Aircraft anti-collision early warning method and device

Abstract

The invention discloses an aircraft anti-collision early warning method and device. The method comprises the steps that first flight information of a first aircraft and multiple pieces of second flight information corresponding to multiple second aircrafts adjacent to the first aircraft in a one-to-one mode are obtained in real time; analyzing a plurality of corresponding three-dimensional linear distances D between the first aircraft and the plurality of second aircrafts one by one according to the first flight information and the plurality of pieces of second flight information; allocating corresponding early warning levels to the plurality of three-dimensional linear distances according to a preset early warning strategy; according to the plurality of three-dimensional linear distances, distributing corresponding early warning levels to match an early warning mode so as to generate early warning information corresponding to the first airplane; and performing early warning prompt according to the sequence of the early warning information. The real-time receiving of the aircraft information in the preset range is realized, and the timeliness of the anti-collision early warning information is ensured. And real-time monitoring and accurate positioning of surrounding aircrafts are realized. Meanwhile, a multi-level early warning mechanism and a humanized interaction interface are adopted, and it is ensured that a pilot can timely and accurately perceive potential collision risks.

Description

Technical Field

[0001] The present invention relates to the field of aviation transportation technology, and in particular to an aircraft anti-collision warning method and device. Background Art

[0002] With the rapid development of general aviation, the importance of aircraft collision avoidance warning systems has become increasingly prominent. At present, there are still many technical problems to be solved in the field of general aviation. In the field of civil aviation, the collision avoidance system commonly used by aircraft works through interrogation transponders, which can provide pilots with the location information and avoidance suggestions of other aircraft. However, due to the high cost and complex installation, the system is not popular in general aviation aircraft. General aviation pilots usually do not have available airborne collision avoidance warning devices and systems. Summary of the invention

[0003] In order to solve the technical problems existing in the background technology, the present invention proposes an aircraft anti-collision warning method and device.

[0004] The present invention provides an aircraft collision avoidance warning method, comprising the following steps:

[0005] S1. Acquire in real time first flight information of a first aircraft and a plurality of second flight information corresponding to a plurality of second aircraft adjacent to the first aircraft;

[0006] S2, analyzing one by one a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft according to the first flight information and the plurality of second flight information;

[0007] S3, assigning corresponding warning levels to multiple three-dimensional straight-line distances according to a preset warning strategy;

[0008] S4, assigning corresponding warning levels and matching warning modes according to the multiple three-dimensional straight-line distances to generate warning information corresponding to the first aircraft;

[0009] S5. Issue warning prompts in the order of warning information.

[0010] Preferably, step S1 specifically includes:

[0011] Acquire first flight information of the first aircraft in real time, where the first flight information includes a unique aircraft identification code, longitude, latitude, and altitude of the first aircraft;

[0012] With the first aircraft as the center, an anti-collision area is radiated according to a preset diameter, and multiple second flight information corresponding to multiple second aircraft in the anti-collision area are obtained. The second flight information includes the corresponding second aircraft's unique aircraft identification code, longitude, latitude, and altitude.

[0013] Preferably, step S2 specifically includes:

[0014] Calculate the geographical distance S between the first aircraft and the second aircraft according to the longitude and latitude in the first flight information and the longitude and latitude in the second flight information;

[0015] Calculate the height difference Δh between the first aircraft and the second aircraft according to the height in the first flight information and the height in the second flight information;

[0016] Calculate the three-dimensional straight-line distance D between the first aircraft and the second aircraft according to the geographical distance S and the height difference Δh;

[0017] According to the above steps, a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft are calculated one by one.

[0018] Preferably, the calculating the geographical distance S between the first aircraft and the second aircraft according to the longitude and latitude in the first flight information and the longitude and latitude in the second flight information specifically includes:

[0019] According to the longitude and latitude in the first flight information and the longitude and latitude in the second flight information, the longitude and latitude of the first aircraft are set to (lonA, latA) and the longitude and latitude of the second aircraft are set to (lonB, latB);

[0020] The longitude difference ΔL is calculated based on the longitude and latitude of the first aircraft (lonA, latA) and the longitude and latitude of the second aircraft (lonB, latB);

[0021] A first parameter related to the first aircraft, a second parameter related to the second aircraft, and the equatorial radius of the earth ellipsoid are obtained, and a geographic distance S between the first aircraft and the second aircraft is calculated based on the equatorial radius of the earth ellipsoid, the first parameter, and the second parameter.

[0022] Preferably, the preset early warning strategy specifically includes:

[0023] When the height difference Δh between the first aircraft and the second aircraft is less than or equal to x meters, and the corresponding three-dimensional straight-line distance D is less than y meters, the warning level is level 1 warning;

[0024] When the height difference Δh between the first aircraft and the second aircraft is greater than x meters, and the corresponding three-dimensional straight-line distance D is less than y meters, the warning level is level 2 warning;

[0025] When the three-dimensional straight-line distance D between the first aircraft and the second aircraft is greater than or equal to y meters and less than z meters, the warning level is level 3 warning;

[0026] When the three-dimensional straight-line distance D between the first aircraft and the second aircraft is greater than or equal to z meters and less than w meters, the warning level is level 4 warning;

[0027] Among them, x<y<z<w.

[0028] Preferably, step S4 specifically includes:

[0029] Assign an alarm sound and visual reminder light to each warning level;

[0030] The warning levels corresponding to the plurality of second aircraft are associated with the corresponding second aircraft information, and the warning levels corresponding to the plurality of second aircraft and the first aircraft are sorted in descending order to generate warning information corresponding to the first aircraft.

[0031] The present invention provides an aircraft anti-collision warning device, comprising:

[0032] A data acquisition module, used for acquiring in real time first flight information of a first aircraft and a plurality of second flight information corresponding to a plurality of second aircraft adjacent to the first aircraft;

[0033] A first processing module is used to analyze a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft one by one according to the first flight information and the plurality of second flight information;

[0034] The second processing module is used to assign corresponding warning levels to multiple three-dimensional straight-line distances according to a preset warning strategy;

[0035] An early warning generation module is used to assign corresponding early warning levels and match early warning modes according to a plurality of three-dimensional straight-line distances to generate early warning information corresponding to the first aircraft;

[0036] The prompt module is used to provide warning prompts in the order of warning information.

[0037] In the present invention, the proposed aircraft anti-collision warning method and device obtain the first flight information of the first aircraft and the multiple second flight information corresponding to the multiple second aircraft adjacent to the first aircraft in real time; analyze the multiple three-dimensional straight-line distances D corresponding to the first aircraft and the multiple second aircraft one by one according to the first flight information and the multiple second flight information; assign corresponding warning levels to the multiple three-dimensional straight-line distances according to the preset warning strategy; match the warning mode according to the corresponding warning levels assigned to the multiple three-dimensional straight-line distances to generate the warning information corresponding to the first aircraft; and give warning prompts in the order of the warning information. Real-time reception of aircraft information within a preset range is achieved, ensuring the timeliness of anti-collision warning information. Real-time monitoring and precise positioning of surrounding aircraft are achieved. At the same time, the multi-level warning mechanism and humanized interactive interface are adopted to ensure that pilots can perceive potential collision risks in a timely and accurate manner. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 A schematic diagram of the work flow structure of an aircraft collision avoidance warning method proposed by the present invention;

[0039] Figure 2 A schematic diagram of the device architecture of an aircraft collision avoidance warning device proposed by the present invention. DETAILED DESCRIPTION

[0040] Reference Figure 1 The present invention provides an aircraft collision avoidance warning method, comprising the following steps:

[0041] S1. Acquire in real time first flight information of a first aircraft and a plurality of second flight information of a plurality of second aircraft that are adjacent to the first aircraft and correspond to each other in a one-to-one manner.

[0042] In this embodiment, step S1 specifically includes:

[0043] Acquire first flight information of the first aircraft in real time, where the first flight information includes a unique aircraft identification code, longitude, latitude, and altitude of the first aircraft;

[0044] With the first aircraft as the center, an anti-collision area is radiated according to a preset diameter, and multiple second flight information corresponding to multiple second aircraft in the anti-collision area are obtained. The second flight information includes the corresponding second aircraft's unique aircraft identification code, longitude, latitude, and altitude.

[0045] In this embodiment, the ADS-B signal is continuously monitored and the binary data in the ADS-B signal is decoded to obtain the following data: aircraft unique identification code, longitude, latitude, altitude, speed, and heading; the decoded ADS-B data is sent to a local storage unit through a network interface protocol.

[0046] Specifically, GPS / Beidou positioning latitude and longitude data and barometer data are obtained at a fixed frequency; standard atmospheric pressure altitude is calculated through barometer data in meters;

[0047]

[0048] Among them, P is the atmospheric pressure measured by the barometer (hPa); P0 is the standard atmospheric pressure at the mean sea level (1013.25 hPa); T0 is the mean sea level temperature (288.15 Kelvin); L is the temperature lapse rate (0.0065 Kelvin per meter); R is the gas constant (287.05 joules / (kilogram·Kelvin)); g is the acceleration of gravity (9.80665 meters per second squared). The processed position information and standard pressure altitude of the aircraft are broadcast through the ADS-B transmission module.

[0049] S2. Analyze one by one a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft according to the first flight information and the plurality of second flight information.

[0050] In this embodiment, step S2 specifically includes:

[0051] The geographical distance S between the first aircraft and the second aircraft is calculated according to the longitude and latitude in the first flight information and the longitude and latitude in the second flight information.

[0052] Specifically, according to the longitude and latitude in the first flight information and the longitude and latitude in the second flight information, the longitude and latitude of the first aircraft are assumed to be (lonA, latA) and the longitude and latitude of the second aircraft are assumed to be (lonB, latB); based on the longitude and latitude of the first aircraft (lonA, latA) and the longitude and latitude of the second aircraft (lonB, latB), the longitude difference ΔL is calculated; a first parameter related to the first aircraft, a second parameter related to the second aircraft, and the equatorial radius of the earth ellipsoid are obtained, and the geographical distance S between the first aircraft and the second aircraft is calculated based on the equatorial radius of the earth ellipsoid, the first parameter, and the second parameter.

[0053] Specifically, the first parameter is U1=arctan((1-f)·tan(latA)), and the second parameter is U2=arctan((1-f)·tan(latB)); let λ be the initial longitude difference, that is, λ=ΔL; iterate and repeat the following steps until the convergence condition |λ-λ is met. prev ∣<10 -12 Or reach the maximum number of iterations:

[0054]

[0055] cosσ=sinU1·sinU2+cosU1·cosU2·cosλ;

[0056] σ=arctan2(sinσ,cosσ);

[0057]

[0058] cos 2 α=1-sin 2 α;

[0059] cos2σ m =cosσ-2·sinU1·sinU2 / cos 2 α;

[0060] If cos 2 α=0, then cos2σ m =0, correct longitude difference;

[0061] λ prev =λ; λ=L+(1-C)·f·sinα·(σ+C·sinσ·(cos2σ m +C·cosσ·(-1+2·cos2 2σ m )));

[0062] Where C = f / 16·cos 2 α·(4+f·(4-3·cos 2 α)).

[0063] When the iteration converges, the geographic distance between the two points is calculated as S = b·A·(σ-Δσ); the unit is meter;

[0064] in, Δσ=u 2 / 1024·(σ+u 2 ·(cos 2 σm+u 2 ·(-1+2·cos 2 2σm))); a is the equatorial radius of the earth's ellipsoid, which is 6378137 meters; the flattening f is the degree of flatness of the ellipsoid, which is 1 / 298.26; the minor axis b is calculated by the formula b=a(1-f).

[0065] The altitude difference Δh between the first aircraft and the second aircraft is calculated according to the altitude in the first flight information and the altitude in the second flight information.

[0066] In this embodiment, the height of the first aircraft is denoted as h A , the height of the second aircraft is recorded as h B ;

[0067] The height difference between the first aircraft and the second aircraft Δh=|h B -h A |.

[0068] The three-dimensional straight-line distance D between the first aircraft and the second aircraft is calculated according to the geographical distance S and the height difference Δh.

[0069] According to the above steps, a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft are calculated one by one.

[0070] In this embodiment, the calculation process of the three-dimensional straight-line distance D between two points is as follows:

[0071]

[0072] Wherein, S is the geographical distance; Δh is the height difference between the first aircraft and the second aircraft.

[0073] S3. Allocate corresponding warning levels to multiple three-dimensional straight-line distances according to a preset warning strategy.

[0074] In this embodiment, the preset warning strategy specifically includes:

[0075] When the height difference Δh between the first aircraft and the second aircraft is less than or equal to x meters, and the corresponding three-dimensional straight-line distance D is less than y meters, the warning level is level 1 warning;

[0076] When the height difference Δh between the first aircraft and the second aircraft is greater than x meters, and the corresponding three-dimensional straight-line distance D is less than y meters, the warning level is level 2 warning;

[0077] When the three-dimensional straight-line distance D between the first aircraft and the second aircraft is greater than or equal to y meters and less than z meters, the warning level is level 3 warning;

[0078] When the three-dimensional straight-line distance D between the first aircraft and the second aircraft is greater than or equal to z meters and less than w meters, the warning level is level 4 warning;

[0079] Among them, x<y<z<w.

[0080] Specifically, for example, x=100, y=500, z=1000, w=1500; the range of the three-dimensional straight-line distance D corresponding to each warning level is as follows:

[0081] 1000m≤D<1500m, Level 4 warning;

[0082] 500m≤D<1000m, Level 3 warning;

[0083] D<500m, and Δh>100m, Level 2 warning;

[0084] D<500m, and Δh≤100m, level 1 warning.

[0085] S4. Allocation of corresponding warning levels and matching warning modes according to the plurality of three-dimensional straight-line distances to generate warning information corresponding to the first aircraft.

[0086] In this embodiment, step S4 specifically includes:

[0087] Assign an alarm sound and visual reminder light to each warning level;

[0088] The warning levels corresponding to the plurality of second aircraft are associated with the corresponding second aircraft information, and the warning levels corresponding to the plurality of second aircraft and the first aircraft are sorted in descending order to generate warning information corresponding to the first aircraft.

[0089] Specifically, the visual prompt light corresponding to the fourth level warning is red, the visual prompt light corresponding to the third level warning is orange, the visual prompt light corresponding to the second level warning is yellow, and the visual prompt light corresponding to the first level warning is blue.

[0090] S5. Issue warning prompts in the order of warning information.

[0091] Specifically, the warning information is sent to the user through a display screen and a loudspeaker.

[0092] Reference Figure 2 The present invention provides an aircraft anti-collision warning device, comprising:

[0093] A data acquisition module, used for acquiring in real time first flight information of a first aircraft and a plurality of second flight information corresponding to a plurality of second aircraft adjacent to the first aircraft;

[0094] A first processing module is used to analyze a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft one by one according to the first flight information and the plurality of second flight information;

[0095] The second processing module is used to assign corresponding warning levels to multiple three-dimensional straight-line distances according to a preset warning strategy;

[0096] An early warning generation module is used to assign corresponding early warning levels and match early warning modes according to a plurality of three-dimensional straight-line distances to generate early warning information corresponding to the first aircraft;

[0097] The prompt module is used to provide warning prompts in the order of warning information.

[0098] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aircraft collision avoidance warning method, characterized in that: The following steps are involved: S1. Acquire in real time first flight information of a first aircraft and a plurality of second flight information corresponding one-to-one to a plurality of second aircraft adjacent to the first aircraft; S2, analyzing one by one a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft according to the first flight information and the plurality of second flight information; S3, assigning corresponding warning levels to multiple three-dimensional straight-line distances according to a preset warning strategy; S4, assigning corresponding warning levels and matching warning modes according to the multiple three-dimensional straight-line distances to generate warning information corresponding to the first aircraft; S5. Issue warning prompts in the order of warning information.

2. The aircraft collision avoidance warning method according to claim 1, characterized in that: Step S1 specifically includes: Acquire first flight information of the first aircraft in real time, where the first flight information includes a unique aircraft identification code, longitude, latitude, and altitude of the first aircraft; With the first aircraft as the center, an anti-collision area is radiated according to a preset diameter, and multiple second flight information corresponding to multiple second aircraft in the anti-collision area are obtained. The second flight information includes the corresponding second aircraft's unique aircraft identification code, longitude, latitude, and altitude.

3. The aircraft collision avoidance warning method according to claim 2, characterized in that: Step S2 specifically includes: Calculate the geographical distance S between the first aircraft and the second aircraft according to the longitude and latitude in the first flight information and the longitude and latitude in the second flight information; Calculate the height difference Δh between the first aircraft and the second aircraft according to the height in the first flight information and the height in the second flight information; Calculate the three-dimensional straight-line distance D between the first aircraft and the second aircraft according to the geographical distance S and the height difference Δh; According to the above steps, a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft are calculated one by one.

4. The aircraft collision avoidance warning method according to claim 3, characterized in that: The calculating the geographical distance S between the first aircraft and the second aircraft according to the longitude and latitude in the first flight information and the longitude and latitude in the second flight information specifically includes: According to the longitude and latitude in the first flight information and the longitude and latitude in the second flight information, the longitude and latitude of the first aircraft are set to (lonA, latA) and the longitude and latitude of the second aircraft are set to (lonB, latB); The longitude difference ΔL is calculated based on the longitude and latitude of the first aircraft (lonA, latA) and the longitude and latitude of the second aircraft (lonB, latB); A first parameter related to the first aircraft, a second parameter related to the second aircraft, and the equatorial radius of the earth ellipsoid are obtained, and a geographic distance S between the first aircraft and the second aircraft is calculated based on the equatorial radius of the earth ellipsoid, the first parameter, and the second parameter.

5. The aircraft collision avoidance warning method according to claim 3, characterized in that: The preset early warning strategy specifically includes: When the height difference Δh between the first aircraft and the second aircraft is less than or equal to x meters, and the corresponding three-dimensional straight-line distance D is less than y meters, the warning level is level 1 warning; When the height difference Δh between the first aircraft and the second aircraft is greater than x meters, and the corresponding three-dimensional straight-line distance D is less than y meters, the warning level is level 2 warning; When the three-dimensional straight-line distance D between the first aircraft and the second aircraft is greater than or equal to y meters and less than z meters, the warning level is level 3 warning; When the three-dimensional straight-line distance D between the first aircraft and the second aircraft is greater than or equal to z meters and less than w meters, the warning level is level 4 warning; Among them, x<y<z<w.

6. The aircraft collision avoidance warning method according to claim 5, characterized in that: Step S4 specifically includes: Assign an alarm sound and visual reminder light to each warning level; The warning levels corresponding to the plurality of second aircraft are associated with the corresponding second aircraft information, and the warning levels corresponding to the plurality of second aircraft and the first aircraft are sorted in descending order to generate warning information corresponding to the first aircraft.

7. An aircraft collision avoidance warning device, characterized in that: include: A data acquisition module, used for acquiring in real time first flight information of a first aircraft and a plurality of second flight information corresponding to a plurality of second aircraft adjacent to the first aircraft; A first processing module is used to analyze a plurality of three-dimensional straight-line distances D corresponding to the first aircraft and the plurality of second aircraft one by one according to the first flight information and the plurality of second flight information; The second processing module is used to assign corresponding warning levels to multiple three-dimensional straight-line distances according to a preset warning strategy; An early warning generation module is used to assign corresponding early warning levels and match early warning modes according to a plurality of three-dimensional straight-line distances to generate early warning information corresponding to the first aircraft; The prompt module is used to provide warning prompts in the order of warning information.

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