Flight trajectory optimization and translation method and system

Abstract

The application discloses a flight trajectory optimization and translation method and system, acquires flight timing data in an approach phase of an airplane; from the flight timing data, acquires optimized longitude and latitude values of a kth point; according to the optimized longitude and latitude values of the kth point, a true heading of the airplane at the kth point, and a flight distance between the kth point and a k+1th point, calculates optimized longitude and latitude values of the k+1th point; the kth point and the k+1th point both refer to points in the flight timing data; the optimized longitude and latitude coordinate values of subsequent points of a starting point are sequentially calculated until the airplane lands and enters a parking stand; according to the optimized longitude and latitude coordinate values of each point, the optimized longitude and latitude coordinate values are sequentially connected to generate an optimized flight trajectory; and according to the optimized flight trajectory, the flight trajectory is overall translated with the landing point position as a reference. The flight trajectory is more accurate and smooth, and the flight trajectory is more smoothly displayed in combination with geographic information.

Description

Technical Field

[0001] The present invention relates to the fields of civil aviation and big data technology, and in particular to a method and system for optimizing and shifting flight trajectories. Background Art

[0002] The statements in this section merely mention background art related to the present invention and do not necessarily constitute prior art.

[0003] Flight safety is particularly important to the development of airlines. Formulating corresponding corrective plans for identified safety risks based on flight data is the basis for ensuring the company's continued safety.

[0004] The Quick Access Recorder (QAR) is an airborne flight data recorder that provides fast and convenient access to raw flight data. It is often used by airlines to improve flight safety and operational efficiency and is part of their flight quality monitoring program. The approach and landing phase of an aircraft is characterized by wide speed variations, numerous unexpected situations (such as near-ground air turbulence), complex operating procedures, and difficulty maintaining a stable approach and landing maneuvers. This phase places the highest demands on pilot control skills. When a pilot encounters an unstable approach, utilizing QAR flight data and 3D technology to restore the actual flight scene can be highly valuable, helping pilots intuitively analyze the problem and identify areas for improvement. However, due to the influence of external conditions such as altitude, wind speed, and temperature, the accuracy of QAR data is affected to a certain extent, resulting in uneven flight paths with jitters and jagged shapes.

[0005] The existing flight trajectory optimization methods are: existing methods include vector optimization based on optimization method, or latitude and longitude data completion optimization method.

[0006] The existing flight trajectory optimization method has the following technical flaws: First, the flight trajectory optimization smoothness is not high enough. After combining geographic information and zooming in to a certain map level, the aircraft flight trajectory display is not smooth enough. Second, although the optimized flight trajectory is relatively smooth, some aircraft enter the runway with the flight trajectory at the edge of the runway, which is not realistic. The flight trajectory needs to be shifted to a reasonable position in the middle of the runway.

[0007] Therefore, it is necessary to find a flight trajectory optimization method to achieve smoothing and translation of the trajectory, and use 3D technology in combination with geographic information to display the flight trajectory more smoothly, providing intuitive help for flight teaching, event investigation, etc. Summary of the Invention

[0008] In order to address the shortcomings of the existing technology, the present invention provides a flight trajectory optimization and translation method and system; based on the time-series format data decoded by the aircraft, a flight trajectory optimization and translation method is proposed according to the longitude, latitude, heading, ground speed, airport magnetic declination, and runway magnetic azimuth, which solves the problem of uneven changes in longitude and latitude, making the flight trajectory more accurate and smooth. In combination with geographic information, 3D technology is used to more smoothly display the flight trajectory, providing intuitive assistance for flight teaching, event investigation, etc., helping pilots to intuitively analyze the problems that have occurred and the direction of improvement.

[0009] In a first aspect, the present invention provides a method for optimizing and translating flight trajectories;

[0010] Flight trajectory optimization and translation methods, including:

[0011] Obtaining flight timing data during the aircraft's approach phase; wherein the flight timing data includes: longitude, latitude, heading, and airport magnetic declination;

[0012] Selecting the kth point as the starting point from the flight time series data; obtaining the optimized longitude and latitude values ​​of the kth point; k is a positive integer greater than or equal to 2;

[0013] Calculate the optimized longitude and latitude of the k+1th point based on the optimized longitude and latitude of the kth point, the true heading of the aircraft at the kth point, and the flight distance between the kth point and the k+1th point; where the kth point and the k+1th point are both points in the flight time series data;

[0014] Add 1 to k and calculate the optimized longitude and latitude coordinates of subsequent points of the starting point in sequence until the flight lands and enters the parking position;

[0015] According to the optimized longitude and latitude coordinate values ​​of each point, the optimized longitude and latitude coordinate values ​​are connected in sequence to generate the optimized flight trajectory;

[0016] According to the optimized flight trajectory, the overall flight trajectory is shifted with the touchdown point as a reference.

[0017] In a second aspect, the present invention provides an airliner flight trajectory optimization and translation system;

[0018] Flight trajectory optimization and translation system, including:

[0019] An acquisition module is configured to: acquire flight time series data of an aircraft during its approach phase; wherein the flight time series data includes: longitude, latitude, heading, and airport magnetic declination;

[0020] A preliminary optimization module is configured to: select the kth point as a starting point from the flight time series data; obtain an optimized longitude value and an optimized latitude value of the kth point; k is a positive integer, and k is greater than or equal to 2;

[0021] a calculation module configured to calculate the optimized longitude and latitude of the k+1th point based on the optimized longitude and latitude of the kth point, the true heading of the aircraft at the kth point, and the flight distance between the kth point and the k+1th point; wherein the kth point and the k+1th point are both points in the flight time series data;

[0022] A loop module is configured to: add 1 to k and sequentially calculate the optimized longitude and latitude coordinates of subsequent points of the starting point until the flight lands and enters the parking position;

[0023] an output module configured to: sequentially connect the optimized longitude and latitude coordinate values ​​of each point according to the optimized longitude and latitude coordinate values ​​to generate an optimized flight trajectory;

[0024] According to the optimized flight trajectory, the overall flight trajectory is shifted with the touchdown point as a reference.

[0025] In a third aspect, the present invention further provides an electronic device, comprising:

[0026] a memory for non-transitory storage of computer-readable instructions; and

[0027] a processor for executing said computer-readable instructions,

[0028] When the computer-readable instructions are executed by the processor, the method described in the first aspect is executed.

[0029] In a fourth aspect, the present invention further provides a storage medium that non-temporarily stores computer-readable instructions, wherein when the non-temporary computer-readable instructions are executed by a computer, the instructions of the method described in the first aspect are executed.

[0030] In a fifth aspect, the present invention further provides a computer program product, comprising a computer program, wherein the computer program is used to implement the method described in the first aspect when running on one or more processors.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] This solution is not only suitable for the aircraft approach phase, but also for other flight phases. It achieves smooth flight trajectory, provides a foundation for the restoration of 3D flight scenes, makes the flight trajectory more vivid, and provides strong support for flight teaching and flight incident investigation. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The accompanying drawings, which constitute a part of the present invention, are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0034] Figure 1 This is a flow chart of the flight trajectory optimization method according to the first embodiment of the present application;

[0035] Figure 2 This is a flow chart of the flight trajectory translation method of Example 1 of the present application;

[0036] Figure 3 This is a schematic diagram of the runway sideline of Example 1 of this application;

[0037] Figure 4 This is a schematic diagram of the runway sideline of Example 1 of this application;

[0038] Figure 5 This is the flight trajectory optimization result diagram of Example 1 of this application;

[0039] Figure 6 This is the flight trajectory optimization result diagram of Example 1 of this application;

[0040] Figure 7 This is the result diagram after flight trajectory optimization of Example 1 of this application. DETAILED DESCRIPTION

[0041] It should be noted that the following detailed descriptions are exemplary and intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which the present invention belongs.

[0042] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit exemplary embodiments according to the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0043] In the absence of conflict, the embodiments of the present invention and the features thereof may be combined with each other.

[0044] All data in this embodiment is obtained in compliance with laws and regulations and based on the consent of the user, and is used legally.

[0045] Example 1

[0046] This embodiment provides a flight trajectory optimization and translation method;

[0047] like Figure 1 As shown, the flight trajectory optimization and translation method includes:

[0048] S101: Acquire flight time series data of an aircraft during its approach phase; wherein the flight time series data includes: longitude, latitude, heading, and airport magnetic declination;

[0049] S102: Select the kth point as the starting point from the flight time series data; obtain the optimized longitude and latitude value of the kth point; k is a positive integer, and k is greater than or equal to 2;

[0050] S103: Calculate the optimized longitude and latitude of the k+1th point based on the optimized longitude and latitude of the kth point, the true heading of the aircraft at the kth point, and the flight distance between the kth point and the k+1th point; wherein the kth point and the k+1th point are both points in the flight time series data;

[0051] S104: Increment k by 1, repeat S102 to S103, and sequentially calculate the optimized longitude and latitude coordinates of subsequent points of the starting point until the flight lands and enters the parking position;

[0052] S105: According to the optimized latitude and longitude coordinate values ​​of each point, the optimized latitude and longitude coordinate values ​​are connected in sequence to generate an optimized flight trajectory; according to the optimized flight trajectory, the overall flight trajectory is translated with the touchdown point position as a reference.

[0053] Furthermore, the optimized longitude value and the optimized latitude value of the k-th point are obtained by:

[0054] Add the original longitude value of the k-th point and the longitude values ​​of the k-1 points above and below it, a total of 2*k-1 values, and take the average to get the optimized longitude value of the k-th point;

[0055] The original latitude value of the k-th point and the latitude values ​​of the k-1 points to its left and right, a total of 2*k-1 values, are added and averaged to obtain the optimized latitude value of the k-th point.

[0056] For example, the kth point is selected, for example, k is 7, and the average longitude (ave_Lon) and average latitude (ave_Lat) of this point and the six points above and below it are calculated.

[0057]

[0058]

[0059] Furthermore, the process of obtaining the true heading of the aircraft at the k-th point includes:

[0060] The true heading of the aircraft at the kth point is equal to the sum of the magnetic heading of the aircraft at the kth point and the magnetic declination angle of the airport;

[0061] If the sum is greater than 360, then 360 is subtracted from the sum and the resulting value is used as the true heading of the aircraft at the kth point.

[0062] If the sum is less than 0, add 360 to the sum and use the resulting value as the true heading of the aircraft at the kth point.

[0063] For example, this step loads the original time series data and intercepts the flight data for flights below 2000 feet relative pressure altitude (total length is len). Based on the magnetic declination (MV) of each airport and the aircraft magnetic heading (MH), the true heading (TH) of the aircraft is calculated every second: TH = MH + MV.

[0064] Furthermore, the flight distance between the kth point and the k+1th point specifically includes:

[0065] Calculate the flight distance between the kth point and the k+1th point based on the current ground speed.

[0066] For example, the distance dis between the kth point and the k+1th point is calculated based on the ground speed GS in the time series data:

[0067] dis=GS*1852 / 3600.

[0068] Furthermore, the step S103 of calculating the optimized longitude and latitude of the k+1th point based on the optimized longitude and latitude of the kth point, the true heading of the aircraft at the kth point, and the flight distance between the kth point and the k+1th point may include:

[0069] Lat k+1 =lat2*180 / π;

[0070]

[0071]

[0072]

[0073]

[0074]

[0075]

[0076] Lon k+1 =Lon k +L*180 / π;

[0077]

[0078]

[0079] cos2SigalM=cos(2*sigma1+sigma);

[0080] sigma1=atan2((1-f)*tan(Lat k *π / 180),cos(TH*π / 180));

[0081] sigma = dis / (w_rad*A);

[0082] C=f / 16*(1-sin(TH*π / 180) 2 )*(4+f*(4-3*(1-sin(TH*π / 180) 2 )));

[0083] Among them, l_rad represents the major radius of the earth; w_rad represents the minor radius of the earth; f represents the flattening of the earth; Lon k Indicates the longitude of point k; Lat k Indicates the latitude of the kth point; Lon k+1 Indicates the longitude of the k+1th point; Lat k+1 represents the latitude of the k+1th point; dis represents the distance between two points; TH represents the true heading, and the other parameters are intermediate variables.

[0084] Furthermore, the overall translation of the flight trajectory is achieved based on the optimized flight trajectory and with the touchdown point position as a reference, and this can be achieved by either of two methods, which are in parallel relationship.

[0085] Method 1: Based on the optimized flight trajectory, the overall flight trajectory is shifted with the touchdown point as a reference, specifically including:

[0086] If the distance between the touchdown point and the runway midpoint in the optimized flight trajectory exceeds a set threshold (e.g. 5 meters), the airport magnetic declination MV is adjusted:

[0087] MV'=n*MV;

[0088] Where MV' is the adjusted magnetic declination of the airport; n is a constant that achieves the overall translation of the flight trajectory until the distance between the touchdown point and the runway midpoint is within the set threshold range.

[0089] The present invention realizes the translation of the landing flight track according to whether the touchdown point is in the middle of the runway, so that the landing track is in the middle of the runway.

[0090] Method 2: If Figure 2 As shown, the optimized flight trajectory is used to achieve the overall translation of the flight trajectory with the touchdown point as a reference, specifically including:

[0091] S1061: Calculate the distance s_d between points s1 and s2 based on the optimized longitude and latitude of the touchdown point s1 and the longitude and latitude of the landing runway entrance midpoint s2;

[0092] S1062: Based on the runway magnetic azimuth, point s1 is moved a distance s_d along the runway centerline toward the touchdown point to generate the latitude and longitude coordinates of point s3.

[0093] S1063: Calculate the distance h1 from the ground point s1 to the point s3;

[0094] S1064: If h1 is within the set threshold (e.g., 5 meters), the touchdown point is considered reasonable and there is no need to adjust the overall flight trajectory;

[0095] S1065: If h1 is not within the set threshold, calculate the distance h from point s1 to edge s2s3, and move point s1 in the negative direction of the X-axis by a distance h to obtain point s4_1; where the origin is the midpoint of the landing runway entrance, the runway centerline is the Y-axis, and the line perpendicular to the runway centerline is the X-axis. The positive direction of the Y-axis is the direction the aircraft is moving when landing, and the positive direction of the X-axis is the direction the right wing of the aircraft is pointing when landing. The negative direction of the X-axis is the direction the left wing of the aircraft is pointing when landing.

[0096] S1066: Compare the lengths s_d and s_d1. If s_d is greater than s_d1, the moving direction is correct. s_d1 is the distance from s2, the midpoint of the landing runway entrance, to s4_1. If s_d is less than or equal to s_d1, the moving direction is incorrect. If the moving direction is incorrect, the opposite direction of the current moving direction is selected as the moving direction.

[0097] S1067: Based on the correct moving distance and translation angle (TA), the optimized longitude and latitude coordinate points are translated as a whole by the same distance to generate new longitude and latitude coordinate points.

[0098] After determining the correct translation distance h and translation angle TA, the longitude and latitude values ​​after translation are calculated based on the current longitude and latitude, translation distance h, translation angle, and TA. 3D flight scene reconstruction is achieved based on longitude, latitude, altitude, and heading combined with geographic information.

[0099] like Figure 3 and Figure 4 As shown, this step loads the smoothed time series data (total length is len). Based on the magnetic azimuth (MA) of the runway, the longitude and latitude of the touchdown point, and the longitude and latitude of the runway threshold, the distance h between the touchdown point and the middle of the runway is calculated. Based on this distance h, it is determined whether the flight trajectory requires translation. For flight trajectories that require translation, the optimized longitude and latitude values ​​are calculated based on the magnetic azimuth of the runway, the distance h, and the current longitude and latitude to achieve the translation.

[0100] (11) The translation angle (TA) is calculated based on the magnetic azimuth of the landing runway. Translation can be in two directions, left or right. If the calculated translation angle (TA) is greater than 360, the translation angle (TA) is subtracted by 360. If the translation angle (TA) is less than 0, the translation angle (TA) is increased by 360.

[0101] TA=MA±90

[0102] (12) Calculate the optimized grounding point s1 (longitude: Lon s1 , Latitude: Lat s1 ) and the landing runway threshold midpoint s2 (longitude: Lon s2 , Latitude: Lat s2 )’s distance s_d;

[0103] trad=Lat s1 *π / 180-Lat s2 *π / 180

[0104] nrad=Lon s1 *π / 180-Lon s2 *π / 180

[0105]

[0106] (13) Move the access point s2 along the runway centerline by a distance s_d to point s3. Calculate the longitude and latitude of point s3 based on the runway magnetic azimuth (MA), distance s_d, and the longitude and latitude of point s1 (Longitude: Lon s3 , Latitude: Lat s3 ), other variables are intermediate variables.

[0107]

[0108]

[0109]

[0110]

[0111]

[0112]

[0113] Lat s3 =lat2*180 / π

[0114]

[0115] C=f / 16*(1-sin(MA*π / 180) 2 )*(4+f*(4-3*(1-sin(MA*π / 180) 2 )))

[0116] sigma1=atan2((1-f)*tan(Lat s2 *π / 180),cos(MA*π / 180))

[0117] sigma=s_d / (w_rad*A)

[0118] cos2SigalM=cos(2*sigma1+sigma)

[0119]

[0120] Lon s3 =Lon s2 +L*180 / π

[0121] (14) Calculate the distance h1 from point s1 to point s3. If h1 is greater than 5 meters, calculate the distance h from point s1 to edge s2s3. s1 *π / 180-Lat s3 *π / 180

[0122] nrad=Lon s1 *π / 180-Lon s3 *π / 180

[0123]

[0124] (15) Calculate the distance h from point s1 to edge s2s3 based on the perimeter per.

[0125] per=2*s_d+h1

[0126]

[0127] (16) Move point s1 by a length h in the negative direction of the X-axis to point s4_1. Calculate the longitude and latitude of point s4_1 based on the translation angle (TA), distance h, and the longitude and latitude of point s1 (Longitude: Lon s4_1 , Latitude: Lat s4_1 ), the formula is the same as step (13), except that the runway magnetic azimuth (MA) is replaced by the translation angle (TA) and the distance s_d is replaced by h.

[0128] (17) Calculate the distance s_d1 between point s2 and point s4_1. If s_d is greater than s_d1, the moving direction is correct. Otherwise, the translation angle (TA) is reversed.

[0129] trad=Lat s2 *π / 180-Lat s4_1 *π / 180

[0130] nrad=Lon s2 *π / 180-Lon s4_1 *π / 180

[0131]

[0132] (18) Based on the determined translation angle (TA) and translation distance h, all longitude and latitude points are calculated in turn according to the logic of step (13) to obtain their corresponding longitude and latitude values.

[0133] (19) The final flight time series data, including longitude, latitude, heading, altitude, and ground mark, are input into the three-dimensional simulation system to realize 3D flight scene reproduction.

[0134] The flight's time-series longitude and latitude data is processed to generate optimized longitude and latitude. Based on these optimized longitude and latitude, altitude, and heading, combined with geographic information, 3D technology is used to recreate the flight scene. This method translates the flight trajectory based on whether the touchdown point is in the middle of the runway, aligning the landing track with the center of the runway. The resulting flight time-series data, including longitude, latitude, heading, altitude, and touchdown marker, is input into a three-dimensional simulation system to achieve 3D flight scene reconstruction.

[0135] Figure 5 The right line is the aircraft's flight trajectory drawn from real data, and the left line is the optimized aircraft's flight trajectory. As you can see, the left line is smoother.

[0136] Figure 6 、 Figure 7This is a diagram of an aircraft's flight path on the runway. The curved line represents the aircraft's flight path based on real data, while the non-curved line represents the optimized flight path. As you can see, the non-curved line is smoother.

[0137] Example 2

[0138] This embodiment provides a flight trajectory optimization and translation system;

[0139] Flight trajectory optimization and translation system, including:

[0140] An acquisition module is configured to: acquire flight time series data of an aircraft during its approach phase; wherein the flight time series data includes: longitude, latitude, heading, and airport magnetic declination;

[0141] A preliminary optimization module is configured to: select the kth point as a starting point from the flight time series data; obtain an optimized longitude value and an optimized latitude value of the kth point; k is a positive integer, and k is greater than or equal to 2;

[0142] a calculation module configured to calculate the optimized longitude and latitude of the k+1th point based on the optimized longitude and latitude of the kth point, the true heading of the aircraft at the kth point, and the flight distance between the kth point and the k+1th point; wherein the kth point and the k+1th point are both points in the flight time series data;

[0143] A loop module is configured to: add 1 to k and sequentially calculate the optimized longitude and latitude coordinates of subsequent points of the starting point until the flight lands and enters the parking position;

[0144] The output module is configured to: connect the optimized longitude and latitude coordinate values ​​of each point in sequence to generate an optimized flight trajectory; and realize the overall translation of the flight trajectory based on the optimized flight trajectory and with the touchdown point position as a reference.

[0145] It should be noted that the above modules correspond to the steps in Example 1, and the examples and application scenarios implemented by the above modules and the corresponding steps are the same, but are not limited to the contents disclosed in the above Example 1. It should be noted that the above modules, as part of the system, can be executed in a computer system such as a set of computer-executable instructions.

[0146] The description of each embodiment in the above embodiments has different emphases. For parts not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0147] The proposed system can be implemented in other ways. For example, the system embodiment described above is merely illustrative. For example, the above module division is only a logical function division. In actual implementation, other division methods may be used. For example, multiple modules can be combined or integrated into another system, or some features can be ignored or not implemented.

[0148] Example 3

[0149] This embodiment also provides an electronic device, comprising: one or more processors, one or more memories, and one or more computer programs; wherein the processor is connected to the memory, and the one or more computer programs are stored in the memory. When the electronic device is running, the processor executes the one or more computer programs stored in the memory, so that the electronic device executes the method described in the above embodiment one.

[0150] It should be understood that in this embodiment, the processor may be a central processing unit (CPU), or may be other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), off-the-shelf field-programmable gate arrays (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or any conventional processor, etc.

[0151] The memory may include a read-only memory and a random access memory, and provides instructions and data to the processor. A portion of the memory may also include a non-volatile random access memory. For example, the memory may also store information about the device type.

[0152] During implementation, each step of the above method may be completed by an integrated logic circuit of hardware in a processor or by instructions in the form of software.

[0153] The method in Example 1 can be directly implemented as being executed by a hardware processor, or by a combination of hardware and software modules within the processor. The software module can be located in a storage medium well-established in the art, such as random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, or registers. The storage medium is located in the memory, and the processor reads the information in the memory and, in conjunction with its hardware, completes the steps of the above method. To avoid repetition, a detailed description is not given here.

[0154] Those skilled in the art will appreciate that the units and algorithm steps of the various examples described in conjunction with this embodiment can be implemented using electronic hardware or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professionals and technicians can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of the present invention.

[0155] Example 4

[0156] This embodiment further provides a computer-readable storage medium for storing computer instructions. When the computer instructions are executed by a processor, the method described in the first embodiment is performed.

[0157] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. Flight trajectory optimization and translation method, which is characterized by: include: Obtaining flight timing data during the aircraft's approach phase; wherein the flight timing data includes: longitude, latitude, heading, and airport magnetic declination; Selecting the kth point as the starting point from the flight time series data; obtaining the optimized longitude and latitude values ​​of the kth point; k is a positive integer greater than or equal to 2; Calculate the optimized longitude and latitude of the k+1th point based on the optimized longitude and latitude of the kth point, the true heading of the aircraft at the kth point, and the flight distance between the kth point and the k+1th point; where the kth point and the k+1th point are both points in the flight time series data; Add 1 to k and calculate the optimized longitude and latitude coordinates of subsequent points of the starting point in sequence until the flight lands and enters the parking position; According to the optimized latitude and longitude coordinate values ​​of each point, the optimized latitude and longitude coordinate values ​​are connected in sequence to generate an optimized flight trajectory; according to the optimized flight trajectory, the overall translation of the flight trajectory is achieved with the touchdown point position as a reference.

2. The flight trajectory optimization and translation method according to claim 1, characterized in that: The optimized longitude value and the optimized latitude value of the k-th point are obtained by: Add the original longitude value of the k-th point and the longitude values ​​of the k-1 points above and below it, a total of 2*k-1 values, and take the average to get the optimized longitude value of the k-th point; The original latitude value of the k-th point and the latitude values ​​of the k-1 points to its left and right, a total of 2*k-1 values, are added and averaged to obtain the optimized latitude value of the k-th point.

3. The flight trajectory optimization and translation method according to claim 1, characterized in that: The true heading of the aircraft at the kth point is obtained by: The true heading of the aircraft at the kth point is equal to the sum of the magnetic heading of the aircraft at the kth point and the magnetic declination angle of the airport; If the sum is greater than 360, then 360 is subtracted from the sum and the resulting value is used as the true heading of the aircraft at the kth point. If the sum is less than 0, add 360 to the sum and use the resulting value as the true heading of the aircraft at the kth point.

4. The flight trajectory optimization and translation method according to claim 1, wherein: The flight distance between the kth point and the k+1th point specifically includes: Calculate the flight distance between the kth point and the k+1th point based on the current ground speed.

5. The flight trajectory optimization and translation method according to claim 1, wherein: The optimized flight trajectory is used to achieve the overall translation of the flight trajectory with the touchdown point as a reference, specifically including: If the distance between the touchdown point and the midpoint of the runway in the optimized flight trajectory exceeds the set threshold, the airport magnetic declination Make adjustments: ； in, is the adjusted magnetic declination of the airport; n is a constant, which realizes the overall translation of the flight trajectory until the distance between the touchdown point and the middle point of the runway is within the set threshold range.

6. The flight trajectory optimization and translation method according to claim 1, wherein: The optimized flight trajectory is used to achieve the overall translation of the flight trajectory with the touchdown point as a reference, specifically including: (1): Calculate the distance s_d between points s1 and s2 based on the optimized latitude and longitude of the touchdown point s1 and the latitude and longitude of the midpoint of the landing runway entrance s2; (2): According to the magnetic azimuth of the runway, point s1 is moved along the centerline of the runway toward the touchdown point by a distance s_d to generate the longitude and latitude coordinates of point s3; (3): Calculate the distance h1 from the ground point s1 to point s3; (4): If h1 is within the set threshold, the touchdown point is considered reasonable and there is no need to adjust the overall flight trajectory; (5): If h1 is not within the set threshold, calculate the distance h from point s1 to edge s2s3, move point s1 in the negative direction of the X-axis by a length h, and obtain point s4_1; where the midpoint of the entrance of the landing runway is the origin, the centerline of the runway is the Y-axis, and the line perpendicular to the centerline of the runway is the X-axis. The positive direction of the Y-axis is the direction in which the aircraft is moving when landing, and the positive direction of the X-axis is the direction in which the right wing of the aircraft is pointing when landing; the negative direction of the X-axis is the direction in which the left wing of the aircraft is pointing when landing. (6): Compare the lengths s_d and s_d1. If s_d is greater than s_d1, the moving direction is correct. s_d1 refers to the distance from the midpoint of the landing runway entrance, s2, to s4_1. If s_d is less than or equal to s_d1, the moving direction is wrong. If the moving direction is wrong, the opposite direction of the current moving direction is selected as the moving direction. (7): According to the correct moving distance and translation angle TA , translate the optimized longitude and latitude coordinate points by the same distance to generate new longitude and latitude coordinate points; After determining the translation distance h and the correct translation angle TA, calculate the longitude and latitude values ​​after translation based on the current longitude and latitude, translation distance h, translation angle, and TA; and realize 3D flight scene reproduction based on the longitude, latitude, altitude, and heading combined with geographic information.

7. Flight trajectory optimization and translation system, which is characterized by: include: An acquisition module is configured to: acquire flight time series data of an aircraft during its approach phase; wherein the flight time series data includes: longitude, latitude, heading, and airport magnetic declination; A preliminary optimization module is configured to: select the kth point as a starting point from the flight time series data; obtain an optimized longitude value and an optimized latitude value of the kth point; k is a positive integer, and k is greater than or equal to 2; a calculation module configured to calculate the optimized longitude and latitude of the k+1th point based on the optimized longitude and latitude of the kth point, the true heading of the aircraft at the kth point, and the flight distance between the kth point and the k+1th point; wherein the kth point and the k+1th point are both points in the flight time series data; A loop module is configured to: add 1 to k and sequentially calculate the optimized longitude and latitude coordinates of subsequent points of the starting point until the flight lands and enters the parking position; The output module is configured to: connect the optimized longitude and latitude coordinate values ​​of each point in sequence according to the optimized longitude and latitude coordinate values ​​to generate an optimized flight trajectory.

8. An electronic device, comprising: a memory for non-transitory storage of computer-readable instructions; as well as a processor for executing said computer-readable instructions, When the computer-readable instructions are executed by the processor, the method according to any one of claims 1 to 6 is executed.

9. A storage medium, characterized by non-transitory storage of computer-readable instructions, wherein: When the non-transitory computer-readable instructions are executed by a computer, the instructions of the method according to any one of claims 1 to 6 are executed.

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