CN115856946A - Aircraft alignment channel detection method, device, terminal and storage medium - Google Patents
Aircraft alignment channel detection method, device, terminal and storage medium Download PDFInfo
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Abstract
The invention relates to the field of aligning an aircraft to a channel, and particularly discloses a method, a device, a terminal and a storage medium for detecting the aligning of the aircraft to the channel, which are used for acquiring real-time longitude and latitude coordinates of the aircraft; acquiring a channel connection line; under the spherical coordinates, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft; judging whether the calculated horizontal distance is within a first preset distance threshold range; if so, aligning the aircraft with the channel; if not, the aircraft is not aligned with the channel, and an alarm is given. The invention judges whether to align the channel by using the horizontal distance between the aircraft coordinate and the channel extension line, has convenient and quick operation, is not influenced by scenes, is suitable for various airplanes, and improves the alignment efficiency.
Description
Technical Field
The invention relates to the field of aircraft alignment channel, in particular to a method, a device, a terminal and a storage medium for detecting an aircraft alignment channel.
Background
With the development of various aircrafts such as a GPS positioning technology, an airplane and the like, the requirements for real-time accurate monitoring of the aircrafts are increasing, and means and methods required for preventing accidents are increasing, such as airplane take-off and landing monitoring at an airport, whether the airplane is off-tracking, whether the airplane is aligned with a channel for early warning, real-time monitoring of the distance between the airplane and the channel entrance, a plan view of the aircrafts and the channel, and display of a three-dimensional coordinate graph.
Early warning of the pilot flight of an aircraft to a channel is currently generally performed using an ILS (Instrument Landing System) Instrument Landing System. The ILS is used for realizing course and glide-slope guidance by two beams of radio signals transmitted from the ground, establishing a virtual path pointing to the air from a runway, determining the relative position of the aircraft and the path through airborne receiving equipment, enabling the aircraft to fly to the runway along the correct direction and descend stably, and finally realizing safe landing aiming at the runway.
The complete ILS system contains two subsystems, one being a course stage that provides horizontal guidance and a lower stage that provides vertical guidance. The course platform antenna is mainly a directional antenna and is generally fixed at the tail end of a runway, when the course platform antenna is used, the antenna can send a narrow wave beam, one wave beam is deviated to the left of the centerline of the runway, the other wave beam is deviated to the right of the centerline, and the intersection line of the two wave beams is the centerline of the runway. The signal is searched from the time of descending of the airplane, if the airplane is not on the central line of the runway, the intensities of the two waves with different frequencies received by the airplane are different, and the airplane is inclined to the side where the intensities are high. If the two received waves have the same intensity, the aircraft is indicated to be on the intersection line of the two waves, namely on the central line of the runway.
The Instrument Landing System (ILS) has the advantages of providing accurate data information even under complex weather conditions and being capable of changing according to changes in weather conditions, but has the disadvantages of providing fewer runway types, resulting in that individual airplanes are not suitable for the system and the use scene is limited, so that it is necessary to provide an alignment channel detection scheme suitable for various airplanes.
Disclosure of Invention
In order to solve the problems, the invention provides a method, a device, a terminal and a storage medium for detecting an aircraft alignment channel, which are used for judging whether the aircraft is aligned with the channel or not by using the horizontal distance between the coordinates of the aircraft and the extended line of the channel, are convenient and quick to operate, are not influenced by scenes, are suitable for various airplanes, and improve the alignment efficiency.
In a first aspect, the technical solution of the present invention provides a method for detecting an aircraft alignment channel, including the following steps:
acquiring real-time longitude and latitude coordinates of an aircraft;
acquiring a channel connection line;
under the spherical coordinates, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft;
judging whether the calculated horizontal distance is within a first preset distance threshold range;
if so, aligning the aircraft with the channel; if not, the aircraft is not aligned with the channel, and an alarm is given.
Further, acquiring a channel connection line specifically includes:
measuring longitude and latitude coordinates A of a point A at a channel entrance, wherein the point A is on a channel central line;
measuring longitude and latitude coordinates B of another point B on the center line of the channel; the distance between the point A and the point B is larger than a second preset distance threshold;
and connecting the point B of the channel to the point A to obtain a channel connecting line.
Further, under the spherical coordinate, based on the real-time longitude and latitude coordinate of the aircraft, the horizontal distance between the real-time position of the aircraft and the extended line of the channel is calculated, and the method specifically comprises the following steps:
recording real-time longitude and latitude coordinates of the aircraft as C;
calculating the distances of the line segments AB, AC and BC by utilizing the longitude and latitude coordinates of the spherical surface;
calculating the area S of a triangle formed by the three points A, B and C according to the distances of the line segments AB, AC and BC;
calculating the horizontal distance h between the real-time position of the aircraft and the extended line of the channel by using the following formula:
h=2S/ L AB ；
wherein L is AB The distance of the line segment AB.
Further, the distance between the line segments AB, AC and BC is calculated by using the longitude and latitude coordinates of the spherical surface, specifically by using the following formula:
L AB = arccos (cos (a point latitude arc value) × cos (B point latitude arc value) × cos (a point longitude arc value-B point longitude arc value) + sin (a point latitude arc value) × sin (B point latitude arc value)) × 6378.137 × 1000;
L AC = arccos (cos (a point latitude arc value) × cos (C point latitude arc value) × cos (a point longitude arc value-C point longitude arc value) + sin (a point latitude arc value) × sin (C point latitude arc value)) × 6378.137 × 1000;
L BC = arccos (cos (point B latitude arc value) × cos (point C latitude arc value) × cos (point B longitude arc value-point C longitude arc value) + sin (point B latitude arc value) × sin (point C latitude arc value)) × 6378.137 × 1000;
where 6378.137 is the earth radius and arccos refers to an inverse cosine operation.
Further, calculating the area S of a triangle formed by the three points a, B and C according to the distances of the line segments AB, AC and BC, specifically calculating by the following formula:
S = sqrt[(L general (1) /2 ）* （(L General (1) /2） - L AB ) * （(L General assembly /2） -L BC ) * （(L General (1) /2） - L AC )]；
Wherein L is General assembly Is the sum of AB, AC, BC line segments, L General assembly = (L AB + L BC + L AC ) (ii) a sqrt refers to the square root operation.
Further, the method comprises the following steps:
drawing points A and B on a map, and drawing an AB extension line;
projecting the ground of the real-time position of the aircraft on a map, and drawing and marking the ground as a point C;
the horizontal distance h is displayed on the map in real time.
Further, the method specifically comprises the following steps:
and if the distance between the aircraft and the channel entrance is smaller than a third preset distance threshold before the aircraft enters the channel entrance, and the horizontal distance between the real-time position of the aircraft and the channel extension line is not in the threshold range, sending an adjustment alarm.
In a second aspect, the invention provides an aircraft alignment channel detection device, including,
an aircraft position acquisition module: acquiring real-time longitude and latitude coordinates of an aircraft;
channel connection acquisition module: acquiring a channel connection line;
a deviation distance calculation module: under the spherical coordinates, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft;
an alignment judgment module: judging whether the calculated horizontal distance is within a first preset distance threshold range or not;
an alignment processing module: if so, aligning the aircraft with the channel; if not, the aircraft is not aligned with the channel, and an alarm is given.
In a third aspect, a technical solution of the present invention provides a terminal, including:
a memory for storing an aircraft alignment channel detection program;
and the processor is used for realizing the steps of the aircraft alignment channel detection method in any one of the above aspects when executing the aircraft alignment channel detection program.
In a fourth aspect, the present invention provides a computer-readable storage medium, where an aircraft alignment channel detection program is stored, and when executed by a processor, the aircraft alignment channel detection program implements the steps of the aircraft alignment channel detection method according to any one of the above items.
Compared with the prior art, the aircraft alignment channel detection method, the aircraft alignment channel detection device, the aircraft alignment channel detection terminal and the aircraft alignment channel detection storage medium have the following beneficial effects: the method is simple and convenient, is not influenced by environment, is suitable for various airplanes, and improves the alignment efficiency.
Drawings
For a clearer explanation of the embodiments or technical solutions of the prior art of the present application, the drawings needed for the description of the embodiments or prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic flow chart of a method for detecting an aircraft alignment channel according to an embodiment of the present invention.
Fig. 2 is a schematic flowchart of an embodiment of a method for detecting an aircraft alignment channel according to an embodiment of the present invention.
Fig. 3 is a block diagram illustrating a structure of an aircraft alignment channel detection device according to an embodiment of the present invention.
Fig. 4 is a schematic structural diagram of a terminal according to an embodiment of the present invention.
Detailed Description
In order that those skilled in the art will better understand the disclosure, the following detailed description will be given with reference to the accompanying drawings. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Fig. 1 is a schematic flow chart of an aircraft alignment channel detection method provided by an embodiment of the present invention, and as shown in fig. 1, the method includes the following steps.
S1, acquiring real-time longitude and latitude coordinates of the aircraft.
The aircraft reports the longitude and latitude coordinates of the GPS in real time, namely the GPS on the aircraft sends the longitude and latitude coordinates to the background in real time, and the background judges whether the aircraft is aligned with a channel according to the longitude and latitude coordinates of the aircraft.
And S2, acquiring a channel connection line.
The channel connecting line is a connecting line of channel central lines, and the extending line of the channel central lines can be correspondingly made after the channel connecting line is obtained.
And S3, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft under the spherical coordinates.
It should be noted that the channel connection line is represented by coordinates, the aircraft latitude and longitude coordinates represent the position of the aircraft, and the horizontal distance between the aircraft latitude and longitude coordinates and the channel extension line, that is, the length between the aircraft distance and the channel extension line, is calculated.
And S4, judging whether the calculated horizontal distance is within a first preset distance threshold range.
And S5, if so, aligning the aircraft to the channel.
And S6, if the aircraft is not in the air, the aircraft is not aligned with the channel, and an alarm is given.
It should be noted that the staff configures a first preset distance threshold according to the precision requirement, if the horizontal distance is within the first preset distance threshold range, it is indicated that the aircraft is aligned with the channel, and if the horizontal distance exceeds the first preset distance threshold range, it is indicated that the aircraft is not aligned with the channel, and at this time, an alarm is sent to prompt the flight staff. For example, a first preset distance threshold is set to 0.5m, and if the calculated horizontal distance is less than 0.5m, it is indicated that the aircraft is aligned with the channel.
According to the method for detecting the alignment of the aircraft to the channel, the longitude and latitude coordinates of the aircraft are obtained in real time, the channel connecting line is obtained, the horizontal distance between the aircraft and the channel extension line is calculated under the spherical coordinates, and whether the aircraft is aligned to the channel is judged based on the horizontal distance.
To further understand the present invention, an embodiment is provided below to further explain the present invention in detail, and fig. 2 is a schematic flow chart of the embodiment, which is utilized by the embodimentAnd connecting the channels B to A by using the GPS longitude and latitude coordinate C reported by the aircraft in real time, the channel entrance longitude and latitude coordinate A and the longitude and latitude coordinate B of the other point of the linear channel according to mathematical calculation, judging whether the aircraft C is positioned on the extension line from B to A, and judging whether the real-time position of the aircraft is aligned with the runway and the deviation error. Calculating the distance of the aircraft deviating from the channel is to calculate the vertical distance between the projection coordinate of the aircraft C point on the spherical surface and the extension line of the channel AB under the spherical coordinate. Forming a triangle by using points A, B and C, calculating the spherical distances of line segments AB, AC and BC, calculating the area S of the triangle by using a Helen formula, and calculating the area according to another area calculating method, wherein S = (L) AB * h) 2, the length of the line segment AB is the bottom, S is the area obtained by using the Helen formula, h is the distance of the aircraft deviating from the channel to be calculated, and h = 2S/L AB . And judging h, and when h is smaller than a certain error (such as smaller than 0.5m and other values), considering that the aircraft is aligned with the runway.
As shown in fig. 2, this embodiment includes the following steps.
S1, measuring longitude and latitude coordinates A of a point A at a channel entrance, wherein the point A is on a channel central line, and measuring longitude and latitude coordinates B of another point B on the channel central line.
It should be noted that the point a and the point B are both on the center line of the air path, and the distance between the point a and the point B is greater than the second preset distance threshold. The second preset distance threshold is set according to requirements, for example, 500m or 1000m is guaranteed to be separated between the point a and the point B, so that the detection accuracy is guaranteed.
And measuring the longitude and latitude of the channel entry point A and the channel B by adopting a unified coordinate system and an accurate coordinate acquisition tool.
And S2, connecting the point B of the channel to the point A to obtain a channel connecting line.
And S3, acquiring real-time longitude and latitude coordinates C of the aircraft.
The GPS on the aircraft sends the latitude and longitude coordinates of the aircraft to the background.
And S4, calculating the distances of the line segments AB, AC and BC by utilizing the longitude and latitude coordinates of the spherical surface.
The distance formula for calculating the A and B points of the spherical surface 2 is as follows:
L AB = arccos (cos (a point latitude arc value) × cos (B point latitude arc value) × cos (a point longitude arc value-B point longitude arc value) + sin (a point latitude arc value) × sin (B point latitude arc value)) × 6378.137 × 1000.
The distance formula for calculating the A and C points of the spherical surface 2 is as follows:
L AC = arccos (cos (a point latitude arc value) × cos (C point latitude arc value) × cos (a point longitude arc value-C point longitude arc value) + sin (a point latitude arc value) × sin (C point latitude arc value)) × 6378.137 × 1000.
The distance formula of B and C of the spherical 2 point is calculated as follows:
L BC = arccos (cos (point B latitude arc value) × cos (point C latitude arc value) × cos (point B longitude arc value-point C longitude arc value) + sin (point B latitude arc value) × sin (point C latitude arc value)) × 6378.137 × 1000.
Where 6378.137 is the earth radius and arccos refers to an inverse cosine operation.
And S5, calculating the area S of a triangle formed by the three points A, B and C according to the distances of the line segments AB, AC and BC.
Calculating the sum L of the triangle area, AB, AC and BC line segments by using the Helen formula General assembly = (L AB + L BC +L AC )。
Area S = sqrt [ (L) of triangle formed by three points A, B and C General (1) /2 ）* （(L General assembly /2） - L AB ) * （(L General assembly /2） -L BC ) * （(L General assembly /2） - L AC )]. sqrt refers to the square root operation.
And S6, calculating the horizontal distance h between the real-time position of the aircraft and the extended line of the channel.
Specifically, h = 2S/L AB 。
Namely, the line segment AB is used as the bottom of the triangle, and the vertical distance h of the extension line of the line segment AB is calculated through the area S. I.e. using another area finding method S = (L) AB * h) /2, deducing h = 2S/L AB 。
The calculated h is the horizontal distance between the ground projection C point of the aircraft and the extended line of the channel, and whether the aircraft is aligned with the runway or not and how far the aircraft deviates from the runway can be obtained by judging the distance.
And S7, judging whether the horizontal distance h is within a first preset distance threshold range.
And S8, if so, aligning the aircraft to the channel.
And S9, if the aircraft is not in the air, the aircraft is not aligned with the channel, and an alarm is given. And simultaneously, the aircraft adjusts the position and continuously acquires the real-time longitude and latitude coordinates C of the aircraft.
In order to facilitate the checking of the background and the flight personnel, in some specific embodiments, the points A and B are drawn on a system map, a navigation channel and the effect processing of the dotted line of the extension line of the navigation channel are drawn, and then the real-time position transmitted back by a radar or an aircraft is used for the real-time landing aircraft position on the map. Specifically, drawing points A and B on a map, drawing an AB extension line, projecting the ground of the real-time position of the aircraft on the map, drawing and marking the ground as a point C, and then displaying the calculated horizontal distance h on the map in real time. Whether the landing point of aircraft C falls on an extension line, indicating that substantial alignment has occurred, can be seen on the map.
In some specific embodiments, specifically before the aircraft enters the channel entrance, when the distance from the channel entrance is smaller than a third preset distance threshold, if the horizontal distance between the real-time position of the aircraft and the channel extension line is still not within the threshold range, an adjustment alarm is issued to inform flight personnel of adjusting the direction of the aircraft. It should be noted that the third preset distance threshold is set by the staff according to actual needs or situations, and it is understood that, within an allowable range, the larger the third preset distance threshold is set, the longer the time for the pilot to adjust the third preset distance threshold is.
In addition, auxiliary means can be arranged for confirming that the aircraft is finely adjusted by means of laser alignment to a channel and the like at a short distance, and the aircraft can be ensured to be aligned to a runway entrance by various means.
The above detailed description is given to an embodiment of an aircraft alignment channel detection method, and based on the aircraft alignment channel detection method described in the above embodiment, an embodiment of the present invention further provides an aircraft alignment channel detection device corresponding to the method.
Fig. 3 is a schematic block diagram of a structure of an aircraft alignment channel detection apparatus provided in an embodiment of the present invention, and as shown in fig. 3, the apparatus includes: the device comprises an aircraft position acquisition module, a channel connecting line acquisition module, a deviation distance calculation module, an alignment judgment module and an alignment processing module.
An aircraft position acquisition module: and acquiring real-time longitude and latitude coordinates of the aircraft.
Channel connection acquisition module: and acquiring a channel connection line.
A deviation distance calculation module: and under the spherical coordinates, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft.
An alignment judgment module: and judging whether the calculated horizontal distance is within a first preset distance threshold range.
An alignment processing module: if so, aligning the aircraft with the channel; if not, the aircraft is not aligned with the channel, and an alarm is given.
The aircraft position acquisition module acquires a channel connecting line, and specifically comprises: measuring longitude and latitude coordinates A of a point A at the entrance of the navigation channel, wherein the point A is on the center line of the navigation channel; measuring longitude and latitude coordinates B of another point B on the center line of the channel; the distance between the point A and the point B is larger than a second preset distance threshold; and connecting the point B of the channel to the point A to obtain a channel connecting line.
The deviation distance calculation module specifically calculates the horizontal distance by the following process: recording real-time longitude and latitude coordinates of the aircraft as C; calculating the distances of the line segments AB, AC and BC by utilizing the longitude and latitude coordinates of the spherical surface; calculating the area S of a triangle formed by the three points A, B and C according to the distances of the line segments AB, AC and BC; calculating the horizontal distance h between the real-time position of the aircraft and the extended line of the channel by using the following formula: h = 2S/L AB (ii) a Wherein L is AB The distance of the line segment AB.
The formula for calculating the distance of the line segment AB is as follows: l is AB = arccos (cos (a point latitude arc value) × cos (B point latitude arc value) × cos (a point longitude arc value-B point longitude arc value) + sin (a point latitude arc value) × sin (B point latitude arc value)) × 6378.137 = 1000; wherein, 6378.137 is the earth radius.
The formula for calculating the line segment AC distance is: l is AC = arccos (cos (a point latitude arc value) × cos (C point latitude arc value) × cos (a point longitude arc value-C point longitude arc value) + sin (a point latitude arc value) × sin (C point latitude arc value)) × 6378.137 × 1000.
The formula for calculating the distance of the line segment BC is: l is BC = arccos (cos (point B latitude arc value) × cos (point C latitude arc value) × cos (point B longitude arc value-point C longitude arc value) + sin (point B latitude arc value) × sin (point C latitude arc value)) × 6378.137 × 1000.
A. Area S = sqrt [ (L) of triangle formed by three points B and C General assembly /2 ）* （(L General assembly /2） - L AB ) * （(L General assembly /2） - L BC ) * （(L General assembly /2） -L AC )](ii) a Wherein L is General assembly Is the sum of AB, AC, BC line segments, L General assembly = (L AB + L BC +L AC )。
In some implementations, a display module is further provided: and drawing a point A and a point B on a map, drawing an AB extension line, projecting the ground of the real-time position of the aircraft on the map, drawing and marking the ground as a point C, and displaying the horizontal distance h on the map in real time.
In some embodiments, the alignment processing module is specifically configured to: and if the distance between the aircraft and the channel entrance is smaller than a third preset distance threshold before the aircraft enters the channel entrance, and the horizontal distance between the real-time position of the aircraft and the channel extension line is not in the threshold range, sending an adjustment alarm.
The aircraft alignment channel detection device of the present embodiment is used for implementing the aircraft alignment channel detection method described above, and therefore, the specific implementation of the device can be seen in the example section of the aircraft alignment channel detection method described above, and therefore, the specific implementation thereof can refer to the description of the corresponding partial embodiments, and will not be described herein again.
In addition, since the aircraft alignment channel detection device of this embodiment is used to implement the aircraft alignment channel detection method, its function corresponds to that of the above method, and is not described herein again.
Fig. 4 is a schematic structural diagram of a terminal device 400 according to an embodiment of the present invention, including: a processor 410, a memory 420, and a communication unit 430. The processor 410 is configured to implement the aircraft alignment channel detection program stored in the memory 420 by performing the following steps:
s1, acquiring real-time longitude and latitude coordinates of an aircraft;
s2, acquiring a channel connection line;
s3, under the spherical coordinates, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft;
s4, judging whether the calculated horizontal distance is within a first preset distance threshold range;
s5, if yes, aligning the aircraft to the channel; if not, the aircraft is not aligned with the channel, and an alarm is given.
The method acquires longitude and latitude coordinates of the aircraft in real time, acquires a channel connecting line, calculates the horizontal distance between the aircraft and the channel extension line under the spherical coordinates, and judges whether the aircraft aligns to the channel based on the horizontal distance.
The terminal apparatus 400 includes a processor 410, a memory 420, and a communication unit 430. The components communicate via one or more buses, and those skilled in the art will appreciate that the architecture of the servers shown in the figures is not intended to be limiting, and may be a bus architecture, a star architecture, a combination of more or less components than those shown, or a different arrangement of components.
The memory 420 may be used for storing instructions executed by the processor 410, and the memory 420 may be implemented by any type of volatile or non-volatile storage terminal or combination thereof, such as Static Random Access Memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic memory, flash memory, magnetic disk or optical disk. The executable instructions in memory 420, when executed by processor 410, enable terminal 400 to perform some or all of the steps in the method embodiments described below.
The processor 410 is a control center of the storage terminal, connects various parts of the entire electronic terminal using various interfaces and lines, and performs various functions of the electronic terminal and/or processes data by operating or executing software programs and/or modules stored in the memory 420 and calling data stored in the memory. The processor may be composed of an Integrated Circuit (IC), for example, a single packaged IC, or a plurality of packaged ICs connected with the same or different functions. For example, the processor 410 may include only a Central Processing Unit (CPU). In the embodiment of the present invention, the CPU may be a single operation core, or may include multiple operation cores.
A communication unit 430, configured to establish a communication channel so that the storage terminal can communicate with other terminals. And receiving user data sent by other terminals or sending the user data to other terminals.
The present invention also provides a computer storage medium, wherein the storage medium may be a magnetic disk, an optical disk, a read-only memory (ROM) or a Random Access Memory (RAM).
The computer storage medium stores an aircraft alignment channel detection program that when executed by a processor performs the steps of:
s1, acquiring real-time longitude and latitude coordinates of an aircraft;
s2, acquiring a channel connection line;
s3, under the spherical coordinates, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft;
s4, judging whether the calculated horizontal distance is within a first preset distance threshold range;
s5, if so, aligning the aircraft to the channel; if not, the aircraft is not aligned with the channel, and an alarm is given.
The method acquires longitude and latitude coordinates of the aircraft in real time, acquires a channel connecting line, calculates the horizontal distance between the aircraft and the channel extension line under the spherical coordinates, and judges whether the aircraft aligns to the channel based on the horizontal distance.
Those skilled in the art will readily appreciate that the techniques of the embodiments of the present invention may be implemented as software plus a required general purpose hardware platform. Based on such understanding, the technical solutions in the embodiments of the present invention may be substantially or partially embodied in the form of a software product, where the computer software product is stored in a storage medium, such as a usb disk, a removable hard disk, a Read-only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and the like, and includes several instructions to enable a computer terminal (which may be a personal computer, a server, or a second terminal, a network terminal, and the like) to execute all or part of the steps of the method in the embodiments of the present invention.
In the embodiments provided in the present invention, it should be understood that the disclosed system, apparatus and method may be implemented in other ways. For example, the above-described apparatus embodiments are merely illustrative, and for example, the division of the units is only one type of logical functional division, and other divisions may be realized in practice, for example, multiple units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection through some interfaces, devices or units, and may be in an electrical, mechanical or other form.
The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit.
The above disclosure is only for the preferred embodiments of the present invention, but the present invention is not limited thereto, and any non-inventive changes that can be made by those skilled in the art and several modifications and amendments made without departing from the principle of the present invention shall fall within the protection scope of the present invention.
Claims (10)
1. An aircraft alignment channel detection method is characterized by comprising the following steps:
acquiring real-time longitude and latitude coordinates of an aircraft;
acquiring a channel connection line;
under the spherical coordinates, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft;
judging whether the calculated horizontal distance is within a first preset distance threshold range;
if so, aligning the aircraft with the channel; if not, the aircraft is not aligned with the channel, and an alarm is given.
2. The aircraft alignment channel detection method according to claim 1, wherein obtaining a channel connection specifically comprises:
measuring longitude and latitude coordinates A of a point A at the entrance of the navigation channel, wherein the point A is on the center line of the navigation channel;
measuring longitude and latitude coordinates B of another point B on the center line of the channel; the distance between the point A and the point B is larger than a second preset distance threshold;
and connecting the point B of the channel to the point A to obtain a channel connecting line.
3. The method for detecting the alignment of the aircraft with the navigation channel according to claim 2, wherein the step of calculating the horizontal distance between the real-time position of the aircraft and the extended line of the navigation channel based on the real-time longitude and latitude coordinates of the aircraft under the spherical coordinates comprises the following steps:
recording real-time longitude and latitude coordinates of the aircraft as C;
calculating the distances of the line segments AB, AC and BC by utilizing the longitude and latitude coordinates of the spherical surface;
calculating the area S of a triangle formed by the three points A, B and C according to the distances of the line segments AB, AC and BC;
calculating the horizontal distance h between the real-time position of the aircraft and the extended line of the channel by using the following formula:
h=2S/ L AB ；
wherein L is AB The distance of the line segment AB.
4. The method according to claim 3, wherein the distances of the segments AB, AC, BC are calculated using the coordinates of the spherical longitude and latitude, specifically by the following formula:
L AB = arccos (cos (a point latitude arc value) × cos (B point latitude arc value) × cos (a point longitude arc value-B point longitude arc value) + sin (a point latitude arc value) × sin (B point latitude arc value)) × 6378.137 × 1000;
L AC = arccos (cos (a point latitude arc value) × cos (C point latitude arc value) × cos (a point longitude arc value-C point longitude arc value) + sin (a point latitude arc value) × sin (C point latitude arc value)) × 6378.137 × 1000;
L BC = arccos (cos (point B latitude arc value) × cos (point C latitude arc value) × cos (point B longitude arc value-point C longitude arc value) + sin (point B latitude arc value) × sin (point C latitude arc value)) × 6378.137 × 1000;
where 6378.137 is the earth radius and arccos refers to an inverse cosine operation.
5. The aircraft alignment channel detection method according to claim 4, wherein an area S of a triangle formed by three points A, B and C is calculated according to distances of line segments AB, AC and BC, specifically by the following formula:
S = sqrt[(L general assembly /2 ）* （(L General (1) /2） - L AB ) * （(L General assembly /2） -L BC ) * （(L General assembly /2） - L AC )]；
Wherein L is General (1) Is the sum of AB, AC, BC line segments, L General (1) = (L AB + L BC +L AC ) (ii) a sqrt refers to the square root operation.
6. The aircraft alignment channel detection method of claim 5, further comprising the steps of:
drawing points A and B on a map, and drawing an AB extension line;
the ground projection of the real-time position of the aircraft is drawn and marked as a point C on a map;
the horizontal distance h is displayed on the map in real time.
7. The aircraft alignment channel detection method of claim 6, comprising in particular the steps of:
and if the horizontal distance between the real-time position of the aircraft and the extended line of the channel is not within the range of the first preset distance threshold before the aircraft enters the channel entrance and the distance between the aircraft and the channel entrance is less than the third preset distance threshold, sending an adjustment alarm.
8. An aircraft alignment channel detection device is characterized by comprising,
an aircraft position acquisition module: acquiring real-time longitude and latitude coordinates of an aircraft;
channel connection acquisition module: acquiring a channel connection line;
a deviation distance calculation module: under the spherical coordinates, calculating the horizontal distance between the real-time position of the aircraft and the extended line of the channel based on the real-time longitude and latitude coordinates of the aircraft;
an alignment judgment module: judging whether the calculated horizontal distance is within a first preset distance threshold range;
an alignment processing module: if so, aligning the aircraft with the channel; if not, the aircraft is not aligned with the channel, and an alarm is given.
9. A terminal, comprising:
a memory for storing an aircraft alignment channel detection program;
a processor for implementing the steps of the aircraft alignment channel detection method according to any one of claims 1 to 7 when executing the aircraft alignment channel detection program.
10. A computer-readable storage medium, wherein the readable storage medium has stored thereon an aircraft alignment lane detection program, which when executed by a processor implements the steps of the aircraft alignment lane detection method of any one of claims 1-7.
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