WO2013141605A1 - Système et procédé d'identification de type d'avion et guidage d'accostage - Google Patents

Système et procédé d'identification de type d'avion et guidage d'accostage Download PDF

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Publication number
WO2013141605A1
WO2013141605A1 PCT/KR2013/002301 KR2013002301W WO2013141605A1 WO 2013141605 A1 WO2013141605 A1 WO 2013141605A1 KR 2013002301 W KR2013002301 W KR 2013002301W WO 2013141605 A1 WO2013141605 A1 WO 2013141605A1
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Prior art keywords
aircraft
vertical
distance
horizontal
model
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PCT/KR2013/002301
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English (en)
Korean (ko)
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이기창
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(주)안세기술
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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
    • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
    • G01S17/02—Systems using the reflection of electromagnetic waves other than radio waves
    • G01S17/06—Systems determining position data of a target
    • 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
    • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
    • G01S17/88—Lidar systems specially adapted for specific applications
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/002—Taxiing aids

Definitions

  • the present invention relates to a system and method for aircraft type identification and cycle induction, and more particularly, when the aircraft lands at the airport and travels and enters the boarding point where the boarding pier is installed, the visual cycle induction system ( VDGS) relates to a system and method for aircraft type identification and cycle guidance that can automatically determine the aircraft type using the laser beam, guide and guide to the correct cycle position.
  • VDGS visual cycle induction system
  • VDGS Visual Docking Guiding System
  • the aircraft guider guides the aircraft by manual signal every time the aircraft takes off and lands to guide the aircraft to the correct position.
  • VDGS electronic visual cycle guidance system
  • the fog is severely caught because the video image of the aircraft is extracted using the video camera and the reference image data is compared with the image pattern.
  • accurate image extraction is difficult due to environmental factors such as bad weather, hail, extreme weather, and backlighting, it is difficult to discriminate, and there are problems such as frequent determination errors.
  • the present invention has been made to solve the above problems, the object of the present invention is to launch a laser beam vertically and horizontally to scan the aircraft to measure the distance, length, height, etc. to the aircraft, and calculate the required algebraic calculation After calculating the desired information, and comparing the aircraft model database (DB) for each aircraft model to determine the type of aircraft, laser system that can increase the operation rate and reduce errors regardless of environmental factors such as bad weather
  • DB aircraft model database
  • the purpose of the present invention is to provide a system and method for aircraft type identification and periodic guidance.
  • the present invention provides a vertical / horizontal laser scanning and distance measuring device for measuring a distance as a signal reflected by being hit by an aircraft by firing a laser beam, and measuring the specifications of major parts of various types of aircraft. And a type data memory for storing, adding and updating information about the aircraft, and information measured by the vertical / horizontal laser scanning and distance measuring device and the type data memory.
  • the present invention provides a system for model discrimination and period induction of an aircraft including a data analysis determination algorithm processing device for comparing the information, reading the type or model of the aircraft, and controlling the vertical / horizontal laser scanning and the distance measuring device.
  • the system for model determination and periodic guidance of the aircraft is controlled by the data analysis determination algorithm processing apparatus, and visually outputs the results processed by the data analysis determination algorithm processing apparatus to the aircraft pilot as text and / or symbols.
  • Characterized in that it further comprises a character display device.
  • the system for model determination and the periodic guidance of the aircraft is controlled by the data analysis determination algorithm processing apparatus, the image camera for taking a real image of the aircraft entering the airport, and the data analysis determination algorithm processing apparatus It is controlled by, and further comprises an image display device provided in the pilot guide indicator to receive the video image generated by the video camera, the aircraft pilot and the like to visually see the entry state of the aircraft.
  • the display device is controlled by the data analysis determination algorithm processing apparatus, and the pilot guide indicator to visually display and provide the results of the processing in the data analysis determination algorithm processing apparatus to the aircraft pilot in text and symbols Characterized in that it further comprises a character display device.
  • the system for model identification and periodic guidance of the aircraft further includes a manual operation control panel that allows the operator to instruct the aircraft pilot through the display by manual button operation instead of an unmanned automatic operation in an emergency or when necessary. Characterized in that.
  • the system for model identification and periodic guidance of the aircraft is controlled by the data analysis determination algorithm processing apparatus, and interconnected with the comprehensive operating system in the airport, to receive the airport comprehensive information, the derived result and operation status Characterized in that it further comprises an external system communication connection interface that can be sent to the integrated operating system.
  • the vertical / horizontal laser scanning and distance measuring device comprises a laser generating source device for generating a laser beam to an aircraft, a laser signal receiving device for detecting a laser beam reflected and received by the aircraft, and the laser signal receiving device And controlling a laser generating source device, measuring a distance between the time when the laser beam is emitted from the laser generating source device and the time received by the laser signal receiving device to measure the distance of the aircraft, and when the received signal is weak. And a range finder circuit that amplifies it to an appropriate level.
  • the vertical / horizontal laser scanning and distance measuring device is provided in the laser generating source element and the vertical mirror provided to send a laser beam in a vertical direction to the aircraft, and the laser generating source element is provided in the laser beam
  • a horizontal mirror provided to send the aircraft to the aircraft in a horizontal direction
  • a vertical step motor provided on one side of the vertical mirror to adjust the mirror angle of the vertical mirror, and to adjust the mirror angle of the horizontal mirror.
  • a horizontal step motor provided on one side of the horizontal mirror, and a step motor control circuit for controlling the rotation of the vertical step motor and the horizontal step motor is characterized in that it further comprises.
  • the laser beam generated by the laser generation source device is characterized in that having a wavelength of 900nm.
  • the data analysis determination algorithm processing apparatus calculates three pieces of information of the wing width, the gas field, and the nose tip height of the aircraft with the distance from the aircraft measured by the vertical / horizontal laser scanning and the distance measuring device.
  • the type or model of the aircraft may be read by comparing the preset information in the data memory with the three pieces of calculated information.
  • the data analysis determination algorithm processing apparatus calculates the wing width by measuring the distance and the horizontal angle between the leftmost reflection point and the rightmost reflection point of the aircraft, and measures the distance and vertical angle of the tip of the nose which is the most recent reflection point of the aircraft,
  • the gas field of the aircraft is calculated by measuring the distance and the vertical angle of the vertical rear wing, which is the most reflective spot
  • the nose tip height is calculated by measuring the distance and the vertical angle of the nose tip, which is the latest reflection of the aircraft.
  • the data analysis determination algorithm processing apparatus calculates the wing width by measuring the distance and the horizontal angle of the leftmost or rightmost reflecting point of the aircraft and doubles the distance and the vertical angle of the tip of the nose which is the most recent reflecting point of the aircraft. It is characterized by calculating the gas field of the aircraft by measuring the distance and the vertical angle of the vertical rear wing, the most reflective point, and calculating the nose tip height by measuring the distance and the vertical angle of the nose tip, which is the recent reflection point of the aircraft.
  • the present invention is a vertical / horizontal laser scanning and distance measuring device for measuring the distance to each part of the aircraft as a laser beam, a model data memory in which information of various aircraft is stored, and the type or model of the aircraft to read
  • a system for model identification and periodic induction of an aircraft comprising a data analysis determination algorithm processing device, the first step of initializing a system for model identification and periodic induction of the aircraft, and thereafter, the aircraft via a runway
  • the third step is a laser beam emitted from the vertical / horizontal laser scanning and distance measuring device to measure the horizontal angle of the vertical rear wing which is the most reflective point of the aircraft and the horizontal angle of the nose tip of the aircraft which is the most recent reflection point.
  • the fifth step is to calculate the wing width with the value measured in the step 4-1 and calculates the wing width, and the gas field of the aircraft with the value measured in the step 4-2 And a fifth step of calculating a nose tip height of the aircraft using the fifth-step and the value measured in the fourth-third.
  • the present invention is measured by the laser beam method, it can be used regardless of environmental factors, there is little measurement error, there is an effect that the accurate operation can be performed without additional illumination.
  • FIG. 1 is a block diagram schematically showing a system for model discrimination and periodic induction of an aircraft according to an embodiment of the present invention.
  • FIG. 2 is a view showing details of a configuration of the vertical / horizontal laser scanning and distance measuring apparatus shown in FIG. 1;
  • FIG. 2 is a view showing details of a configuration of the vertical / horizontal laser scanning and distance measuring apparatus shown in FIG. 1;
  • FIG. 3 is a flow chart briefly showing a comprehensive software algorithm for performing aircraft sensing, model discrimination, and periodic induction in accordance with one embodiment of the present invention.
  • FIG. 5 shows various angle specifications in the case of maneuvering by using a system and method for model discrimination and periodic induction of an aircraft according to an embodiment of the present invention, and illustrates the principle of measuring and calculating the wing width of an aircraft. Showing drawings.
  • Figure 6 is a principle of measuring and calculating the height of the nose tip of the aircraft using the system and method for aircraft type identification and periodic induction according to an embodiment of the present invention, the aircraft from the nose tip of the aircraft to the vertical rear wing Drawing showing the principle of measuring and calculating chapters.
  • 7A, 7B, and 7C are flow charts showing the flowchart of FIG. 3 in more detail.
  • the aircraft type is automatically determined using a laser beam and the aircraft type discrimination is performed to guide and guide the vehicle to the correct cycle position. And a system and method for cycle induction.
  • the present invention can identify the type and type of aircraft navigating (entry) using the laser-based visual period guidance system, and also accurately identify the aircraft type information in real time within a relatively short time, the airport By providing it to the control system of the management department, it provides technical features to properly control the entrance position and height of the boarding pier appropriate for the aircraft type.
  • FIG. 1 is a block diagram schematically illustrating a system for model identification and periodic induction of an aircraft according to an embodiment of the present invention.
  • the data analysis determination algorithm processing apparatus 2 is provided with a vertical / horizontal laser scanning and distance measuring apparatus 1, a model data memory 3, and a pilot guide indicator.
  • the character display apparatus 4 and the image display apparatus 8, the manual control panel 5 installed in the mobile boarding bridge, the external system communication connection interface 6, and the image camera 7 may be connected to each other.
  • the power supply unit 9 supplies powers necessary for each of the above components to operate correctly and stably.
  • the vertical / horizontal laser scanning and distance measuring device 1 emits a laser beam and measures distance as a signal reflected from the aircraft, and measures the size of the main part of the aircraft.
  • the data analysis determination algorithm processing apparatus 2 can read out the type or model of the aircraft by calculating with the information measured by the vertical / horizontal laser scanning and distance measuring apparatus 1.
  • the data analysis determination algorithm processing apparatus 2 actually controls and adjusts the step motors 114 and 115 and the laser generator provided in the vertical / horizontal laser scanning and distance measuring apparatus 1 to be described later, and reflects the laser beam. It is a key part that includes algorithms that receive signals, store and analyze data, and make judgments for model identification.
  • the data analysis determination algorithm processing apparatus 2 outputs the determination result to the display apparatuses 4 and 8 of the pilot guidance indicator which will be described later, and manages data exchange with an external system.
  • the model data memory 3 is a memory device for storing the elements of the specifications and characteristics of various aircraft in advance and providing the comparison data necessary for the data analysis determination algorithm processing apparatus 2 to make a model recognition decision. You may delete, add, or update information about your aircraft.
  • the text display device 4 is a display device that can visually display and instruct the pilot of the result of the processing by the data analysis determination algorithm processing apparatus 2 as text and / or symbols.
  • the manual operation control panel 5 is an operation device that allows an operator to instruct an aircraft pilot through a display by manual button operation instead of an unmanned automatic operation in an emergency or when necessary.
  • the external system communication connection interface 6 interconnects a comprehensive operating system in an airport (not shown) and an aircraft type identification and periodic guidance system according to an embodiment of the present invention.
  • a communication interface device capable of transmitting a result and an operation state derived from a model discrimination and a periodic guidance system of an aircraft to an airport information device.
  • the image camera 7 may be configured as a commercial video image camera, and the image display apparatus may be controlled by the data analysis determination algorithm processing apparatus 2 and outputs an image image generated by capturing a real image of an entering aircraft. 8) It is a device that makes it easy for the pilots to visually monitor the entry status of the aircraft by transmitting to the aircraft.
  • the image display apparatus 8 is a video display apparatus such as a general LED, LCD or PDP for displaying a video image.
  • FIG. 2 is a view showing in detail the configuration of the vertical / horizontal laser scanning and distance measuring apparatus 1 shown in FIG.
  • the vertical / horizontal laser scanning and distance measuring device 1 uses two precision step motors 114 and 115 and two mirrors 117 and 118 provided in the vertical and horizontal directions to vertically generate the generated laser beam. By scanning horizontally and firing in front, you can detect the aircraft in front and measure the distance.
  • the vertical / horizontal laser scanning and distance measuring apparatus 1 includes a laser signal receiving element 112 as an input unit and a laser generating source element 111 as an output unit.
  • the laser generation source element 111 is a component of a front-end device, and preferably generates a Class 1 laser beam having a wavelength of 900 nm.
  • the laser signal receiving element 112 detects a laser beam reflected by the aircraft and received.
  • the laser range finder circuit 113 to which the laser generating source element 111 and the laser signal receiving element 112 are connected is a control device of the vertical / horizontal laser scanning and distance measuring device 1 and is not shown.
  • the laser generation source element 111 and the laser signal receiving element 112 are controlled by the CPU to process the input / output signal.
  • the laser range finder circuit 113 measures the difference between the time when the laser beam is emitted from the laser generating source element 111 and the time received by the laser signal receiving element, thereby measuring the distance of the aircraft and receiving the received signal. If it is weak, it amplifies it to an appropriate level, receives a control signal from the CPU and outputs the processed result to the CPU.
  • the laser generation source element 111 is configured such that the vertical step motor 114 is connected via the vertical mirror 117, the horizontal step motor 115 is connected via the horizontal mirror 118.
  • the vertical step motor 114 and the horizontal step motor 115 are precisely rotated vertically and horizontally under CPU control, and vertical mirrors 117 attached to the vertical step motor 114 and the horizontal step motor 115 respectively. ) And the horizontal mirror 118 transmits the laser beam vertically and horizontally to scan the aircraft in two dimensions.
  • the step motor control circuit 116 receives the control signal from the CPU and converts the signal to interface the vertical step motor 114 and the horizontal step motor 115 to the appropriate rotation.
  • the system for model discrimination and periodic guidance of an aircraft measures the distance of the aircraft as a signal reflected from the impact by hitting the aircraft by firing a laser beam, and the specification of the main parts of various forms of the aircraft. It is possible to read the type and model of the aircraft by calculating the. Also, by installing a video camera and a large video display device, the aircraft pilot adds to the text display device and supplements the actual entry state of the aircraft with the visual image. It is easy to observe.
  • the present invention uses only the laser generation source element 111 and the laser signal receiving element 112 to measure only the left or right reflection point of the aircraft, that is, not to measure the right or left reflection point, It is also possible to calculate the wing width value by doubling the measurement.
  • FIG. 3 is a flow chart briefly illustrating a comprehensive software algorithm for performing aircraft sensing, model discrimination and periodic induction in accordance with one embodiment of the present invention.
  • the present invention provides a laser scanning and ranging (Laser Scanning & Ranging) system for measuring a distance and a direction by measuring a received signal that is reflected by hitting the aircraft by firing a laser beam.
  • Laser Scanning & Ranging Laser Scanning & Ranging
  • the distance of the vertical rear wing Scanning allows you to compare aircraft type and model to setpoints to determine the aircraft type, automatically directing the display to guide and guide the aircraft's cycles, and using video cameras and display devices to help aircraft pilots Convenience can be enhanced by allowing the actual entry image to be viewed directly.
  • the aircraft model can be determined by three items, the wing width of the aircraft, the gas field and the height of the nose tip.
  • the length of the wing width is calculated by measuring the distance and the horizontal angle between the leftmost reflecting point and the rightmost reflecting point of the aircraft, and measuring the distance and the vertical angle of the most recent point (nose tip) of the aircraft to increase the height of the nose / end of the aircraft.
  • the aircraft's gas field can be calculated by measuring the distance and vertical angle of the most recent reflecting point (nose tip) of the aircraft and measuring the distance and vertical angle of the most reflective point (vertical rear wing).
  • a method for model identification and periodic guidance of an aircraft includes starting a program, performing various initializations, and performing self-diagnosis and testing of hardware and software systems before performing a task. It performs (S121).
  • an operation procedure such as a direction indication may be performed so that the aircraft is aligned on a vertical line (S122).
  • the aircraft pilot is provided with an instruction to stop to check the model of the aircraft (S123).
  • the distance and direction of the nearest reflection point and the farest reflection point are measured (S124), and then the measured values are determined according to the geometric formula according to the geometric formula.
  • L is calculated (S125), and then, N, the height of the nose tip (Nosal Height) of the aircraft, is calculated according to a geometric formula (S126).
  • the leftmost reflection point and the rightmost reflection point are measured (S127), and then, using the measured distance and angle of the two points, the wing span value of the aircraft is geometrically determined. Calculate W (S128).
  • L gas length
  • N nose tip height
  • W wing width
  • model discrimination When the model discrimination is completed, it enters the procedure to guide the aircraft to the stop line in front of the gate, and again finds the position of the nose tip of the aircraft and displays the distance and direction (S130).
  • a calculation is performed to subtract the distance information of the stop line determined for each model from the measured distance value of the nose tip of the current aircraft, and informs the aircraft pilot of the calculated distance value through a display (S131). It checks whether or not it becomes 0 and outputs an indication to STOP for DOCKING for the instantaneous period when it becomes 0 (S132).
  • FIG. 4 is a vertical rear wing horizontal angle for confirming the state that the aircraft is aligned in a vertical line with respect to the vertical / horizontal laser scanning and distance measuring device 1 according to an embodiment of the present invention when trying to determine the aircraft model and This figure shows the horizontal angle definition of the tip of the nose.
  • FIG. 4 is a procedure for confirming that the aircraft is aligned vertically with respect to the vertical / horizontal laser scanning and distance measuring device 1 for accurate and rapid determination when determining the aircraft model.
  • Figure 2 shows the definition of the horizontal angle ⁇ T of the vertical rear wing, which is the most reflective point of the laser signal, and the horizontal angle ⁇ N of the nose tip of the aircraft, which is the latest reflection point.
  • FIG. 5 shows various angle specifications in the case of maneuvering by using a system and method for model discrimination and periodic induction of an aircraft according to an embodiment of the present invention, and illustrates the principle of measuring and calculating the wing width of an aircraft. Figure showing.
  • the distance from the nose tip of the aircraft to the vertical rear wing is called a body length, and calculated by the algorithm to determine the model and model name of the aircraft through these three factors.
  • Figure 6 is a principle of measuring and calculating the height of the nose tip of the aircraft using the system and method for aircraft type identification and periodic induction according to an embodiment of the present invention, the aircraft from the nose tip of the aircraft to the vertical rear wing
  • VDGS Data measured in VDGS is the distance R T to the choewon reflection point perpendicular underwing position T, and the vertical angle ⁇ of the vertical underwing, recent reflection point of the distance R N of the aircraft to the nose N, the vertical angle ⁇ of the aircraft nose .
  • the length defined as a gas field is NT .
  • the distance R N to the tip of the aircraft and the angle ⁇ of the tip of the nose have already been measured in the previous process
  • the distance R T to the vertical rear wing is measured by finding the most laser reflection point of the aircraft, and the angle ⁇ in the vertical rear wing direction is measured. If we measure, we can calculate the length of NT corresponding to the aircraft's gas field length through the calculation given in the above equation.
  • the exact gas field actually reflects the angle that the line segment NT makes with the horizon and must additionally incorporate the length of a portion of the body behind the vertical rear wing of the aircraft, but here it does not reflect them, so the calculated value is the exact gas field of the aircraft body. There is a slight difference from the specification value.
  • FIG. 7A, 7B, and 7C are flow charts illustrating the flowchart of FIG. 3 in more detail. Specifically, a flow chart briefly summarizing the overall software algorithm for model discrimination, aircraft anchoring guidance, and delivery of the present invention. It is a chart.
  • an initialization step is an initialization process, and basic operations such as zeroing necessary items prior to executing software, and loading and storing necessary items or elements in the steps to be described below are performed.
  • S11 program for self-test and check diagnosis
  • the laser beam horizontal angle is in the direction of 0 °
  • the laser beam vertical angle is It may be set to measure in the range of about 2 ° ⁇ 8 ° (S12).
  • this process continues to operate in a loop. For example, when the aircraft appears on the entry path at a distance of about 60 to 100 m, the reflected wave number signal of the laser beam is vertical / horizontal laser scanning of the visual period guide system. And it reaches the receiver of the distance measuring device 1, recognizes that the aircraft is detected, the loop operation is stopped, and proceeds to the next step.
  • the central left and right scanning step accurately scans the center of the nose of the aircraft vertically and vertically, horizontally to the left and right (S13), and then the horizontal angle with respect to the most recent reflection point and the most far reflection point and Is detected (S14, S15).
  • the next step is to find the most recent reflection point accurately and precisely.
  • the vertical angle ⁇ and the distance R N are measured (S20).
  • the ground height setting value K of the laser beam transmitting apparatus which may be different for each location where the visual period induction system is installed, is loaded from the memory location stored at the initialization of the step S11, and the vertical angle ⁇ value measured in the step S19. And R N values are called (S21).
  • step 22 using the values calculated in the previous steps, A function calculation of the equation is performed to calculate a height H of the nose tip of the aircraft (S22).
  • the laser scanning mechanism is different depending on the installation situation under the direction of the control unit, but quickly rotates to the leftmost position, which is usually about -55 °, and starts precise scanning inward from there (S24). Find the point at which the first laser reflection is received and determine its horizontal angle , The distance D 1 is measured (S25).
  • step S26 the scanning mechanism is quickly rotated to the rightmost position where the horizontal scanning server motor (horizontal step motor 115) is usually + 55 ° to perform this step under the direction of the control unit. Move and start precise scanning from there to find the point where the first laser reflection is received and its horizontal angle And measure the distance D 2 (S27).
  • the model data is retrieved (S30).
  • the laser scanning mechanism is returned to the central scanning position in this step (S32).

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  • Engineering & Computer Science (AREA)
  • Electromagnetism (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
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  • Optical Radar Systems And Details Thereof (AREA)
  • Traffic Control Systems (AREA)

Abstract

La présente invention concerne un système et un procédé d'identification de type d'avion et de guidage pour l'accostage, et, plus particulièrement, se rapporte à un système et à un procédé d'identification de type d'avion et de guidage d'accostage, pour identifier un type d'avion et mener et guider l'avion vers une position d'accostage précise automatiquement, à l'aide d'un faisceau laser.
PCT/KR2013/002301 2012-03-21 2013-03-20 Système et procédé d'identification de type d'avion et guidage d'accostage WO2013141605A1 (fr)

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KR20120028586 2012-03-21

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WO2016015546A1 (fr) * 2014-08-01 2016-02-04 深圳中集天达空港设备有限公司 Système et procédé de guidage d'aéronef sur aire de stationnement et d'identification du type d'aéronef
WO2016015547A1 (fr) * 2014-08-01 2016-02-04 深圳中集天达空港设备有限公司 Procédé et système basés sur la vision artificielle pour guidage d'amarrage d'aéronef et identification de type d'aéronef
EP3222529A1 (fr) * 2016-03-21 2017-09-27 ADB Safegate Sweden AB Optimisation de la portée d'un système d'atterrissage pour aéronef
EP3196128A4 (fr) * 2014-08-01 2017-12-20 Shenzhen Cimc-tianda Airport Support Ltd. Système et procédé de guidage d'accostage d'aéronef et d'identification de type d'aéronef
CN112461201A (zh) * 2020-11-18 2021-03-09 中航通飞华南飞机工业有限公司 一种飞机水平测量方法及***
CN113706930A (zh) * 2021-09-01 2021-11-26 浙江华是科技股份有限公司 一种桥区引航方法、装置、***及计算机存储介质
CN116068452A (zh) * 2023-03-08 2023-05-05 石家庄科林电气股份有限公司 基于电源特征的供电类别判断方法、双源电能计量方法及双源计量电能表
KR102668998B1 (ko) * 2023-07-31 2024-05-27 인천국제공항공사 항공기 지상조업 보조 장치 및 이의 동작 방법

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US10290219B2 (en) 2014-08-01 2019-05-14 Shenzhen Cimc-Tianda Airport Support Ltd. Machine vision-based method and system for aircraft docking guidance and aircraft type identification
WO2016015547A1 (fr) * 2014-08-01 2016-02-04 深圳中集天达空港设备有限公司 Procédé et système basés sur la vision artificielle pour guidage d'amarrage d'aéronef et identification de type d'aéronef
US20170263139A1 (en) * 2014-08-01 2017-09-14 Shenzhen Cimc-Tianda Airport Support Ltd. Machine vision-based method and system for aircraft docking guidance and aircraft type identification
US20170262732A1 (en) * 2014-08-01 2017-09-14 Shenzhen Cimc-Tianda Airport Support Ltd. System and method for aircraft docking guidance and aircraft type identification
WO2016015546A1 (fr) * 2014-08-01 2016-02-04 深圳中集天达空港设备有限公司 Système et procédé de guidage d'aéronef sur aire de stationnement et d'identification du type d'aéronef
US10562644B2 (en) 2014-08-01 2020-02-18 Shenzhen Cimc-Tianda Airport Support Ltd. System and method for aircraft docking guidance and aircraft type identification
EP3196128A4 (fr) * 2014-08-01 2017-12-20 Shenzhen Cimc-tianda Airport Support Ltd. Système et procédé de guidage d'accostage d'aéronef et d'identification de type d'aéronef
US10255520B2 (en) 2014-08-01 2019-04-09 Shenzhen Cimc-Tianda Airport Support Ltd. System and method for aircraft docking guidance and aircraft type identification
EP3222529A1 (fr) * 2016-03-21 2017-09-27 ADB Safegate Sweden AB Optimisation de la portée d'un système d'atterrissage pour aéronef
US10384805B2 (en) 2016-03-21 2019-08-20 Adb Safegate Sweden Ab Optimizing range of aircraft docking system
EP3564133A1 (fr) * 2016-03-21 2019-11-06 ADB Safegate Sweden AB Optimisation de la portée d'un système d'atterrissage pour aéronef
WO2017162432A1 (fr) * 2016-03-21 2017-09-28 Adb Safegate Sweden Ab Optimisation de la portée d'un système d'amarrage d'aéronef
CN112461201A (zh) * 2020-11-18 2021-03-09 中航通飞华南飞机工业有限公司 一种飞机水平测量方法及***
CN113706930A (zh) * 2021-09-01 2021-11-26 浙江华是科技股份有限公司 一种桥区引航方法、装置、***及计算机存储介质
CN116068452A (zh) * 2023-03-08 2023-05-05 石家庄科林电气股份有限公司 基于电源特征的供电类别判断方法、双源电能计量方法及双源计量电能表
CN116068452B (zh) * 2023-03-08 2023-06-06 石家庄科林电气股份有限公司 基于电源特征的供电类别判断方法、双源电能计量方法及双源计量电能表
KR102668998B1 (ko) * 2023-07-31 2024-05-27 인천국제공항공사 항공기 지상조업 보조 장치 및 이의 동작 방법

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