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Analysis method of line-of-sight coverage of civil aviation navigation equipment combined with flight trajectory and altitude

A technology of flight trajectory and navigation equipment, which is applied in the field of line-of-sight coverage analysis of civil aviation navigation equipment combined with flight trajectory and variable altitude, can solve problems such as inability to guarantee flight safety, and achieve the effect of ensuring flight safety, ingenious conception, and scientific design

Active Publication Date: 2022-06-24
THE SECOND RES INST OF CIVIL AVIATION ADMINISTRATION OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a method for analyzing the line-of-sight coverage of civil aviation navigation equipment in combination with the variable altitude of the flight track, so as to solve the problem that there is no method for analyzing the line-of-sight coverage of the flight track with variable altitude in the prior art, and the problem of flight safety cannot be guaranteed.

Method used

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  • Analysis method of line-of-sight coverage of civil aviation navigation equipment combined with flight trajectory and altitude
  • Analysis method of line-of-sight coverage of civil aviation navigation equipment combined with flight trajectory and altitude
  • Analysis method of line-of-sight coverage of civil aviation navigation equipment combined with flight trajectory and altitude

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0133] as attached Figure 5 As shown, the present invention provides an example of an airport applying the method of the present invention to perform line-of-sight coverage analysis, which specifically includes the following steps:

[0134] S1. Taking true north as 0 degrees, calculate the azimuth angle B of all obstacles relative to the navigation device, in degrees;

[0135] In the S1, the calculation formula of the azimuth angle B is:

[0136] B=90-A+360×T (1)

[0137] T=A / 360, rounded down (2)

[0138] A=atan2(x,y) , converted into an angle (3)

[0139] x = sin( O j - N j ) ×cos( O w ) (4)

[0140] y = cos( N w )×sin( O w )- sin( N w ) ×cos( O w ) ×cos( O j - N j ) (5)

[0141] in,( O w , O j ): the coordinates of the obstacle, where, O w is the latitude, O j is longitude;

[0142] ( N w , N j ) coordinates of the navigation device, where, N w is the latitude, N j is longitude.

[0143] S2. Screen the obstacles with the same orient...

example 1

[0192] Example 1: Fθ=20°, h 1 = 100 meters, H i = 250 meters, F 1 = 300 meters, D 1 =2500m, F 2 = 900 meters, D 2 =6000m.

[0193] 1. Since the obstacle has a width, the azimuth range formed by the obstacle and true north is calculated according to the boundary of the obstacle. After calculation, the azimuth angles formed by the left and right boundaries of the obstacle and the true north are 11.90° and 21.5° respectively, so the azimuth angle of the obstacle ranges from 11.9° to 21.5°.

[0194] 2. Fθ is located in the range of the obstacle azimuth angle of 11.9°~21.5°. Therefore, the obstacle is in the same orientation as the flight trajectory.

[0195] 3. After calculation, the shortest distance L between the left and right boundaries of the obstacle and the navigation equipment i =1508m.

[0196] Satisfy 0 i D 2 , so it may occlude the flight path.

[0197] 4. After calculation, k i = 0.1, k F =0.17, k i k F , h xi = 416 meters, therefore, h xi > F ...

example 2

[0200] Example 2: Fθ=20°, h 1 = 100 meters, H i = 400 meters, F 1 = 600 meters, D 1 =2000m, F 2 = 900 meters, D 2 =6000m.

[0201] The azimuth angle formed by the connection line between the flight trajectory and the navigation device and true north is Fθ, the obstacle coordinates ( O w , O j ) and navigation device coordinates ( N w , N j ) does not change, therefore, the calculation process for determining whether the obstacle may block the flight trajectory in the first three steps is the same as that in Example 1, so it will not be repeated here, and the calculation will start from step 4 below.

[0202] 4. After calculation, k i =0.20, k F =0.075, k i > k F , h xi = 661 meters, therefore, h xi F 2 , the obstacle will block the flight height from 661 meters to 900 meters in the flight path, which is marked as a dashed line, and 600 meters to 661 meters without blocking, which is marked as a solid line.

[0203] 5. After calculation, the dista...

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Abstract

The invention discloses a method for analyzing the line-of-sight coverage of civil aviation navigation equipment combined with flight track and variable altitude, which belongs to the technical field of civil aviation navigation equipment, and solves the problem that there is no method for line-of-sight coverage analysis for the flight track with variable altitude in the prior art, and flight safety cannot be guaranteed The problem. The method of the present invention comprises the following steps: S1. Taking the true north as 0 degree, calculate the azimuth angle B of all obstacles relative to the navigation equipment; S2. screen the obstacles with the same orientation as the flight track; S3. calculate n obstacle pairs Whether the flight path causes occlusion, and calculate the occlusion position. The present invention proposes for the first time the blockage calculation method of the obstacle to the variable altitude flight track, including the specific block position caused, that is, the critical position where the received signal changes from presence to non-existence, and the signal coverage on the flight track after blockage. Altitude control and aircraft flight altitude adjustment provide a reference basis, which effectively guarantees flight safety.

Description

technical field [0001] The invention belongs to the technical field of civil aviation navigation equipment, and in particular relates to a line-of-sight coverage analysis method for civil aviation navigation equipment combined with flight trajectory variable height. Background technique [0002] Civil aviation ground-based navigation equipment mainly provides guidance for aircraft flight, such as omnidirectional beacons, which provide guidance for aircraft on the route and when flying in and out of the airport, while the instrument landing system provides localizer and glide path guidance for aircraft approach to facilitate The aircraft aligns with the runway and descends along the established glide angle until landing. Since the land-based navigation equipment is a radio equipment, the electromagnetic wave signals transmitted by the equipment and the signals received by the aircraft onboard equipment are easily affected by terrain and buildings. If they encounter high obsta...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/20G01C5/00G01C3/00G01C1/00G08G5/00
CPCG01C21/20G01C3/00G01C5/005G01C1/00G08G5/0073
Inventor 林欢梁飞叶家全李沅锴许健袁斌杨萍孙彦龙李鑫李润文施瑞邹杰李清栋高静杨正波崔铠韬
Owner THE SECOND RES INST OF CIVIL AVIATION ADMINISTRATION OF CHINA
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