CN115236663A - System and method for detecting airplane landing deviation runway in low-visibility environment - Google Patents
System and method for detecting airplane landing deviation runway in low-visibility environment Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/91—Radar or analogous systems specially adapted for specific applications for traffic control
- G01S13/913—Radar or analogous systems specially adapted for specific applications for traffic control for landing purposes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/41—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00 using analysis of echo signal for target characterisation; Target signature; Target cross-section
- G01S7/411—Identification of targets based on measurements of radar reflectivity
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
Abstract
The invention discloses a system and a method for detecting landing deviation runway of an airplane in a low visibility environment, wherein the detection system comprises: the device comprises a detection module, a main control module, an alarm module, a release module and an imaging module; the method for detecting the system comprises the following steps: receiving angle information of a plurality of angle reflectors in real time, and selecting the angle information of two echoes returned by one of the angle reflectors; respectively substituting the angle information of the two echoes into a deviation runway detection model to obtain a detection and identification result, and carrying out two-dimensional imaging on the selected angle information to obtain the relative position of the airplane and the runway; based on the result of detection and identification, selecting to output alarm information or release information; and outputs the relative positions of the aircraft and the runway in a visual form. The system of the invention carries out monitoring and early warning on the airplane landing runway in the low visibility environment, and timely makes early warning on the condition that the airplane deviates from the runway to remind a pilot, thereby avoiding flight accidents caused by the fact that the airplane lands and deviates from the runway.
Description
Technical Field
The invention belongs to the technical field of monitoring and early warning of flight equipment, and particularly relates to a system and a method for detecting aircraft landing deviation from a runway in a low-visibility environment.
Background
With the rapid improvement of national economy, the civil aviation industry in China is rapidly developed, and the safety of airplane navigation is increasingly concerned by people. Although the probability of accidents occurring on the airplane is greatly reduced in the last decade with the improvement of scientific technology and the further enhancement of management measures, the statistical data of scientific institutions show that the probability of accidents occurring on the airplane during landing and runway approach is relatively high. Through research and analysis, the reasons for accidents of the aircraft in the stages of landing and approaching the runway are mostly caused by human misoperation because the pilot cannot completely know the runway environment. Therefore, it is necessary to design a system that can monitor deviation from the runway and give an alarm in time when the aircraft lands in a low visibility environment.
When the current aircraft is landing, the pilot still needs to visually observe the condition of the runway. When the airport is cloudy and the visibility is low, judgment of a pilot is affected, and the pilot is easily mistakenly disconnected, so that accidents are caused.
Disclosure of Invention
The purpose of the invention is as follows: in order to overcome the defects in the prior art, the invention provides a system and a method for detecting the deviation of the airplane from the runway in the low visibility environment.
The technical scheme is as follows: in a first aspect, the present invention provides a system for detecting a departure runway for aircraft landing in a low visibility environment, comprising:
the device comprises a detection module, a main control module, an alarm module, a release module and an imaging module;
wherein, the detection module: the runway condition detection system is used for detecting the runway condition when an airplane lands, collecting angle information when the airplane lands and transmitting the angle information to the main control module;
a main control module: the system is used for detecting and identifying angle information when the airplane lands, sending different control information to the alarm module and the release module based on the detection and identification result, and sending the angle information to the imaging module for two-dimensional imaging;
an alarm module: the alarm device is used for receiving the alarm information sent by the main control module, entering an alarm state and controlling the alarm to send an alarm prompt;
a releasing module: the alarm is used for receiving the releasing information sent by the main control module, releasing the alarm state and controlling the alarm to stop sending an alarm prompt;
an imaging module: and the image acquisition module is used for receiving the angle information forwarded by the main control module and carrying out two-dimensional imaging according to the angle information.
In a further embodiment, the detection module comprises: the radar system comprises a monopulse radar and a difference angle measurement radar which are respectively deployed on an airplane, and a plurality of corner reflectors arranged on two sides of a runway; wherein, the corner reflectors on each side have the same interval, and the interval is 2-3 m.
In a further embodiment, the imaging module outputs the two-dimensional images in a visualization mode to provide the pilot with the relative positions of the airplane and the runway.
In a second aspect, the present invention provides a method for detecting a departure runway for aircraft landing in a low visibility environment, including:
receiving angle information of a plurality of angle reflectors in real time, and selecting the angle information of two echoes returned by one of the angle reflectors;
respectively substituting the angle information of the two echoes into a deviation runway detection model to obtain a detection and identification result, and carrying out two-dimensional imaging on the selected angle information to obtain the relative position of the airplane and the runway;
based on the result of detection and identification, selecting to output alarm information or release information; and outputs the relative positions of the aircraft and the runway in a visual form.
In a further embodiment, the angle information of a plurality of angle reflectors is received in real time, and the angle information of two echoes returned by one of the angle reflectors is selected as follows:
collecting angle information theta of two echo signals returned by corner reflector in aircraft landing process 0 Wherein theta 0 The off-angle between the central axis of the two beams and the equal strength signal axis, the direction of the equal strength signal axis of the two echo signals is a known quantity because the two planar beams partially overlap each other.
In a further embodiment, the method for substituting the angle information of the two echoes into the deviation runway detection model respectively to obtain the detection identification result comprises the following steps:
substituting the angle information of the two echo signals into directional diagram functions of the two sub-beams to obtain a sum beam directional diagram and a difference beam directional diagram;
deriving a sum beam directional diagram and a difference beam directional diagram according to the Taylor expansion, and obtaining the amplitude of a sum signal and the amplitude of a difference signal;
calculating the ratio of the amplitude of the sum signal to the amplitude of the difference signal to obtain a target echo signal deflection angle;
and comparing the target echo signal deflection angle with a preset threshold value, and judging whether the airplane deviates from the orbit according to the comparison result.
In a further embodiment, in the antenna beam pattern function, the expression of the pattern function of the two sub-beams is:
in the formula, F 1 (theta) is the first sub-beam, F 2 (theta) is the second sub-beam, theta 0 Theta is the deflection angle between the central axis of the two wave beams and the equal-strength signal axis respectively;
substituting the angle information of the two echo signals into the antenna beam directional diagram function has the expression:
in the formula, K a Is a proportionality coefficient; wherein, K a Related to factors such as radar parameters; u. of 1 (θ) is the first echo signal, u 2 (θ) is the second echo signal;
the calculation formula for obtaining the amplitude of the sum signal and the amplitude of the difference signal is:
in the formula, F Σ (θ)＝F(θ 0 +θ)+F(θ 0 - θ) is the sum beam pattern, F Δ (θ)＝F(θ 0 +θ)-F(θ 0 - θ) is a difference beam pattern;
deriving a sum beam pattern and a difference beam pattern according to the Taylor expansion, and obtaining a calculation expression of the amplitude of the sum signal and the amplitude of the difference signal as follows:
wherein F' (θ) 0 ) Is F (theta) 0 ) Derivative of, o (theta) 2 ) Is theta 2 High order infinitesimal quantity of u Δ (theta) is the amplitude of the difference signal, u Σ (θ) is the amplitude of the sum signal;
the calculation expression for calculating the ratio of the amplitude of the sum signal to the amplitude of the difference signal is:
where ρ is the antenna patternBeam deflection angle theta 0 A normalized slope coefficient of (d);
the calculation expression for obtaining the target echo signal deflection angle is as follows:
in a further embodiment, the method for comparing the target echo signal deflection angle with a preset threshold value and determining whether the aircraft deviates from the orbit according to the comparison result comprises the following steps: if the target echo signal deflection angle theta is larger than the threshold value theta m Judging that the airplane deviates from the runway, and if the target echo signal deflection angle theta is less than or equal to the threshold value theta m The aircraft is not determined to deviate from the runway.
A third aspect the present invention provides a processing apparatus comprising a memory and a processor, the memory storing a computer program which is executed by the processor to implement the detection method described above.
A fourth aspect the present invention provides a readable storage medium having stored thereon a computer program which, when executed by a processor, performs the steps of the method described above.
Has the advantages that: compared with the prior art, the invention has the following advantages:
the system is based on the monopulse and the differential angle measuring radar, the reliability of the system is high, the detection system is used for monitoring and early warning the airplane landing runway in a low visibility environment, and early warning is timely made on the condition that the airplane deviates from the runway to remind a pilot, so that the pilot can be favorably changed in time and can return to the normal track again, and thus, the flight accident caused by the fact that the airplane lands and deviates from the runway is avoided;
the target echo signal deflection angle can be calculated through the detection method, so that the deflection data of the airplane landing can be rapidly and accurately obtained in real time.
Drawings
FIG. 1 is a network topology diagram of an aircraft landing deviation runway detection system in a low visibility environment according to the present invention;
FIG. 2 is a diagram of an embodiment of an aircraft landing deviation runway detection by a detection module angle reflector according to the present invention;
FIG. 3 is a diagram of an embodiment of a detection module radar apparatus for aircraft landing deviation runway detection in accordance with the present invention;
fig. 4 is a flow chart of the method for detecting landing deviation from a runway in a low visibility environment according to the present invention.
Detailed Description
In order to more fully understand the technical content of the present invention, the technical solution of the present invention will be further described and illustrated with reference to the following specific embodiments, but not limited thereto.
As shown in fig. 1, further illustrating the embodiment, a system for detecting landing deviation from runway of an airplane disclosed in the embodiment comprises: the device comprises a detection module, a main control module, an alarm module, a release module and an imaging module;
wherein, the detection module: the runway condition detection system is used for detecting the runway condition when an airplane lands, collecting angle information when the airplane lands and transmitting the angle information to the main control module;
the main control module: the system is used for detecting and identifying angle information when the airplane lands, sending different control information to the alarm module and the release module based on the detection and identification result, and sending the angle information to the imaging module for two-dimensional imaging;
an alarm module: the alarm device is used for receiving the alarm information sent by the main control module, entering an alarm state and controlling the alarm to give an alarm prompt;
a releasing module: the alarm is used for receiving the releasing information sent by the main control module, releasing the alarm state and controlling the alarm to stop sending an alarm prompt;
an imaging module: and the image acquisition module is used for receiving the angle information forwarded by the main control module and carrying out two-dimensional imaging according to the angle information.
As shown in fig. 2 to fig. 3, further illustrating the detecting module in the embodiment, the detecting module includes: the radar system comprises a monopulse radar and a difference angle measurement radar which are respectively deployed on an airplane, and a plurality of corner reflectors arranged on two sides of a runway; wherein, the corner reflectors on each side have the same interval, and the interval is 2-3 m.
And the imaging module outputs the two-dimensional imaging result in a visualization mode to provide the relative positions of the airplane and the runway for the pilot.
Fig. 4 further illustrates a method for detecting a departure runway for aircraft landing in a low visibility environment, which includes the following steps:
receiving angle information of a plurality of angle reflectors in real time, and selecting the angle information of two echoes returned by one of the angle reflectors;
respectively substituting the angle information of the two echoes into a deviation runway detection model to obtain a detection and identification result, and carrying out two-dimensional imaging on the selected angle information to obtain the relative position of the airplane and the runway;
based on the result of detection and identification, selecting to output alarm information or release information; and outputs the relative positions of the aircraft and the runway in a visual form.
Receiving angle information of a plurality of angle reflectors in real time, and selecting the angle information of two echoes returned by one of the angle reflectors as follows:
collecting angle information theta of two echo signals returned by a corner reflector in the landing process of an airplane 0 Wherein theta 0 The off-angle between the central axis of the two beams and the equal strength signal axis, the direction of the equal strength signal axis of the two echo signals is a known quantity because the two planar beams partially overlap each other.
The method for respectively substituting the angle information of the two echoes into the deviation runway detection model to obtain the detection and identification result comprises the following steps:
substituting the angle information of the two echo signals into directional diagram functions of the two sub-beams to obtain a sum beam directional diagram and a difference beam directional diagram;
deriving a sum beam directional diagram and a difference beam directional diagram according to the Taylor expansion, and obtaining the amplitude of a sum signal and the amplitude of a difference signal;
calculating the ratio of the amplitude of the sum signal to the amplitude of the difference signal to obtain a target echo signal deflection angle;
and comparing the target echo signal deflection angle with a preset threshold value, and judging whether the airplane deviates from the orbit according to the comparison result.
In the antenna beam pattern function, the expression of the pattern function of the two sub-beams is:
in the formula, F 1 (theta) is the first sub-beam, F 2 (theta) is the second sub-beam, theta 0 Theta is the deflection angle between the central axis of the two wave beams and the equal-strength signal axis respectively;
the expression for substituting the angle information of the two echo signals into the antenna beam pattern function is:
in the formula, K a Is a proportionality coefficient; wherein, K a Related to factors such as radar parameters; u. u 1 (θ) is the first echo signal, u 2 (θ) is the second echo signal;
the calculation formula for obtaining the amplitude of the sum signal and the amplitude of the difference signal is:
in the formula, F Σ (θ)＝F(θ 0 +θ)+F(θ 0 - θ) is the sum beam pattern, F Δ (θ)＝F(θ 0 +θ)-F(θ 0 - θ) is a difference beam pattern;
deriving a sum beam pattern and a difference beam pattern according to the Taylor expansion, and obtaining a calculation expression of the amplitude of the sum signal and the amplitude of the difference signal as follows:
wherein F' (θ) 0 ) Is F (theta) 0 ) Derivative of, o (theta) 2 ) Is theta 2 High order infinitesimal quantity of u Δ (theta) is the amplitude of the difference signal, u Σ (θ) is the amplitude of the sum signal;
the calculation expression for calculating the ratio of the amplitude of the sum signal to the amplitude of the difference signal is:
where ρ is the beam deflection angle θ of the antenna pattern 0 A normalized slope coefficient of (d);
the calculation expression for obtaining the target echo signal deflection angle is as follows:
in a further embodiment, the method for comparing the target echo signal deflection angle with a preset threshold value and determining whether the aircraft deviates from the orbit according to the comparison result comprises the following steps: if the target echo signal deflection angle theta is larger than the threshold value theta m Judging that the airplane deviates from the runway, and if the target echo signal deviation angle theta is less than or equal to the threshold value theta m The aircraft is not determined to deviate from the runway.
The third embodiment discloses a processing device, which comprises a memory and a processor, wherein the memory stores a computer program, and the computer program is executed by the processor to realize the following detection method:
receiving angle information of a plurality of angle reflectors in real time, and selecting the angle information of two echoes returned by one of the angle reflectors;
respectively substituting the angle information of the two echoes into a deviation runway detection model to obtain a detection and identification result, and carrying out two-dimensional imaging on the selected angle information to obtain the relative position of the airplane and the runway;
based on the result of detection and identification, selecting to output alarm information or release information; and outputs the relative positions of the aircraft and the runway in a visual form.
The fourth embodiment discloses a readable storage medium, on which a computer program is stored, which program, when being executed by a processor, realizes the steps of the method:
receiving angle information of a plurality of angle reflectors in real time, and selecting the angle information of two echoes returned by one of the angle reflectors;
respectively substituting the angle information of the two echoes into a deviation runway detection model to obtain a detection and identification result, and carrying out two-dimensional imaging on the selected angle information to obtain the relative position of the airplane and the runway;
based on the result of detection and identification, selecting to output alarm information or release information; and outputs the relative positions of the aircraft and the runway in a visual form.
The system is based on the monopulse and the differential angle radar, has high reliability, monitors and warns the runway of the airplane landing in a low visibility environment through the detection system, warns the condition that the airplane deviates from the runway in time, reminds the pilot, is beneficial to changing the pilot in time and returns to the positive rail again, thereby avoiding flight accidents caused by the fact that the airplane lands and deviates from the runway;
and secondly, the deflection angle of the target echo signal can be calculated by a detection method, so that the deflection data of the airplane landing can be rapidly and accurately obtained in real time.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, it is possible to make various improvements and modifications without departing from the technical principle of the present invention, and those improvements and modifications should be considered as the protection scope of the present invention.
Claims (10)
1. An aircraft landing deviation runway detection system in a low visibility environment, comprising:
the device comprises a detection module, a main control module, an alarm module, a release module and an imaging module;
wherein, the detection module: the runway condition detection system is used for detecting the runway condition when an airplane lands, collecting angle information when the airplane lands and transmitting the angle information to the main control module;
the main control module: the system is used for detecting and identifying angle information when the airplane lands, sending different control information to the alarm module and the release module based on the detection and identification result, and sending the angle information to the imaging module for two-dimensional imaging;
an alarm module: the alarm device is used for receiving the alarm information sent by the main control module, entering an alarm state and controlling the alarm to give an alarm prompt;
a releasing module: the alarm is used for receiving the releasing information sent by the main control module, releasing the alarm state and controlling the alarm to stop sending an alarm prompt;
an imaging module: and the two-dimensional imaging module is used for receiving the angle information forwarded by the main control module and carrying out two-dimensional imaging according to the angle information.
2. The system of claim 1, wherein the detection module comprises: the radar system comprises a monopulse radar and a difference angle measurement radar which are respectively deployed on an airplane, and a plurality of corner reflectors arranged on two sides of a runway; wherein, the corner reflectors on each side have the same interval, and the interval is 2-3 m.
3. The system of claim 1, wherein the imaging module outputs the two-dimensional images in a visualization mode to provide the pilot with the relative position of the airplane and the runway.
4. A method for detecting landing deviation from a runway of an airplane in a low visibility environment is characterized by comprising the following steps:
receiving angle information of a plurality of angle reflectors in real time, and selecting the angle information of two echoes returned by one of the angle reflectors;
respectively substituting the angle information of the two echoes into a deviation runway detection model to obtain a detection and identification result, and carrying out two-dimensional imaging on the selected angle information to obtain the relative position of the airplane and the runway;
based on the result of detection and identification, selecting to output alarm information or release information; and outputs the relative positions of the aircraft and the runway in a visual form.
5. The method as claimed in claim 4, wherein the angle information of the angle reflectors is received in real time, and the angle information of two echoes returned by one of the angle reflectors is selected as:
collecting angle information theta of two echo signals returned by a corner reflector in the landing process of an airplane 0 Wherein theta 0 Is the deflection angle between the central axis of the two beams and the equal strength signal axis.
6. The method as claimed in claim 4, wherein the step of substituting the angle information of the two echoes into the deviation runway detection model to obtain the detection recognition result comprises:
substituting the angle information of the two echo signals into directional diagram functions of the two sub-beams to obtain a sum beam directional diagram and a difference beam directional diagram;
deriving a sum beam directional diagram and a difference beam directional diagram according to the Taylor expansion, and obtaining the amplitude of a sum signal and the amplitude of a difference signal;
calculating the ratio of the amplitude of the sum signal to the amplitude of the difference signal to obtain a target echo signal deflection angle;
and comparing the target echo signal deflection angle with a preset threshold value, and judging whether the airplane deviates from the orbit according to the comparison result.
7. The method as claimed in claim 6, wherein in the antenna beam pattern function, the expression of the pattern function of the two sub-beams is:
in the formula, F 1 (theta) is the first sub-beam, F 2 (theta) is the second sub-beam, theta 0 Theta is respectively a deflection angle between the central axis of the two wave beams and the equal-strength signal axis;
substituting the angle information of the two echo signals into the antenna beam directional diagram function has the expression:
in the formula, K a Is a proportionality coefficient; wherein, K a Related to radar parameter factors; u. of 1 (θ) is the first echo signal, u 2 (θ) is the second echo signal;
the calculation formula for obtaining the amplitude of the sum signal and the amplitude of the difference signal is:
in the formula, F Σ (θ)＝F(θ 0 +θ)+F(θ 0 - θ) is the sum beam pattern, F Δ (θ)＝F(θ 0 +θ)-F(θ 0 - θ) is a difference beam pattern;
deriving a sum beam pattern and a difference beam pattern according to the Taylor expansion, and obtaining a calculation expression of the amplitude of the sum signal and the amplitude of the difference signal as follows:
in the formula (I), the compound is shown in the specification,F'(θ 0 ) Is F (theta) 0 ) Derivative of, o (theta) 2 ) Is theta 2 High order infinitesimal quantity of u Δ (theta) is the amplitude of the difference signal, u Σ (θ) is the amplitude of the sum signal;
the calculation expression for calculating the ratio of the amplitude of the sum signal to the amplitude of the difference signal is:
where ρ is the beam deflection angle θ of the antenna pattern 0 A normalized slope coefficient of (d);
the calculation expression for obtaining the target echo signal deflection angle is as follows:
8. the method for detecting whether the airplane lands on a runway in a low visibility environment as claimed in claim 6, wherein the method for comparing the target echo signal deflection angle with a preset threshold value and determining whether the airplane deviates from the orbit according to the comparison result comprises the following steps: if the target echo signal deflection angle theta is larger than the threshold value theta m Judging that the airplane deviates from the runway, and if the target echo signal deflection angle theta is less than or equal to the threshold value theta m The aircraft is not determined to deviate from the runway.
9. A processing apparatus comprising a memory and a processor, wherein the memory stores a computer program that is executed by the processor to implement the detection method of any one of claims 4 to 8.
10. A readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the steps of the method according to any one of claims 4 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210649675.3A CN115236663A (en) | 2022-06-10 | 2022-06-10 | System and method for detecting airplane landing deviation runway in low-visibility environment |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210649675.3A CN115236663A (en) | 2022-06-10 | 2022-06-10 | System and method for detecting airplane landing deviation runway in low-visibility environment |
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| CN115236663A true CN115236663A (en) | 2022-10-25 |
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| CN202210649675.3A Withdrawn CN115236663A (en) | 2022-06-10 | 2022-06-10 | System and method for detecting airplane landing deviation runway in low-visibility environment |
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- 2022-06-10 CN CN202210649675.3A patent/CN115236663A/en not_active Withdrawn
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