CN116449381B - Rapid identifying method and device for wake vortexes of airplane - Google Patents
Rapid identifying method and device for wake vortexes of airplane Download PDFInfo
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Abstract
The application discloses a method and a device for rapidly identifying wake vortexes of an airplane, and belongs to the technical field of aviation. Detecting wake vortexes of the aircraft by using a laser radar to obtain a two-dimensional radial velocity field; constructing a wake vortex recognition operator according to the characteristics that the wake vortices of the airplane show similar diagonal speeds and opposite adjacent speeds on a radial speed section; constructing an evaluation function according to the wake vortex recognition operator, traversing the two-dimensional radial velocity field by adopting the wake vortex recognition operator, and calculating the evaluation function values of all positions; screening out all areas with wake vortexes according to the evaluation function values of all the positions; and constructing a wake vortex core positioning operator in the screened wake vortex region according to the wake vortex recognition operator to obtain the vortex core position of the aircraft wake vortex. The application can greatly reduce the calculated amount and the occupation of calculation resources and improve the recognition accuracy.
Description
Technical Field
The application relates to the technical field of aviation, in particular to a method and a device for rapidly identifying wake vortexes of an airplane.
Background
The aircraft wake flow (wake vortex) is a pair of counter-rotating turbulence vortices formed behind the aircraft wing when the aircraft flies due to the pressure difference between the upper surface and the lower surface of the aircraft wing, and has the characteristics of large spatial dimension, long duration, strong rotation and the like. As a new category of atmospheric turbulence that accompanies aircraft, aircraft wake presents a significant threat to aviation safety, as the latter aircraft enters the wake of the former aircraft, jolts, roll, or even loss of control may occur. On the port entering/exiting route of an airport and an aircraft carrier, the influence of wake vortexes of the aircraft is larger due to intensive take-off and landing of the aircraft, and the wake vortexes are one of main factors which restrict the throughput capacity of the airport and the safe take-off and landing of the carrier-borne aircraft of the aircraft carrier, and the tail vortexes of the oiling machine also influence the operation process during air oiling. The accurate identification of the position of the wake vortex of the airplane has important significance for improving the operation efficiency of an airport and guaranteeing the aviation safety.
The airplane wake Vortex tangential velocity model is widely applied and mainly comprises a Lamb-Osen wake Vortex tangential velocity model, a Hall-Burnham wake Vortex tangential velocity model, an Adapted Vortex wake Vortex tangential velocity model and the like. The laser radar is the most effective wake vortex detection means and has become common knowledge, at present, most of existing algorithms are used for identifying wake vortices based on wake vortex speed models, inversion is carried out on the basis of the wake vortex speed models to obtain wake vortex parameters, and the models are complex, large in calculation amount, low in robustness and unfavorable for identifying the wake vortices of an airplane rapidly.
Disclosure of Invention
The application aims to provide a rapid identification method and device for wake vortexes of an airplane, which are used for overcoming the defects that the existing wake vortexes identification method needs to invert two-dimensional speed according to radial speed, has complex model, large calculated amount, low robustness and the like.
In order to achieve the above purpose, the application adopts the following technical scheme:
in a first aspect, the present application provides a method for rapidly identifying wake vortexes of an aircraft, including:
detecting wake vortexes of the aircraft by using a laser radar to obtain a two-dimensional radial velocity field;
constructing a wake vortex recognition operator according to the characteristics that the wake vortices of the airplane show similar diagonal speeds and opposite adjacent speeds on a radial speed section;
constructing an evaluation function according to the wake vortex recognition operator, traversing the two-dimensional radial velocity field by adopting the wake vortex recognition operator, and calculating evaluation function values of all positions;
screening out all areas with wake vortexes according to the evaluation function values of all the positions;
and constructing a wake vortex core positioning operator in the screened wake vortex area according to the wake vortex recognition operator to obtain the vortex core position of the aircraft wake vortex.
Further, the detecting the wake vortex of the aircraft by using the laser radar to obtain a two-dimensional radial velocity field includes:
and detecting wake vortexes of the aircraft by using a laser radar to obtain Doppler velocity distribution of a vertical section, and carrying out normalization processing on the Doppler velocity distribution to obtain a two-dimensional radial velocity field.
Further, the construction method of the wake vortex recognition operator comprises the following steps:
constructing a rectangle, taking the gravity center of the rectangle as the center point of a wake vortex recognition operator, calculating the average value of radial speeds in four right-angle areas in a fixed area of the rectangle, wherein the lengths and the widths of the four right-angle areas are the same, the position of the rectangle is determined by the coordinates of the center point, and the size of the rectangle is determined by the length of a connecting line from the gravity center of the rectangle to the position corresponding to the average value of the radial speeds in any right-angle areadAnd the included angle between the connecting line and the upper edge or the lower edge of the rectangleθDetermining the size of the right angle region,dAndθcan be adjusted, a right angle area can be selected as one point, an area can be selected, the coordinates of a central point,dAndθthe following conditions are also satisfied:
wherein ,（X i ,Y j ) The coordinates of the center point of the operator are identified for wake vortices,X max 、Y max respectively a horizontal maximum value and a vertical maximum value in a laser radar scanning area,Alength isdIs used for the purpose of the maximum value of (a),B 1 the maximum value of the width of the operator rectangle,B 2 for operator rectangleThe length is the maximum value.
Further, the constructed evaluation function is:
F=f 1 -f 2
f 1 =[(V 1 -V 4 ) 2 +(V 2 -V 3 ) 2 ]
f 2 =[(V 1 -V 2 ) 2 +(V 1 -V 3 ) 2 +(V 4 -V 2 ) 2 +(V 4 -V 3 ) 2 ]/λ
wherein ,Fin order to evaluate the function of the device,f 1 in order to evaluate the function of the diagonal,f 2 the adjacent evaluation function is adopted;λdetermining a size based on in-situ measurement wake vortex data for adjusting the coefficients;V 1 、V 2 、V 3 、V 4 the radial velocity averages in the four right angle areas of the upper left, upper right, lower left and lower right respectively.
Further, screening out all regions with wake vortexes according to the evaluation function values of the positions, including:
judging whether the evaluation function value of each position is in a predetermined threshold interval, if so, judging that wake vortexes exist in the position, and screening out all areas with the wake vortexes according to the evaluation function value of each position in the threshold interval.
Further, the constructing a wake vortex scroll positioning operator according to the wake vortex recognition operator to obtain a scroll position of the aircraft wake vortex includes:
assuming that the wake vortex of the airplane is in the shape of a standard circle, the four right-angle areas calculated according to the wake vortex recognition operator are respectively positioned right above and right below two wake vortex standard circles, the two vortex cores are respectively positioned at the symmetry centers of the upper right-angle area and the lower right-angle area, and according to the characteristics, a wake vortex core positioning operator is designed:
wherein ,X a 、X b respectively the abscissa of two vortex cores of the wake vortex of the airplane;
finally, the positions of the two vortex cores are respectivelyX a ，Y j ） and （X b ，Y j ）。
In a second aspect, the present application provides an aircraft wake vortex rapid identification device, comprising:
the two-dimensional velocity field acquisition module is used for detecting the wake vortex of the airplane by using a laser radar to acquire a two-dimensional radial velocity field;
the wake vortex recognition operator construction module is used for constructing wake vortex recognition operators according to the characteristics that the opposite angles of the wake vortices of the aircraft are similar in speed and opposite in speed on the radial speed profile;
the evaluation function calculation module is used for constructing an evaluation function according to the wake vortex recognition operator, traversing the two-dimensional radial velocity field by adopting the wake vortex recognition operator, and calculating the evaluation function values of all positions;
the wake vortex judging module is used for screening out all areas with wake vortex according to the evaluation function values of all the positions;
and the wake vortex position determining module is used for constructing a wake vortex scroll positioning operator in the screened wake vortex area according to the wake vortex recognition operator to obtain the scroll position of the aircraft wake vortex.
In a third aspect, the present application provides a computer readable storage medium storing one or more programs, the one or more programs comprising instructions, which when executed by a computing device, cause the computing device to perform the aircraft wake vortex rapid identification method of the first aspect.
In a fourth aspect, the present application provides a computing device comprising: one or more processors, one or more memories, and one or more programs, wherein the one or more programs are stored in the one or more memories and configured to be executed by the one or more processors, the one or more programs comprising instructions for performing the aircraft wake vortex rapid identification method of the first aspect.
Compared with the prior art, the application has the beneficial technical effects that:
according to the application, the laser radar scanning radial speed is not required to invert the two-dimensional wind speed, and the correlation coefficients of the field wind field and the airplane wake vortex simulation model are not required to be calculated, so that the calculated amount and the occupation of calculation resources are greatly reduced, the synchronous and rapid calculation can be realized in the laser radar scanning process, and the purpose of timely early warning is achieved. Meanwhile, according to the physical structure of wake vortexes, operators with adjustable shapes are adopted, and the statistics thought is combined, so that operator parameters can be adjusted according to local conditions according to the training result of the early-stage laser radar data, and the identification accuracy is improved.
Drawings
FIG. 1 is a flow chart of a method for identifying wake vortexes of an aircraft in accordance with an embodiment of the present application;
FIG. 2 is a schematic view of aircraft wake vortices;
FIG. 3 is a schematic diagram of wake vortex recognition operator ψ1;
fig. 4 is a schematic diagram of the wake vortex recognition operator ψ1 superimposed on the aircraft wake vortex;
FIG. 5 is a schematic diagram of wake vortex core positioning operator ψ2;
FIG. 6 is a schematic diagram of a radial wind speed detection result and a located wake vortex center position of a certain detection sample of the laser radar in an experimental example of the application;
fig. 7 is a schematic structural diagram of an aircraft wake vortex rapid identifying device according to an embodiment of the present application.
Description of the embodiments
The application is further described below in connection with specific embodiments. The following examples are only for more clearly illustrating the technical aspects of the present application, and are not intended to limit the scope of the present application.
As shown in fig. 1, an embodiment of the present application provides a method for quickly identifying wake vortexes of an aircraft, including the following steps:
step S1, detecting wake vortexes of an airplane by using a laser radar to obtain a two-dimensional radial velocity field;
performing RHI (Range-Height-Indicator) scanning at laser radar end to obtain Doppler velocity distribution of vertical section, and performing normalization processing to obtain the final productX，Y，V) A two-dimensional radial velocity field, wherein,X，Yis the position of a two-dimensional plane,Vis the speed at that location.
S2, constructing a wake vortex recognition operator according to the characteristics that the wake vortices of the airplane show similar diagonal speeds and opposite adjacent speeds on a radial speed section;
fig. 2 is a schematic view of the wake vortex of an aircraft. According to the characteristics that the aircraft wake vortexes show similar diagonal speeds and opposite adjacent speeds on a radial speed section, a wake vortex recognition operator psi 1 is constructed, and the construction method is as follows:
constructing a rectangle, taking the gravity center of the rectangle as the center point of a wake vortex recognition operator, calculating the average value of radial speeds in four right-angle areas in a fixed area of the rectangle, wherein the lengths and the widths of the four right-angle areas are the same, the position of the rectangle is determined by the coordinates of the center point, and the size of the rectangle is determined by the length of a connecting line from the gravity center of the rectangle to the position corresponding to the average value of the radial speeds in any right-angle areadAnd the included angle between the connecting line and the upper edge or the lower edge of the rectangleθAnd (5) determining. Wherein the right angle area is of a size,d、θCan be adjusted, a right angle area can be selected as one point, or one area can be selected, and the coordinates of the central point can be obtained,d，θThe parameters satisfy the set conditions.
More specifically, as shown in fig. 3, a graphical depiction of wake vortex recognition operator ψ1 is shown. Wherein%X i ,Y j ) As the coordinates of the central point of the operator,Sfor any one of the calculated areas (right angle areas),V 1 、V 2 、V 3 or (b)V 4 The radial velocity averages over four calculated area,dfor any one calculation region inside the operatorSThe distance from the position corresponding to the average value of the radial velocity in the inner part to the center of the operator,θfor any one calculation region inside the operatorSAnd an included angle between a connecting line from the position corresponding to the radial velocity average value in the inner to the operator center and the abscissa of the operator center.S，d，θIs adjustable and can be used for controlling the temperature,Sa point may be selected or a region may be selected.
At the same time, toX i The limitations of (2) are:
for a pair ofY j The limitations of (2) are:
for a pair ofdAndθthe limitations of (2) are:
wherein ,X max 、Y max respectively a horizontal maximum value and a vertical maximum value in a laser radar scanning area,Alength isdIs used for the purpose of the maximum value of (a),B 1 the maximum value of the width of the operator rectangle,B 2 the length of the operator rectangle is maximally valued. Typically, the aircraft has a wing span of about 60m, the wake vortex width is two wing spans, i.e. about 120m,dtaking a maximum of 100m, the overall rectangular length of the operator is as short as 140m, which can meet the detection requirement, and therefore, in the embodiment of the application,Athe value of 100m can be taken,B 1 、B 2 the value can be 140m.
Fig. 4 is a schematic diagram of the wake vortex superposition of the wake vortex recognition operators ψ1.
Step S3, constructing an evaluation function according to the wake vortex recognition operator, traversing the two-dimensional radial velocity field by adopting the wake vortex recognition operator, and calculating evaluation function values of all positions;
constructing an evaluation function according to the wake vortex recognition operator ψ1FEvaluation functionFFor measuring the difference in speed in the four calculation areas.
The evaluation function may include standard root mean square error, etc., in order to reduce the amount of computation, an embodiment of the present application chooses to construct the following functions:
constructing diagonal evaluation functionsf 1 And adjacent evaluation functionf 2 ：
f 1 =[(V 1 -V 4 ) 2 +(V 2 -V 3 ) 2 ]
f 2 =[(V 1 -V 2 ) 2 +(V 1 -V 3 ) 2 +(V 4 -V 2 ) 2 +(V 4 -V 3 ) 2 ]/λ
wherein ,λto adjust the coefficients, the size is determined from the in-situ measurement wake vortex data.
Diagonal evaluation functionf 1 For measuring the speed similarity of diagonal areas, adjacent evaluation functionsf 2 For measuring the opposite speed of adjacent areas. The structure of the wake vortex of the airplane shows that the speeds of the diagonal areas of the operators are close, and the speeds of the adjacent areas of the operators are opposite.
For evaluation functionsFIt is necessary to screen out the region where the diagonal velocity difference is the smallest and the adjacent velocity difference is the largest, so an evaluation function is constructedFThe following are provided:
F=f 1 -f 2
wherein ,Fthe smaller the better.
Traversing the two-dimensional radial velocity field obtained in the step S1 by adopting a wake vortex recognition operator ψ1, and constructing an evaluation function according to the constructed evaluation functionFCalculating evaluation function values of all positions, i.eFValues.
Step S4, screening out all areas with wake vortexes according to the evaluation function values of the positions;
first, an evaluation function is determinedFIs set in the threshold interval of (a). Evaluation functionFThe threshold interval of (2) is set according to the history data. Specifically, historical aircraft wake vortex data is used for evaluation functionFA threshold of the evaluation function is obtained according to statistics as a criterion for distinguishing whether wake vortices exist.
Judging the evaluation function of each position obtained in step S3FAnd judging whether the value is in a threshold interval or not, if so, judging that the wake vortex exists in the position, and screening out all areas with the wake vortex according to the wake vortex.
S5, constructing a wake vortex scroll positioning operator in the screened wake vortex area according to the wake vortex recognition operator to obtain the scroll position of the aircraft wake vortex;
as shown in fig. 4 and 5, two vortex cores of the wake vortexes of the aircraft are assumed to be in the shape of a standard circle, and then four right-angle areas calculated according to the wake vortex recognition operator ψ1 should be located directly above and directly below the two wake vortex standard circles respectively, and the two vortex cores should be located at the symmetry centers of the upper right-angle area and the lower right-angle area respectively, so that a wake vortex core positioning operator ψ2 is designed:
wherein ,X a 、X b respectively the abscissa of two vortex cores of the wake vortex of the airplane;
finally, the positions of the two vortex cores are respectivelyX a ，Y j ） and （X b ，Y j ) Thereby obtaining the specific position of wake vortexes.
In order to verify the effectiveness of the method of the application, the application is verified and illustrated by using an experimental example, which is specifically as follows:
airport field data from 6 months to 8 months in 2020 were used as the data set. Manually framing aircraft wake vortexes, calculated by the operator of the application, in this exampleIn (3) optimumθAt 40.1 °, optimumdThe thickness of the film was set to 39.2m,λtake the value as 100, evaluate the functionFThe threshold range of the method is from-2.4 to-0.07. The observation data of 9 months in 2020 is used for verification, and compared with the existing model correlation coefficient method (for example, pan Weijun and other methods for identifying wake vortexes of an airplane by Doppler laser radar, "laser technology" 2019, 02 nd, 235 th page), and specific results are shown in table 1:
TABLE 1
| Accuracy of identification | Average calculation time | |
| Operator method | 91.67% | 0.03s |
| Model correlation coefficient method | 91.52% | 0.16s |
As can be seen from Table 1, compared with the existing model correlation coefficient method, the aircraft wake vortex recognition method not only improves a quantity level in calculation time, but also has slightly better recognition accuracy than the model correlation coefficient method.
Fig. 6 is a schematic diagram of a radial wind speed detection result of a certain detection sample of the laser radar and a located wake vortex center position in an experimental example of the present application, and a middle black frame part is an area where an operator judges that wake flows exist.
Wherein, the excitationThe optical radar detects the radial speed in the airport in the field, the speed close to the laser radar is positive, the speed far away from the laser radar is negative, and the speed of the background wind field is not more than 0.3m/s. Operator traversal speed field, calculated evaluation functionFIs-0.87, within the threshold range of-2.4 to-0.07,V 1 、V 2 、V 3 、V 4 the wake vortexes are positioned at (0.29, 0.37) and (0.34,0.37) at-1.5 m/s, 3m/s, 3.3m/s and-1.2 m/s respectively.
According to the application, the laser radar scanning radial speed is not required to invert the two-dimensional wind speed, and the correlation coefficients of the field wind field and the airplane wake vortex simulation model are not required to be calculated, so that the calculated amount and the occupation of calculation resources are greatly reduced, the synchronous and rapid calculation can be realized in the laser radar scanning process, and the purpose of timely early warning is achieved. Meanwhile, according to the physical structure of wake vortexes, operators with adjustable shapes are adopted, and the statistics thought is combined, so that operator parameters can be adjusted according to local conditions according to the training result of the early-stage laser radar data, and the identification accuracy is improved.
As shown in fig. 7, the present application provides a device for quickly identifying wake vortexes of an aircraft, comprising:
the two-dimensional velocity field acquisition module is used for detecting the wake vortex of the airplane by using a laser radar to acquire a two-dimensional radial velocity field;
the wake vortex recognition operator construction module is used for constructing wake vortex recognition operators according to the characteristics that the opposite angles of the wake vortices of the aircraft are similar in speed and opposite in speed on the radial speed profile;
the evaluation function calculation module is used for constructing an evaluation function according to the wake vortex recognition operator, traversing the two-dimensional radial velocity field by adopting the wake vortex recognition operator, and calculating the evaluation function values of all positions;
the wake vortex judging module is used for screening out all areas with wake vortex according to the evaluation function values of all the positions;
and the wake vortex position determining module is used for constructing a wake vortex scroll positioning operator in the screened wake vortex area according to the wake vortex recognition operator to obtain the scroll position of the aircraft wake vortex.
The present application also provides a computer readable storage medium storing one or more programs, the one or more programs comprising instructions, which when executed by a computing device, cause the computing device to perform the aforementioned method of rapid identification of aircraft wake vortexes.
The present application also provides a computing device comprising: one or more processors, one or more memories, and one or more programs, wherein the one or more programs are stored in the one or more memories and configured to be executed by the one or more processors, the one or more programs comprising instructions for performing the aforementioned aircraft wake vortex rapid identification method.
It will be appreciated by those skilled in the art that embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
Claims (9)
1. The method for rapidly identifying the wake vortexes of the aircraft is characterized by comprising the following steps of:
detecting wake vortexes of the aircraft by using a laser radar to obtain a two-dimensional radial velocity field;
constructing a wake vortex recognition operator according to the characteristics that the wake vortices of the airplane show similar diagonal speeds and opposite adjacent speeds on a radial speed section;
constructing an evaluation function according to the wake vortex recognition operator, traversing the two-dimensional radial velocity field by adopting the wake vortex recognition operator, and calculating evaluation function values of all positions;
screening out all areas with wake vortexes according to the evaluation function values of all the positions;
and constructing a wake vortex core positioning operator in the screened wake vortex area according to the wake vortex recognition operator to obtain the vortex core position of the aircraft wake vortex.
2. The method for quickly identifying wake vortexes of an aircraft according to claim 1, wherein the detecting the wake vortexes of the aircraft by using the laser radar to obtain a two-dimensional radial velocity field comprises:
and detecting wake vortexes of the aircraft by using a laser radar to obtain Doppler velocity distribution of a vertical section, and carrying out normalization processing on the Doppler velocity distribution to obtain a two-dimensional radial velocity field.
3. The method for quickly identifying wake vortexes of an aircraft according to claim 1, wherein the method for constructing the wake vortexes identification operator is as follows:
constructing a rectangle, taking the gravity center of the rectangle as the center point of a wake vortex recognition operator, calculating the average value of radial speeds in four right-angle areas in a fixed area of the rectangle, wherein the lengths and the widths of the four right-angle areas are the same, the position of the rectangle is determined by the coordinates of the center point, and the size of the rectangle is determined by the length of a connecting line from the gravity center of the rectangle to the position corresponding to the average value of the radial speeds in any right-angle areadAnd the included angle between the connecting line and the upper edge or the lower edge of the rectangleθDetermining the size of the right angle region,dAndθall can be adjusted, a right angle area is selected as a point or an area is selected, the coordinates of a central point,dAndθthe following conditions are also satisfied:
，
，
，
，
wherein ,（X i ,Y j ) The coordinates of the center point of the operator are identified for wake vortices,X max 、Y max respectively a horizontal maximum value and a vertical maximum value in a laser radar scanning area,Alength isdIs used for the purpose of the maximum value of (a),B 1 the maximum value of the width of the operator rectangle,B 2 the length of the operator rectangle is maximally valued.
4. A method for rapid identification of wake vortexes in an aircraft according to claim 3, characterized in that the constructed evaluation function is:
F=f 1 -f 2
f 1 =[(V 1 -V 4 ) 2 +(V 2 -V 3 ) 2 ]
f 2 =[(V 1 -V 2 ) 2 +(V 1 -V 3 ) 2 +(V 4 -V 2 ) 2 +(V 4 -V 3 ) 2 ]/λ
wherein ,Fin order to evaluate the function of the device,f 1 in order to evaluate the function of the diagonal,f 2 the adjacent evaluation function is adopted;λdetermining a size based on in-situ measurement wake vortex data for adjusting the coefficients;V 1 、V 2 、V 3 、V 4 the radial velocity averages in the four right angle areas of the upper left, upper right, lower left and lower right respectively.
5. The method for quickly identifying wake vortexes of an aircraft according to claim 1, wherein the step of screening out all regions with wake vortexes according to the evaluation function values of the positions comprises the steps of:
judging whether the evaluation function value of each position is in a predetermined threshold interval, if so, judging that wake vortexes exist in the position, and screening out all areas with the wake vortexes according to the evaluation function value of each position in the threshold interval.
6. The method for quickly identifying wake vortexes of an aircraft according to claim 3, wherein constructing wake vortex scroll positioning operators according to the wake vortexes identification operators to obtain scroll positions of wake vortexes of the aircraft comprises:
assuming that the wake vortex of the airplane is in the shape of a standard circle, the four right-angle areas calculated according to the wake vortex recognition operator are respectively positioned right above and right below two wake vortex standard circles, the two vortex cores are respectively positioned at the symmetry centers of the upper right-angle area and the lower right-angle area, and according to the characteristics, a wake vortex core positioning operator is designed:
，
wherein ,X a 、X b respectively the abscissa of two vortex cores of the wake vortex of the airplane;
finally, the positions of the two vortex cores are respectivelyX a ，Y j ） and （X b ，Y j ）。
7. An aircraft wake vortex rapid identification device, comprising:
the two-dimensional velocity field acquisition module is used for detecting the wake vortex of the airplane by using a laser radar to acquire a two-dimensional radial velocity field;
the wake vortex recognition operator construction module is used for constructing wake vortex recognition operators according to the characteristics that the opposite angles of the wake vortices of the aircraft are similar in speed and opposite in speed on the radial speed profile;
the evaluation function calculation module is used for constructing an evaluation function according to the wake vortex recognition operator, traversing the two-dimensional radial velocity field by adopting the wake vortex recognition operator, and calculating the evaluation function values of all positions;
the wake vortex judging module is used for screening out all areas with wake vortex according to the evaluation function values of all the positions;
and the wake vortex position determining module is used for constructing a wake vortex scroll positioning operator in the screened wake vortex area according to the wake vortex recognition operator to obtain the scroll position of the aircraft wake vortex.
8. A computer readable storage medium storing one or more programs, the one or more programs comprising instructions, which when executed by a computing device, cause the computing device to perform the aircraft wake vortex rapid identification method of any of claims 1-6.
9. A computing device, comprising: one or more processors, one or more memories, and one or more programs, wherein the one or more programs are stored in the one or more memories and configured to be executed by the one or more processors, the one or more programs comprising instructions for performing the aircraft wake vortex rapid identification method of any of claims 1-6.
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| CN114880784A (en) * | 2022-07-07 | 2022-08-09 | 中国民航大学 | Vortex core position estimation method based on aircraft wake vortex scanning characteristics |
| CN115932881A (en) * | 2023-01-31 | 2023-04-07 | 青岛镭测创芯科技有限公司 | Draught fan wake flow detection method |
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| CN114880784A (en) * | 2022-07-07 | 2022-08-09 | 中国民航大学 | Vortex core position estimation method based on aircraft wake vortex scanning characteristics |
| CN115932881A (en) * | 2023-01-31 | 2023-04-07 | 青岛镭测创芯科技有限公司 | Draught fan wake flow detection method |
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|---|
| 基于形态学和K近邻算法的飞机尾流识别;潘卫军 等;《航空计算技术》;第52卷(第2期);第1-4页 * |
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