Method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing

Abstract

The method for quickly inverting aircraft wake vortex parameters based on mobile platform laser remote sensing comprises the following steps: a laser radar system scans a wake vortex influence area, and measurement data are subjected to quality control processing; a wake vortex core position and a vortex core radius are estimated; a wind speed of an arbitrary measurement point A located in the wake vortex range is subjected to vector decomposition, and the wind speed is expressed as a function of a wake vortex circulation parameter W 、 V 、 U A background wind speed and a laser radar motion speed are eliminated by using a non-wake vortex area measurement point; a difference between radial velocities of two measurement points in and out of a wake vortex influence range in the same laser emission direction is expressed as a function of a wake vortex circulation; and a turbulent disturbance is weakened by multiple measurements in the wake vortex influence range, and then a least square method is used to fit and solve the wake vortex circulation. The present application can accurately invert and correct aircraft wake vortex parameters by using less observation data. The calculation result is fast and accurate, and can provide scientific and reliable data support for aviation safety and aircraft cooperative operation.

Description

Technical Field

[0001] This invention relates to a rapid inversion method for aircraft wake vortex parameters based on mobile platform laser remote sensing, belonging to the field of aviation safety meteorological support. Background Technology

[0002] The airplane, one of the most significant inventions of the early 20th century, spurred the development of the air transport industry and transformed human transportation, economy, production, and daily life. Consequently, aviation safety has gradually become a focus of attention. The lift generated by an aircraft, specifically the wake vortex at the wing, is invisible to the naked eye and has a wide impact range. When a following aircraft inadvertently enters the wake vortex of a preceding aircraft, the rolling torque makes it difficult to control. With the advent of heavy aircraft, especially the B747-100, the aviation safety issues caused by aircraft wake vortices have become undeniable. Therefore, effective monitoring of aircraft wake vortices is necessary. Rapidly and accurately obtaining information on the location and intensity of aircraft wake vortices not only helps ensure flight safety but also improves airport runway utilization and facilitates air traffic management. In particular, monitoring aircraft wake vortices during flight provides a scientifically reliable basis for optimizing flight paths and can further improve the collaborative capabilities of aircraft.

[0003] Currently, among ground-based wind speed sensors, coherent Doppler pulsed lidar has become the ideal detection device for aircraft wake vortices under clear-sky conditions due to its advantages such as eye safety, high spatiotemporal resolution, and high precision. Meanwhile, through the joint efforts of experts and scholars both domestically and internationally, several methods have been proposed, including the maximum likelihood method (Frehlich et al., 2005), the tangential velocity adaptive spectrum method based on pulsed lidar systems (Hadi S et al., 2011), the radial velocity method for estimating aircraft wake vortex parameters using data measured by coherent Doppler lidar (Smalikho et al., 2015), the path integral method (Li Jianbing et al., 2020), and the localization and classification of aircraft wake vortices observed by lidar based on convolutional neural networks (Zhang Xinyu, 2024). These methods have continuously improved the accuracy and speed of extracting aircraft wake vortex characteristic parameter information from lidar spectral data. Effective monitoring of aircraft wake vortices in near-ground airport environments is no longer a challenge. However, when observation equipment is mounted on a mobile platform, such as an aircraft, the structural integrity of the aircraft wake vortex and the data density of the detection space cannot be guaranteed due to the complexity of the aircraft wake vortex, the limitations of observation technology, and the special nature of the monitoring environment. Currently, research on monitoring equipment, monitoring methods, and inversion methods for aircraft wake vortices on mobile platforms is still in the experimental stage.

[0004] Therefore, in response to the need for real-time detection of aircraft wake vortices in collaborative aircraft operations, and the current situation of insufficient detection methods and capabilities for high-altitude wake vortices, this paper utilizes laser remote sensing technology based on a mobile platform to quickly and effectively detect the wind field around the aircraft. This enables the rapid extraction and evaluation of aircraft wake vortex parameter information, providing reliable data support for flight path optimization and navigation safety, and promoting the development of the blue sky economy. Summary of the Invention

[0005] The purpose of this invention is to provide a rapid inversion method for aircraft wake vortex parameters based on mobile platform laser remote sensing. This method aims to overcome the unique challenges of high-altitude environmental monitoring, addressing issues such as insufficient spatial density of detection data and missing aircraft wake vortex structure information due to laser detection rate limitations in high-speed environments, as well as the insufficient performance of traditional aircraft wake vortex inversion algorithms. Furthermore, this method will break through the limitations of conventional aircraft wake vortex observation modes, namely the range-height indicator (RHI) measurement mode, providing robust and reliable data support for aviation safety and aircraft collaborative operations.

[0006] A rapid inversion method for aircraft wake vortex parameters based on mobile platform laser remote sensing is characterized by the following steps:

[0007] 1) The lidar system installed on the mobile platform scans the area affected by the wake vortex or the alarm triggering area, with the laser emission azimuth angle being... α Angle of elevation is i First, the measurement data from the lidar is denoised and quality controlled; then, based on the set threshold... L th Determine the spectral width corresponding to the measurement point in the lidar power spectrum. B w ,when B w Less than the preset experience value B thr If the measurement point is unaffected by the wake vortex, then the location of the aircraft wake vortex core is considered to be unaffected. X 1, X 2, Y 1, Y 2) Radius of the aircraft's tail vortex core ( r c1 , r c2 Make estimates and complete the preparation phase.

[0008] 2) Actual wind speed at measurement point A within the influence area of ​​the wake vortex V A It consists of the following components: background wind speed ( U air , Vair , W air ), LiDAR movement speed V Lidar The wake vortex velocity and turbulent disturbances caused by the interaction between aircraft wake vortices; where the wake vortex velocity can be determined by the intensity of the left and right vortex circulation. C 1 and C 2. Calculated;

[0009] The wind speed at any measurement point A within the influence range of the wake vortex. V A Perform vector decomposition: wind speed from point A towards the center of the vortex core. W Wind speed in the direction of the aircraft's flight V Wind speed in the tangential direction of the aircraft's wake vortex U At this time, the measured radial wind speed V LA It can be represented as:

[0010]

[0011] wind speed W , V , U Through the coordinates of the center of the left tail vortex core ( X 1， Y 1) Coordinates of the center of the vortex core on the right side of the aircraft ( X 2， Y 2) Coordinates of measurement point A ( X 3， Y 3) Background wind speed ( U air , V air , W air ), the speed of the aircraft's wake vortex along the direction of flight V wv Circulation intensity value of the left vortex C 1. Radius of the vortex core r c1 Circulation intensity value of the right vortex C 2. Vortex core radius r c2 To characterize, where r c1 Approximately equivalent to r c2 The two are based on r c express;

[0012] 3) Utilize measurements in non-wake vortex regions to eliminate the influence of background wind speed and lidar motion speed, i.e., along... The radial wind speed is measured at a point A' located away from the core of the aircraft's wake vortex. V LA' It can be represented as:

[0013]

[0014] At this point, the radial velocity difference measured at points A and A' is calculated. V L(A-A') It can remove the corresponding background wind speed and lidar motion speed items, while the speed of the aircraft's wake vortex along the aircraft's flight direction can be removed. V wv It can be approximated as the speed of an airplane, in which case the equation does not contain any division. C 1 and C Unknown parameters other than 2;

[0015] 4) Using step 3), the difference in radial velocity between two measurement points inside and outside the influence range of the wake vortex in the same laser emission direction can be expressed as the value to be determined. C 1. C The function of 2; the turbulent disturbance is weakened by multiple measurements within the influence range of the wake vortex, and then the solution is obtained by least squares fitting. C 1 and C 2. The range of the aircraft wake vortex circulation intensity values ​​obtained by the solution is limited to [0, 1000]. At this time, a pair of wake vortex circulation intensity values ​​can be obtained under the given parameters. C 1, C 2) Achieve rapid inversion of aircraft wake vortex parameters.

[0016] The method also includes step 5) adjusting the position of the aircraft wake vortex core in the initial parameters ( X 1, Y 1, X 2, Y 2) Result correction: As the position of the aircraft wake vortex core changes, a series of wake vortex circulation intensity values ​​can be obtained ( C m1 , C m2 ); Set evaluation parameters

[0017]

[0018] Where sign represents the sign function. n 1 can be set to 0.4. n 2 can be set to 0.7. s It can be set at 500. d It can be set to 2500, and the parameter value can be adjusted according to the actual situation; select QThe location of the aircraft wake vortex core and the aircraft wake vortex annulus value under the maximum value are output results.

[0019] In step 5), the position of the aircraft tail vortex core in the initial parameters is adjusted. X 1, Y 1, X 2, Y 2) Adjustments are made at 4 m intervals along the horizontal axis, with an adjustment range of ±8 m; adjustments are made at 2 m intervals along the vertical axis, with an adjustment range of ±4 m. The specific values ​​can be adjusted according to the actual situation.

[0020] In step 2), the coordinates of the center of the left tail vortex core are used ( X 1， Y 1) Coordinates of the center of the vortex core on the right side of the aircraft ( X 2， Y 2) Coordinates of measurement point A ( X 3， Y 3) Background wind speed ( U air , V air , W air ), the speed of the aircraft's wake vortex along the direction of flight Circulation intensity value of the left vortex C 1. Radius of the vortex core r c1 Circulation intensity value of the right vortex C 2. Vortex core radius r c2 Wind speed for characterization W , V , U as follows:

[0021]

[0022] in, V wv It can be approximated as the speed of an airplane.

[0023] In step 3), the radial velocity difference V L(A-A') = V ΔL This can be represented as follows:

[0024]

[0025]

[0026]

[0027] in, V wv This can be approximated as the aircraft's flight speed; in the RHI (Range Height Indicator) scanning mode commonly used for aircraft wake vortices, α Since the angle is 90°, this item can be ignored.

[0028] because( X 1, Y 1, X 2, Y 2, X3, Y3 α , θ,r c It is known that the above formula can be simplified to:

[0029]

[0030]

[0031] .

[0032] In step 4),

[0033] The radial velocity difference V between two measurement points inside and outside the vortex influence domain along the same laser beam emission direction is... ΔL Through the unknown parameter wake circulation ( C 1， C 2 ) and known parameters ( l, x ) represents Among them, the known parameters are ( l, x The value is composed of the aircraft wake vortex core position, the measurement point position, the aircraft wake vortex core radius, and the laser emission azimuth and elevation angles.

[0034]

[0035] To reduce the interference effect of turbulent disturbances on the flow field parameter measurement, the sampling data volume is set. k ≥20, meaning that statistically stable flow field parameters are obtained through repeated measurements; under this condition, the number of equations exceeds the number of unknown parameters ( C 1, C 2) The number of equations forms an overdetermined system, so the least squares method can be used for parameter fitting to obtain the solution. C 1, C 2) The optimal estimate. The range of the aircraft wake vortex circulation intensity value obtained by the solution is limited to [0, 1000] (this intensity range can be adjusted by the theoretical calculation formula of the initial wake vortex intensity). At this time, a pair of wake vortex circulation intensity values ​​can be obtained under the given parameters. C 1, C 2) Complete the model establishment and inversion work.

[0036] In step 1), the lidar system installed on the mobile platform includes an airborne lidar system, a shipborne lidar system, and a vehicle-mounted lidar system; the lidar is a coherent Doppler lidar (CDL).

[0037] In step 1), the threshold line L thr Take 0.17 times the maximum peak signal strength.

[0038] In step 1), the preset experience value is taken as... B thr =10.

[0039] In step 1), the rotational characteristics of the wake vortex (when viewed from behind the aircraft, the right wingtip vortex rotates counterclockwise, and the left wingtip vortex rotates clockwise, forming a coaxial, opposite-rotating double helix structure) or the principle of aircraft wake vortex generation (aircraft wake vortices are generated at approximately π / 4 of the wing) are used to determine the location of the wake vortex core. X 1, X 2, Y 1, Y 2) Make a prediction, using the velocity envelope method to estimate the radius of the aircraft wake vortex core ( r c1 , r c2 ) to make a forecast.

[0040] In step 2), the wind speeds W, V, and U are expressed through the coordinates (X) of the center of the left-side wake vortex core. 1， Y1), coordinates of the center of the right tail vortex core of the aircraft (X) 2， Y2), coordinates of measurement point A (X 3， Y3), background wind speed (U) air V air W air ), the velocity Vwv of the aircraft wake vortex along the direction of aircraft flight, the circulation intensity Γ1 of the left vortex, and the radius r of the vortex core. c1 The circulation intensity value Γ2 of the right vortex, and the vortex core radius r c2 Characterization is performed. In addition to the idealized aircraft wake vortex model, the aircraft wake vortex dissipation and transport model can also be used.

[0041] The main advantages of this invention compared to existing methods are:

[0042] 1. Building upon existing research on aircraft wake vortices, this study reconstructs actual aircraft wake vortices using an idealized model and establishes a correlation between the aircraft wake vortex circulation and the radial velocity measured by lidar. Least squares fitting is performed using sampling points at multiple locations to reduce turbulence interference and mitigate the impact of reduced data density in the detection space and incomplete wake vortex structure on the detection results.

[0043] 2. Breaking through the limitations of traditional RHI (Radar Induction Heliographies) observation modes for aircraft wake vortices, the scanning methods are more diverse, reducing measurement errors caused by the movement of wake vortices during lidar scanning. Furthermore, it can assess the position and intensity of aircraft wake vortices not only from complete wake vortex segments, significantly improving the speed of acquiring characteristic parameters. Simultaneously, it utilizes changes in the circulation of the aircraft wake vortex to correct the position of the vortex core, further improving the accuracy of wake vortex core localization. Attached Figure Description

[0044] Figure 1 Flowchart of the rapid inversion method for aircraft wake vortex parameters based on mobile platform laser remote sensing of the present invention.

[0045] Figure 2 A schematic diagram showing the relationship between the airborne lidar and the aircraft's wake vortex.

[0046] Figure 3 Schematic diagram of vortex core position estimation (rotation feature prediction).

[0047] Figure 4 A schematic diagram of the spatial positioning results of the wake vortex core based on rotational feature calculation.

[0048] Figure 5 A schematic diagram of the spatial localization results of the wake vortex core based on the Q-maximum principle.

[0049] Figure 6 Simulation results of LiDAR RHI scanning. Detailed Implementation

[0050] To enable those skilled in the art to better understand the present invention, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. See also Figure 1 In this embodiment of the invention, a method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing includes:

[0051] 1. This invention is illustrated using an aircraft as a mobile platform (airborne, shipborne, vehicle-mounted, etc.), in which case an airborne lidar system is employed. The airborne lidar system is mounted on the aircraft wing and scans backward; the laser beam passes through both the wake vortex-affected and non-wake vortex-affected areas. A schematic diagram illustrating the positional relationship between the lidar and the aircraft's wake vortex is shown below. Figure 2As shown, point L is the location where the lidar is deployed, and point L is used as the reference point. The vortex core spacing of the aircraft's wake vortex is... B The lidar system along A laser beam is emitted in a certain direction. Point A is a measurement point within the influence area of ​​the wake vortex. At this time, the distance between the line connecting point A and the center of the vortex core is... r The laser emission azimuth angle is α Angle of elevation is i .

[0052] First, the scanning data from the Coherent Doppler Lidar (CDL) is preprocessed to perform noise reduction and quality control. Then, based on a set threshold... L thr (e.g., 0.17 times the maximum peak signal strength) Measure its corresponding spectral width B w .when B w Less than one experience value B thr If (e.g., 10), then the region is considered unaffected by the wake vortex. Because the wake vortex influence region exhibits spectral width enhancement, the wake vortex influence region is identified based on this spectral width. Then, the location of the wake vortex core is determined using the wake vortex's rotational characteristics or the principle of wake vortex generation (aircraft wake vortices are generated approximately at π / 4 of the wing). X 1, X 2, Y 1, Y 2) Radius of the aircraft's tail vortex core ( r c1 , r c2 Make estimates and complete the preparation phase.

[0053] 2. Based on the principle of vector decomposition, the wind speed at point A is... V A Perform vector decomposition: wind speed from point A towards the center of the vortex core. W Wind speed in the direction of the aircraft's flight V Wind speed in the tangential direction of the aircraft's wake vortex U The radial wind speed measured by lidar is obtained by using the three decomposed wind speed vectors. V LA Characterization, the radial wind speed measured at this time V LA It can be represented as:

[0054]

[0055] and V AIt consists of the following components: background wind speed ( U air , V air , W air ), LiDAR movement speed V Lidar Interaction between aircraft wake vortices and turbulent disturbances.

[0056] Using the WAU plane as the reference coordinate system, and the projection of point L onto this plane as the origin, the coordinates of the center of the vortex core on the left side of the aircraft are marked as ( X 1， Y 1), The coordinates of the center of the vortex core on the right side of the aircraft are marked as ( X 2， Y 2), the measurement point location A is denoted as ( X 3， Y 3). The circulation intensity value of the left vortex is... C 1. The radius of the vortex core is r c1， The circulation intensity of the right vortex is C 2, the radius of the vortex core is r c2 ,in r c1 Approximately equivalent to r c2 The two are based on r c express.

[0057] 3. Use the circulation value of the wake vortex ( C 1, C 2) Location of the vortex core center of the wake vortex ( X 1, X 2, Y 1, Y 2) Scan configuration parameters ( α , i This can achieve the decomposition of wind speed vectors at point A within the wake vortex influence area. W, U, V This allows for the characterization of the radial wind speed measured by lidar, and thus enables the determination of the radial wind speed. V LA Characterization. The quantitative mapping model between the wake circulation and the radial velocity measured by lidar can then be expressed as:

[0058]

[0059] in, V wv It can be approximated as the speed of an airplane.

[0060] 4. Utilize measurements in non-wake regions to eliminate the influence of background wind and lidar velocity, i.e., along... The radial wind speed is measured at a point A' located away from the core of the aircraft's wake vortex. V LA' It can be represented as:

[0061]

[0062] At this point, the radial velocity difference measured at points A and A' is calculated. V L(A-A') The corresponding background wind speed and lidar motion speed items can be removed, as shown below:

[0063]

[0064]

[0065]

[0066] because( X 1, Y 1, X 2, Y 2, X3, Y3 α , θ,r c It is known that the above formula can be simplified to:

[0067]

[0068]

[0069] .

[0070] 5. The radial velocity difference V between two measurement points inside and outside the vortex influence domain along the same laser beam emission direction. ΔL Through the unknown parameter wake circulation ( C 1 , C 2 ) and known parameters ( l , x ) is represented as: Among them, the known parameters are ( l , x The value is composed of the aircraft wake vortex core position, the measurement point position, the aircraft wake vortex core radius, and the laser emission azimuth and elevation angles.

[0071]

[0072] To reduce the interference effect of turbulent disturbances on the flow field parameter measurement, the sampling data volume is set. k≥20, meaning that statistically stable flow field parameters are obtained through repeated measurements; under this condition, the number of equations exceeds the number of unknown parameters ( C 1, C 2) The number of equations forms an overdetermined system, so the least squares method can be used for parameter fitting to obtain the solution. C 1, C 2) The optimal estimate. The range of the aircraft wake vortex circulation intensity value obtained by the solution is limited to [0, 1000] (this intensity range can be adjusted by the theoretical calculation formula of the initial wake vortex intensity). At this time, a pair of wake vortex circulation intensity values ​​can be obtained under the given parameters. C 1, C 2) Complete the model establishment and inversion work.

[0073] 6. Finally, the results are corrected. This is done by adjusting the position of the aircraft wake vortex core in the initial parameters ( X 1, Y 1, X 2, Y 2) Adjustments are made at 4-m intervals along the horizontal axis, with an adjustment range of ±8 m. Adjustments are also made at 2-m intervals along the vertical axis, with an adjustment range of ±4 m. The adjustment intervals and ranges can be adjusted according to the scanning resolution and computation time requirements. As the position of the aircraft wake vortex core changes, a series of wake vortex circulation intensity values ​​can be obtained. C m1 , C m2 Set evaluation parameters.

[0074]

[0075] Where sign represents the sign function. n 1 can be set to 0.4. n 2 can be set to 0.7. s It can be set at 500. d It can be set to 2500, and the parameter value can be adjusted according to the actual situation. Select Q The location of the aircraft wake vortex core and the aircraft wake vortex annulus value under the maximum value are output results.

[0076] Example 1

[0077] 1. Taking the lidar position L as the reference point (0, 0), the laser emission azimuth angle is... α The angle is 90°, and the elevation angle is... i Scan from 0.14° to 10° with a step size of 0.2°.

[0078] 2. Using 0.17P max (i.e., 0.17 times the maximum peak signal strength) is the threshold line standard Lthr The influence area of ​​the wake vortex is delineated. The location of the wake vortex core is predicted using the vortex's rotational characteristics, i.e., ... Figure 3 As shown, , , , , estimated r c =3 m.

[0079] 3. Characterize the wind speed at any measurement point A within the influence range of the wake vortex, such as (490, 55). At this point, θ is 6.4°, azimuth α is 90°, X3=490, Y3=55. Then...

[0080]

[0081] 4. Utilize measurements in non-wake vortex regions to eliminate the influence of background wind and lidar velocity. For example, at point (98, 11), θ is 6.4° and azimuth α is 90°. Since this location is far from the wake vortex influence, and θ and α are the same, the radial velocity difference between the two is... .

[0082] 5. Repeat the above steps to obtain a series of radial velocity differences, which will form an overdetermined system of equations. Then, solve for Γ1 = 449.2 m. 2 / s, Γ2=236.8 m 2 / s. Wake vortex location information as follows Figure 4 As shown.

[0083] 6. By adjusting the position of the aircraft's tail vortex core in the initial parameters ( X 1, Y 1, X 2, Y 2) Select the aircraft wake vortex core position and aircraft wake vortex circulation value under the condition of maximum Q as the output results. At this time, the wake vortex core position coordinates ( X 1, Y 1, X 2, Y 2) Corresponding to (495.4, 57.8, 514.3, 59.2), circulation value ( C 1, C 2) Corresponding to (553.2, 529.6). The wake vortex position information at this time is as follows: Figure 5 As shown. After adjustment, the vertical height difference between the left and right vortex cores is smaller. Closer heights indicate better vortex core symmetry and a more physically accurate positioning (such as the symmetry assumption of the wake vortex), reducing inversion errors caused by height deviations. Furthermore, the circulations are closer, consistent with the characteristic of similar wake vortex intensities. In addition, from Figure 5It is evident that this method is more suitable for parameters at the current vortex scale. Therefore, the method presented in this paper can effectively achieve accurate inversion and correction of aircraft wake vortex parameters, providing scientific and reliable data support for aviation safety and aircraft collaborative operations.

[0084] Example 2

[0085] 1. Simulation of lidar scanning is performed using a background wind field superimposed with a wake vortex model. First, the aircraft's model parameters and wake vortex location information are input. The aircraft parameters are as follows: aircraft weight 73500 kg, gravitational acceleration 9.8 m / s². 2 The aircraft has a flight speed of 75 m / s, a shape parameter of pi / 4, a wingspan of 34.09 m, and an air density of 1.225 kg / m³. 3 The vortex core radius is 4m. Location information of the wake vortex ( X 1, Y 1, X 2, Y 2) is (497, 22, 532, 17). At this time, the circulation values ​​of the two vortex cores are ( C 1, C 2) Corresponds to (293, 293). Simulation results are as follows: Figure 6 As shown.

[0086] 2. Repeat the steps in Case 1 to obtain a series of radial velocity differences and construct an overdetermined system of equations. Select the aircraft wake vortex core position and wake vortex circulation value at the maximum Q value as the output. The coordinates of the wake vortex core position at this time are ( X 1, Y 1, X 2, Y 2) Corresponding to (495, 23, 532, 18), circulation value ( C 1, C 2) The corresponding value is (256, 277). The calculation time is 1.3s, and it shows high consistency with the input simulation parameters.

Claims

1. A method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing, characterized in that Comprising the steps of: 1) The laser radar system installed on the mobile platform scans the wake vortex influence area or the warning trigger area, the laser emission azimuth angle is α , and the elevation angle is Theta ; first, the measurement data of the laser radar is denoised and quality controlled; then, based on the set threshold line L th In the power spectrum of the laser radar, the corresponding spectral width of the measurement point is determined B w When B w is less than the preset empirical value B thr , it is considered that the measurement point is not affected by the wake vortex; then, the aircraft wake vortex core position (x X 1, X 2, Y 1, Y 2) and the aircraft wake vortex core radius (r r c1 , r c2 ) are estimated, and the preparation stage work is completed; 2) Real wind speed at measuring point A in the wake vortex influence area V A Background wind speed (Vb) U air , V air , W air Laser radar moving speed (Vl) V Lidar Wake vortex moving speed and turbulence disturbance caused by the interaction of the aircraft wake vortex; wherein the wake vortex moving speed can be calculated by the left and right vortex ring intensity Gamma 1 and Gamma 2 The wind speed at any measuring point A located within the wake influence range V A The vector decomposition is performed: the wind speed from the point A to the direction of the vortex core center W ; the wind speed in the forward direction of the aircraft V ; the wind speed in the tangential direction of the aircraft wake U ; at this time, the measured radial wind speed V LA can be expressed as: The wind speed W , V , U The vortex core center coordinates of the left side tail vortex (x X 1, Y 1), the vortex core center coordinates of the right side tail vortex (x X 2, Y 2), the coordinate of the measuring point A (x X 3, Y 3), the background wind speed (u U air , V air , W air ), the speed of the aircraft tail vortex along the flight direction of the aircraft (u V wv , the circulation intensity value of the left vortex (γ Gamma 1, the vortex core radius (r r c1 , the circulation intensity value of the right vortex (γ Gamma 2, the vortex core radius (r r c2 are characterized, wherein r c1 approximately equal to r c2 , both are expressed as r c ; 3) The influence of background wind speed and the velocity of the laser radar is eliminated by measuring in the non-tail vortex area, i.e. a point A' far from the position of the tail vortex core is obtained along the The radial wind speed measured at the point A' can be expressed as: V LA' ​ The radial velocity difference measured at points A and A' is calculated at this time V L(A-A') The corresponding background wind speed term and the lidar motion speed term can be removed, while the speed of the aircraft wake vortex along the flight direction of the aircraft V wv Approximately equal to the flight speed of the aircraft, at this time, the equation does not contain unknown parameters other than Gamma 1 and Gamma 2; 4) Using step 3), the difference between the radial velocities of the two measuring points within and outside the range of the wake vortex influence in the same laser emission direction can be expressed as a function of the to-be-solved values Gamma 1, Gamma 2; the turbulent disturbance weakens its influence through multiple measurements within the range of the wake vortex influence, and then a least squares fitting is performed to solve Gamma 1and Gamma 2, and the range of the vortex strength values of the aircraft wake obtained by solving is limited to [0, 1000], at which time a pair of vortex strength values of the aircraft wake ( Gamma 1, Gamma 2) can be solved under given parameters to achieve rapid inversion of the parameters of the aircraft wake.

2. The method of claim 1, wherein the method further comprises: determining the wake vortex parameters based on the laser remote sensing data. The method further comprises a step 5) of modifying the results by adjusting the initial parameters of the position of the vortex core of the aircraft wake ( X 1, Y 1, X 2, Y 2) of the position of the vortex core of the aircraft wake, a series of wake circulation intensity values can be solved ( Gamma m1 , Gamma m2 ) evaluation parameters where sign denotes the sign function, n 1 can be set to 0.4, n 2 can be set to 0.7, s can be set to 500, d can be set to 2500, wherein the parameter values can be adjusted according to actual situations; selection Q The position of the aircraft wake vortex core and the circulation value of the aircraft wake vortex in the maximum value case are taken as the output results.

3. The method of claim 2, wherein the method further comprises: determining the wake vortex parameters based on the laser remote sensing data. In the step 5), the position of the vortex core of the aircraft wake vortex in the initial parameters is adjusted X 1, Y 1, X 2, Y 2) is adjusted at intervals of 4 m in the horizontal coordinate direction, and the adjustment range is ±8 m; and is adjusted at intervals of 2 m in the vertical coordinate direction, and the adjustment range is ±4 m.

4. The method of claim 1, wherein the method further comprises: In the step 2), the vortex core center coordinates of the left side tail vortex are calculated by X 1, Y 1) the vortex core center coordinates of the right side tail vortex of the airplane X 2, Y 2) the coordinate of the measuring point A X 3, Y 3) the background wind speed U air , V air , W air the speed of the airplane tail vortex along the flight direction of the airplane the circulation intensity value of the left vortex Gamma 1, the vortex core radius r c1 the circulation intensity value of the right vortex Theta, r 2, the vortex core radius r c2 the wind speed to be characterized W , V , U as follows: wherein V wv may be approximately equal to the speed of flight of the aircraft.

5. The method of claim 4, wherein the method further comprises: In the step 3), the radial velocity difference V L(A-A') = V ΔL is expressed by: wherein, V wv may be approximately equivalent to the flight speed of the aircraft; in the RHI scan mode commonly used for aircraft wake vortices, α is 90°, so this term can be neglected; Because (1 X 1, Y 1, X 2, Y 2, X3, Y3, α , In step 4), c ) is known, the above formula can be simplified as: 。 6. The method of claim 5, wherein the method further comprises: Gamma The radial velocity difference V ΔL The unknown parameter wake vortex circulation (C , Gamma 1 Lambda, xi 2 ) and the known parameter (K Lambda, xi ) are expressed as Where the known parameter (K Gamma ) is composed of the wake vortex core position of the aircraft, the measuring point position, the wake vortex core radius of the aircraft, the laser emission azimuth angle and the elevation angle. To reduce the interference effect of turbulent disturbance on the measurement of flow field parameters, the amount of sampling data is set k ≥20, that is, the flow field parameters with statistical stability are obtained by repeated measurement; under this condition, the number of equation groups exceeds the number of unknown parameters ( Gamma 1, Gamma 2), forming an overdetermined equation group, so the least square method can be used for parameter fitting, so that the optimal estimated value of ( Gamma 1, In step 1), the laser radar system installed on the mobile platform comprises an airborne laser radar system, a shipborne laser radar system, and a vehicle-mounted laser radar system; and the laser radar is a coherent Doppler laser radar. 2) is obtained.

7. The method of claim 1, wherein the method further comprises: determining the wake vortex parameters based on the laser remote sensing data. ​ 8. The method of claim 1, wherein the method further comprises: determining the wake vortex parameters based on the laser remote sensing data. In the step 1), the threshold line L thr Take 0.17 times of the maximum peak signal intensity.

9. The method of claim 1, wherein the method further comprises: determining the wake vortex parameters based on the laser remote sensing data. In the step 1), the preset experience value is taken as B thr = 10.

10. The method of claim 1, wherein the method further comprises: determining the wake vortex parameters based on the laser remote sensing data. In the step 1), the position of the vortex core of the tail vortex is estimated by using the rotation characteristics of the tail vortex or the generation principle of the tail vortex of the aircraft X 1, X 2, Y 1, Y 2) is estimated by using the velocity envelope method. r c1 , r c2 ) is estimated by using the velocity envelope method.

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