Methods, systems, and media for calculating the launch zone of a spacecraft under the constraint of debris impact point

Abstract

This invention discloses a method, system, and medium for calculating the launch area of ​​an aircraft under debris landing point constraints, belonging to the field of aircraft mission planning technology. This method determines the primary launch area based on an initial region, a destination point, the aircraft's maximum range, and the distance to the aircraft debris. The primary launch area is the estimated launch area of ​​the aircraft. The initial region is the area where the aircraft's starting point is located; the destination point is the final destination reached by the aircraft; and the distance to the aircraft debris is the distance from the aircraft's starting point to the ground landing point of the debris. The launch area is determined based on the initial region, the primary launch area, and the aircraft's maximum range. This method effectively promotes resource optimization in selecting aircraft deployment areas and improves initial situational analysis capabilities.

Description

Technical Field

[0001] This invention belongs to the field of aircraft mission planning technology, and in particular relates to a method, system and medium for calculating the launch area of ​​an aircraft under the constraint of debris landing point. Background Technology

[0002] In existing technologies, aircraft have the problem of debris shedding during flight. To avoid the impact of debris shedding on the landing site, it is necessary to select the launch area of ​​the aircraft in advance. In addition, the construction of the launch area consumes resources. By integrating data such as the aircraft's range, debris landing point information and destination location in advance, and quickly analyzing and calculating the launch area and debris shedding area, the selection of the launch area can be optimized, which can reduce unnecessary waste of resources to a certain extent.

[0003] By analyzing the aircraft's range, debris drop point, and destination requirements, we can quickly deduce and locate the aircraft's deployment position, which has certain reference value in aircraft research. Summary of the Invention

[0004] This invention provides a method, system, and medium for calculating the launch zone of an aircraft under the constraint of debris landing point, which is used to solve the technical problem of launch zone selection.

[0005] In a first aspect, a method for calculating the launch zone of a spacecraft under the constraint of debris impact point is disclosed, the method comprising the following steps:

[0006] Step S1: Determine the primary launch area based on the initial area, destination point, maximum range of the aircraft, and distance to the aircraft wreckage. The primary launch area is the estimated launch zone of the aircraft.

[0007] Wherein, the initial area is the area where the aircraft's starting point is located; the destination point is the target destination reached by the aircraft; and the aircraft wreckage distance is the distance from the aircraft's starting point to the point where the aircraft wreckage lands on the ground.

[0008] Step S2: Determine the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft. The launch area is the area in which the aircraft takes off if it meets the ground landing point constraint conditions of the aircraft debris.

[0009] Preferably, step S1, determining the primary launch area based on the initial area, destination point, maximum range of the aircraft, and distance to the aircraft wreckage, includes:

[0010] Step S11: For each boundary point of the initial region, perform the following operations:

[0011] Determine the azimuth angle between the boundary point of the initial region and the destination point. The formula for calculating the azimuth angle is:

[0012]

[0013] Where (L1, B1) are the coordinates of the boundary point of the initial region, L1 is the longitude coordinate of the boundary point of the initial region, and B1 is the latitude coordinate of the boundary point of the initial region; (L2, B2) are the coordinates of the destination point, L2 is the longitude coordinate of the destination point, B2 is the latitude coordinate of the destination point, π is pi, and fmod is a function to find the remainder when two floating-point numbers are divided.

[0014] Step S12: For each boundary point of the initial region, perform the following operations:

[0015] The boundary point of the initial region is translated along its corresponding azimuth angle by the distance of the aircraft wreckage, and the coordinates of the translated point (L′1, B′1) are determined. L′1 is the longitude coordinate of the translated boundary point, and B′1 is the latitude coordinate of the translated boundary point.

[0016]

[0017] Where, r e tp, s λ c λ This is intermediate data, where dis is the distance to the aircraft wreckage;

[0018] Step S13: The area defined by the points after translating all the boundary points of the initial region is taken as the emission region to be screened; wherein, the points after translating all the boundary points of the initial region are the boundary points to be screened, and the coordinates of all the boundary points to be screened are stored in the first array.

[0019] Step S14: Perform the following operation on each array element in the first array:

[0020] Determine the distance S between the array element and the destination point. R The calculation formula is:

[0021]

[0022] Where 'a' represents intermediate data, 'rng' represents the angle between the first and second connecting lines, the first connecting line is the line connecting the boundary point of the initial region corresponding to the array element to the destination point, and the second connecting line is the line connecting the boundary point to be filtered corresponding to the array element to the destination point; tan -1 For reverse tangent;

[0023] If S R ≤Smax If the array element is stored in the second array, then the processing of that array element is complete; otherwise, the processing of that array element is complete. max Indicates the aircraft's maximum range;

[0024] Step S15: Take the region defined by the boundary points to be filtered corresponding to all the array elements of the second array as the primary emission region R′.

[0025] Preferably, the primary emission region R′ is represented as:

[0026]

[0027] Where R′ represents the second array corresponding to the primary launch region, G is the array formed by all boundary points of the initial region; az1 is the azimuth angle from the destination point to each boundary point corresponding to G, and S c Distance to the aircraft wreckage Indicates the direction of translation. S represents the translation distance; R S represents the distance between each point in the first data set R and the destination point. max This indicates the aircraft's maximum range.

[0028] Preferably, step S2, determining the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft, includes:

[0029] Step S21: Obtain the intersection of the initial region and the primary emission region. The boundary points of the region formed by the intersection are stored in the third array, which is denoted as R″. Each array element in R″ includes longitude and latitude.

[0030] Step S22: For each point within the region formed by the intersection, perform the following operation:

[0031] Step S221: Determine the azimuth and distance from this point to the boundary point corresponding to each array element of the first array, denoted as az respectively. OG S OG The points, along with the azimuth and distance from that point to the boundary points corresponding to each element of the second array, form four arrays, denoted as a, b, c, and a. OR′ S OR′ ;

[0032] Step S222: Determine the line connecting the point to the boundary point of the primary emission region along the firing direction, and determine each connecting line. num The number of intersection points N with the initial region num Where num is the number of lines connecting the point to the boundary point of the primary emission region, and the value of num is the same as the number of boundary points of the primary emission region;

[0033] Step S223: If N num If the number is even, then the point is determined to be inside the initial region; otherwise, the point is outside the initial region.

[0034] Step S23: Obtain a subset of points in the region formed by the intersection, wherein all points in the subset are within the initial region, and the region defined by the subset is the launch area of ​​the flight zone; determine the boundary points of the launch area of ​​the flight zone and store the boundary points of the launch area of ​​the flight zone into the fourth array.

[0035] Preferably, the method includes step S3, which determines the debris landing area of ​​the aircraft based on the destination point, the distance to the aircraft debris, the maximum range of the aircraft, and the launch area of ​​the aircraft.

[0036] Secondly, a system for calculating the launch zone of a spacecraft under debris impact point constraints is disclosed, the system comprising:

[0037] Initial module: configured to determine the primary launch area based on the initial region, destination point, maximum range of the aircraft, and distance to the aircraft wreckage, wherein the primary launch area is the estimated launch zone of the aircraft;

[0038] Wherein, the initial area is the area where the aircraft's starting point is located; the destination point is the target destination reached by the aircraft; and the aircraft wreckage distance is the distance from the aircraft's starting point to the point where the aircraft wreckage lands on the ground.

[0039] Calculation module: configured to determine the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft. The launch area is the area in which the aircraft takes off if it meets the constraints of the aircraft debris landing point.

[0040] Thirdly, an electronic device is disclosed, the electronic device comprising:

[0041] At least one processor; and

[0042] A memory communicatively connected to the at least one processor; wherein,

[0043] The memory stores instructions that can be executed by the at least one processor to enable the at least one processor to perform the method as described above.

[0044] Fourthly, a non-transitory computer-readable storage medium storing computer instructions for causing the computer to perform the method described above is disclosed.

[0045] The present invention has the following technical effects:

[0046] This invention provides a method for rapidly calculating the launch area and debris disposal area of ​​an aircraft that meets its range and debris landing requirements by using initial area information, destination location information, and aircraft range and debris landing point information. This invention supports and verifies the advanced deployment of aircraft, integrates initial resources, and optimizes launch areas, effectively promoting resource optimization in selecting aircraft deployment areas and improving initial situational analysis capabilities. Attached Figure Description

[0047] Figure 1 A flowchart illustrating the method for calculating the launch zone of an aircraft under the constraint of debris impact point;

[0048] Figure 2 A schematic diagram illustrating the specific process of calculating the launch zone of an aircraft under the constraint of debris impact point;

[0049] Figure 3 A flowchart illustrating the process of determining the number of intersection points in the calculation method for the launch zone of an aircraft under the constraint of debris landing point;

[0050] Figure 4 A schematic diagram illustrating the determination of the values ​​of the overlapping region array in the calculation method of the launch zone of an aircraft under the constraint of debris landing point;

[0051] Figure 5 This is a schematic diagram illustrating the initial area and destination information in an embodiment of the present invention.

[0052] Figure 6 This is a schematic diagram of the initial launch area according to an embodiment of the present invention;

[0053] Figure 7 These are intermediate calculation results from embodiments of the present invention;

[0054] Figure 8 This is a schematic diagram of the structure of the spacecraft launch area calculation system under the constraint of debris impact point. Detailed Implementation

[0055] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0056] like Figure 1-Figure 2 As shown, this invention provides a method for calculating the launch zone of an aircraft under the constraint of debris impact point. The method includes the following steps:

[0057] Step S1: Determine the primary launch area based on the initial area, destination point, maximum range of the aircraft, and distance to the aircraft wreckage. The primary launch area is the estimated launch zone of the aircraft.

[0058] Wherein, the initial area is the area where the aircraft's starting point is located; the destination point is the target destination reached by the aircraft; and the aircraft wreckage distance is the distance from the aircraft's starting point to the point where the aircraft wreckage lands on the ground.

[0059] Step S2: Determine the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft. The launch area is the area in which the aircraft takes off if it meets the ground landing point constraint conditions of the aircraft debris.

[0060] Step S1: Determine the primary launch area based on the initial area, destination point, maximum range of the aircraft, and distance to the aircraft wreckage, including:

[0061] Step S11: For each boundary point of the initial region, perform the following operations:

[0062] Determine the azimuth angle between the boundary point of the initial region and the destination point. The formula for calculating the azimuth angle is:

[0063]

[0064] Where (L1, B1) are the coordinates of the boundary point of the initial region, L1 is the longitude coordinate of the boundary point of the initial region, and B1 is the latitude coordinate of the boundary point of the initial region; (L2, B2) are the coordinates of the destination point, L2 is the longitude coordinate of the destination point, B2 is the latitude coordinate of the destination point, π is pi, and fmod is a function to find the remainder when two floating-point numbers are divided.

[0065] Step S12: For each boundary point of the initial region, perform the following operations:

[0066] The boundary point of the initial region is translated along its corresponding azimuth angle by the distance of the aircraft wreckage, and the coordinates of the translated point (L′1, B′1) are determined. L′1 is the longitude coordinate of the translated boundary point, and B′1 is the latitude coordinate of the translated boundary point.

[0067]

[0068] Where, r e tp, s λ c λ This is intermediate data, where dis is the distance to the aircraft wreckage;

[0069] Step S13: The area defined by the points after translating all the boundary points of the initial region is taken as the emission region to be screened; wherein, the points after translating all the boundary points of the initial region are the boundary points to be screened, and the coordinates of all the boundary points to be screened are stored in the first array.

[0070] Step S14: Perform the following operation on each array element in the first array:

[0071] Determine the distance S between the array element and the destination point. R The calculation formula is:

[0072]

[0073] Where 'a' represents intermediate data, 'rng' represents the angle between the first and second connecting lines, the first connecting line is the line connecting the boundary point of the initial region corresponding to the array element to the destination point, and the second connecting line is the line connecting the boundary point to be filtered corresponding to the array element to the destination point; tan -1 For reverse tangent;

[0074] If S R ≤S max If the array element is stored in the second array, then the processing of that array element is complete; otherwise, the processing of that array element is complete. max Indicates the aircraft's maximum range;

[0075] Step S15: Take the region defined by the boundary points to be filtered corresponding to all the array elements of the second array as the primary emission region R′;

[0076] In this invention, the primary emission region R′ is represented as:

[0077]

[0078] Where R′ represents the second array corresponding to the primary launch region, G is the array formed by all boundary points of the initial region; az1 is the azimuth angle from the destination point to each boundary point corresponding to G, and S c Distance to the aircraft wreckage Indicates the direction of translation. S represents the translation distance; R S represents the distance between each point in the first data set R and the destination point. max This indicates the aircraft's maximum range.

[0079] In this invention, the primary launch area can meet the range constraints, and each array element in the second array contains longitude and latitude.

[0080] In this invention, it is determined whether the great circle distance between the data in the first array and the destination meets the flight distance requirement, i.e., S. R ≤S max If the requirements are met, the point is added to the second array, and the area enclosed by the boundary points to be screened corresponding to all the array elements of the second array is taken as the primary emission area.

[0081] Step S2, which determines the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft, includes:

[0082] Step S21: Obtain the intersection of the initial region and the primary emission region. The boundary points of the region formed by the intersection are stored in the third array, which is denoted as R″. Each array element in R″ includes longitude and latitude.

[0083] Step S22: For each point within the region formed by the intersection, perform the following operation:

[0084] Step S221: Determine the azimuth and distance from this point to the boundary point corresponding to each array element of the first array, denoted as az respectively. OG S OG The points, along with the azimuth and distance from that point to the boundary points corresponding to each element of the second array, form four arrays, denoted as a, b, c, and a. OR′ S OR′ ;

[0085] Step S222: Determine the line connecting the point to the boundary point of the primary emission region along the firing direction, and determine each connecting line. num The number of intersection points N with the initial region num Where num is the number of lines connecting the point to the boundary point of the primary emission region, and the value of num is the same as the number of boundary points of the primary emission region;

[0086] Step S223: If N num If the number is even, then the point is determined to be inside the initial region; otherwise, the point is outside the initial region.

[0087] Step S23: Obtain a subset of points in the region formed by the intersection, wherein all points in the subset are within the initial region, and the region defined by the subset is the launch area of ​​the flight zone; determine the boundary points of the launch area of ​​the flight zone and store the boundary points of the launch area of ​​the flight zone into the fourth array.

[0088] Further, step S222: Determine the line connecting the point to the boundary point of the primary emission region along the firing direction, and determine each connecting line. num The number of intersection points N with the initial region num ,include:

[0089] Whether a point intersects with the initial region is determined based on the azimuth and distance from the point to two adjacent boundary points of the primary launch region.

[0090] In this invention, step S3 specifically includes: calculating the intersection of the two arrays R″=G∩R′, where: R′ is the primary launch area boundary point array that satisfies the range constraint condition, containing latitude and longitude information; G is the initial area boundary point array, containing latitude and longitude information; R″ is the final overlapping area boundary point data, containing longitude and latitude.

[0091] S3.1 Select any point O in the overlapping region of the initial region and the initial launch region obtained in step S2; calculate the azimuth and distance from point O to each point on the boundary of the initial region and the primary launch region according to Equations 1.1 and 1.3, respectively, denoted as az. OG S OG , az OR′ S OR′ .

[0092] S3.2 Calculate the number N of intersection points between the line connecting the selected point O in S3.1 and the boundary line of the primary emission region obtained in step S2 with the initial region.

[0093] Where N is the number of intersection points, satisfying condition N+1, az OG S is an array of azimuth angles from the selected point O in S3.1 to each point on the initial region boundary. OG This is an array of distances from the selected point O in S3.1 to each point on the initial region boundary, where j is the position of the array value; az OP′ S is an array of azimuth angles from center point O to the boundary of the primary launch area. OP′ This is an array of distances from the center point O to each point on the boundary of the primary launch region, where k is the position of the array value.

[0094] S3.3 Based on the judgment result N of S3.2, combine the array. If N is even, determine that the current calculation boundary point is inside the initial region; otherwise, it is outside the initial region.

[0095] Where R″ is the overlapping region boundary array, R′ is the primary launch region boundary point array obtained by S2 that satisfies the range constraint, and G is the initial region boundary point array.

[0096] The overlapping region boundary array must also satisfy the condition that the distance from each point on the boundary to the destination F is within the maximum range of the aircraft; S R″ ≤S max S R″ S is the distance from the boundary point of the overlapping region to the destination F. max This is the maximum range of the aircraft.

[0097] Furthermore, the present invention also includes step S3: determining the debris landing area of ​​the aircraft based on the destination point, the distance of the aircraft debris, the maximum range of the aircraft, and the launch area of ​​the aircraft.

[0098] In step S3, the debris landing area of ​​the aircraft is represented as follows:

[0099]

[0100] Where P is the fifth array of boundary points of the spacecraft's debris landing area, and each array element contains longitude and latitude; R″ is the fourth array corresponding to the spacecraft's launch area, and each array element of the fourth array contains longitude and latitude; az2 is the azimuth angle from each point on the R″ boundary to the destination point F; S c Distance to the aircraft wreckage.

[0101] like Figures 3-7 As shown, the present invention provides a method for calculating the launch zone of an aircraft under the constraint of debris impact point.

[0102] This embodiment has two examples. In example 1, the location information of the initial region G and the destination F (141.185 degrees east longitude, 9.615 degrees north latitude) is as follows: Figure 5 As shown, the aircraft data (distance S between the wreckage drop point and the takeoff point) c =300000m, maximum range S max =3,000,000m). The location information of the initial region G and destination F in Example 2 (138.354 degrees East longitude, 3.331 degrees North latitude) is as follows: Figure 8 As shown, the aircraft data (distance S between the wreckage drop point and the takeoff point) c =300000m, maximum range S max =3,000,000m).

[0103] In this embodiment, the simulation software is Visual Studio 2015 and Matlab 2019, and the simulation computer is configured with an "Intel Core i9-13900KF 3.00GHz 32-core CPU + 128GB of memory". Example 1 of this embodiment has an initial region ( Figure 5 The array shown contains 9051 elements, and the calculation results are as follows. Figure 7 As shown, the calculation time is 0.064s. Example 2 Initial region ( Figure 8 The array (as shown) contains 2394 elements, and the calculation time is 0.015 seconds.

[0104] This example is based on a rapid calculation method for the launch area of ​​an aircraft under the constraint of debris impact point. It provides effective technical support for aircraft planning and deployment, and initial situation analysis.

[0105] like Figure 8 As shown, the present invention provides a system for calculating the launch zone of a spacecraft under the constraint of debris impact point, the system comprising:

[0106] Initial module: configured to determine the primary launch area based on the initial region, destination point, maximum range of the aircraft, and distance to the aircraft wreckage, wherein the primary launch area is the estimated launch zone of the aircraft;

[0107] Wherein, the initial area is the area where the aircraft's starting point is located; the destination point is the target destination reached by the aircraft; and the aircraft wreckage distance is the distance from the aircraft's starting point to the point where the aircraft wreckage lands on the ground.

[0108] Calculation module: configured to determine the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft. The launch area is the area in which the aircraft takes off if it meets the constraints of the aircraft debris landing point.

[0109] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein, and such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for calculating the launch zone of an aircraft under the constraint of debris impact point, characterized in that, The method includes the following steps: Step S1: Determine the primary launch area based on the initial area, destination point, maximum range of the aircraft, and distance to the aircraft wreckage. The primary launch area is the estimated launch zone of the aircraft. Wherein, the initial area is the area where the aircraft's starting point is located; the destination point is the target destination reached by the aircraft; and the aircraft wreckage distance is the distance from the aircraft's starting point to the point where the aircraft wreckage lands on the ground. Step S2: Determine the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft. The launch area is the area in which the aircraft takes off if it meets the ground landing point constraint conditions of the aircraft debris. Step S2, which determines the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft, includes: Step S21: Obtain the intersection of the initial region and the primary emission region. Store the boundary points of the region formed by this intersection in a third array, denoted as [array name missing]. , Each array element includes longitude and latitude; Step S22: For each point within the region formed by the intersection, perform the following operation: Step S221: Determine the azimuth and distance from this point to the boundary point corresponding to each array element of the first array, and denot them as follows: , The azimuth and distance from this point to the boundary points corresponding to each element of the second array are used to form four arrays, denoted as follows: , ; Step S222: Determine the line connecting the point to the boundary point of the primary emission region along the firing direction, and determine each connecting line. num The number of intersection points N with the initial region num Where num is the number of lines connecting the point to the boundary point of the primary emission region, and the value of num is the same as the number of boundary points of the primary emission region; Step S223: If N num If the number is even, then the point is determined to be inside the initial region; otherwise, the point is outside the initial region. Step S23: Obtain a subset of points in the region formed by the intersection, wherein all points in the subset are within the initial region, and the region defined by the subset is the launch area of ​​the flight zone; determine the boundary points of the launch area of ​​the flight zone and store the boundary points of the launch area of ​​the flight zone into the fourth array.

2. The method as described in claim 1, characterized in that, Step S1: Determine the primary launch area based on the initial area, destination point, maximum range of the aircraft, and distance to the aircraft wreckage, including: Step S11: For each boundary point of the initial region, perform the following operations: Determine the azimuth angle between the boundary point of the initial region and the destination point, the azimuth angle The calculation formula is: ， in, The coordinates of the boundary points of the initial region are given. The longitude coordinates of the boundary points of the initial region. The latitude coordinates of the boundary points of the initial region; The coordinates of the destination point are... Here are the longitude coordinates of the destination point. The latitude coordinates of the destination point. Pi The function is used to find the remainder when two floating-point numbers are divided. Step S12: For each boundary point of the initial region, perform the following operations: The boundary points of the initial region are translated along their corresponding azimuth angle by a distance equal to the distance of the aircraft wreckage, and the coordinates of the translated points are determined. , These are the longitude coordinates of the point after the boundary point has been translated. The latitude coordinates of the point after the boundary point has been translated; , in, The average radius of the Earth; , , For intermediate data, dis Distance to the aircraft wreckage; Step S13: The area defined by the points after translating all the boundary points of the initial region is taken as the emission region to be screened; wherein, the points after translating all the boundary points of the initial region are the boundary points to be screened, and the coordinates of all the boundary points to be screened are stored in the first array. Step S14: Perform the following operation on each array element in the first array: Determine the distance between the array element and the destination point. The calculation formula is: , in, For intermediate data, The angle between the first line and the second line is the angle between the boundary point of the initial region corresponding to the array element and the destination point. The first line is the line connecting the boundary point to be filtered corresponding to the array element and the destination point. For reverse tangent; like If the array element is stored in the second array, the array element has been processed; otherwise, the array element has been processed. Indicates the aircraft's maximum range; Step S15: Use the region defined by the boundary points to be filtered corresponding to all elements of the second array as the primary emission region. .

3. The method as described in claim 2, characterized in that, The primary launch area Represented as: , in, The second array represents the primary launch region, and G is an array formed by all the boundary points of the initial region. Let G be the azimuth angle from the destination point to each corresponding boundary point. Distance to the aircraft wreckage Indicates the direction of translation. Indicates the translation distance; Indicates the first data R The distance between each point in the map and the destination point. This indicates the aircraft's maximum range.

4. The method as described in claim 3, characterized in that, The method includes step S3, which determines the debris landing area of ​​the aircraft based on the destination point, the distance to the aircraft debris, the maximum range of the aircraft, and the launch area of ​​the aircraft.

5. A calculation system for the launch area of ​​an aircraft under the constraint of debris impact point, characterized in that, The system includes: Initial module: configured to determine the primary launch area based on the initial region, destination point, maximum range of the aircraft, and distance to the aircraft wreckage, wherein the primary launch area is the estimated launch zone of the aircraft; Wherein, the initial area is the area where the aircraft's starting point is located; the destination point is the target destination reached by the aircraft; and the aircraft wreckage distance is the distance from the aircraft's starting point to the point where the aircraft wreckage lands on the ground. Calculation module: configured to determine the launch area of ​​the aircraft based on the initial area, the primary launch area, and the maximum range of the aircraft, wherein the launch area is the area in which the aircraft takes off and meets the constraints of the aircraft debris ground landing point; The determination of the launch zone based on the initial region, the primary launch region, and the aircraft's maximum range includes: Obtain the intersection of the initial region and the primary emission region. Store the boundary points of the region formed by this intersection in a third array, denoted as . , Each array element includes longitude and latitude; For each point within the region formed by the intersection, perform the following operations: Determine the azimuth and distance from this point to the boundary point corresponding to each element of the first array, denoted as [reference to ]. , The azimuth and distance from this point to the boundary points corresponding to each element of the second array are used to form four arrays, denoted as follows: , ; Determine the line connecting this point to the boundary point of the primary emission region along the firing direction, and determine each connecting line. num The number of intersection points N with the initial region num Where num is the number of lines connecting the point to the boundary point of the primary emission region, and the value of num is the same as the number of boundary points of the primary emission region; If N num If the number is even, then the point is determined to be inside the initial region; otherwise, the point is outside the initial region. Obtain a subset of points in the region formed by the intersection, wherein all points in the subset are within the initial region, and the region defined by the subset is the launch area of ​​the flight zone; determine the boundary points of the launch area of ​​the flight zone and store the boundary points of the launch area of ​​the flight zone into the fourth array.

6. An electronic device, the device comprising: At least one processor; as well as A memory communicatively connected to the at least one processor; wherein, The memory stores instructions that can be executed by the at least one processor to enable the at least one processor to perform the method as described in any one of claims 1-4.

7. A non-transitory computer-readable storage medium storing computer instructions for causing the computer to perform the method as described in any one of claims 1-4.

Images