Flight anti-collision method and apparatus based on electromagnetic field detection of overhead transmission line

Patent metadata

Field	Value
Publication number	US-12416928-B2
Application number	US-202217926879-A
Country	US
Kind code	B2
Filing date	Jun 17, 2022
Priority date	Aug 26, 2021
Publication date	Sep 16, 2025
Grant date	Sep 16, 2025

Abstract

The present disclosure provides a flight anti-collision method and apparatus based on electromagnetic field detection of an overhead transmission line. An example method includes: determining whether an overhead transmission line around is an Alternating Current (AC) transmission line or a (Direct Current) DC transmission line; if the overhead transmission line is an AC transmission line, determining a position relationship between an aircraft and the overhead transmission line on the basis of a phase distribution model and an electric field phase and a magnetic field phase measured by a phase detector on the aircraft; if the overhead transmission line around is a DC transmission line, determining the position relationship between the aircraft and the overhead transmission line on the basis of a magnetic field intensity distribution model and the magnetic field intensities collected by magnetic field intensity sensors on the aircraft; and thus controlling the aircraft.

First claim

What is claimed is:

1. A flight anti-collision method for an aircraft having a resonant circuit, one or more phase detectors and one or more intensity sensors to detect an electromagnetic field of an overhead transmission line, comprising:
determining, from an output of the resonant circuit, whether the overhead transmission line is an Alternating Current (AC) transmission line or a Direct Current (DC) transmission line;
if the overhead transmission line is an AC transmission line, determining a first position relationship between the aircraft and the overhead transmission line from a phase distribution model and an electric field phase and a magnetic field phase measured by the one or more phase detectors, wherein the phase distribution model provides a distribution of electric field phases and magnetic field phases generated by the AC transmission line at a plurality of points of a three-dimensional space;
if the overhead transmission line is a DC transmission line, determining the first position relationship between the aircraft and the overhead transmission line from a magnetic field intensity distribution model and one or more magnetic field intensities collected by the one or more intensity sensors on the aircraft, wherein the magnetic field intensity distribution model provides a relationship between the magnetic field intensity at a plurality of points in the three-dimensional space and a vertical distance from each of the plurality of points to the overhead transmission line; and
controlling the aircraft using the first position relationship between the aircraft and the overhead transmission line;
wherein the phase distribution model is:

ΔΦ
=

Φ
H

-

Φ
E

=

180
π

[

arc
⁢

cot
⁡
(

c

ω
⁢
r

-

ω
⁢
r

c

)

-

arc
⁢

cot
⁡
(

ω
⁢
r

c

)

]

wherein Φ H is the magnetic field phase, Φ E is the electric field phase, ω is a current change frequency of the AC transmission line, C is light velocity, and r is a vertical distance from the aircraft to the AC transmission line.

2. The method according to claim 1 , wherein if the overhead transmission line is the AC transmission line, the method further comprises:
determining a second position relationship between the aircraft and the overhead transmission line using the magnetic field intensity distribution model and the magnetic field intensity collected by the magnetic field intensity sensor on the aircraft;
fusing the first position relationship and the second position relationship to obtain a final position relationship between the aircraft and the overhead transmission line.

3. The method according to claim 2 , further comprising:
determining a first weight corresponding to the first position relationship and a second weight corresponding to the second position relationship during the fusing using an estimated distance from the aircraft to the overhead transmission line, wherein the estimated distance is positively related to the first weight, and the estimated distance is negatively related to the second weight.

4. The method according to claim 3 , wherein the determining a first weight corresponding to the first position relationship and a second weight corresponding to the second position relationship during the fusing comprises:
if the estimated distance from the aircraft to the overhead transmission line is less than a preset value, determining that the first position relationship corresponds to a weight value W1, and the second position relationship corresponds to a weight value W2; and otherwise, determining that first position relationship corresponds to a weight value W2, and the second position relationship corresponds to a weight value W1, wherein W1 is less than W2.

5. The method according to claim 1 , wherein the determining the first position relationship comprises:
acquiring the vertical distance from the aircraft to the AC transmission line using the phase distribution model and the electric field phase and the magnetic field phase measured by the one or more phase detectors on the aircraft;
acquiring a magnetic field direction measured by a magnetic field direction sensor and an electric field direction measured by an electric field direction sensor on the aircraft;
obtaining a Poynting vector of the position where the aircraft is located on the basis of the magnetic field direction and the electric field direction;
determining the power line trend of the AC transmission line using the Poynting vector; and
determining the spatial position of the AC transmission line relative to the aircraft using the electric field direction, the vertical direction, and the power line trend.

6. The method according to claim 1 , wherein a magnetic field intensity sensor Q1 and a magnetic field intensity sensor Q2 are symmetrically arranged on both sides of a central axis of the aircraft; the distance between the magnetic field intensity sensor Q1 and the magnetic field intensity sensor Q2 is L; the magnetic field intensity distribution model is

B
=

μ
0

⁢
I

2
⁢
π
⁢
r

,

 wherein I is the current intensity of the overhead transmission line, r is the vertical direction from a certain point in the three-dimensional space to the overhead transmission line, and B is the magnetic field intensity generated by the overhead transmission line at a certain point in the three-dimensional space.

7. An electronic device, comprising a memory, a processor, and

Assignees

• The Second Res Institute Of Caac
• Univ Electronic Sci & Tech China

Inventors

• Gao Mingyang
• Yan Fengshuo
• Huang Rui
• Yu Hui
• Xiong Kui
• Zhang Jingting
• Niu Xialei
• Mu Fengjun
• Zeng Jing
• Zhao Jianwei
• Bai Weicheng
• Liu Kun

Classifications

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G05D1/622

  Obstacle avoidance (predicting or avoiding probable or impending collision of road vehicles B60W30/08) · CPC title

• G05D2109/20

  Aircraft, e.g. drones · CPC title

• G05D2111/30

  Radio signals · CPC title

• G05D1/2435 Primary

  Extracting 3D information · CPC title