CN114265068A - Reactive wind shear false alarm suppression method fusing meteorological radar information - Google Patents
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Abstract
The invention provides a reactive wind shear false alarm suppression method fusing meteorological radar information, which comprises the following steps of: firstly, carrying out wind field inversion on wind field information; step two, introducing wind field information to judge turbulence, correcting integral duration and extracting a predicted wind shear F factor; calculating a reactive wind shear F factor according to a reactive wind shear mode, and comparing the reactive wind shear F factor with an alarm threshold to obtain a wind shear alarm result; calculating and comparing the reactive wind shear F factor and an F factor of an airplane position point in wind field inversion, if the integral average difference value of the reactive wind shear F factor and the predicted wind shear F factor is larger than tolerance, detecting the maneuver type, and finishing the correction of the reactive wind shear F factor; generating a wind shear alarm if the integral average difference of the reactive wind shear F factor and the F factor of the aircraft position point in the wind field inversion is less than the tolerance; and step five, obtaining the corrected F factor.
Description
Technical Field
The invention relates to the technical field of radar, in particular to a reactive wind shear false alarm suppression method fusing meteorological radar information.
Background
Wind shear detection systems are classified into two broad categories, predictive (forward looking) and reactive (present-state) according to the alarm principle. Wind shear characteristic parameters such as echo power, Doppler wind speed and spectral width are extracted from radar echoes based on a predictive wind shear function of the airborne weather radar so as to judge the existence of wind shear and the danger degree of the wind shear, and the wind shear information on a distant navigation path can be detected.
The reactive wind shear is that when the aircraft is in a wind shear wind field, the current windward wind speed change rate and the vertical wind speed of the aircraft are calculated through the airspeed, the attack angle and the sideslip angle provided by an Atmospheric Data Computer (ADC) and the aircraft speed and attitude information provided by an Inertial Reference System (IRS), the hazard degree of the low altitude wind shear is judged through a hazard factor F, and warning information is sent to a pilot.
Reactive wind shear has certain limitations if the standard F-factor method is adopted, which is particularly characterized in that the method is easily influenced by turbulence to generate a wind shear false alarm, and in addition, the maneuvering action of the airplane during the flight process also generates the wind shear false alarm.
Disclosure of Invention
In view of this, embodiments of the present disclosure provide a reactive wind shear false alarm suppression method fusing weather radar information, so as to achieve the purpose of reducing the reactive wind shear false alarm rate.
The embodiment of the specification provides the following technical scheme: a reactive wind shear false alarm suppression method fusing meteorological radar information comprises the following steps:
firstly, carrying out wind field inversion on wind field information;
step two, introducing wind field information to judge turbulence, correcting integral duration and extracting a predicted wind shear F factor;
calculating a reactive wind shear F factor according to a reactive wind shear mode, and comparing the reactive wind shear F factor with an alarm threshold to obtain a wind shear alarm result;
calculating and comparing the reactive wind shear F factor with an F factor of an airplane position point in wind field inversion, and if the integral average difference value of the reactive wind shear F factor and the predicted wind shear F factor is larger than the tolerance, performing maneuver type detection by a reactive wind shear module and finishing the correction of the reactive wind shear F factor; generating a wind shear alarm if the integral average difference of the reactive wind shear F factor and the F factor of the aircraft position point in the wind field inversion is less than the tolerance;
and step five, based on the time interval sensitivity characteristic, obtaining a corrected F factor through the weighted fusion of the predicted wind shear F factor and the reactive wind shear F factor, and executing the step three again and giving a wind shear alarm result.
Further, the first step comprises:
step 1.1, defining wind field information obtained from the predictive wind shear in a radar coordinate system with an airplane position as an origin, wherein each node comprises horizontal wind speed, vertical wind speed, F factors and turbulence characteristic value information;
step 1.2, determining a longitude and latitude range of the prediction type wind shear forward-looking detection according to the airplane position, the heading information and the detection distance, taking set three points in the prediction type wind shear forward-looking detection range, converting the set three points into longitude and latitude values in an ink card support projection mode, and taking the maximum and minimum value of the longitude and latitude as a boundary value of the prediction type wind shear forward-looking detection range;
step 1.3, carrying out grid division on an area in a space range of the forecast type wind shear foresight detection to form a longitude and latitude grid, and filling the forecast type wind shear detection result into the longitude and latitude grid.
Further, the second step is specifically as follows: and B, according to the position of the airplane, searching corresponding position information in the longitude and latitude grid formed in the step one, checking whether turbulent flow information exists at the position of the airplane in the longitude and latitude grid, adjusting the integration time of the reactive wind shear F factor according to the characteristic value of turbulent flow, and extracting a predicted wind shear F factor.
Further, the third step specifically comprises:
step 3.1, reactive wind shear F factor according to formula
Performing a calculation in which
For the horizontal component of the wind along the flight path, W is the vertical component of the wind, VaIs airspeed, g is acceleration of gravity;
and 3.2, comparing the integral average value of the reactive wind shear F factor for a period of time with an alarm threshold and giving an alarm result.
Further, the fourth step includes: and 4.1, calculating difference integral average numbers of the reactive wind shear F factor and the predicted wind shear F factor, and comparing the difference integral average numbers with a judgment threshold to determine whether the maneuvering action influence exists.
Further, the fourth step includes: step 4.2, if there is a maneuver impact, comprising the steps of:
the method comprises the following steps of qualitatively analyzing the variation trend of flight parameters under different maneuvering types aiming at the variation characteristics of the flight parameters under the wind shear environment;
according to the flight parameter variation trend under different maneuver types, establishing a matrix A1 ═ a of the occurrence probability of each maneuver1 a2 a3 a4 a5 a6]Wherein a is1～a6Representing the probability of the maneuver occurring at the current flight phase of the aircraft;
establishing a matrix B1 ═ B according to the similarity of maneuver types and flight parameters in a wind shear environment1 b2 b3 b4b5 b6]Wherein b is1～b6Representing the probability of the maneuver identified to occur based on the aircraft parameters.
According to A1 ═ a1 a2 a3 a4 a5 a6]And B1 ═ B1 b2 b3 b4 b5 b6]Judging the occurrence factor lambda f (A) of each current maneuvering type of the airplane1，B1)；
Obtaining an experience influence factor f of the current maneuver according to a lookup maneuver type library table;
obtaining a large maneuvering influence factor according to the empirical influence factor, the generating factor and the maneuvering influence correction function Fun ═ Fun (f, lambda);
by F1＝Fun·F1Obtaining a modified reactive wind shear F1A factor.
Further, the fourth step further comprises: and 4.3, if no maneuvering action influence exists, generating a wind shear alarm.
Further, the fifth step comprises:
by Fmix(t)＝kF1(t)+(1-k)F2(t) weighted fusion of the predicted and reactive wind shear F-factors, wherein F2(t) is the predicted wind shear F factor, k ═ t1-t)/(t1-t0) T is the time when the wind field information of the position is obtained by the predicted wind shear, t0Calculating the starting time, t, for the fusion1The starting time of the detection blind area;
by passing
Integral calculation and corrected F factor, t2Is the current time;
and comparing and judging the corrected F factor with an alarm threshold and generating an alarm result.
Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise: in order to reduce turbulence in reactive wind shear and wind shear false alarms caused by maneuvering actions and improve the performance of reactive wind shear alarms, a wind field detected by a weather radar is introduced into a ground proximity alarm system to carry out wind field inversion, and wind field data are arranged into a data form convenient to use for reactive wind shear. And correcting the integral time of the current F factor calculation by using the turbulence characteristics of the detected wind field information at the reactive wind shear alarm processing stage, and reducing the F factor contribution caused by disturbance as much as possible. In addition, large maneuvering action influence factors are combined in reactive wind shear alarm processing, different weight ratio prediction type wind shear F factors and reactive wind shear F factors are calculated based on time interval sensitivity, and false alarm probability is effectively reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic flow diagram of an embodiment of the present invention;
FIG. 2 is a reactive wind shear false alarm suppression functional architecture diagram of the present invention;
FIG. 3 is a graph of a large-kinematical factor based reactive wind shear F-factor correction architecture;
FIG. 4 is a schematic diagram of the F-factor fusion calculation;
FIG. 5 is a diagram of wind field inversion operations.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 to 5, an embodiment of the present invention provides a reactive wind shear false alarm suppression method fusing weather radar information, including the following steps:
firstly, carrying out wind field inversion on wind field information;
step two, introducing wind field information to judge turbulence, correcting integral duration and extracting a predicted wind shear F factor;
calculating a reactive wind shear F factor according to a reactive wind shear mode, and comparing the reactive wind shear F factor with an alarm threshold to obtain a wind shear alarm result;
calculating and comparing the reactive wind shear F factor with an F factor of an airplane position point in wind field inversion, and if the integral average difference value of the reactive wind shear F factor and the predicted wind shear F factor is larger than the tolerance, performing maneuver type detection by a reactive wind shear module and finishing the correction of the reactive wind shear F factor; generating a wind shear alarm if the integral average difference of the reactive wind shear F factor and the F factor of the aircraft position point in the wind field inversion is less than the tolerance;
and step five, based on the time interval sensitivity characteristic, obtaining a corrected F factor through the weighted fusion of the predicted wind shear F factor and the reactive wind shear F factor, and executing the step three again and giving a wind shear alarm result.
In order to reduce turbulence in reactive wind shear and wind shear false alarms caused by maneuvering actions and improve the performance of reactive wind shear alarms, a wind field detected by a weather radar is introduced into a ground proximity alarm system to carry out wind field inversion, and wind field data are arranged into a data form convenient to use for reactive wind shear. And correcting the integral time of the current F factor calculation by using the turbulence characteristics of the detected wind field information at the reactive wind shear alarm processing stage, and reducing the F factor contribution caused by disturbance as much as possible. In addition, large maneuvering action influence factors are combined in reactive wind shear alarm processing, different weight ratio prediction type wind shear F factors and reactive wind shear F factors are calculated based on time interval sensitivity, and false alarm probability is effectively reduced.
The first step comprises the following steps:
step 1.1, defining wind field information obtained from the predictive wind shear in a radar coordinate system with an airplane position as an origin, wherein each node comprises horizontal wind speed, vertical wind speed, F factors and turbulence characteristic value information;
step 1.2, determining a longitude and latitude range of the prediction type wind shear forward-looking detection according to the airplane position, the heading information and the detection distance, taking set three points in the prediction type wind shear forward-looking detection range, converting the set three points into longitude and latitude values in an ink card support projection mode, and taking the maximum and minimum value of the longitude and latitude as a boundary value of the prediction type wind shear forward-looking detection range;
step 1.3, carrying out grid division on an area in a space range of the forecast type wind shear foresight detection to form a longitude and latitude grid, and filling the forecast type wind shear detection result into the longitude and latitude grid.
The second step is specifically as follows: and B, according to the position of the airplane, searching corresponding position information in the longitude and latitude grid formed in the step one, checking whether turbulent flow information exists at the position of the airplane in the longitude and latitude grid, adjusting the integration time of the reactive wind shear F factor according to the characteristic value of turbulent flow, and extracting a predicted wind shear F factor.
The third step specifically comprises:
step 3.1, reactive wind shear F factor according to formula
Performing a calculation in which
For the horizontal component of the wind along the flight path, W is the vertical component of the wind, VaIs airspeed, g is acceleration of gravity;
and 3.2, comparing the integral average value of the reactive wind shear F factor for a period of time with an alarm threshold and giving an alarm result.
The fourth step comprises the following steps: and 4.1, calculating difference integral average numbers of the reactive wind shear F factor and the predicted wind shear F factor, and comparing the difference integral average numbers with a judgment threshold to determine whether the maneuvering action influence exists.
Step 4.2, if there is a maneuver impact, comprising the steps of:
the method comprises the following steps of qualitatively analyzing the variation trend of flight parameters under different maneuvering types aiming at the variation characteristics of the flight parameters under the wind shear environment;
according to the flight parameter variation trend under different maneuver types, establishing a matrix A1 ═ a of the occurrence probability of each maneuver1 a2 a3 a4 a5 a6]Wherein a is1～a6Representing the probability of the maneuver occurring at the current flight phase of the aircraft;
establishing a matrix B1 ═ B according to the similarity of maneuver types and flight parameters in a wind shear environment1 b2 b3 b4b5 b6]Wherein b is1～b6Representing the probability of the maneuver identified to occur based on the aircraft parameters.
According to A1 ═ a1 a2 a3 a4 a5 a6]And B1 ═ B1 b2 b3 b4 b5 b6]Judging the occurrence factor lambda f (A) of each current maneuvering type of the airplane1，B1)；
Obtaining an experience influence factor f of the current maneuver according to a lookup maneuver type library table;
obtaining a large maneuvering influence factor according to the empirical influence factor, the generating factor and the maneuvering influence correction function Fun ═ Fun (f, lambda);
by F1＝Fun·F1Obtaining a modified reactive wind shear F1A factor.
And 4.3, if no maneuvering action influence exists, generating a wind shear alarm.
The fifth step comprises the following steps:
by Fmix(t)＝kF1(t)+(1-k)F2(t) weighted fusion of the predicted and reactive wind shear F-factors, wherein F2(t) is the predicted wind shear F factor, k ═ t1-t)/(t1-t0) T is the time when the wind field information of the position is obtained by the predicted wind shear, t0Calculating the starting time, t, for the fusion1To detect the start time of the blind spot:
by passing
Integral calculation and corrected F factor, t2Is the current time;
and comparing and judging the corrected F factor with an alarm threshold and generating an alarm result.
Compared with the existing reactive wind shear warning method of the ground proximity warning system, the method disclosed by the invention integrates the wind field detection information of the predictive wind shear, adjusts the judgment sensitivity by utilizing the actually detected turbulence characteristic information, reduces the F factor fluctuation component contributed by turbulence, and reduces false alarms.
According to the method, a predicted wind shear F factor and a reactive wind shear F factor fusion mode is introduced, and when the difference value between the reactive wind shear F factor and the predicted wind shear F factor is larger than a threshold value, a reactive wind shear module performs weighted fusion on the reactive wind shear F factor and the predicted wind shear F factor according to the airplane maneuvering state, so that reactive wind shear false alarms caused by maneuvering are reduced.
The specific application example of the embodiment of the invention is as follows:
the method comprises the following steps: predictive wind shear wind field inversion.
As shown in fig. 5, wind field information derived from the predicted wind shear is defined in a radar coordinate system with the aircraft position as the origin, wherein each node contains horizontal wind speed, vertical wind speed, F-factor, and turbulence characteristic value information. And determining latitude and longitude ranges Lat _ Min, Lat _ Max, Lon _ Min and Lon-Max of the predictive wind shear forward-looking detection according to the position of the airplane, the heading information and the detection distance. And taking three points A [ -For _ Dis, 0], B [0, For _ Dis ] and C [ For _ Dis, 0], converting the three points into longitude and latitude values by using an ink card holder projection mode, and taking the maximum and minimum value of the longitude and latitude as boundary values Lat _ Min, Lat _ Max, Lon _ Min and Lon-Max. And carrying out grid division on areas within the space range of [ Lat _ Min, Lat _ Max ], [ Lon _ Min, Lon _ Max ], and filling the predicted wind shear detection result into the latitude and longitude grid.
Step two: and introducing wind field information to judge turbulence, correcting integration duration and extracting a predicted wind shear F factor.
And B, according to the position of the airplane, searching corresponding position information in the inversion wind field result matrix formed in the step one, checking that no turbulent flow information exists at the current position, and adjusting the integral time of the F factor according to the size of the turbulent flow characteristic value. The predicted wind shear F factor is extracted for subsequent calculations.
Step three: reactive wind shear standard F factor alarm determination
The reactive wind shear F factor is calculated according to equation 1, where
For the horizontal component of the wind along the flight path, W is the vertical component of the wind, VaIs the airspeed, g is the acceleration of gravity.
The F factor represents a wind field term of the aircraft response to wind shear and is used to define a threshold value for dangerous wind shear in an airborne wind shear warning device. And judging whether the average value of the F factor integrals exceeds an alarm threshold value or not by adopting a period of time, and giving an alarm result.
Step four: and judging whether the maneuvering action influence exists or not by comparing the reactive wind shear F factor with the F factor difference integral average of the airplane position points in the inversion wind field, if so, correcting the maneuvering influence of the reactive wind shear F factor, and otherwise, generating a reactive wind shear alarm.
Aiming at the change characteristics of flight parameters in a wind shear environment, listing common maneuvering types, qualitatively analyzing the change trend of each main flight parameter and the flight characteristics of civil aircrafts, listing a flight parameter change trend comparison table under different maneuvering types, and referring to table 1 in detail.
TABLE 1 reference table for flight parameter variation trend under different maneuver types
The large maneuvering influence factor calculation flow is shown in fig. 3, and the specific steps are as follows:
firstly, determining the probability of each maneuver type occurring in the current flight scene through a hierarchical analysis method (AHP) according to input flight parameters and maneuver type databases, and establishing a matrix A1 ═ a of the probability of each maneuver action according to the characteristics of a low-altitude wind shear wind field and scene recognition1 a2 a3 a4 a5 a6](ii) a Similarly, depending on the type of maneuver and the flight in a windshear environmentSimilarity of parameters establishes matrix B1 ═ B1 b2 b3 b4 b5 b6]. Then, according to the probability and similarity matrix information of each maneuver, the occurrence factor λ of each maneuver at present is determined to be f (A)1，B1) And looking up the maneuvering influence factor by a maneuvering type library to determine the empirical influence factor f. Then, from the empirical influence factor and the generation factor, a large maneuvering influence factor is obtained by a maneuvering influence correction function Fun ═ Fun (f, λ). Final correction of reactive wind shear F1Factor, i.e. F1＝Fun·F1。
Step five: and fusing and recalculating the multi-source F factors and detecting the alarm.
The calculation schematic diagram of the factor F is shown in FIG. 4, and the total fusion time is T, T2Is the current time. Due to the presence of radar detection blind areas, i.e. time interval t1，t2]Predicting wind shear unavailable fusion detection data, wherein F is equal to F1。
The fusion interval of multi-source F factors is [ t ]0，t1]. Due to the fast wind field changes, the predicted wind shear F2The factors have the characteristic of timeliness, namely, the confidence coefficient is lower when the time is longer, so that a time variable is introduced as a standard for weighing. On the basis of the time interval sensitivity characteristics, the multi-source F factor (reaction formula F) is subjected to the following formula (2)1And predictive formula F2) Performing weighted fusion, wherein k ═ t1-t)/(t1-t0) And t is the moment when the predicted wind shear obtains the position wind field information.
Fmix(t)＝kF1(t)+(1-k)F2(t) (2)
The integral average of the recalculated F factors is obtained to obtain delta, and the calculation formula is as follows:
and comparing the wind shear alarm with an alarm threshold value, generating a reactive wind shear alarm when the calculation result is higher than the alarm threshold value, and not alarming otherwise.
The above description is only exemplary of the invention and should not be taken as limiting the scope of the invention, so that the invention is intended to cover all modifications and equivalents of the embodiments described herein. In addition, the technical features, the technical schemes and the technical schemes can be freely combined and used.
Claims (8)
1. A reactive wind shear false alarm suppression method fused with meteorological radar information is characterized by comprising the following steps:
firstly, carrying out wind field inversion on wind field information;
step two, introducing wind field information to judge turbulence, correcting integral duration and extracting a predicted wind shear F factor;
calculating a reactive wind shear F factor according to a reactive wind shear mode, and comparing the reactive wind shear F factor with an alarm threshold to obtain a wind shear alarm result;
calculating and comparing the reactive wind shear F factor with an F factor of an airplane position point in wind field inversion, and if the integral average difference value of the reactive wind shear F factor and the predicted wind shear F factor is larger than the tolerance, performing maneuver type detection by a reactive wind shear module and finishing the correction of the reactive wind shear F factor; generating a wind shear alarm if the integral average difference of the reactive wind shear F factor and the F factor of the aircraft position point in the wind field inversion is less than the tolerance;
and step five, based on the time interval sensitivity characteristic, obtaining a corrected F factor through the weighted fusion of the predicted wind shear F factor and the reactive wind shear F factor, and executing the step three again and giving a wind shear alarm result.
2. The weather radar information-fused reactive wind shear false alarm suppression method according to claim 1, wherein the step one comprises:
step 1.1, defining wind field information obtained from the predictive wind shear in a radar coordinate system with an airplane position as an origin, wherein each node comprises horizontal wind speed, vertical wind speed, F factors and turbulence characteristic value information;
step 1.2, determining a longitude and latitude range of the prediction type wind shear forward-looking detection according to the airplane position, the heading information and the detection distance, taking set three points in the prediction type wind shear forward-looking detection range, converting the set three points into longitude and latitude values in an ink card support projection mode, and taking the maximum and minimum value of the longitude and latitude as a boundary value of the prediction type wind shear forward-looking detection range;
step 1.3, carrying out grid division on an area in a space range of the forecast type wind shear forward-looking detection to form a longitude and latitude grid, and filling the forecast type wind shear detection result into the longitude and latitude grid.
3. The method for reactive wind shear false alarm suppression fusing meteorological radar information according to claim 2, wherein the second step is specifically: and B, according to the position of the airplane, searching corresponding position information in the longitude and latitude grid formed in the step one, checking whether turbulent flow information exists at the position of the airplane in the longitude and latitude grid, adjusting the integration time of the reactive wind shear F factor according to the characteristic value of turbulent flow, and extracting a predicted wind shear F factor.
4. The weather radar information-fused reactive wind shear false alarm suppression method according to claim 3, wherein the third step specifically comprises:
step 3.1, reactive wind shear F factor according to formula
Performing a calculation in which
For the horizontal component of the wind along the flight path, W is the vertical component of the wind, VaIs airspeed, g is acceleration of gravity;
and 3.2, comparing the integral average value of the reactive wind shear F factor for a period of time with an alarm threshold and giving an alarm result.
5. The weather radar information-fused reactive wind shear false alarm suppression method according to claim 4, wherein the fourth step comprises: and 4.1, calculating difference integral average numbers of the reactive wind shear F factor and the predicted wind shear F factor, and comparing the difference integral average numbers with a judgment threshold to determine whether the maneuvering action influence exists.
6. The weather radar information-fused reactive wind shear false alarm suppression method according to claim 5, wherein the fourth step comprises: step 4.2, if there is a maneuver impact, comprising the steps of:
the method comprises the following steps of qualitatively analyzing the variation trend of flight parameters under different maneuvering types aiming at the variation characteristics of the flight parameters under the wind shear environment;
according to the flight parameter variation trend under different maneuver types, establishing a matrix A1 ═ a of the occurrence probability of each maneuver1a2 a3 a4 a5 a6]Wherein a is1～a6Representing the probability of the maneuver occurring at the current flight phase of the aircraft;
establishing a matrix B1 ═ B according to the similarity of maneuver types and flight parameters in a wind shear environment1 b2 b3 b4 b5b6]Wherein b is1～b6Representing the probability of the maneuver identified to occur based on the aircraft parameters.
According to A1 ═ a1 a2 a3 a4 a5 a6]And B1 ═ B1 b2 b3 b4 b5 b6]Judging the occurrence factor lambda f (A) of each current maneuvering type of the airplane1，B1)；
Obtaining an experience influence factor f of the current maneuver according to a lookup maneuver type library table;
obtaining a large maneuvering influence factor according to the empirical influence factor, the generating factor and the maneuvering influence correction function Fun ═ Fun (f, lambda);
by F1＝Fun·F1Obtaining a modified reactive wind shear F1A factor.
7. The weather radar information-fused reactive wind shear false alarm suppression method according to claim 6, wherein the fourth step further comprises: and 4.3, if no maneuvering action influence exists, generating a wind shear alarm.
8. The weather radar information-fused reactive wind shear false alarm suppression method according to claim 7, wherein the step five comprises:
by Fmix(t)＝kF1(t)+(1-k)F2(t) weighted fusion of the predicted and reactive wind shear F-factors, wherein F2(t) is the predicted wind shear F factor, k ═ t1-t)/(t1-t0) T is the time when the wind field information of the position is obtained by the predicted wind shear, t0Calculating the starting time, t, for the fusion1The starting time of the detection blind area;
by passing
Integral calculation and corrected F factor, t2Is the current time;
and comparing and judging the corrected F factor with an alarm threshold and generating an alarm result.
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| CN115494521B (en) * | 2022-09-22 | 2023-08-22 | 中国民航大学 | Airport runway low-altitude wind shear early warning method based on laser radar |
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