CN114090564A - Flight trajectory optimization and translation method and system - Google Patents
Flight trajectory optimization and translation method and system Download PDFInfo
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Abstract
The invention discloses a flight trajectory optimization and translation method and a flight trajectory optimization and translation system, which are used for acquiring flight time sequence data of an airplane at an approach stage; obtaining the optimized longitude and latitude value of the kth point from the flight time sequence data; calculating the optimized longitude and latitude value of the k +1 point according to the optimized longitude and latitude value of the k point, the true heading of the airplane at the k point and the flight distance between the k point and the k +1 point; the kth point and the (k + 1) th point are points in flight time sequence data; sequentially calculating longitude and latitude coordinate values of the optimized subsequent points of the starting point until the flight lands in the stand; according to the longitude and latitude coordinate values optimized by each point, sequentially connecting the optimized longitude and latitude coordinate values to generate an optimized flight track; and according to the optimized flight path of the flight, taking the position of the grounding point as a reference to realize the integral translation of the flight path. The flight path is more accurate and smooth, and the flight path is more smoothly displayed by combining with the geographic information.
Description
Technical Field
The invention relates to the technical field of civil aviation and big data, in particular to a flight trajectory optimization and translation method and system.
Background
The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.
Flight safety is particularly important for the development of an airline company, and a corresponding correction scheme is formulated for identified safety risks according to flight data, so that the basis for ensuring the continuous safety of the company is provided.
A Quick Access Recorder (QAR) is an airborne flight data recorder that provides quick and convenient access to raw flight data, is often used by airlines to improve flight safety and operational efficiency, and is part of a flight quality monitoring plan. The change range of the flying speed of the airplane in the approach landing stage is large, the number of emergency situations (near-ground air turbulence and the like) is large, the operation procedure is complex, the stable approach state of the airplane and the landing action are difficult to control, and the method is one of the stages with the highest operating technical requirements for pilots. When the condition that the pilot enters the aircraft unstably, the QAR flight data is utilized, the 3D technology is adopted to restore the actual flight scene, the pilot is helped to analyze the problems and improve the direction intuitively, and the method has high value. However, the accuracy of the QAR data is influenced to a certain extent by the influence of external conditions such as height, wind speed, temperature and the like, and the flight track has the unsmooth problems such as jumping, jaggy and the like.
The existing flight path optimization adopts the following modes: the existing mode is based on a vector optimization mode, or a longitude and latitude data completion optimization mode.
The technical defects of the existing flight path optimization method are as follows: firstly, the excellent smoothness of the flight path in the existing mode is not high enough, and the playing and displaying of the flight path of the airplane are not smooth enough after the map is amplified to a certain map level by combining geographic information. Secondly, although the optimized flight path is relatively smooth, the flight path is at the edge of the runway after some airplanes enter the runway, which is not practical, and the flight path needs to be translated integrally to a reasonable position in the middle of the runway.
Therefore, a flight trajectory optimization method needs to be found, so that the trajectory is smooth and translated, the flight trajectory is displayed more smoothly by adopting a 3D technology in combination with geographic information, and visual help is provided for flight teaching, event investigation and the like.
Disclosure of Invention
In order to solve the defects of the prior art, the invention provides a flight trajectory optimization and translation method and a flight trajectory optimization and translation system; a flight track optimization and translation method is provided according to longitude, latitude, course, ground speed, airport declination and runway declination based on time sequence format data of airplane decoding, the problem of unsmooth change of longitude and latitude is solved, the flight track is more accurate and smooth, the flight track is more smoothly displayed by adopting a 3D technology in combination with geographic information, visual help is provided for flight teaching, event investigation and the like, and a pilot is helped to visually analyze the occurrence problem and improve the direction.
In a first aspect, the invention provides a flight trajectory optimization and translation method;
the flight trajectory optimization and translation method comprises the following steps:
acquiring flight time sequence data of an airplane at an approach stage; wherein the flight timing data comprises: longitude, latitude, heading, and airport declination;
selecting a k point from the flight time sequence data as a starting point; acquiring an optimized longitude value and an optimized latitude value of a kth point; k is a positive integer, and k is greater than or equal to 2;
calculating the optimized longitude value and the optimized latitude value of the k +1 point according to the optimized longitude value of the k point, the optimized latitude value of the k point, the true heading of the airplane of the k point and the flight distance between the k point and the k +1 point; the kth point and the (k + 1) th point are points in flight time sequence data;
adding 1 to k, and sequentially calculating longitude and latitude coordinate values of the optimized subsequent points of the starting point until the flight lands in the stand;
according to the longitude and latitude coordinate values optimized by each point, sequentially connecting the optimized longitude and latitude coordinate values to generate an optimized flight track;
and according to the optimized flight path of the flight, taking the position of the grounding point as a reference to realize the integral translation of the flight path.
In a second aspect, the invention provides a flight trajectory optimization and translation system;
flight trajectory optimization and translation system includes:
an acquisition module configured to: acquiring flight time sequence data of an airplane at an approach stage; wherein the flight timing data comprises: longitude, latitude, heading, and airport declination;
a preliminary optimization module configured to: selecting a k point from the flight time sequence data as a starting point; acquiring an optimized longitude value and an optimized latitude value of a kth point; k is a positive integer, and k is greater than or equal to 2;
a computing module configured to: calculating the optimized longitude value and the optimized latitude value of the k +1 point according to the optimized longitude value of the k point, the optimized latitude value of the k point, the true heading of the airplane of the k point and the flight distance between the k point and the k +1 point; the kth point and the (k + 1) th point are points in flight time sequence data;
a loop module configured to: adding 1 to k, and sequentially calculating longitude and latitude coordinate values of the optimized subsequent points of the starting point until the flight lands in the stand;
an output module configured to: according to the longitude and latitude coordinate values optimized by each point, sequentially connecting the optimized longitude and latitude coordinate values to generate an optimized flight track;
and according to the optimized flight path of the flight, taking the position of the grounding point as a reference to realize the integral translation of the flight path.
In a third aspect, the present invention further provides an electronic device, including:
a memory for non-transitory storage of computer readable instructions; and
a processor for executing the computer readable instructions,
wherein the computer readable instructions, when executed by the processor, perform the method of the first aspect.
In a fourth aspect, the present invention also provides a storage medium storing non-transitory computer readable instructions, wherein the non-transitory computer readable instructions, when executed by a computer, perform the instructions of the method of the first aspect.
In a fifth aspect, the invention also provides a computer program product comprising a computer program for implementing the method of the first aspect when run on one or more processors.
Compared with the prior art, the invention has the beneficial effects that:
this scheme not only is suitable for the aircraft and advances the phase, also is fit for the other phases of flight. The flight track is smooth, a foundation is provided for restoring a flight 3D flight scene, the flight track is more vivid, and powerful support is provided for flight teaching and flight event investigation.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
Fig. 1 is a flowchart of a flight trajectory optimization method according to a first embodiment of the present application;
FIG. 2 is a flowchart of a flight trajectory translation method according to a first embodiment of the present application;
fig. 3 is a schematic view of a runway edge according to a first embodiment of the present disclosure;
fig. 4 is a schematic view of a runway edge according to a first embodiment of the present disclosure;
FIG. 5 is a diagram of a result of the flight trajectory optimization according to the first embodiment of the present application;
FIG. 6 is a diagram of a result of the flight trajectory optimization according to the first embodiment of the present application;
fig. 7 is a diagram of a result of optimizing a flight trajectory according to a first embodiment of the present application.
Detailed Description
It is to be understood that the following detailed description is exemplary and is intended to provide further explanation of the invention as claimed. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention. As used herein, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise, and it should be understood that the terms "comprises" and "comprising", and any variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The embodiments and features of the embodiments of the present invention may be combined with each other without conflict.
All data are obtained according to the embodiment and are legally applied on the data on the basis of compliance with laws and regulations and user consent.
Example one
The embodiment provides a flight trajectory optimization and translation method;
as shown in fig. 1, the flight trajectory optimization and translation method includes:
s101: acquiring flight time sequence data of an airplane at an approach stage; wherein the flight timing data comprises: longitude, latitude, heading, and airport declination;
s102: selecting a k point from the flight time sequence data as a starting point; acquiring an optimized longitude value and an optimized latitude value of a kth point; k is a positive integer, and k is greater than or equal to 2;
s103: calculating the optimized longitude value and the optimized latitude value of the k +1 point according to the optimized longitude value of the k point, the optimized latitude value of the k point, the true heading of the airplane of the k point and the flight distance between the k point and the k +1 point; the kth point and the (k + 1) th point are points in flight time sequence data;
s104: adding 1 to k, repeating S102-S103, and sequentially calculating the longitude and latitude coordinate values of the optimized subsequent points of the starting point until the flight lands in the stand;
s105: according to the longitude and latitude coordinate values optimized by each point, sequentially connecting the optimized longitude and latitude coordinate values to generate an optimized flight track; and according to the optimized flight path of the flight, taking the position of the grounding point as a reference to realize the integral translation of the flight path.
Further, the obtaining process of the optimized longitude value and the optimized latitude value of the kth point includes:
adding 2 x k-1 numerical values in total to the original longitude value of the kth point and the longitude values of k-1 points above and below the k point to calculate the average to obtain the optimized longitude value of the kth point;
and adding 2 x k-1 numerical values in total to the original latitude value of the k point and the latitude values of the left and right k-1 points of the original latitude value to calculate the average to obtain the optimized latitude value of the k point.
Illustratively, the k-th point, for example, k is 7, and the average longitude (ave _ Lon) and the average latitude (ave _ Lat) of this point and the 6 upper and lower points are calculated.
Further, the obtaining process of the true heading of the k-th point aircraft includes:
the true heading of the k point aircraft is equal to the sum of the magnetic heading of the k point aircraft and the magnetic declination of the airport;
if the summation result is larger than 360, subtracting 360 from the summation result, and taking the obtained value as the true heading of the k-th point aircraft;
and if the summation result is less than 0, adding 360 to the summation result, and taking the obtained value as the true heading of the k point airplane.
Illustratively, this step loads the raw timing data, intercepting flight data (total length len) below 2000 feet relative barometric altitude. Calculating the True Heading (TH) of the airplane every second according to the magnetic declination (MV) of each airport and the Magnetic Heading (MH) of the airplane: TH ═ MH + MV.
Further, the flying distance between the kth point and the (k + 1) th point specifically includes:
and calculating the flight distance between the kth point and the (k + 1) th point according to the current ground speed.
Illustratively, from the ground speed GS in the time series data, the distance dis of the k-th point from the k + 1-th point is calculated:
dis＝GS*1852/3600。
further, the step S103: calculating the optimized longitude value and the optimized latitude value of the k +1 point according to the optimized longitude value of the k point, the optimized latitude value of the k point, the true heading of the airplane of the k point and the flight distance between the k point and the k +1 point; the method specifically comprises the following steps:
Latk+1＝lat2*180/π；
Lonk+1＝Lonk+L*180/π；
cos2SigalM＝cos(2*sigma1+sigma)；
sigma1＝atan2((1-f)*tan(Latk*π/180),cos(TH*π/180))；
sigma＝dis/(w_rad*A)；
C＝f/16*(1-sin(TH*π/180)2)*(4+f*(4-3*(1-sin(TH*π/180)2)))；
wherein l _ rad represents the earth major radius; w _ rad represents the short radius of the earth; f represents the earth oblateness; lonkRepresents the longitude of the k-th point; latkRepresents the latitude of the k-th point; lonk+1Represents the longitude of the k +1 th point; latk+1Represents the latitude of the k +1 point; dis represents the distance between two points; TH denotes true heading, other parameters are intermediate variables.
Further, according to the optimized flight trajectory, the integral translation of the flight trajectory is realized by taking the position of the ground point as a reference, and the integral translation is realized by selecting one of two modes, wherein the two modes are in parallel relation.
The first method is as follows: according to the flight trajectory after optimization, the integral translation of the flight trajectory is realized by taking the position of the grounding point as a reference, and the method specifically comprises the following steps:
if the distance between the grounding point and the middle point of the runway in the optimized flight trajectory exceeds a set threshold (for example, 5 meters), the magnetic declination MV of the airport is adjusted:
MV'＝n*MV；
wherein MV' is the adjusted airport declination; and n is a constant, so that the integral translation of the flight track is realized until the distance between the grounding point and the middle point of the runway is within a set threshold range.
According to the invention, the translation of the landing track is realized according to whether the grounding point is in the middle position of the runway, so that the landing track is in the middle position of the runway.
The second method comprises the following steps: as shown in fig. 2, the implementing integral translation of the flight trajectory by using the location of the ground point as a reference according to the optimized flight trajectory specifically includes:
s1061: calculating the distance s _ d between the two points s1 and s2 according to the optimized longitude and latitude of the grounding point s1 and the longitude and latitude of the entrance midpoint s2 of the landing runway;
s1062: according to the magnetic azimuth angle of the runway, moving the point s1 to the grounding point along the centerline of the runway by a distance s _ d to generate longitude and latitude coordinates of the point s 3;
s1063: calculating the distance h1 from the point-to-point s1 to the point s 3;
s1064: if h1 is within a set threshold (e.g., 5 meters), the grounding point is considered reasonable and the overall flight trajectory does not need to be adjusted;
s1065: if h1 is not within the set threshold, calculating the distance h from the point s1 to the side s2s3, and moving the point s1 by the length h in the negative axis direction of the X coordinate axis to obtain a point s4_ 1; the method is characterized in that the center point of an entrance of a landing runway is used as an original point, the centerline of the runway is used as a Y coordinate axis, a line perpendicular to the centerline of the runway is used as an X coordinate axis, the positive direction of the Y coordinate axis is the advancing direction of the airplane when landing, and the positive direction of the X coordinate axis is the direction pointed by the right wing when landing. The negative direction of the X coordinate axis is the direction pointed by the left wing when the airplane lands,
s1066: comparing the length s _ d with the size of s _ d1, if s _ d is larger than s _ d1, the moving direction is correct; s _ d1 refers to the distance from the entry midpoint s2 to the s4_1 point of the landing runway; if s _ d is less than or equal to s _ d1, the moving direction is wrong; if the moving direction is wrong, selecting the opposite direction of the current moving direction as the moving direction;
s1067: and translating the optimized longitude and latitude coordinate points by the same integral translation distance to generate a new longitude and latitude coordinate point according to the correct moving distance and Translation Angle (TA).
And after the translation distance h and the correct translation angle TA are determined, calculating the longitude and latitude values after translation according to the current longitude and latitude, the translation distance h, the translation angle and the TA. And realizing 3D flight scene reproduction according to the longitude, the latitude, the altitude and the heading by combining geographic information.
As shown in fig. 3 and 4, this step loads the smoothed time series data (total length len). And calculating the distance h between the grounding point and the runway according to the magnetic azimuth angle (MA) of the airport landing runway, the longitude and latitude of the grounding point and the longitude and latitude of the runway entrance point, and judging whether the flight track needs to translate according to the distance h. And calculating the optimized longitude and latitude value according to the magnetic azimuth angle, the distance h and the current longitude and latitude of the airport landing runway on the flying track needing translation, so as to achieve the purpose of translation.
(11) The Translation Angle (TA) is calculated according to the magnetic azimuth angle of the landing runway, and the translation has two directions, namely left or right. If the calculated Translation Angle (TA) is greater than 360, the Translation Angle (TA) is subtracted from 360, and if the Translation Angle (TA) is less than 0, the Translation Angle (TA) is added to 360.
TA＝MA±90
(12) Calculate optimized ground point s1 (longitude: Lon)s1And latitude: lats1) And a landing runway threshold midpoint s2 (longitude: lons2And latitude: lats2) S _ d;
trad＝Lats1*π/180-Lats2*π/180
nrad＝Lons1*π/180-Lons2*π/180
(13) moving the access port midpoint s2 to a point s3 by a distance s _ d along the central line of the runway, and calculating the longitude and latitude value (longitude: Lon) of the point s3 according to the Magnetic Azimuth (MA) of the runway, the distance s _ d and the longitude and latitude of the point s1s3And latitude: lats3) And the other variables are intermediate variables.
Lats3＝lat2*180/π
C＝f/16*(1-sin(MA*π/180)2)*(4+f*(4-3*(1-sin(MA*π/180)2)))
sigma1＝atan2((1-f)*tan(Lats2*π/180),cos(MA*π/180))
sigma＝s_d/(w_rad*A)
cos2SigalM＝cos(2*sigma1+sigma)
Lons3＝Lons2+L*180/π
(14) The distance h1 from point s1 to point s3 is calculated, and if h1 is greater than 5 meters, the distance h from point s1 to side s2s3 is calculated. trad ═ Lats1*π/180-Lats3*π/180
nrad＝Lons1*π/180-Lons3*π/180
(15) The distance h from the point s1 to the side s2s3 is calculated from the perimeter per.
per＝2*s_d+h1
(16) Moving the point s1 to the negative axis direction of the X coordinate axis by a length h to a point s4_1, and calculating the longitude and latitude value (longitude: Lon) of the point s4_1 according to the Translation Angle (TA), the distance h and the longitude and latitude of the point s1s4_1And latitude: lats4_1) The formula is the same as the step (13), except that the runway magnetic azimuth angle (MA) is replaced by the Translation Angle (TA), and the distance s _ d is replaced by h.
(17) The distance s _ d1 between the point s2 and the point s4_1 is calculated, if s _ d is larger than s _ d1, the moving direction is proved to be correct, otherwise the Translation Angle (TA) is reversed.
trad＝Lats2*π/180-Lats4_1*π/180
nrad＝Lons2*π/180-Lons4_1*π/180
(18) And (4) according to the determined Translation Angle (TA) and the translation distance h, sequentially calculating all longitude and latitude points according to the logic of the step (13) to obtain corresponding longitude and latitude values.
(19) And inputting the finally generated flight time sequence data including longitude, latitude, course, altitude, grounding identification and the like into the three-dimensional simulation system to realize 3D flight scene reproduction.
And processing the time sequence warp and weft data of the flight to generate an optimized longitude and latitude, and realizing flight scene reproduction by adopting a 3D technology according to the optimized longitude, the optimized latitude, the optimized altitude and the optimized course and combining geographic information. According to the invention, the translation of the landing track is realized according to whether the grounding point is in the middle position of the runway, so that the landing track is in the middle position of the runway. And inputting the finally generated flight time sequence data including longitude, latitude, course, altitude, grounding identification and the like into the three-dimensional simulation system to realize 3D flight scene reproduction.
Fig. 5 is an aerial flight trajectory diagram, in which the right side line is the flight trajectory of the airplane drawn by the real data, and the left side line is the flight trajectory of the airplane after optimization. It can be seen that the left line is smoother.
Fig. 6 and 7 are flight path diagrams of airplanes on a runway, wherein a bent line is a flight path of the airplane drawn by real data, and a non-bent line is a flight path of the airplane after optimization. It can be seen that the non-curved lines are smoother.
Example two
The embodiment provides a flight trajectory optimization and translation system;
flight trajectory optimization and translation system includes:
an acquisition module configured to: acquiring flight time sequence data of an airplane at an approach stage; wherein the flight timing data comprises: longitude, latitude, heading, and airport declination;
a preliminary optimization module configured to: selecting a k point from the flight time sequence data as a starting point; acquiring an optimized longitude value and an optimized latitude value of a kth point; k is a positive integer, and k is greater than or equal to 2;
a computing module configured to: calculating the optimized longitude value and the optimized latitude value of the k +1 point according to the optimized longitude value of the k point, the optimized latitude value of the k point, the true heading of the airplane of the k point and the flight distance between the k point and the k +1 point; the kth point and the (k + 1) th point are points in flight time sequence data;
a loop module configured to: adding 1 to k, and sequentially calculating longitude and latitude coordinate values of the optimized subsequent points of the starting point until the flight lands in the stand;
an output module configured to: according to the longitude and latitude coordinate values optimized by each point, sequentially connecting the optimized longitude and latitude coordinate values to generate an optimized flight track; and according to the optimized flight path of the flight, taking the position of the grounding point as a reference to realize the integral translation of the flight path.
It should be noted that the modules correspond to the steps in the first embodiment, and the modules are the same as the corresponding steps in the implementation example and the application scenario, but are not limited to the disclosure in the first embodiment. It should be noted that the modules described above as part of a system may be implemented in a computer system such as a set of computer-executable instructions.
In the foregoing embodiments, the descriptions of the embodiments have different emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments.
The proposed system can be implemented in other ways. For example, the above-described system embodiments are merely illustrative, and for example, the division of the above-described modules is merely a logical division, and in actual implementation, there may be other divisions, for example, multiple modules may be combined or integrated into another system, or some features may be omitted, or not executed.
EXAMPLE III
The present embodiment also provides an electronic device, including: one or more processors, one or more memories, and one or more computer programs; wherein, a processor is connected with the memory, the one or more computer programs are stored in the memory, and when the electronic device runs, the processor executes the one or more computer programs stored in the memory, so as to make the electronic device execute the method according to the first embodiment.
It should be understood that in this embodiment, the processor may be a central processing unit CPU, and the processor may also be other general purpose processors, digital signal processors DSP, application specific integrated circuits ASIC, off-the-shelf programmable gate arrays FPGA or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, and so on. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like.
The memory may include both read-only memory and random access memory, and may provide instructions and data to the processor, and a portion of the memory may also include non-volatile random access memory. For example, the memory may also store device type information.
In implementation, the steps of the above method may be performed by integrated logic circuits of hardware in a processor or instructions in the form of software.
The method in the first embodiment may be directly implemented by a hardware processor, or may be implemented by a combination of hardware and software modules in the processor. The software modules may be located in ram, flash, rom, prom, or eprom, registers, among other storage media as is well known in the art. The storage medium is located in a memory, and a processor reads information in the memory and completes the steps of the method in combination with hardware of the processor. To avoid repetition, it is not described in detail here.
Those of ordinary skill in the art will appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware or combinations of computer software and electronic hardware. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the implementation. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
Example four
The present embodiments also provide a computer-readable storage medium for storing computer instructions, which when executed by a processor, perform the method of the first embodiment.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The flight path optimizing and translating method for the flight is characterized by comprising the following steps:
acquiring flight time sequence data of an airplane at an approach stage; wherein the flight timing data comprises: longitude, latitude, heading, and airport declination;
selecting a k point from the flight time sequence data as a starting point; acquiring an optimized longitude value and an optimized latitude value of a kth point; k is a positive integer, and k is greater than or equal to 2;
calculating the optimized longitude value and the optimized latitude value of the k +1 point according to the optimized longitude value of the k point, the optimized latitude value of the k point, the true heading of the airplane of the k point and the flight distance between the k point and the k +1 point; the kth point and the (k + 1) th point are points in flight time sequence data;
adding 1 to k, and sequentially calculating longitude and latitude coordinate values of the optimized subsequent points of the starting point until the flight lands in the stand;
according to the longitude and latitude coordinate values optimized by each point, sequentially connecting the optimized longitude and latitude coordinate values to generate an optimized flight track; and according to the optimized flight path of the flight, taking the position of the grounding point as a reference to realize the integral translation of the flight path.
2. The method for optimizing and translating flight trajectory according to claim 1, wherein the obtaining of the optimized longitude value and the optimized latitude value at the kth point comprises:
adding 2 x k-1 numerical values in total to the original longitude value of the kth point and the longitude values of k-1 points above and below the k point to calculate the average to obtain the optimized longitude value of the kth point;
and adding 2 x k-1 numerical values in total to the original latitude value of the k point and the latitude values of the left and right k-1 points of the original latitude value to calculate the average to obtain the optimized latitude value of the k point.
3. The method as claimed in claim 1, wherein the obtaining of the true heading of the k-th point aircraft comprises:
the true heading of the k point aircraft is equal to the sum of the magnetic heading of the k point aircraft and the magnetic declination of the airport;
if the summation result is larger than 360, subtracting 360 from the summation result, and taking the obtained value as the true heading of the k-th point aircraft;
and if the summation result is less than 0, adding 360 to the summation result, and taking the obtained value as the true heading of the k point airplane.
4. The flight trajectory optimization and translation method according to claim 1, wherein the flight distance between the kth point and the (k + 1) th point specifically includes:
and calculating the flight distance between the kth point and the (k + 1) th point according to the current ground speed.
5. A flight trajectory optimization and translation method according to claim 1, wherein the optimized longitude value and the optimized latitude value of the k +1 point are calculated based on the optimized longitude value of the k point, the optimized latitude value of the k point, the true heading of the airplane at the k point, and the flight distance between the k point and the k +1 point; the method specifically comprises the following steps:
Latk+1＝lat2*180/π；
Lonk+1＝Lonk+L*180/π；
cos2SigalM＝cos(2*sigma1+sigma)；
sigma1＝atan2((1-f)*tan(Latk*π/180),cos(TH*π/180))；
sigma＝dis/(w_rad*A)；
C＝f/16*(1-sin(TH*π/180)2)*(4+f*(4-3*(1-sin(TH*π/180)2)))；
wherein l _ rad represents groundA ball major radius; w _ rad represents the short radius of the earth; f represents the earth oblateness; lonkRepresents the longitude of the k-th point; latkRepresents the latitude of the k-th point; lonk+1Represents the longitude of the k +1 th point; latk+1Represents the latitude of the k +1 point; dis represents the distance between two points; TH denotes true heading, other parameters are intermediate variables.
6. The flight trajectory optimization and translation method according to claim 1,
according to the flight trajectory after optimization, the integral translation of the flight trajectory is realized by taking the position of the grounding point as a reference, and the method specifically comprises the following steps:
if the distance between the grounding point and the middle point of the runway in the optimized flight trajectory exceeds a set threshold, the magnetic declination MV of the airport is adjusted:
MV'＝n*MV；
wherein MV' is the adjusted airport declination; and n is a constant, so that the integral translation of the flight track is realized until the distance between the grounding point and the middle point of the runway is within a set threshold range.
7. The flight trajectory optimization and translation method according to claim 1,
according to the flight trajectory after optimization, the integral translation of the flight trajectory is realized by taking the position of the grounding point as a reference, and the method specifically comprises the following steps:
(1): calculating the distance s _ d between the two points s1 and s2 according to the optimized longitude and latitude of the grounding point s1 and the longitude and latitude of the entrance midpoint s2 of the landing runway;
(2): according to the magnetic azimuth angle of the runway, moving the point s1 to the grounding point along the centerline of the runway by a distance s _ d to generate longitude and latitude coordinates of the point s 3;
(3): calculating the distance h1 from the point-to-point s1 to the point s 3;
(4): if h1 is within the set threshold value, the grounding point is considered to be reasonable, and the flight track of the whole flight does not need to be adjusted;
(5): if h1 is not within the set threshold, calculating the distance h from the point s1 to the side s2s3, and moving the point s1 by the length h in the negative axis direction of the X coordinate axis to obtain a point s4_ 1; the method comprises the following steps of taking the center point of an entrance of a landing runway as an origin, taking the centerline of the runway as a Y coordinate axis, taking a line perpendicular to the centerline of the runway as an X coordinate axis, wherein the positive direction of the Y coordinate axis is the advancing direction of an airplane when landing, and the positive direction of the X coordinate axis is the direction pointed by a right wing when the airplane lands; the negative direction of the X coordinate axis is the direction pointed by the left wing when the airplane lands,
(6): comparing the length s _ d with the size of s _ d1, if s _ d is larger than s _ d1, the moving direction is correct; s _ d1 refers to the distance from the entry midpoint s2 to the s4_1 point of the landing runway; if s _ d is less than or equal to s _ d1, the moving direction is wrong; if the moving direction is wrong, selecting the opposite direction of the current moving direction as the moving direction;
(7): translating the optimized longitude and latitude coordinate points by the same integral translation distance to generate new longitude and latitude coordinate points according to the correct moving distance and translation angle TA;
after the translation distance h and the correct translation angle TA are determined, calculating the longitude and latitude values after translation according to the current longitude and latitude, the translation distance h, the translation angle and the TA; and realizing 3D flight scene reproduction according to the longitude, the latitude, the altitude and the heading by combining geographic information.
8. Flight trajectory optimization and translation system, characterized by includes:
an acquisition module configured to: acquiring flight time sequence data of an airplane at an approach stage; wherein the flight timing data comprises: longitude, latitude, heading, and airport declination;
a preliminary optimization module configured to: selecting a k point from the flight time sequence data as a starting point; acquiring an optimized longitude value and an optimized latitude value of a kth point; k is a positive integer, and k is greater than or equal to 2;
a computing module configured to: calculating the optimized longitude value and the optimized latitude value of the k +1 point according to the optimized longitude value of the k point, the optimized latitude value of the k point, the true heading of the airplane of the k point and the flight distance between the k point and the k +1 point; the kth point and the (k + 1) th point are points in flight time sequence data;
a loop module configured to: adding 1 to k, and sequentially calculating longitude and latitude coordinate values of the optimized subsequent points of the starting point until the flight lands in the stand;
an output module configured to: and sequentially connecting the optimized longitude and latitude coordinate values according to the optimized longitude and latitude coordinate values of each point to generate an optimized flight track.
9. An electronic device, comprising:
a memory for non-transitory storage of computer readable instructions; and
a processor for executing the computer readable instructions,
wherein the computer readable instructions, when executed by the processor, perform the method of any of claims 1-7.
10. A storage medium storing non-transitory computer-readable instructions, wherein the non-transitory computer-readable instructions, when executed by a computer, perform the instructions of the method of any one of claims 1-7.
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| CN114359350A (en) * | 2022-03-14 | 2022-04-15 | 中航信移动科技有限公司 | Data processing method and device, electronic equipment and storage medium |
| CN115856946A (en) * | 2023-02-21 | 2023-03-28 | 和普威视光电股份有限公司 | Aircraft alignment channel detection method, device, terminal and storage medium |
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| CN114359350A (en) * | 2022-03-14 | 2022-04-15 | 中航信移动科技有限公司 | Data processing method and device, electronic equipment and storage medium |
| CN114359350B (en) * | 2022-03-14 | 2022-05-20 | 中航信移动科技有限公司 | Data processing method and device, electronic equipment and storage medium |
| CN115856946A (en) * | 2023-02-21 | 2023-03-28 | 和普威视光电股份有限公司 | Aircraft alignment channel detection method, device, terminal and storage medium |
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