Method for determining aircraft damage debris impact point partition based on heterogeneous parallel computing

Abstract

The application discloses a kind of based on heterogeneous parallel computing's aircraft damage fragment landing point partition determination method, comprising: S101: CPU obtains the state parameter of each damage fragment at initial time and is copied to GPU;S102: GPU is respectively for each damage fragment, determine the coordinate of damage fragment at first time;S103: GPU judges whether the height parameter H in coordinate is greater than preset height threshold h, and judges whether it is less than zero;S104: if H is greater than h, increase the value of first time, and obtain the coordinate of damage fragment at new first time, turn S103;S105: if H <0, reduce the value of first time, and obtain the coordinate of damage fragment at new first time, turn S103;S106: if 0≤H <h, output the coordinate of damage fragment;S107: GPU determines the landing point partition of damage fragment according to the coordinate of each damage fragment.The efficiency of determining the landing point partition of damage fragment is high.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of motion trajectory simulation calculation, in particular to a method for determining the falling point partition of aircraft damage debris based on heterogeneous parallel computing. BACKGROUND

[0002] A large number of damage debris will be generated after the aircraft is damaged, and these debris may cause certain damage when falling. In order to avoid the loss caused by the falling of the damage debris, it is necessary to calculate the damage debris falling point area in advance, so as to take measures in advance for the calculated damage debris falling point area. However, due to the large number of damage debris, the traditional calculation method needs a long time, which is not conducive to the early warning and taking measures for the falling point area. SUMMARY

[0003] Therefore, the embodiments of the present application provide a method for determining the falling point partition of aircraft damage debris based on heterogeneous parallel computing, and corresponding devices and electronic equipment are also provided to solve the problem of low calculation efficiency of the falling point area of the existing aircraft damage debris.

[0004] According to a first aspect, the embodiments of the present application provide a method for determining the falling point partition of aircraft damage debris based on heterogeneous parallel computing, which comprises:

[0005] S101: A central processing unit acquires state parameters of each damage debris at an initial time and copies the state parameters to a graphics processing unit, wherein the state parameters at least include position and velocity;

[0006] S102: The graphics processing unit determines the coordinates of each damage debris at a first time according to the state parameters, wherein the coordinates are coordinates in a geodetic coordinate system; wherein the first time is greater than the initial time;

[0007] S103: The graphics processing unit judges whether the height parameter in the coordinates is greater than a preset height threshold, and judges whether the height parameter in the coordinates is less than zero;

[0008] S104: In the case that the height parameter in the coordinates is greater than the preset height threshold, the graphics processing unit increases the value of the first time, acquires the coordinates of the damage debris at a new first time, and returns to step S103;

[0009] S105: In the case that the height parameter in the coordinates is less than zero, the graphics processing unit decreases the value of the first time, acquires the coordinates of the damage debris at a new first time, and returns to step S103;

[0010] S106: In a case where the elevation parameter in the coordinate is greater than zero and less than the preset height threshold or equal to zero, the graphics processor outputs the coordinate of the damage fragment;

[0011] S107: The graphics processor determines a landing point partition of the damage fragment according to the coordinate of each damage fragment.

[0012] In some optional embodiments, the determination of the coordinate of the damage fragment at the first time according to the state parameter comprises:

[0013] obtaining an orbital element of the damage fragment at an initial time according to the state parameter;

[0014] determining an orbital element of the damage fragment at the first time according to the orbital element at the initial time;

[0015] determining the coordinate of the damage fragment at the first time according to the orbital element at the first time.

[0016] In some optional embodiments, the determination of the coordinate of the damage fragment at the first time according to the orbital element at the first time comprises:

[0017] determining a first coordinate of the damage fragment in an orbital coordinate system according to the orbital element at the first time;

[0018] obtaining the coordinate of the damage fragment in a terrestrial coordinate system by conversion according to the first coordinate.

[0019] In some optional embodiments, in a case where the elevation parameter in the coordinate is less than zero, the value of the first time is reduced, comprising:

[0020] obtaining a first step length of the last adjustment of the value of the first time;

[0021] determining a second step length of the current adjustment, the second step length being less than the first step length;

[0022] reducing the value of the first time by the second step length.

[0023] In some optional embodiments, the determination of the landing point partition of the damage fragment according to the coordinate of each damage fragment comprises:

[0024] S1071: obtaining the preset iteration number and initial centroids, the initial centroids being a plurality of coordinates randomly selected from the coordinates of the damage fragments;

[0025] S1072: for each coordinate, respectively calculating distances from the coordinate to each initial centroid, and adding the coordinate to a cluster corresponding to the initial centroid with the minimum distance.

[0026] S1073: After each coordinate is added to the corresponding cluster, the average value of the coordinates in each cluster is calculated as the new centroid;

[0027] S1074: For each of the coordinates, calculate the cluster from the coordinate to each of the new centroids, and add the coordinate to the cluster corresponding to the new centroid with the smallest distance;

[0028] S1075: Repeat steps S1073 and S1074 until the number of repetitions reaches the preset number of iterations;

[0029] S1076: Determine the landing point partition of the damaged fragments according to the final clustering.

[0030] In some optional implementations, determining the impact point partition of the damaged fragments based on the coordinates of each damaged fragment includes:

[0031] Cluster the coordinates of the damaged fragments according to distance;

[0032] For each cluster obtained, the coordinate with the smallest y-axis value in the cluster is taken as the second coordinate;

[0033] For the remaining coordinates in the cluster, sort them according to their polar angle with the second coordinate, and retain only the coordinates rotated counterclockwise.

[0034] According to a second aspect, embodiments of the present invention provide a device for determining the impact point of aircraft debris based on heterogeneous parallel computing, the device comprising:

[0035] The acquisition module is used to acquire the state parameters of each damaged fragment at the initial moment, and the state parameters include at least position and velocity;

[0036] The first determining module is used to determine the coordinates of each damaged fragment at a first moment based on the state parameters, wherein the coordinates are coordinates in a geodetic coordinate system; wherein the first moment is greater than the initial moment.

[0037] The judgment module is used to determine whether the elevation parameter in the coordinates is greater than a preset height threshold, and to determine whether the elevation parameter in the coordinates is less than zero;

[0038] The second determining module is used to increase the value of the first moment when the elevation parameter in the coordinates is greater than a preset height threshold, and to obtain the coordinates of the damaged fragment at the new first moment.

[0039] a third determining module, configured to reduce the value of the first moment and obtain the coordinates of the damage fragments at a new first moment if the elevation parameter in the coordinates is less than zero;

[0040] an output module, configured to output the coordinates of the damage fragments if the elevation parameter in the coordinates is greater than zero and less than the preset height threshold or equal to zero;

[0041] a fourth determining module, configured to determine the damage fragment landing point partition according to the coordinates of the damage fragments.

[0042] According to a third aspect, an electronic device is provided, comprising:

[0043] a memory, a central processing unit and a graphics processing unit, which are communicatively connected with each other, the memory is configured to store a computer program, and the computer program is executed by the central processing unit and the graphics processing unit to implement any of the aircraft damage fragment landing point partition determination methods based on heterogeneous parallel computing according to the first aspect.

[0044] According to a fourth aspect, a computer readable storage medium is provided, which is configured to store a computer program, and the computer program is executed by a central processing unit and a graphics processing unit to implement any of the aircraft damage fragment landing point partition determination methods based on heterogeneous parallel computing according to the first aspect.

[0045] The embodiments of the present application provide an aircraft damage fragment landing point partition determination method based on heterogeneous parallel computing, and corresponding devices and electronic devices. The method calculates the orbit root number of damage fragments according to the state parameters of the damage fragments at an initial moment, recursively calculates the landing point coordinates of the damage fragments, and then determines the area range of the landing points of all damage fragments according to the landing point coordinates of all damage fragments. The method has high efficiency in determining the area range of the landing points of damage fragments, and is convenient for early warning and taking measures for the landing point area of damage fragments to avoid or reduce damage caused by damage fragments. In addition, the CPU-based computing mode has a long computing time due to the limitation of the number of threads. Therefore, the embodiments of the present application copy the initial state parameters of the damage fragments to the GPU, utilize the parallel computing capability of the GPU to calculate the landing point coordinates of a large number of damage fragments, greatly improve the efficiency of damage fragment landing point calculation, and quickly obtain the landing point partition of the damage fragments. That is, the embodiments of the present application improve the calculation speed of the landing point coordinates and partition of damage fragments by using the heterogeneous parallel computing mode. BRIEF DESCRIPTION OF DRAWINGS

[0046] The features and advantages of the present application will be appreciated upon reference to the following detailed description and drawings, in which:

[0047] Figure 1 A flowchart of a method for determining a falling point partition of aircraft damage debris based on heterogeneous parallel computing provided by an embodiment of the present application is shown in FIG. 1.

[0048] Figure 2 A structural diagram of a device for determining a falling point partition of aircraft damage debris based on heterogeneous parallel computing provided by an embodiment of the present application is shown in FIG. 2.

[0049] Figure 3 A structural diagram of an electronic device provided by an embodiment of the present application is shown in FIG. 3. DETAILED DESCRIPTION

[0050] In order to make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described below in connection with the drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0051] It should be noted that the terms “comprising”, “containing” or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a list of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such a process, method, article or device. Without more limitations, the element defined by the phrase “comprising a” does not exclude the presence of additional identical elements in the process, method, article or device including the element. In addition, the terms “first”, “second” and the like are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. In the description of the following embodiments, the meaning of “a plurality of” is two or more, unless otherwise specifically limited.

[0052] Referring to Figure 1 The embodiments of the present application provide a method for determining a falling point partition of aircraft damage debris based on heterogeneous parallel computing, which comprises:

[0053] S101: A central processing unit (CPU) acquires state parameters of each damage fragment at an initial time, and copies the state parameters to a graphics processing unit (GPU), the state parameters at least including position and velocity; wherein the position can be represented by coordinate values;

[0054] The state parameters of the damage fragments obtained here can be based on different coordinate systems, and for the convenience of subsequent calculation and processing, coordinate system conversion is needed, for example, conversion to the geocentric inertial coordinate system. Each state parameter (including position (X, Y, Z) and velocity ) converted to the geocentric inertial coordinate system can be formed into an initial time damage fragment state parameter list.

[0055] S102: The graphics processor determines the coordinates of each damage fragment at a first time according to the state parameters, the coordinates being coordinates in the geodetic coordinate system; wherein the first time is greater than the initial time;

[0056] S103: The graphics processor determines whether the height parameter H in the coordinates is greater than a preset height threshold h, and determines whether the height parameter H in the coordinates is less than zero;

[0057] S104: In the case where the height parameter H in the coordinates is greater than the preset height threshold h, the graphics processor increases the value of the first time, and acquires the coordinates of the damage fragment at a new first time, and goes to step S103;

[0058] S105: In the case where the height parameter H in the coordinates is less than zero, the graphics processor decreases the value of the first time, and acquires the coordinates of the damage fragment at a new first time, and goes to step S103;

[0059] S106: In the case where the height parameter in the coordinates is greater than zero and less than the preset height threshold, or equal to zero, the graphics processor outputs the coordinates of the damage fragment; the landing point coordinates of all damage fragments can form a damage fragment landing point coordinate list, which contains the longitude and latitude information of each damage fragment in the geodetic coordinate system;

[0060] In the embodiment of the application, when the height parameter of the coordinates is greater than zero and less than the preset height threshold, or equal to zero, the coordinates are the landing point coordinates of the damage fragment;

[0061] S107: The graphics processor determines the landing point partition of the damage fragment according to the coordinates of each damage fragment.

[0062] The large amount of debris generated after the aircraft is damaged will fly freely along their new orbits and eventually fall to the ground. In the embodiments of the present application, it is assumed that the landing coordinates of the debris of the damaged aircraft are only affected by the earth's gravity and the initial state, and the influence of the atmosphere on the landing coordinates of the debris is ignored.

[0063] The embodiments of the present application provide a method for determining the landing point partition of the debris of a damaged aircraft. The method calculates the orbital elements of the debris of the damaged aircraft according to the state parameters of the debris of the damaged aircraft at the initial time, recursively calculates the landing coordinates of the debris of the damaged aircraft, and then determines the area range of the landing points of all the debris of the damaged aircraft according to the landing coordinates of all the debris of the damaged aircraft. The method for determining the area range of the landing points of the debris of the damaged aircraft has high efficiency, and is convenient for early warning and taking measures against the landing area of the debris of the damaged aircraft to avoid or reduce the damage caused by the debris of the damaged aircraft. In addition, the CPU-based calculation method has a long calculation time due to the limitation of the number of threads. Therefore, in the embodiments of the present application, the initial state parameters of the debris of the damaged aircraft are copied to the GPU, and the parallel computing capability of the GPU is used to calculate the landing coordinates of a large amount of debris of the damaged aircraft, thereby greatly improving the efficiency of the landing point calculation of the debris of the damaged aircraft and quickly obtaining the landing point partition of the debris of the damaged aircraft. That is, the embodiments of the present application improve the calculation speed of the landing coordinates and partition of the debris of the damaged aircraft by using a heterogeneous parallel computing method.

[0064] In some specific embodiments, the determining the coordinates of the debris of the damaged aircraft at the first time according to the state parameters comprises:

[0065] obtaining the orbital elements of the debris of the damaged aircraft at the initial time according to the state parameters;

[0066] determining the orbital elements of the debris of the damaged aircraft at the first time according to the orbital elements at the initial time;

[0067] determining the coordinates of the debris of the damaged aircraft at the first time according to the orbital elements at the first time. In some specific embodiments, the determining the coordinates of the debris of the damaged aircraft at the first time according to the orbital elements at the first time comprises:

[0068] determining a first coordinate of the debris of the damaged aircraft in an orbital coordinate system according to the orbital elements at the first time;

[0069] obtaining the coordinates of the debris of the damaged aircraft in a terrestrial coordinate system by coordinate transformation according to the first coordinate.

[0070] In some specific embodiments, in the case that the height parameter in the coordinates is less than zero, the value of the first time is reduced, comprising:

[0071] obtaining a first step length for adjusting the value of the first time last time;

[0072] determining a second step size of the current adjustment, the second step size being smaller than the first step size;

[0073] decreasing the value of the first time by the second step size.

[0074] For example, the embodiment of the present application defines a specific damage debris drop point coordinate recursive calculation kernel function to calculate the damage debris drop point coordinate, and the specific process is as follows:

[0075] a) initializing the state parameters of the damage debris, the time T and the height threshold h, wherein T=T0, T0 is the initial time;

[0076] b) calculating the orbit elements (a, e, i, Omega, omega, theta) at the time T;

[0077] c) calculating the coordinates of the damage debris in the orbit coordinate system according to the orbit elements;

[0078] d) converting the coordinates of the damage debris in the orbit coordinate system to obtain the coordinates of the damage debris in the earth coordinate system;

[0079] e) in the earth coordinate system, comparing the height parameter (H) in the coordinates of the damage debris with the pre-set height threshold h, if 0<=H<h, executing step f; if H>h, setting T=T+DeltaT, executing step b; if H<0, using the dichotomy method to calculate the drop point coordinates of the damage debris;

[0080] f) obtaining the coordinates of the debris in the earth coordinate system and outputting.

[0081] In the embodiment of the present application, it is judged whether the height parameter H of the damage debris coordinates is less than the pre-set height threshold h, if yes, it is considered that the damage debris has landed, and the drop point coordinates of the debris can be output. However, when H<0, it indicates that the current DeltaT (i.e. the time adjustment step size) is too large to miss the drop point, at this time, the dichotomy method is selected to continue to calculate the drop point coordinates, and the specific method is as follows:

[0082] e1) setting the time T=T-DeltaT, that is, the time is returned to the time when the coordinates of the damage debris are calculated last time, the height parameter H in the coordinates of the damage debris calculated this time is less than 0, the height parameter H in the coordinates of the damage debris calculated last time is greater than h, and then setting

[0083] e2) setting T=T+DeltaT, calculating the orbit elements (a, e, i, Omega, omega, theta) at the time T;

[0084] e3) calculating the coordinates of the damage debris in the orbit coordinate system according to the orbit elements;

[0085] e4) In the geodetic coordinate system, compare the height parameter (H) in the damage fragment coordinate with the preset height threshold h, if 0≤H<h, obtain the landing point coordinate and exit the binary search calculation; if H>h, let Step e2 is performed; if H<0, step el is performed.

[0086] Through the above steps, the coordinates of the damage fragments in the geodetic coordinate system can be calculated.

[0087] In some specific embodiments, the determination of the landing point partition of the damage fragments according to the coordinates of the damage fragments comprises:

[0088] S1071: Obtain the preset iteration number and the initial centroid, wherein the initial centroid is a plurality of coordinates randomly selected from the coordinates of the damage fragments;

[0089] S1072: For each of the coordinates, calculate the distance from the coordinate to each of the initial centroids, and add the coordinate to the cluster corresponding to the initial centroid with the minimum distance, to obtain the initial clustering result;

[0090] S1073: After each of the coordinates is added to the corresponding cluster, calculate the average value of the coordinates in each of the clusters as a new centroid;

[0091] S1074: For each of the coordinates, calculate the distance from the coordinate to each of the new centroids, and add the coordinate to the cluster corresponding to the new centroid with the minimum distance;

[0092] S1075: Repeat steps S1073 and S1074 until the number of repetitions reaches the preset iteration number;

[0093] S1076: Determine the landing point partition of the damage fragments according to the final clustering result. Specifically, the landing point partition of the damage fragments can be determined according to the coordinates of the damage fragments in each cluster.

[0094] Generally, the landing point coordinates of the damage fragments are relatively dense, so the influence of the earth's surface on the calculation is ignored when calculating the landing point partition, and the landing point coordinates are regarded as two-dimensional plane. Therefore, in the two-dimensional rectangular coordinate system, the centroid coordinates of the damage fragment clusters and the landing point coordinates in the clusters can be calculated based on K-means.

[0095] In other optional embodiments, the initial clustering method is not limited to the above method, and the initial clustering can also be performed according to other methods.

[0096] In some optional embodiments, the determination of the landing point partition of the damage fragments according to the coordinates of the damage fragments comprises:

[0097] clustering the coordinates of the damaging fragments according to distance;

[0098] For each cluster obtained, the coordinate with the minimum y-axis value in the cluster is obtained as a second coordinate; in the embodiment of the present application, the influence of the earth's surface is ignored in the case of dense landing point coordinates, and only the plane is considered. Under this condition, the latitude and longitude are regarded as the rectangular coordinate system, and the prime meridian and the equatorial intersection point can be taken as the origin, the y-axis points to the north, and the x-axis points to the east, so the y-axis value here corresponds to the latitude value in the geodetic coordinate system;

[0099] For the remaining coordinates in the cluster, the polar angle value is sorted according to the second coordinate, and only the coordinates rotating counterclockwise are retained.

[0100] For example, if there are n coordinate points in a cluster, for the n coordinate points, first, the point p with the minimum y-axis value is screened out, and then the remaining n-1 coordinate points are sorted according to the polar angle value of the coordinate point p, and only the coordinate points rotating counterclockwise are retained, and the coordinate points obtained at this time are the convex hull list of the landing point partition corresponding to the cluster.

[0101] Since a large number of coordinate points cannot intuitively describe the landing point partition information of the damaging fragments, the embodiment of the present application uses the Graham Scan algorithm to calculate the outer polygon of each cluster, that is, the fragment landing point partition polygon, to obtain the convex hull list of the fragment landing point partition, which contains the landing point combination of each convex hull.

[0102] In summary, the embodiment of the present application provides a heterogeneous parallel computing method for aircraft damaging fragment landing point partitioning. The method calculates the orbit root number of the damaging fragments according to the state parameters of the damaging fragments at the initial time, thereby recursively calculating the landing point coordinates of the damaging fragments. In addition, in order to better describe the landing point information of the damaging fragments, the embodiment of the present application further calculates the main landing point area according to the landing point coordinates of all damaging fragments through a clustering algorithm, and then calculates the outer polygon of each area using the Graham Scan algorithm, and describes all the landing point areas of the damaging fragments using a set of polygon coordinates.

[0103] Correspondingly, please refer to Figure 2 The embodiment of the present application provides a device for determining the landing point partition of aircraft damaging fragments based on heterogeneous parallel computing, which comprises:

[0104] The acquisition module 201 is configured to acquire the state parameters of each damaging fragment at the initial time, and the state parameters at least include the position and the speed;

[0105] The first determining module 202 is configured to determine the coordinates of the damage fragments at the first time according to the state parameters, respectively for each damage fragment, wherein the coordinates are coordinates in a geodetic coordinate system, and the first time is greater than the initial time.

[0106] The judging module 203 is configured to judge whether the height parameter in the coordinates is greater than a preset height threshold, and judge whether the height parameter in the coordinates is less than zero.

[0107] The second determining module 204 is configured to increase the value of the first time when the height parameter in the coordinates is greater than the preset height threshold, and obtain the coordinates of the damage fragments at the new first time.

[0108] The third determining module 205 is configured to decrease the value of the first time when the height parameter in the coordinates is less than zero, and obtain the coordinates of the damage fragments at the new first time.

[0109] The output module 206 is configured to output the coordinates of the damage fragments when the height parameter in the coordinates is greater than zero and less than the preset height threshold, or equal to zero.

[0110] The fourth determining module 207 is configured to determine the landing point partition of the damage fragments according to the coordinates of the damage fragments.

[0111] The embodiment of the present application provides a device for determining the landing point partition of damage fragments of an aircraft based on heterogeneous parallel computing. The device calculates the orbital elements of the damage fragments according to the state parameters of the damage fragments at an initial time, recursively calculates the landing point coordinates of the damage fragments, and then determines the area range of the landing points of all the damage fragments according to the landing point coordinates of all the damage fragments. The method has high efficiency in determining the area range of the landing points of the damage fragments, and is convenient for early warning and taking measures for the landing point area of the damage fragments to avoid or reduce the damage caused by the damage fragments. In addition, the initial state parameters of the damage fragments are copied to a GPU based on the CPU computing mode, the parallel computing capability of the GPU is utilized to calculate the landing point coordinates of a large number of damage fragments, the efficiency of the landing point calculation of the damage fragments is greatly improved, and the landing point partition of the damage fragments is quickly obtained. That is, the embodiment of the present application improves the calculation speed of the landing point coordinates and partition of the damage fragments by using the heterogeneous parallel computing mode.

[0112] In some optional embodiments, the first determining module 202 comprises:

[0113] The first obtaining unit is configured to obtain the orbital elements of the damage fragments at the initial time according to the state parameters.

[0114] The first determining unit is used to determine the number of orbital elements of the damaged fragment at the first moment based on the number of orbital elements at the initial moment;

[0115] The second determining unit is used to determine the coordinates of the damaged fragment at the first moment based on the orbital elements at the first moment.

[0116] In some optional implementations, the second determining unit is specifically used to determine the first coordinates of the damaged fragment in the orbital coordinate system based on the orbital elements at the first moment; and to obtain the coordinates of the damaged fragment in the geodetic coordinate system based on the first coordinate transformation.

[0117] In some optional implementations, the third determining module 205 includes:

[0118] The second acquisition unit is used to acquire the first step length of the value at the first moment of the last adjustment;

[0119] The third determining unit is used to determine the second step size of the current adjustment, wherein the second step size is smaller than the first step size;

[0120] The first calculation unit is used to decrease the value at the first moment according to the second step size.

[0121] In some optional implementations, the fourth determining module 207 includes:

[0122] The third acquisition unit is used to acquire the preset number of iterations and the initial centroid, wherein the initial centroid is a plurality of coordinates randomly selected from the coordinates of the damaged fragments;

[0123] The first clustering unit is used to calculate the distance from each coordinate to each initial centroid for each coordinate, and add the coordinate to the cluster corresponding to the initial centroid with the smallest distance;

[0124] The third calculation unit is used to calculate the average value of the coordinates in each cluster as the new centroid after each coordinate is added to the corresponding cluster.

[0125] The second clustering unit is used to calculate the cluster from each coordinate to each new centroid for each coordinate, and add the coordinate to the cluster corresponding to the new centroid with the smallest distance;

[0126] The control unit controls the third calculation unit and the second clustering unit to run repeatedly until the number of repetitions reaches the preset number of iterations;

[0127] The fourth determining unit is used to determine the landing point partitions of the damaged fragments according to the final clustering.

[0128] In some optional embodiments, the fourth determining module 207 comprises:

[0129] a third clustering unit, configured to cluster the coordinates of the damage fragments according to distances;

[0130] a fourth obtaining unit, configured to obtain, for each obtained cluster, the coordinate with the minimum y-axis value in the cluster as a second coordinate;

[0131] a screening module, configured to sort the remaining coordinates in the cluster according to polar angle values of the second coordinates, and keep only the coordinates rotating counterclockwise

[0132] The embodiment of the present application is a device embodiment based on the same inventive concept as the above-mentioned method embodiment, and therefore specific technical details and corresponding technical effects are described in the above-mentioned method embodiment, which will not be repeated here.

[0133] The embodiment of the present application also provides an electronic device, as shown in the figure. Figure 3 The electronic device can include a central processor 31, a memory 32 and a graphics processor 33, wherein the central processor 31, the memory 32 and the graphics processor 33 can be connected to each other through a bus or other means, Figure 3 for example, by bus connection.

[0134] The memory 32 is a kind of non-transient computer readable storage medium, which can be used to store non-transient software programs, non-transient computer executable programs and modules, such as program instructions / modules (for example, Figure 2 the obtaining module 201, the first determining module 202, the judging module 203, the second determining module 204, the third determining module 205, the output module 206 and the fourth determining module 207) in the embodiment of the present application. The central processor 31 and the graphics processor 33 execute various functions of the central processor 31 and the graphics processor 33 and data processing by running the non-transient software programs, instructions and modules stored in the memory 32, that is, implement the method of determining the damage fragment fall point partition of the aircraft based on heterogeneous parallel computing in the above-mentioned method embodiment.

[0135] The memory 32 can include a program storage area and a data storage area, wherein the program storage area can store an operating system, at least one application required by a function, and the data storage area can store data created by the central processor 31 and the graphics processor 33, etc. In addition, the memory 32 can include a high-speed random access memory, and can also include a non-transitory memory, such as at least one magnetic disk storage device, a flash memory device, or other non-transitory solid-state memory device. In some embodiments, the memory 32 can optionally include a memory disposed remotely relative to the central processor 31 and the graphics processor 33, and these remote memories can be connected to the central processor 31 and the graphics processor 33 through a network. Examples of the above network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0136] The one or more modules are stored in the memory 32 and, when executed by the central processor 31 and the graphics processor 33, perform the above-described method for determining a damage fragment impact area of an aircraft based on heterogeneous parallel computing. Figure 1 The method for determining a damage fragment impact area of an aircraft based on heterogeneous parallel computing in the illustrated embodiment.

[0137] The specific details of the above electronic device can be referred to in the above description of the embodiments. Figure 1 The corresponding related descriptions and effects in the illustrated embodiments are understood, and will not be repeated here.

[0138] Correspondingly, the embodiments of the present application also provide a computer readable storage medium for storing a computer program, wherein the computer program is executed by the central processor 31 and the graphics processor 33 to implement the above-described various processes of the method for determining a damage fragment impact area of an aircraft based on heterogeneous parallel computing, and achieve the same technical effects. To avoid repetition, details will not be repeated here.

[0139] Each of the embodiments in the specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other. Each embodiment focuses on the differences from other embodiments.

[0140] The above only describes the embodiments of the present application and is not intended to limit the present application. The present application can have various changes and modifications for those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the scope of the claims of the present application.

Claims

1. A method for determining the impact point partitioning of aircraft debris based on heterogeneous parallel computing, characterized in that, The method comprises: S101: a central processor acquires state parameters of each damage fragment at an initial moment and copies the state parameters to a graphics processor, the state parameters at least including position and velocity; S102: the graphics processor respectively determines coordinates of each damage fragment at a first moment according to the state parameters, the coordinates being coordinates in a terrestrial coordinate system; wherein the first moment is greater than the initial moment; The determination of the coordinates of the damage fragment at the first moment according to the state parameters specifically comprises: acquiring orbit elements of the damage fragment at the initial moment according to the state parameters; determining orbit elements of the damage fragment at the first moment according to the orbit elements at the initial moment; determining the coordinates of the damage fragment at the first moment according to the orbit elements at the first moment; S103: the graphics processor judges whether an elevation parameter in the coordinates is greater than a preset height threshold and whether the elevation parameter in the coordinates is less than zero; S104: the graphics processor increases the value of the first moment in the case that the elevation parameter in the coordinates is greater than the preset height threshold, and acquires the coordinates of the damage fragment at a new first moment, and returns to step S103; S105: the graphics processor decreases the value of the first moment in the case that the elevation parameter in the coordinates is less than zero, and acquires the coordinates of the damage fragment at a new first moment, and returns to step S103; S106: the graphics processor outputs the coordinates of the damage fragment in the case that the elevation parameter in the coordinates is greater than zero and less than the preset height threshold or equal to zero; S107: the graphics processor determines a landing point partition of the damage fragment according to the coordinates of each damage fragment; The determination of the landing point partition of the damage fragment according to the coordinates of each damage fragment specifically comprises: S1071: acquiring a preset iteration number and initial centroids, the initial centroids being a plurality of coordinates randomly selected from the coordinates of the damage fragment; S1072: for each coordinate, respectively calculating distances from the coordinate to each initial centroid, and adding the coordinate to a cluster corresponding to the initial centroid with the minimum distance; S1073: after each coordinate is added to the corresponding cluster, calculating an average value of the coordinates in each cluster as a new centroid; S1074: for each coordinate, respectively calculating clusters from the coordinate to each new centroid, and adding the coordinate to a cluster corresponding to the new centroid with the minimum distance; S1075: repeating steps S1073 and S1074 until the number of repetitions reaches the preset iteration number; S1076: determining the landing point partition of the damage fragment according to the finally obtained clusters.

2. The method of claim 1, wherein, The determination of the coordinates of the damage fragment at the first moment according to the orbit elements at the first moment comprises: determining a first coordinate of the damage fragment in an orbit coordinate system according to the orbit elements at the first moment; The first coordinate conversion is used to obtain the coordinates of the damage fragments in a geodetic coordinate system.

3. The method of claim 1, wherein, In a case where an elevation parameter in the coordinates is less than zero, the value of the first time is reduced, including: Obtaining a first step length for last time adjustment of the value of the first time; Determining a second step length for current time adjustment, the second step length being less than the first step length; Reducing the value of the first time according to the second step length.

4. The method of claim 1, wherein, The determination of the impact point partition of the damage fragments according to the coordinates of the damage fragments further includes: Clustering the coordinates of the damage fragments according to distances; For each obtained cluster, obtaining a second coordinate with a minimum y-axis value in the cluster as a second coordinate; For the remaining coordinates in the cluster, sorting the coordinates according to polar angle values of the second coordinate, and only retaining the coordinates in counterclockwise rotation.

5. A device for determining the impact point of aircraft debris based on heterogeneous parallel computing, characterized in that, The device includes: An obtaining module, configured to obtain state parameters of damage fragments at an initial time, the state parameters including at least positions and velocities; A first determining module, configured to determine coordinates of the damage fragments at a first time according to the state parameters, respectively for each damage fragment, the coordinates being coordinates in a geodetic coordinate system; wherein the first time is greater than the initial time; the first determining module specifically includes: A first obtaining unit, configured to obtain orbit elements of the damage fragments at the initial time according to the state parameters; A first determining unit, configured to determine orbit elements of the damage fragments at the first time according to the orbit elements at the initial time; A second determining unit, configured to determine the coordinates of the damage fragments at the first time according to the orbit elements at the first time; A judging module, configured to judge whether an elevation parameter in the coordinates is greater than a preset height threshold, and whether the elevation parameter in the coordinates is less than zero; A second determining module, configured to increase the value of the first time in a case where the elevation parameter in the coordinates is greater than the preset height threshold, and obtain coordinates of the damage fragments at a new first time; A third determining module, configured to reduce the value of the first time in a case where the elevation parameter in the coordinates is less than zero, and obtain coordinates of the damage fragments at a new first time; An output module, configured to output the coordinates of the damage fragments in a case where the elevation parameter in the coordinates is greater than zero and less than the preset height threshold, or equal to zero; A fourth determining module, configured to determine an impact point partition of the damage fragments according to the coordinates of the damage fragments; the fourth determining module specifically includes: A third obtaining unit, configured to obtain a preset iteration number and initial centroids, the initial centroids being a plurality of coordinates randomly selected from the coordinates of the damage fragments; A first clustering unit, configured to calculate distances from each coordinate to each initial centroid, respectively for each coordinate, and add the coordinate to a cluster corresponding to the initial centroid with the minimum distance; A third calculating unit, configured to calculate an average value of the coordinates in each cluster as a new centroid after each coordinate is added to a corresponding cluster. a second clustering unit, configured to calculate a cluster of each coordinate to each new centroid respectively for each coordinate, and add the coordinate to the cluster corresponding to the new centroid with the smallest distance; a control unit, configured to control the third calculation unit and the second clustering unit to repeat until the number of repetitions reaches the preset iteration number; a fourth determination unit, configured to determine the impact point partition of the damage debris according to the finally obtained clusters.

6. An electronic device, comprising: comprising: a memory, a central processing unit and a graphics processing unit, which are in communication connection with each other, the memory is used to store a computer program, and the computer program is executed by the central processing unit and the graphics processing unit to realize the aircraft damage debris impact point partition determination method based on heterogeneous parallel computing according to any one of claims 1 to 4.

7. A computer-readable storage medium, characterized in that, the computer readable storage medium is used to store a computer program, and the computer program is executed by the central processing unit and the graphics processing unit to realize the aircraft damage debris impact point partition determination method based on heterogeneous parallel computing according to any one of claims 1 to 4.

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