identification of non-equidistant node tracks, a medium and equipment. The method comprises the following steps: in response to obtaining a current climb rate of a target aircraft, a climb rate information set P is obtained; according to P, a bump determination function H2() corresponding to a second target time period [T2, T3] is obtained; and if MAX(|H2(t2)|) > YP, it is determined that the target aircraft has a bump in [T2, T3]. Different bump determination functions are established for non-equidistant data acquisition time intervals, the climb rate directly obtained by the airborne equipment is used to calculate the vertical acceleration (first derivative), the second derivative of the barometric height is used as the vertical acceleration in the related technology, and different climb rate functions are determined for different acquisition time intervals, so that the vertical acceleration obtained is more accurate.

Description

Technical Field

[0001] This application relates to the field of data processing, and in particular to a method, apparatus, medium, and device for identifying bumps in non-equidistant node trajectories. Background Technology

[0002] Turbulence refers to the impact of varying horizontal airflow (horizontal gusts) and vertical airflow (vertical gusts) on an aircraft during flight, causing irregular changes in the forces and torques acting on the aircraft, resulting in up-and-down movement, swaying, and vibration of the fuselage. Turbulence can cause injury to passengers or crew members and affect flight safety.

[0003] In related technologies, the main approach is passive, manual announcement. This involves broadcasting information to passengers when turbulence occurs and recording the data. However, the turbulence information obtained in this way is not only very delayed in terms of timeliness, but its accuracy is also affected by factors such as the subjectivity of the announcer and differences in aircraft type. Summary of the Invention

[0004] The technical problem this application aims to solve is: how to improve the accuracy and timeliness of bump detection.

[0005] To address the aforementioned technical problems, this application provides the following technical solutions:

[0006] According to a first aspect of this application, this application provides a method for bump identification of non-equidistant node trajectories, the method comprising:

[0007] S100, in response to obtaining the target aircraft's current rate of climb, a rate of climb information set P = (P1, P2, P3, P4) is obtained based on the four rate of climb closest to the current time; where P i Let P be the i-th climb rate information, where i = 1, 2, 3, 4; P i =(J i T i ); J i Let T be the ramp rate corresponding to Pi. i For J i The acquisition time, and T j <T j+1 J = 1, 2, 3; J4 is the target aircraft's current rate of climb; J i The climb rate is obtained directly from the ADS-B data sent by the target aircraft; the climb rate is determined based on the geometric altitude of the target aircraft; the time interval between any two adjacent climb rates is less than a preset time interval;

[0008] S200, based on P, obtain the turbulence determination function H2() corresponding to the second target time period [T2, T3];

[0009] H2() meets the following conditions:

[0010] H2(t2)=α2t2 2 +β2t2+γ2;

[0011] F1(T2)=F2(T2); F2(T3)=F3(T3); H1(T2)=H2(T2); H2(T3)=H3(T3);

[0012] Where α2, β2, and γ2 are all turbulence impact coefficients corresponding to H2(); t2 is the second target time, t2∈[T2, T3]; F1() is the climb rate function corresponding to the first target time period [T1, T2]; F2() is the climb rate determination function corresponding to [T2, T3]; F3() is the climb rate function corresponding to the third target time period [T3, T4]; H1() is the turbulence determination function corresponding to F1(), and H1(t1)=F1(t1)', t1 is the first target time, t1∈[T1, T2]; H2() is the turbulence determination function corresponding to F2(), and H2(t2)=F2(t2)'; H3() is the turbulence determination function corresponding to F3(), and H3(t3)=F3(t3)', t3 is the third target time, t3∈[T3, T4];

[0013] S300, if MAX(|H2(t2)|)>YP, then it is determined that the target aircraft experienced turbulence within [T2, T3]; YP is the preset vertical acceleration threshold; MAX() is the preset maximum value determination function.

[0014] According to a second aspect of this application, this application provides a bump identification device for non-equidistant node trajectories, the device comprising:

[0015] The climb rate acquisition unit, in response to acquiring the current climb rate of the target aircraft, obtains a climb rate information set P = (P1, P2, P3, P4) based on the four climb rates most recent in time; where P... i Let P be the i-th climb rate information, where i = 1, 2, 3, 4; P i =(J i T i ); J i Let T be the ramp rate corresponding to Pi. i For J i The acquisition time, and T j <T j+1 J = 1, 2, 3; J4 is the target aircraft's current rate of climb; J iThe climb rate is obtained directly from the ADS-B data sent by the target aircraft; the climb rate is determined based on the geometric altitude of the target aircraft; the time interval between any two adjacent climb rates is less than a preset time interval;

[0016] The function acquisition unit is used to obtain the turbulence determination function H2() corresponding to the second target time period [T2, T3] based on P;

[0017] H2() meets the following conditions:

[0018] H2(t2)=α2t2 2 +β2t2+γ2;

[0019] F1(T2)=F2(T2); F2(T3)=F3(T3); H1(T2)=H2(T2); H2(T3)=H3(T3);

[0020] Where α2, β2, and γ2 are all turbulence impact coefficients corresponding to H2(); t2 is the second target time, t2∈[T2, T3]; F1() is the ascent rate function corresponding to the first target time period [T1, T2]; F2() is the ascent rate determination function corresponding to [T2, T3]; F3() is the ascent rate function corresponding to the third target time period [T3, T4]; H1() is the turbulence determination function corresponding to F1(), and H1(t1)=F1(t1)', t1 is the first target time, t1∈[T1, T2]; H2() is the turbulence determination function corresponding to F2(), and H2(t2)=F2(t2)'; H3() is the turbulence determination function corresponding to F3(), and H3(t3)=F3(t3)', t3 is the third target time, t3∈[T3, T4];

[0021] The determination unit is used to determine if the target aircraft experienced turbulence within [T2, T3] if MAX(|H2(t2)|)>YP; YP is a preset vertical acceleration threshold; MAX() is a preset maximum value determination function.

[0022] According to a third aspect of this application, a non-transient computer-readable storage medium is provided, wherein at least one instruction or at least one program is stored in the storage medium, and the at least one instruction or at least one program is loaded and executed by a processor to implement the above-described method for identifying bumps in non-equidistant node trajectories.

[0023] According to a fourth aspect of this application, an electronic device is provided, including a processor and the aforementioned non-transitory computer-readable storage medium.

[0024] This application has at least the following beneficial effects:

[0025] The turbulence identification method for non-equidistant node trajectories provided in this application firstly, in response to acquiring the current climb rate of the target aircraft, a climb rate information set P is obtained based on the four climb rates closest to the current time. Here, the climb rate is directly acquired from ADS-B data in the airborne equipment, and it is determined based on geometric altitude. The acquisition time interval between any two adjacent climb rate data is less than a preset time interval. Secondly, according to J, the corresponding turbulence determination function is obtained. Here, since the time interval of ADS-B data may be non-equidistant and not suitable for spectral decomposition technology, in order to improve the accuracy of turbulence identification, a corresponding turbulence determination function is established based on the climb rate and climb rate derivative (the turbulence value corresponding to the turbulence determination function, i.e., vertical acceleration) of the start and end points corresponding to each acquisition time interval and its nearest acquisition time points (four points). This ensures that the corresponding climb rate function is smooth and avoids turbulence that does not actually occur when solving for the turbulence value (the derivative of the climb rate, i.e., vertical acceleration). This turbulence determination function is used to solve for the vertical acceleration at any time point within the corresponding time range. Then, if MAX(|H2(t2)|)>YP, where YP is a preset vertical acceleration threshold, it indicates that the target aircraft's vertical acceleration is relatively large at at least one moment within [T2, T3]. Therefore, it is determined that the target aircraft experienced turbulence within [T2, T3]. This application establishes different turbulence determination functions for different time intervals, using the climb rate directly obtained from the airborne equipment to calculate the vertical acceleration (first derivative), avoiding multiple calculations based on the data (related technologies use the second derivative of air pressure altitude as vertical acceleration). Furthermore, different climb rate functions are determined for different acquisition time intervals, resulting in more accurate vertical acceleration. Attached Figure Description

[0026] 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. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 A flowchart illustrating a bump identification method for non-equidistant node trajectories provided in this application embodiment;

[0028] Figure 2 This is a structural block diagram of a bump recognition device for non-equidistant node trajectories provided in an embodiment of this application. Detailed Implementation

[0029] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0030] like Figure 1 The diagram illustrates a bump identification method for non-equidistant node trajectories according to this application, comprising the following steps:

[0031] S100, in response to obtaining the target aircraft's current rate of climb, a rate of climb information set P = (P1, P2, P3, P4) is obtained based on the four rate of climb closest to the current time; where P i Let P be the i-th climb rate information, where i = 1, 2, 3, 4; P i =(J i T i ); J i Let T be the ramp rate corresponding to Pi. i For J i The acquisition time, and T j <T j+1 J = 1, 2, 3; J4 is the target aircraft's current rate of climb; J i The climb rate is obtained directly from the ADS-B data sent by the target aircraft; the climb rate is determined based on the geometric altitude of the target aircraft; the time interval between any two adjacent climb rates is less than a preset time interval.

[0032] Specifically, the target aircraft is the target flight. The rate of climb is data directly obtained from the flight's onboard equipment; it is the first derivative of the geometric altitude. Geometric altitude is obtained based on GPS positioning. The basic principle of the GPS navigation system is to measure the distance between satellites at known locations and the receiver, and then combine data from multiple satellites to determine the receiver's exact location. In other words, the more satellites used to determine the geometric altitude, the more accurate the determined geometric altitude will be.

[0033] In this embodiment, the climb rate corresponding to each target aircraft's ADS-B data is acquired, specifically the four climb rates closest to the current time, thus obtaining a climb rate set P. The time interval between any two adjacent climb rate data is less than a preset time interval, for example, 10 seconds. This is because the duration of flight turbulence is generally 10 seconds. If the acquisition time interval is greater than the preset time interval (e.g., 10 seconds), the acquired climb rate data may directly miss a turbulence event. In other words, if the acquisition time interval is greater than the preset time interval, using the acquired climb rate data to identify whether turbulence occurred during that period is meaningless. Therefore, in this application, it is determined that the time interval between any two adjacent climb rate data is less than the preset time interval.

[0034] S200, based on P, obtain the turbulence determination function H2() corresponding to the second target time period [T2, T3];

[0035] H2() meets the following conditions:

[0036] H2(t2)=α2t2 2 +β2t2+γ2;

[0037] F1(T2)=F2(T2); F2(T3)=F3(T3); H1(T2)=H2(T2); H2(T3)=H3(T3);

[0038] Where α2, β2 and γ2 are the turbulence impact coefficients corresponding to H2(); t2 is the second target time, t2∈[T2,T3]; F1() is the climb rate function corresponding to the first target time period [T1,T2]; F2() is the climb rate determination function corresponding to [T2,T3]; F3() is the climb rate function corresponding to the third target time period [T3,T4]; H1() is the turbulence determination function corresponding to F1(), and H1(t1)=F1(t1)', t1 is the first target time, t1∈[T1,T2]; H2() is the turbulence determination function corresponding to F2(), and H2(t2)=F2(t2)'; H3() is the turbulence determination function corresponding to F3(), and H3(t3)=F3(t3)', t3 is the third target time, t3∈[T3,T4].

[0039] Specifically, since the time intervals of the acquired ADS-B data may be non-equidistant, in order to improve the accuracy of bump identification, a corresponding bump determination function is established based on the rise rate and its derivative (bump value, i.e., vertical acceleration) corresponding to the start and end points of each acquisition time interval and its adjacent acquisition time points (four acquisition time points). In order to ensure that bumps that do not actually exist are avoided when acquiring vertical acceleration (bump determination function), it is necessary to ensure that the rise rate and its derivative (bump value, i.e., vertical acceleration) are the same at each acquisition time point (the junction of two function segments), that is, the rise rate function is smooth at that acquisition time point, so that the bump determination function obtained after differentiation will not contain bumps that do not actually exist. Therefore, we determine F1(T2) = F2(T2); F2(T3) = F3(T3); H1(T2) = H2(T2); H2(T3) = H3(T3); where α2, β2, and γ2 are the turbulence influence coefficients corresponding to H2(); by solving the system of equations F1(T2) = F2(T2); F2(T3) = F3(T3); H1(T2) = H2(T2); H2(T3) = H3(T3), we can obtain the values ​​of α2, β2, and γ2. t2 is the second target time, t2∈[T2,T3]; F1() is the climb rate function corresponding to the first target time period [T1,T2]; F2() is the climb rate determination function corresponding to [T2,T3]; F3() is the climb rate function corresponding to the third target time period [T3,T4]; H1() is the bump determination function corresponding to F1(), and H1(t1)=F1(t1)', where F1(t1)' is the first derivative of F1(t1); t1 is the first target time, t1∈[T1,T2]; H2() is the bump determination function corresponding to F2(), and H2(t2)=F2(t2)'; H3() is the bump determination function corresponding to F3(), and H3(t3)=F3(t3)', where F3(t3)' is the first derivative of F3(t3); t3 is the third target time, t3∈[T3,T4]. That is, for each time period, such as [T2, T3] or [T3, T4], the climb rate function can be obtained based on the corresponding climb rate and its first derivative (vertical acceleration). Then, by differentiating the climb rate function, the corresponding turbulence determination function can be obtained. The turbulence determination function is different for each time period.

[0040] S300, if MAX(|H2(t2)|)>YP, then it is determined that the target aircraft experienced turbulence within [T2, T3]; YP is the preset vertical acceleration threshold; MAX() is the preset maximum value determination function.

[0041] Specifically, if MAX(|H2(t2)|)>YP, where YP is a preset vertical acceleration threshold, it indicates that the target aircraft has a large vertical acceleration at at least one moment within [T2, T3]. Therefore, it is determined that the target aircraft experienced turbulence within [T2, T3].

[0042] In one exemplary embodiment of this application, the method further includes:

[0043] S000, if J a The number of associated satellites at the corresponding geometric altitude is less than the preset number, so L is obtained. a1 and L a2 Where a = 2 or 3; L a1 For J a With J a-1 The acquisition time interval; L a1 =T a -T a-1 L a2 For J a With J a+1 The acquisition time interval; L a2 =T a+1 -T a The associated satellite is a satellite used to determine geometric altitude.

[0044] Specifically, the rate of climb is data directly obtained from the flight's onboard equipment, and it is the first derivative of the geometric altitude. Geometric altitude is obtained based on GPS positioning. The basic principle of the GPS navigation system is to measure the distance between satellites at known locations and the receiver, and then combine data from multiple satellites to determine the receiver's precise location. That is, the more satellites used to determine the geometric altitude, the more accurate the determined geometric altitude will be. Therefore, when J... a If the number of associated satellites at the corresponding geometric altitude is less than the preset number, it indicates that J a The corresponding geometric height may be unreliable. In this case, obtain J respectively. a The time interval between the acquisition time of the climb rate and the time of the adjacent climb rate.

[0045] S001, if L a1 +L a2 >L0; then obtain J a Corresponding air pressure height h a h a Obtained directly from the ADS-B data sent by the target aircraft; L0 is the critical time interval.

[0046] Specifically, if L a1 +L a2 If > L0, it means J aThe time interval between two consecutive climb rates is relatively large. To ensure the accuracy of the calculation results, it is necessary to use J... i The corresponding data determines whether there is a bumpy ride.

[0047] Conversely, if L a1 +L a2 If ≤L0, then delete J. a The corresponding ADS-B data. Here, L a1 +L a2 If ≤L0, then it means J a When the time interval between two consecutive climb rates is small and frequent, J can be directly deleted to improve calculation efficiency. a The corresponding ADS-B data is used for calculations using other ADS-B data.

[0048] S002, according to h a , obtain J a The corresponding geometric height correction function G a ();

[0049] G a () meets the following conditions:

[0050] G a (h a v a )=x a h a +y a v a +z a ;

[0051] Where, x a y a , z a All are G a (h a v a The corresponding correction factor; v a For J a The corresponding airspeed.

[0052] Specifically, according to h a , obtain J a The corresponding geometric altitude correction function. Here, when the geometric altitude may be unreliable, it is corrected based on the barometric altitude from ADS-B data. The barometric altitude is obtained directly from onboard equipment, and this data is affected by air pressure, changing according to pressure variations. It should be noted that x... a y a , z a It can be determined based on the relevant data (corresponding airspeed, corresponding atmospheric pressure altitude) corresponding to a reliable geometric altitude (the number of associated satellites is equal to or greater than the preset number).

[0053] S003, according to G a (h a v a ), to obtain J a 1 J a 1 For T a The corresponding corrected first crawl rate.

[0054] S004, according to J a 1 H2 was obtained 1 (t2); H2 1 (t2) is based on J a 1 The first correction turbulence determination function corresponding to the second target time period [T2, T3] is obtained.

[0055] Specifically, according to G a (h a v a ), can obtain J a The corresponding corrected geometric height is used to obtain the first corrected crawl rate. Furthermore, due to J... a Corrected to J a 1 Thus, H2 was obtained. 1 (t2), H2 1 The process of obtaining (t2) is the same as step S200, and will not be repeated here.

[0056] S005, according to J m and J n , obtain J a 2 J a 2 For T a The corresponding corrected second crawl rate; J m To obtain time in J a Previously, and at a distance from J a The number of the nearest associated satellites at the corresponding geometric altitude is equal to or greater than the preset rate of ascent; J n To obtain time in J a After that, and at a distance of J a The number of the nearest associated satellites at the corresponding geometric altitude is equal to or greater than the preset rate of ascent;

[0057] S006, according to J a 2 H2 was obtained 2 (t2); H2 2 (t2) is based on Ja 2 The second corrected turbulence determination function corresponding to the second target time period [T2, T3] is obtained;

[0058] Specifically, here, according to J a Two adjacent reliable climb rates (the number of associated satellites at the corresponding geometric altitude is equal to or greater than a preset number of climb rates) are used to construct a new climb rate function. Then, based on this new climb rate function, J is obtained. a 2 This leads to the corresponding second corrected turbulence determination function, H2. 2 The process of obtaining (t2) is the same as step S200, and will not be repeated here.

[0059] S007, if MAX(|H2) 1 (t2)|)>YP, and MAX(|H2) 2 If (t2)|)>YP, then it is determined that the target aircraft experienced turbulence within [T2, T3].

[0060] Specifically, since barometric altitude is affected by air pressure, in order to improve the accuracy of turbulence detection, according to J a Two adjacent reliable climb rates (the number of associated satellites at the corresponding geometric altitude is equal to or greater than a preset number of climb rates) are used to construct a new climb rate function. Then, based on this new climb rate function, J is obtained. a 2 This leads to the corresponding second correction turbulence determination function. When MAX(|H2 1 (t2)|)>YP, and MAX(|H2) 2 Only when (t2)|)>YP is it determined that the target aircraft experienced turbulence within [T2, T3]. In this embodiment, for potentially unreliable geometric altitudes and pressure altitudes affected by air pressure, corresponding corrected turbulence determination functions are constructed respectively. Dual judgment is performed during turbulence identification, improving the accuracy of turbulence identification results in cases where geometric altitudes are unreliable.

[0061] It should be noted that if MAX(|H2) 1 (t2)|)≤YP, and MAX(|H2) 2 If (t2)|)≤YP, then it is determined that the target aircraft did not experience any turbulence within [T2, T3].

[0062] In one exemplary embodiment of this application, the method further includes:

[0063] S010, if J a If the number of associated satellites at the corresponding geometric altitude is equal to or greater than the preset number, then proceed directly to step S100.

[0064] Specifically, if J a If the number of associated satellites at the corresponding geometric altitude is equal to or greater than the preset number, then it indicates that J is at this time. a The accuracy is relatively high, so it can be directly based on J. a To identify aircraft turbulence.

[0065] In this embodiment, J is added. a The accuracy of the judgment improves the final accuracy of aircraft turbulence identification.

[0066] according to Figure 2 As shown, this application also provides a bump identification device 100 for non-equidistant node trajectories, comprising:

[0067] Climb rate acquisition unit 110 is used to, in response to acquiring the current climb rate of the target aircraft, obtain a climb rate information set P = (P1, P2, P3, P4) based on the four climb rates most recent in time; where P i Let P be the i-th climb rate information, where i = 1, 2, 3, 4; P i =(J i T i ); J i Let T be the ramp rate corresponding to Pi. i For J i The acquisition time, and T j <T j+1 J = 1, 2, 3; J4 is the target aircraft's current rate of climb; J i The climb rate is obtained directly from the ADS-B data sent by the target aircraft; the climb rate is determined based on the geometric altitude of the target aircraft; the time interval between any two adjacent climb rates is less than a preset time interval;

[0068] The function acquisition unit 120 is used to obtain the turbulence determination function H2() corresponding to the second target time period [T2, T3] based on P;

[0069] H2() meets the following conditions:

[0070] H2(t2)=α2t2 2 +β2t2+γ2;

[0071] F1(T2)=F2(T2); F2(T3)=F3(T3); H1(T2)=H2(T2); H2(T3)=H3(T3);

[0072] Where α2, β2, and γ2 are all turbulence impact coefficients corresponding to H2(); t2 is the second target time, t2∈[T2, T3]; F1() is the ascent rate function corresponding to the first target time period [T1, T2]; F2() is the ascent rate determination function corresponding to [T2, T3]; F3() is the ascent rate function corresponding to the third target time period [T3, T4]; H1() is the turbulence determination function corresponding to F1(), and H1(t1)=F1(t1)', t1 is the first target time, t1∈[T1, T2]; H2() is the turbulence determination function corresponding to F2(), and H2(t2)=F2(t2)'; H3() is the turbulence determination function corresponding to F3(), and H3(t3)=F3(t3)', t3 is the third target time, t3∈[T3, T4];

[0073] Unit 130 is used to determine that if MAX(|H2(t2)|)>YP, the target aircraft has experienced turbulence within [T2, T3]; YP is a preset vertical acceleration threshold; MAX() is a preset maximum value determination function.

[0074] Embodiments of this application also provide a computer program product including program code that, when the program product is run on an electronic device, causes the electronic device to perform the steps of the methods described above according to various exemplary embodiments of this application.

[0075] Furthermore, although the steps of the method in this disclosure are described in a specific order in the accompanying drawings, this does not require or imply that the steps must be performed in that specific order, or that all the steps shown must be performed to achieve the desired result. Additional or alternative steps may be omitted, multiple steps may be combined into one step, and / or a step may be broken down into multiple steps.

[0076] From 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. Therefore, the technical solutions according to the embodiments of this disclosure 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, mobile terminal, or network device, etc.) to execute the methods according to the embodiments of this disclosure.

[0077] In an exemplary embodiment of this disclosure, an electronic device capable of implementing the above-described method is also provided.

[0078] Those skilled in the art will understand that various aspects of this application can be implemented as a system, method, or program product. Therefore, various aspects of this application can be specifically implemented in the following forms: a completely hardware implementation, a completely software implementation (including firmware, microcode, etc.), or a combination of hardware and software implementations, collectively referred to herein as a "circuit," "module," or "system."

[0079] An electronic device according to this embodiment of the present application. The electronic device is merely an example and should not be construed as limiting the functionality and scope of use of the embodiments of this application.

[0080] Electronic devices are manifested in the form of general-purpose computing devices. Components of an electronic device may include, but are not limited to: at least one processor, at least one memory, and buses connecting different system components (including memory and processor).

[0081] The memory stores program code that can be executed by a processor, causing the processor to perform the steps described in the "Exemplary Methods" section above, according to various exemplary embodiments of this application.

[0082] The storage may include readable media in the form of volatile storage, such as random access memory (RAM) and / or cache memory, and may further include read-only memory (ROM).

[0083] The storage may also include programs / utilities having a set (at least one) of program modules, including but not limited to: an operating system, one or more applications, other program modules, and program data, each or some combination of these examples may include an implementation of a network environment.

[0084] A bus can represent one or more of several bus architectures, including a memory bus or memory controller, a peripheral bus, a graphics acceleration port, a processor, or a local bus that uses any of the various bus architectures.

[0085] The electronic device can also communicate with one or more external devices (e.g., keyboards, pointing devices, Bluetooth devices, etc.), one or more devices that enable a user to interact with the electronic device, and / or any device that enables the electronic device to communicate with one or more other computing devices (e.g., routers, modems, etc.). This communication can be achieved through input / output (I / O) interfaces. Furthermore, the electronic device can communicate with one or more networks (e.g., local area networks (LANs), wide area networks (WANs), and / or public networks, such as the Internet) via a network adapter. As shown in the figure, the network adapter communicates with other modules of the electronic device via a bus. It should be understood that, although not shown in the figure, other hardware and / or software modules can be used in conjunction with the electronic device, including but not limited to: microcode, device drivers, redundant processors, external disk drive arrays, RAID systems, tape drives, and data backup storage systems.

[0086] From 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. Therefore, the technical solutions according to the embodiments of this disclosure 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, terminal device, or network device, etc.) to execute the methods according to the embodiments of this disclosure.

[0087] In exemplary embodiments of this disclosure, a computer-readable storage medium is also provided, on which a program product capable of implementing the methods described above is stored. In some possible implementations, various aspects of this application may also be implemented as a program product including program code, which, when the program product is run on a terminal device, causes the terminal device to perform the steps of the various exemplary embodiments of this application described in the "Exemplary Methods" section above.

[0088] The program product 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 (a non-exhaustive list) of readable storage media include: electrical connections having 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.

[0089] Computer-readable signal 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 signal medium may also be any readable medium other than a readable storage medium, capable of sending, propagating, or transmitting programs for use by or in conjunction with an instruction execution system, apparatus, or device.

[0090] The program code contained on the readable medium may be transmitted using any suitable medium, including but not limited to wireless, wired, optical fiber, RF, etc., or any suitable combination thereof.

[0091] 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).

[0092] Furthermore, the above figures are merely illustrative of the processes included in the method according to exemplary embodiments of this application, and are not intended to be limiting. It is readily understood that the processes shown in the above figures do not indicate or limit the temporal order of these processes. Additionally, it is readily understood that these processes may be executed synchronously or asynchronously, for example, in multiple modules.

[0093] It should be noted that although several modules or units for the device used to perform actions have been mentioned in the detailed description above, this division is not mandatory. In fact, according to embodiments of this disclosure, the features and functions of two or more modules or units described above can be embodied in one module or unit. Conversely, the features and functions of one module or unit described above can be further divided and embodied by multiple modules or units.

[0094] The above are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for identifying bumps in non-equidistant node trajectories, characterized in that, The method includes: S100, in response to obtaining the target aircraft's current rate of climb, a rate of climb information set P = (P1, P2, P3, P4) is obtained based on the four rate of climb data most recent to the current time; where P... i Let P be the i-th climb rate information, where i = 1, 2, 3, 4; P i =(J i T i ); J i For P i The corresponding climb rate, T i For J i The acquisition time, and T j <T j+1 J = 1, 2, 3; J4 is the target aircraft's current rate of climb; J i The climb rate is obtained directly from the ADS-B data sent by the target aircraft; the climb rate is determined based on the geometric altitude of the target aircraft; the time interval between any two adjacent climb rates is less than a preset time interval; S200, based on P, obtain the turbulence determination function H2() corresponding to the second target time period [T2, T3]; H2() meets the following conditions: H2(t2)=α2t2 2 +β2t2+γ2; F1(T2)=F2(T2); F2(T3)=F3(T3); H1(T2)=H2(T2); H2(T3)=H3(T3); Where α2, β2, and γ2 are all turbulence impact coefficients corresponding to H2(); t2 is the second target time, t2 [T2, T3]; F1() is the climb rate function corresponding to the first target time period [T1, T2]; F2() is the climb rate function corresponding to the second target time period [T2, T3]; F3() is the climb rate function corresponding to the third target time period [T3, T4]; H1() is the turbulence determination function corresponding to F1(), and H1(t1) = F1'(t1), where t1 is the first target time, t1 [T1, T2]; H2() is the turbulence determination function corresponding to F2(), and H2(t2) = F2'(t2); H3() is the turbulence determination function corresponding to F3(), and H3(t3) = F3'(t3), where t3 is the third target time. [T3, T4]; S300, if MAX(|H2(t2)|)>YP, then it is determined that the target aircraft experienced turbulence within [T2, T3]; YP is the preset vertical acceleration threshold; MAX() is the preset maximum value determination function.

2. The bump recognition method for non-equidistant node trajectories according to claim 1, characterized in that, The method further includes: S000, if J a The number of associated satellites at the corresponding geometric altitude is less than the preset number, so L is obtained. a1 and L a2 Where a = 2 or 3; L a1 For J a With J a-1 The acquisition time interval; L a1 =T a -T a-1 L a2 For J a With J a+1 The acquisition time interval; L a2 =T a+1 -T a The associated satellite is a satellite used to determine geometric altitude; S001, if L a1 +L a2 >L0; then obtain J a Corresponding air pressure height h a h a Obtained directly from the ADS-B data sent by the target aircraft; L0 is the critical time interval; S002, according to h a , obtain J a The corresponding geometric height correction function G a ( ); G a ( ) meets the following conditions: G a (h a ,v a )=x a h a +y a v a +z a ; Where, x a y a , z a All are G a (h) a v a The corresponding correction coefficient; v a For J a The corresponding airspeed; S003, according to G a (h) a v a ), to obtain J a 1 J a 1 For T a The corresponding corrected first climb rate; S004, according to J a 1 H2 was obtained 1 (t2); H2 1 (t2) is based on J a 1 The first corrected turbulence determination function corresponding to the second target time period [T2, T3] is obtained; S005, according to J m and J n , obtain J a 2 J a 2 For T a The corresponding corrected second climb rate; J m To obtain time in J a Previously, and at a distance from J a The number of the nearest associated satellites at the corresponding geometric altitude is equal to or greater than the preset rate of ascent; J n To obtain time in J a After that, and at a distance of J a The number of the nearest associated satellites at the corresponding geometric altitude is equal to or greater than the preset rate of ascent; S006, according to J a 2 H2 was obtained 2 (t2); H2 2 (t2) is based on J a 2 The second corrected turbulence determination function corresponding to the second target time period [T2, T3] is obtained; S007, if MAX(|H2) 1 (t2)|)>YP, and MAX(|H2) 2 If (t2)|)>YP, then it is determined that the target aircraft experienced turbulence within [T2, T3].

3. The bump recognition method for non-equidistant node trajectories according to claim 1, characterized in that, After step S000, the method further includes: S008, if L i1 +L i2 If ≤L0, then delete J. a The corresponding ADS-B data.

4. The bump recognition method for non-equidistant node trajectories according to claim 2, characterized in that, The method further includes: S010, if J a If the number of associated satellites at the corresponding geometric altitude is equal to or greater than the preset number, then proceed directly to step S100.

5. A bump recognition device for non-equidistant node trajectories, characterized in that, The device includes: The climb rate acquisition unit, in response to acquiring the current climb rate of the target aircraft, obtains a climb rate information set P = (P1, P2, P3, P4) based on the four climb rates most recent in time; where P... i Let P be the i-th climb rate information, where i = 1, 2, 3, 4; P i =(J i T i ); J i For P i The corresponding climb rate, T i For J i The acquisition time, and T j <T j+1 J = 1, 2, 3; J4 is the target aircraft's current rate of climb; J i The climb rate is obtained directly from the ADS-B data sent by the target aircraft; the climb rate is determined based on the geometric altitude of the target aircraft; the time interval between any two adjacent climb rates is less than a preset time interval; The function acquisition unit is used to obtain the turbulence determination function H2() corresponding to the second target time period [T2, T3] based on P; H2() meets the following conditions: H2(t2)=α2t2 2 +β2t2+γ2; F1(T2)=F2(T2); F2(T3)=F3(T3); H1(T2)=H2(T2); H2(T3)=H3(T3); Where α2, β2, and γ2 are all turbulence impact coefficients corresponding to H2(); t2 is the second target time, t2 [T2, T3]; F1() is the climb rate function corresponding to the first target time period [T1, T2]; F2() is the climb rate function corresponding to the second target time period [T2, T3]; F3() is the climb rate function corresponding to the third target time period [T3, T4]; H1() is the turbulence determination function corresponding to F1(), and H1(t1) = F1'(t1), where t1 is the first target time, t1 [T1, T2]; H2() is the turbulence determination function corresponding to F2(), and H2(t2) = F2'(t2); H3() is the turbulence determination function corresponding to F3(), and H3(t3) = F3'(t3), where t3 is the third target time. [T3, T4]; The determination unit is used to determine if the target aircraft experienced turbulence within [T2, T3] if MAX(|H2(t2)|) > YP; YP is a preset vertical acceleration threshold; MAX() is a preset maximum value determination function.

6. A non-transitory computer-readable storage medium, wherein the storage medium stores at least one instruction or at least one program segment, characterized in that, The at least one instruction or the at least one program segment is loaded and executed by the processor to implement the method as described in any one of claims 1-4.

7. An electronic device, characterized in that, Includes a processor and the non-transitory computer-readable storage medium as described in claim 6.

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