Method and system for calculating launch area of aircraft under constraint of wreckage drop point, and medium

Abstract

The invention discloses an aircraft launching area calculation method and system under the constraint of wreckage drop points and a medium, and belongs to the technical field of aircraft task planning. The method comprises the following steps: determining a primary launching area based on an initial area, a destination, the maximum flight range of an aircraft and the wreckage distance of the aircraft, wherein the primary launching area is an estimated launching area of the aircraft; wherein the initial area is an area where the starting point of the aircraft is located; the destination point is a destination end point where the aircraft flies; the aircraft wreckage distance is the distance from the starting point of the aircraft to the ground landing point of the aircraft wreckage; determining an aircraft launching area based on the initial area, the primary launching area and the maximum voyage of the aircraft; according to the method, resource optimization development of the selected aircraft deployment area is effectively promoted, and the initial situation analysis capability is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft mission planning, and in particular relates to a method, system and medium for calculating an aircraft launch area under debris landing point constraints. Background Art

[0002] In the prior art, there is a problem of debris being dropped during the flight of an aircraft. In order to avoid the impact of the dropped debris on the landing, it is necessary to select the launch area for the aircraft in advance. In addition, the construction of the launch area will consume resources. It is necessary to integrate data such as the aircraft's range, debris landing point information, and destination location in advance, quickly analyze and calculate the aircraft launch area and the debris dropping area, and optimize the launch area selection, which can reduce unnecessary resource waste to a certain extent.

[0003] The aircraft's range, debris drop point, and destination requirements can be used to quickly infer and locate the aircraft's deployment location information, which has certain reference significance in aircraft research. Summary of the invention

[0004] The present invention provides a method, system and medium for calculating an aircraft launch area under debris landing point constraints, which are used to solve the technical problem of selecting a launch area.

[0005] In a first aspect, a method for calculating a launch area of ​​an aircraft under a debris landing point constraint is disclosed, the method comprising the following steps:

[0006] Step S1: determining a primary launch area based on an initial area, a destination point, a maximum range of the aircraft, and a distance from aircraft wreckage, wherein the primary launch area is an estimated launch area of ​​the aircraft;

[0007] The initial area is the area where the aircraft's starting point is located; the destination point is the destination point where the aircraft flies to; the aircraft wreckage distance is the distance from the aircraft's starting point to the ground where the aircraft wreckage lands;

[0008] Step S2: determining an aircraft launch area based on the initial area, the primary launch area, and the maximum range of the aircraft, wherein the aircraft launch area is an area for taking off the aircraft that meets the aircraft wreckage ground landing point constraint.

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

[0010] Step S11: For each boundary point of the initial area, the following operations are performed:

[0011] Determine the azimuth between the boundary point of the initial area and the destination point, the azimuth is calculated as follows:

[0012]

[0013] Wherein, (L1, B1) are the coordinates of the boundary point of the initial area, L1 is the longitude coordinate of the boundary point of the initial area, and B1 is the latitude coordinate of the boundary point of the initial area; (L2, B2) are the coordinates of the destination point, L2 is the longitude coordinate of the destination point, and B2 is the latitude coordinate of the destination point, π is pi, and the fmod function is a function for finding the remainder of dividing two floating point numbers;

[0014] Step S12: For each boundary point of the initial area, the following operations are performed:

[0015] The boundary point of the initial area is translated along its corresponding azimuth by a distance of the aircraft debris, and the coordinates of the translated point are determined (L′1, B′1), where L′1 is the longitude coordinate of the point after the boundary point is translated, and B′1 is the latitude coordinate of the point after the boundary point is translated;

[0016]

[0017] Among them, r e is the average radius of the Earth; tp, s λ 、c λ is the intermediate data, dis is the distance of the aircraft wreckage;

[0018] Step S13: The area enclosed by the points after all the boundary points of the initial area are translated as the emission area to be screened; wherein the points after all the boundary points of the initial area are translated 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: For each array element in the first array, perform the following operations:

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

[0021]

[0022] Wherein, a is the intermediate data, rng is the angle between the first connecting line and the second connecting line, the first connecting line is the connecting line between the boundary point of the initial area corresponding to the array element and the destination point, and the second connecting line is the connecting line between the boundary point to be screened corresponding to the array element and the destination point; tan -1 is the inverse tangent;

[0023] If S R ≤Smax , the array element is stored in the second array, and the array element is processed; otherwise, the array element is processed; S max Indicates the maximum range of the aircraft;

[0024] Step S15: The area enclosed by the boundary points to be screened corresponding to all array elements of the second array is used as the primary emission area R′.

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

[0026]

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

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

[0029] Step S21: obtaining the intersection of the initial area and the primary emission area, and storing the boundary points of the area formed by the intersection into a third array, wherein the third array is denoted as R″, and each array element in R″ includes longitude and latitude;

[0030] Step S22: For each point inside the area formed by the intersection, the following operations are performed:

[0031] Step S221: Determine the azimuth and distance from the point to the boundary point corresponding to each array element of the first array, denoted as az OG , S OG , and the azimuth and distance from this point to the boundary point corresponding to each array element of the second array, forming four arrays, respectively denoted as az OR′ , S OR′ ;

[0032] Step S222: Determine the lines connecting the point to the boundary point of the primary emission area in the emission direction, and determine the lines num The number of intersections with the initial area N num , where num is the number of lines from the point to the boundary points of the primary emission area in the emission direction, and the value of num is the same as the number of boundary points of the primary emission area;

[0033] Step S223: If N num If is an even number, the point is considered to be inside the initial region, otherwise it is outside the initial region;

[0034] Step S23: obtaining a subset of points in the area formed by the intersection, wherein all points in the subset are within the initial area, and the area defined by the subset is used as the flight zone launch area; determining the boundary points of the flight zone launch area and storing the boundary points of the flight zone launch area in a fourth array.

[0035] Preferably, the method comprises step S3, determining the wreckage landing area of ​​the aircraft based on the destination point, the distance of the aircraft wreckage, the maximum range of the aircraft, and the aircraft launch area.

[0036] In a second aspect, a system for calculating an aircraft launch area under debris impact point constraints is disclosed, the system comprising:

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

[0038] The initial area is the area where the aircraft's starting point is located; the destination point is the destination point where the aircraft flies to; the aircraft wreckage distance is the distance from the aircraft's starting point to the ground where the aircraft wreckage lands;

[0039] The calculation module is configured to determine the aircraft launch area based on the initial area, the primary launch area, and the maximum range of the aircraft. The aircraft launch area is the take-off area of ​​the aircraft that meets the ground landing point constraint conditions of the aircraft wreckage.

[0040] In a third aspect, 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, and the instructions are executed by the at least one processor to enable the at least one processor to perform the method described above.

[0044] In a fourth aspect, a non-transitory computer-readable storage medium storing computer instructions is disclosed, wherein the computer instructions are used to cause the computer to execute the method as described above.

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

[0046] The present invention is a method for quickly calculating the launch area of ​​the aircraft that meets the range and wreckage drop point and the area where the aircraft wreckage is dropped through the initial area information, the destination location information, the aircraft range, and the wreckage drop point information. The present invention plays a supporting and verifying role in the advanced deployment of the traction aircraft, the integration of initial resources, and the optimization of the launch area, effectively promoting the resource optimization development of the selected aircraft deployment area and improving the initial situation analysis capability. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 The figure is a flow chart of the method for calculating the launch area of ​​an aircraft under the constraints of the debris landing point;

[0048] Figure 2 A schematic diagram of the specific process of calculating the launch area of ​​an aircraft under the constraints of the debris landing point;

[0049] Figure 3 A flow chart showing the number of intersections for the method of calculating the launch area of ​​an aircraft under the constraints of the debris landing point;

[0050] Figure 4 A schematic diagram of determining the values ​​of the overlap area array for the method of calculating the launch area of ​​an aircraft under the constraints of the debris landing point;

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

[0052] Figure 6 A schematic diagram of an initial emission area according to an embodiment of the present invention;

[0053] Figure 7 is the intermediate calculation result of the embodiment of the present invention;

[0054] Figure 8 This is a schematic diagram of the structure of the aircraft launch area calculation system under the constraints of the debris landing point. DETAILED DESCRIPTION

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

[0056] like Figure 1-Figure 2 As shown, the present invention provides a method for calculating the launch area of ​​an aircraft under the constraint of a debris landing point, the method comprising the following steps:

[0057] Step S1: determining a primary launch area based on an initial area, a destination point, a maximum range of the aircraft, and a distance from aircraft wreckage, wherein the primary launch area is an estimated launch area of ​​the aircraft;

[0058] The initial area is the area where the aircraft's starting point is located; the destination point is the destination point where the aircraft flies to; the aircraft wreckage distance is the distance from the aircraft's starting point to the ground where the aircraft wreckage lands;

[0059] Step S2: determining an aircraft launch area based on the initial area, the primary launch area, and the maximum range of the aircraft, wherein the aircraft launch area is an area for taking off the aircraft that meets the aircraft wreckage ground landing point constraint.

[0060] The step S1: determining the primary launch area based on the initial area, the destination point, the maximum range of the aircraft, and the distance of the aircraft wreckage, includes:

[0061] Step S11: For each boundary point of the initial area, the following operations are performed:

[0062] Determine the azimuth between the boundary point of the initial area and the destination point, the azimuth is calculated as follows:

[0063]

[0064] Wherein, (L1, B1) are the coordinates of the boundary point of the initial area, L1 is the longitude coordinate of the boundary point of the initial area, and B1 is the latitude coordinate of the boundary point of the initial area; (L2, B2) are the coordinates of the destination point, L2 is the longitude coordinate of the destination point, and B2 is the latitude coordinate of the destination point, π is pi, and the fmod function is a function for finding the remainder of dividing two floating point numbers;

[0065] Step S12: For each boundary point of the initial area, the following operations are performed:

[0066] The boundary point of the initial area is translated along its corresponding azimuth by a distance of the aircraft debris, and the coordinates of the translated point are determined (L′1, B′1), where L′1 is the longitude coordinate of the point after the boundary point is translated, and B′1 is the latitude coordinate of the point after the boundary point is translated;

[0067]

[0068] Among them, r e is the average radius of the Earth; tp, s λ 、c λ is the intermediate data, dis is the distance of the aircraft wreckage;

[0069] Step S13: The area enclosed by the points after all the boundary points of the initial area are translated as the emission area to be screened; wherein the points after all the boundary points of the initial area are translated 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: For each array element in the first array, perform the following operations:

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

[0072]

[0073] Wherein, a is the intermediate data, rng is the angle between the first connecting line and the second connecting line, the first connecting line is the connecting line between the boundary point of the initial area corresponding to the array element and the destination point, and the second connecting line is the connecting line between the boundary point to be screened corresponding to the array element and the destination point; tan -1 is the inverse tangent;

[0074] If S R ≤S max , the array element is stored in the second array, and the array element is processed; otherwise, the array element is processed; S max Indicates the maximum range of the aircraft;

[0075] Step S15: the area enclosed by the boundary points to be screened corresponding to all array elements of the second array is used as the primary emission area R′;

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

[0077]

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

[0079] In the present invention, the primary launch area can satisfy the range constraint condition, and each array element in the second array includes longitude and latitude.

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

[0081] The step S2, determining the aircraft launch area based on the initial area, the primary launch area, and the maximum range of the aircraft, includes:

[0082] Step S21: obtaining the intersection of the initial area and the primary emission area, and storing the boundary points of the area formed by the intersection into a third array, wherein the third array is denoted as R″, and each array element in R″ includes longitude and latitude;

[0083] Step S22: For each point inside the area formed by the intersection, the following operations are performed:

[0084] Step S221: Determine the azimuth and distance from the point to the boundary point corresponding to each array element of the first array, denoted as az OG , S OG , and the azimuth and distance from this point to the boundary point corresponding to each array element of the second array, forming four arrays, respectively denoted as az OR′ , S OR′ ;

[0085] Step S222: Determine the lines connecting the point to the boundary point of the primary emission area in the emission direction, and determine the lines num The number of intersections with the initial area N num , where num is the number of lines from the point to the boundary points of the primary emission area in the emission direction, and the value of num is the same as the number of boundary points of the primary emission area;

[0086] Step S223: If N num If is an even number, the point is considered to be inside the initial region, otherwise it is outside the initial region;

[0087] Step S23: obtaining a subset of points in the area formed by the intersection, wherein all points in the subset are within the initial area, and the area defined by the subset is used as the flight zone launch area; determining the boundary points of the flight zone launch area and storing the boundary points of the flight zone launch area in a fourth array.

[0088] Further, the step S222: determining the lines from the point to the boundary point of the primary emission area in the emission direction, determining each line line num The number of intersections with the initial area N num ,include:

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

[0090] In the present invention, the step S3 specifically includes: calculating the intersection of two arrays R″=G∩R′, wherein: R′ is the primary launch area boundary point array that meets the range constraint condition, including longitude and latitude information; G is the initial area boundary point array, including longitude and latitude information; R″ is the final overlap area boundary point data, including longitude and latitude;

[0091] S3.1 arbitrarily select a point O in the overlapping area between the initial area and the initial launch area obtained in step S2; calculate the azimuth and distance from point O to each point on the boundary of the initial area and the primary launch area according to equations 1.1 and 1.3, respectively, and record them as az OG , S OG 、az OR′ , S OR′ .

[0092] S3.2 calculates the number of intersections N between the line connecting the point O selected in S3.1 and the boundary line point of the primary emission area obtained in step S2 and the initial area.

[0093] Where N is the number of intersections, and the condition N+1, az OG is the azimuth array from the point O selected in S3.1 to each point on the initial region boundary, S OG is the distance array from the point O selected in S3.1 to each point on the initial region boundary, j is the position where the array value is taken; az OP′ is the azimuth array from the center point O to each point on the boundary of the primary emission area, S OP′ It is the distance array from the center point O to each point on the boundary of the primary emission area, and k is the position where the array takes values.

[0094] S3.3 determines the result N combination array according to S3.2. If N is an even number, the current calculated boundary point is determined to be inside the initial region, otherwise it is outside the initial region;

[0095] Among them, R″ is the overlap area boundary array, R′ is the primary launch area boundary point array obtained by S2 that meets the range constraint conditions, and G is the initial area boundary point array.

[0096] The overlapped area boundary array must also satisfy the requirement that the distance from each boundary point to the destination F is within the maximum range of the aircraft; S R″ ≤S max , where S R″ is the distance from the boundary point of the overlapped area to the destination F, S max The maximum range of the aircraft.

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

[0098] In step S3, the wreckage area of ​​the aircraft is expressed as:

[0099]

[0100] Among them, P is the fifth array composed of the boundary points of the aircraft wreckage landing area, and each array element contains longitude and latitude; R″ is the fourth array corresponding to the aircraft launch area, and each array element of the fourth array contains longitude and latitude; az2 is the azimuth from each point of R″ boundary to the destination point F, S c is the distance to the aircraft wreckage.

[0101] like Figure 3-Figure 7 As shown, the present invention provides a method for calculating the launch area of ​​an aircraft under the constraint of a debris landing point.

[0102] This embodiment has two groups of examples. In Example 1, the location information of the initial area 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 (the distance between the wreckage drop point and the take-off point S c =300000m, maximum range S max = 3000000m). In Example 2, the location information of the initial area G and the destination F (138.354 degrees east longitude, 3.331 degrees north latitude) is as follows Figure 8 As shown, the aircraft data (the distance between the wreckage drop point and the take-off point S c =300000m, maximum range S max =3000000m).

[0103] The simulation software in this embodiment is Visual Studio 2015 and Matlab 2019, and the simulation computer configuration is "Intel Core i9-13900KF 3.00GHz 32-core CPU + 128GB memory". Figure 5 As shown in the figure, the number of arrays is 9051, and the calculation result is Figure 7 As shown, the calculation time is 0.064s. Example 2 Initial area ( Figure 8 The number of arrays is 2394, and the calculation results are obtained. The calculation time is 0.015s.

[0104] This example is based on a method for quickly calculating the launch area of ​​an aircraft under the constraints of debris landing points, providing 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 area of ​​an aircraft under the constraints of debris landing points, the system comprising:

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

[0107] The initial area is the area where the aircraft's starting point is located; the destination point is the destination point where the aircraft flies to; the aircraft wreckage distance is the distance from the aircraft's starting point to the ground where the aircraft wreckage lands;

[0108] The calculation module is configured to determine the aircraft launch area based on the initial area, the primary launch area, and the maximum range of the aircraft. The aircraft launch area is the take-off area of ​​the aircraft that meets the ground landing point constraint conditions of the aircraft wreckage.

[0109] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the above embodiments, it should be understood by those skilled in the art that the technical solutions described in the above embodiments can still be modified, or some or all of the technical features therein can be replaced by equivalents, and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for calculating the launch area of ​​an aircraft under the constraint of debris impact point, characterized in that: The method comprises the following steps: Step S1: determining a primary launch area based on an initial area, a destination point, a maximum range of the aircraft, and a distance from aircraft wreckage, wherein the primary launch area is an estimated launch area of ​​the aircraft; The initial area is the area where the aircraft's starting point is located; the destination point is the destination point where the aircraft flies to; the aircraft wreckage distance is the distance from the aircraft's starting point to the ground where the aircraft wreckage lands; Step S2: determining an aircraft launch area based on the initial area, the primary launch area, and the maximum range of the aircraft, wherein the aircraft launch area is an area for taking off the aircraft that meets the aircraft wreckage ground landing point constraint.

2. The method according to claim 1, characterized in that The step S1: determining the primary launch area based on the initial area, the destination point, the maximum range of the aircraft, and the distance of the aircraft wreckage, includes: Step S11: For each boundary point of the initial area, the following operations are performed: Determine the azimuth angle between the boundary point of the initial area and the destination point, the calculation formula of the azimuth angle az is: Wherein, (L1, B1) are the coordinates of the boundary point of the initial area, L1 is the longitude coordinate of the boundary point of the initial area, and B1 is the latitude coordinate of the boundary point of the initial area; (L2, B2) are the coordinates of the destination point, L2 is the longitude coordinate of the destination point, and B2 is the latitude coordinate of the destination point, π is pi, and the fmod function is a function for finding the remainder of dividing two floating point numbers; Step S12: For each boundary point of the initial area, the following operations are performed: The boundary point of the initial area is translated along its corresponding azimuth by a distance of the aircraft debris, and the coordinates of the translated point are determined (L′1, B′1), where L′1 is the longitude coordinate of the point after the boundary point is translated, and B′1 is the latitude coordinate of the point after the boundary point is translated; Among them, r e is the average radius of the Earth; tp, s λ 、c λ is the intermediate data, dis is the distance of the aircraft wreckage; Step S13: The area enclosed by the points after all the boundary points of the initial area are translated as the emission area to be screened; wherein the points after all the boundary points of the initial area are translated 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: For each array element in the first array, perform the following operations: Determine the distance S between the array element and the destination point R , the calculation formula is: Wherein, a is the intermediate data, rng is the angle between the first connecting line and the second connecting line, the first connecting line is the connecting line between the boundary point of the initial area corresponding to the array element and the destination point, and the second connecting line is the connecting line between the boundary point to be screened corresponding to the array element and the destination point; tan -1 is the inverse tangent; If S R ≤S max , the array element is stored in the second array, and the array element is processed; otherwise, the array element is processed; S max Indicates the maximum range of the aircraft; Step S15: The area enclosed by the boundary points to be screened corresponding to all array elements of the second array is used as the primary emission area R′.

3. The method according to claim 2, characterized in that The primary emission region R′ is expressed as: Where R′ represents the second array corresponding to the primary transmission area, G is the array formed by all boundary points of the initial area; az1 is the azimuth from the destination point to each boundary point corresponding to G, S c is the distance of the aircraft wreckage, represents the translation direction, represents the translation distance; S R represents the distance between each point in the first data R and the destination point, S max Indicates the maximum range of the aircraft.

4. The method according to claim 2, characterized in that The step S2, determining the aircraft launch area based on the initial area, the primary launch area, and the maximum range of the aircraft, includes: Step S21: obtaining the intersection of the initial area and the primary emission area, and storing the boundary points of the area formed by the intersection into a third array, wherein the third array is denoted as R″, and each array element in R″ includes longitude and latitude; Step S22: For each point inside the area formed by the intersection, the following operations are performed: Step S221: Determine the azimuth and distance from the point to the boundary point corresponding to each array element of the first array, denoted as az OG , S OG , and the azimuth and distance from this point to the boundary point corresponding to each array element of the second array, forming four arrays, respectively denoted as az OR′ , S OR′ ; Step S222: Determine the lines connecting the point to the boundary point of the primary emission area in the emission direction, and determine the lines num The number of intersections with the initial area N num , where num is the number of lines from the point to the boundary points of the primary emission area in the emission direction, and the value of num is the same as the number of boundary points of the primary emission area; Step S223: If N num If is an even number, the point is considered to be inside the initial region, otherwise it is outside the initial region; Step S23: obtaining a subset of points in the area formed by the intersection, wherein all points in the subset are within the initial area, and the area defined by the subset is used as the flight zone launch area; determining the boundary points of the flight zone launch area and storing the boundary points of the flight zone launch area in a fourth array.

5. The method according to claim 4, characterized in that The method comprises step S3, determining the aircraft wreckage landing area based on the destination point, the distance of the aircraft wreckage, the maximum range of the aircraft, and the aircraft launch area.

6. A system for calculating the launch area of ​​an aircraft under the constraints of debris landing points, characterized in that: The system comprises: Initial module: configured to determine a primary launch area based on an initial area, a destination point, a maximum range of the aircraft, and a distance from aircraft wreckage, wherein the primary launch area is an estimated launch area of ​​the aircraft; The initial area is the area where the aircraft's starting point is located; the destination point is the destination point where the aircraft flies to; the aircraft wreckage distance is the distance from the aircraft's starting point to the ground where the aircraft wreckage lands; The calculation module is configured to determine the aircraft launch area based on the initial area, the primary launch area, and the maximum range of the aircraft. The aircraft launch area is the take-off area of ​​the aircraft that meets the ground landing point constraint conditions of the aircraft wreckage.

7. An electronic 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, and the instructions are executed by the at least one processor to enable the at least one processor to perform the method according to any one of claims 1 to 5.

8. A non-transitory computer-readable storage medium storing computer instructions, wherein the computer instructions are used to cause the computer to execute the method according to any one of claims 1 to 5.

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