Airplane trailing vortex parameter rapid inversion method based on mobile platform laser remote sensing

Abstract

An aircraft trailing vortex parameter rapid inversion method based on mobile platform laser remote sensing comprises the steps that a laser radar system scans a trailing vortex influence area, and measurement data is subjected to quality control processing; estimating the position and radius of the vortex core of the trailing vortex of the aircraft; performing vector decomposition on the wind speed of any measurement point A in the trailing vortex range, and representing the wind speeds W, V and U through parameters such as trailing vortex circular rector; eliminating the influence of background wind speed and laser radar movement speed by using a non-trailing vortex region measurement point; the difference of the radial speeds of the two measuring points inside and outside the trailing vortex influence range in the same laser emission direction is expressed as a trailing vortex circular rector function; the influence of turbulence disturbance is weakened through multiple times of measurement within the trailing vortex influence range, and then the trailing vortex circular rector is solved through least square fitting. According to the method, accurate inversion and correction of the trailing vortex parameters of the aircraft can be realized through less observation data. The calculation result is fast and accurate, and scientific and reliable data support can be provided for aviation safety and aircraft collaborative 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: 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... 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. 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 , V air , Wair ), 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; 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: 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; 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: 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; 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.

[0007] 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 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.

[0008] In step 5), the position of the aircraft tail vortex core in the initial parameters is adjusted ( X 1, Y 1, X 2, Y2) 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.

[0009] 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: in, V wv It can be approximated as the speed of an airplane.

[0010] In step 3), the radial velocity difference V L(A-A') = V ΔL This can be represented as follows: 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. because( X 1, Y 1, X 2, Y2, X3, Y3 α , θ,r c It is known that the above formula can be simplified to: .

[0011] In step 4), 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. 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 of equations, 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.

[0012] 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).

[0013] In step 1), the threshold line L thr Take 0.17 times the maximum peak signal strength.

[0014] In step 1), the preset experience value is taken as... B thr=10.

[0015] 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.

[0016] 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.

[0017] The main advantages of this invention compared to existing methods are: 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.

[0018] 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

[0019] Figure 1Flowchart of the rapid inversion method for aircraft wake vortex parameters based on mobile platform laser remote sensing of the present invention.

[0020] Figure 2 A schematic diagram showing the relationship between the airborne lidar and the aircraft's wake vortex.

[0021] Figure 3 Schematic diagram of vortex core position estimation (rotation feature prediction).

[0022] Figure 4 A schematic diagram of the spatial positioning results of the wake vortex core based on rotational feature calculation.

[0023] Figure 5 A schematic diagram of the spatial localization results of the wake vortex core based on the Q-maximum principle.

[0024] Figure 6 Simulation results of LiDAR RHI scanning. Detailed Implementation

[0025] 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: 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 2 As 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 .

[0026] 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 Bthr 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.

[0027] 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: and V A It 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.

[0028] 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.

[0029] 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: in, V wv It can be approximated as the speed of an airplane.

[0030] 4. Utilize measurements in non-wake vortex 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: 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: 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: .

[0031] 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. 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 of equations, 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.

[0032] 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. 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.

[0033] Example 1 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°.

[0034] 2. Using 0.17P max (i.e., 0.17 times the maximum peak signal strength) is the threshold line standard L thr 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.

[0035] 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...

[0036] 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... .

[0037] 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.

[0038] 6. By adjusting the position of the aircraft's tail vortex core in the initial parameters ( X 1, Y 1, X 2, Y2) 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 5 It 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.

[0039] Example 2 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.

[0040] 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, C2) 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 rapid inversion method for aircraft wake vortex parameters based on mobile platform laser remote sensing, characterized by: Includes the following steps: 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 θ 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 ( 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. 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 , V air , 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. Γ 1 and Γ 2. Calculated; 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: 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 Γ 1. Vortex core radius r c1 Circulation intensity value of the right vortex Γ 2. Vortex core radius r c2 To characterize, where r c1 Approximately equivalent to r c2 The two are based on r c express; 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: 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. Γ 1 and Γ Unknown parameters other than 2; 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. Γ 1. Γ 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. Γ 1 and Γ 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. Γ 1, Γ 2) Achieve rapid inversion of aircraft wake vortex parameters.

2. The method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 1, characterized in that: 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 ( Γ m1 , Γ m2 ); Set evaluation parameters Where sign represents the sign function. n 1 can be defined as 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.

3. The rapid inversion method for aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 2, characterized in that: 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 4m intervals along the horizontal axis, with an adjustment range of ±8m; adjustments are made at 2m intervals along the vertical axis, with an adjustment range of ±4m.

4. The method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 1, characterized in that: 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 Γ 1. Vortex core radius r c1 Circulation intensity value of the right vortex Γ 2. Vortex core radius r c2 Wind speed for characterization W , V , U as follows: in, V wv It can be approximated as the speed of an airplane.

5. The rapid inversion method for aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 4, characterized in that: In step 3), the radial velocity difference V L(A-A') =V ΔL This can be represented as follows: in, V wv It can be approximated as the aircraft's flight speed; in the RHI scan mode commonly used for aircraft wake vortices, α Since the angle is 90°, this item can be ignored. 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: 。 6. The method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 5, characterized in that: In step 4), 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 ( Γ 1 ,Γ 2 ) and known parameters ( λ,ξ ) represents Among them, the known parameters are ( λ,ξ 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. 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 ( Γ 1, Γ 2) The number of equations forms an overdetermined system, so the least squares method can be used for parameter fitting to obtain the solution. Γ 1, Γ 2) The optimal estimate.

7. The method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 1, characterized in that: 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.

8. The method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 1, characterized in that: In step 1), the threshold line L thr Take 0.17 times the maximum peak signal strength.

9. The method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 1, characterized in that: In step 1), the preset experience value is taken as... B thr =10.

10. The method for rapid inversion of aircraft wake vortex parameters based on mobile platform laser remote sensing as described in claim 1, characterized in that: In step 1), the position of the vortex core is determined by utilizing the rotational characteristics of the wake vortex or the generation principle of aircraft wake vortices. 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.

Images