KR101926928B1 - Ground system appratus and management method for ground based augmentation system by using wireless commucation technology - Google Patents

Abstract

BACKGROUND OF THE INVENTION Field of the Invention [0002] The present invention relates to a ground system device and method for a satellite navigation area reinforcement system. More specifically, in transmitting information between the GPS reference station receivers and the calculation unit, it is unnecessary to install a channel of several hundred meters through a wireless connection, and the GPS reference station receiver can be freely installed. In addition, the existing satellite navigation system reinforcement system is simplified so that it can be applied to take - off and landing system of UAV.

Description

Field of the Invention < RTI ID = 0.0 > Field of the Invention < / RTI >

The present invention relates to a ground system device and method for a satellite navigation area reinforcement system, and more particularly to a ground system device and method for a satellite navigation area reinforcement system using a radio transmission technique.

The Ground Based Augmentation System (GBAS) represents a navigation system that provides precise access and takeoff and landing services to aircraft using satellite navigation signals such as Global Positioning System (GPS) information. More specifically, the satellite navigation area reinforcement system can be divided into a navigation satellite group, a GBAS ground system, and an aircraft mounting system.

The satellite navigation system reinforcement system determines the performance of the system as a whole based on the quality of the GPS satellite signal, the positioning of the satellite, and whether the ground system is operating. Today, a configuration is provided to the user to check whether the ground system is operating normally using an air traffic status unit. However, the conventional air traffic control use monitoring apparatus only provides information at a level that discriminates whether or not the ground system is normally operated, and there is a limitation that it can not provide direct information on accuracy, availability, and reliability in the user's viewpoint .

In addition, since the position or state of the GPS satellite changes with time, there is a growing need for a device for predicting the performance of the satellite navigation system reinforcement system and informing the user in advance of the performance.

According to an embodiment, there is provided a navigation system including a GPS receiver for receiving GPS navigation information from a GPS satellite and a first wireless communication module for transmitting the GPS navigation information received by the GPS receiver to a calculator, A second wireless communication module for receiving the satellite navigation information from the receiving unit, a calculation unit for calculating the first information and the second information of the aircraft from the receiving unit, and a second wireless communication module for receiving the first information and the second information of the calculated aircraft, A terrestrial system device of a satellite navigation area reinforcement system including a third wireless communication module for transmitting a first wireless communication module is disclosed.

According to one embodiment, the calculation unit may be a terrestrial system device of a satellite navigation system reinforcement system including a monitoring unit that monitors the current state of the satellite navigation system reinforcement system according to the first information and the second information. The status of the satellite navigation system reinforcement system can be used to calculate the precise position value of the aircraft and to indicate the expected path accordingly. The aircraft can perform the instrument landing flight to the runway by receiving the precise position value and the anticipated route, and the monitoring device can display this series of processes.

According to one embodiment, the first information and the second information may be terrestrial system devices of the satellite navigation area reinforcement system, which are differential position correction information or integrity information of the aircraft. The first information may be differential position correction information and the second information may be integrity information, conversely, the first information may be integrity information and the second information may be differential position correction information. But may be other information related to the satellite navigation of the aircraft.

According to one embodiment, the calculation unit may be a terrestrial system device of a satellite navigation area strengthening system that calculates satellite navigation information received from three GPS receivers. The number of calculation units can be at least three or more. The reason why the minimum value of three is selected is that when two GPS receivers are operated, if information from any one of the GPS receivers has a large error, it is impossible to know which of the two values approximates the actual value. Therefore, by operating at least three GPS receivers, if there is a large error in the information value of any one receiver, the calculation can be performed while excluding the value. Also, as more GPS receivers are operated, it is possible to reduce errors in calculation and calculate more precise values, but in the case of unmanned aerial vehicles, it is possible to make stable landings with precision of 3 GPS receivers.

According to another embodiment, the GPS receiver may be a ground system device of a satellite navigation area reinforcement system designed to be movable. As the GPS receiver transmits information wirelessly, the GPS receiver may not be connected to the calculation unit by wire, so that the GPS receiver may be free to move. Illustratively, but not exclusively, it may be in the form of attaching a separate wheel to the bottom of the GPS receiver. Or the GPS receiver is not fixed to the ground and simply stands up.

According to one embodiment, the third wireless communication module may be a module for communication between the aircraft and the ground system. The fourth information means information provided from the aircraft, and the detailed contents thereof may be satellite navigation information calculated by the calculation unit of the airplane. For example, the calculation unit of the airplane may be calculated differential position correction information or integrity information, but is not limited thereto.

The aircraft according to one embodiment includes both unmanned and manned aircraft. It is not limited to the name aircraft, and any artificial object flying through the air may be subject to the present application. For example, it can be said to include all names such as a flying saucer, a drones, a reconnaissance aircraft, and an airplane.

According to one embodiment, the terrestrial system arrangement of the satellite navigation area reinforcement system includes being installed in an open area rather than a runway. Since the GPS receiver of the present invention can be designed to be movable, it is not necessarily installed in the airport runway. Therefore, the GPS receiver, the calculation unit and the wireless communication module of the present invention can be installed in an open space where the aircraft can be raised and lowered. Because the aircraft includes a large passenger ship as well as an unmanned aerial vehicle, the open space may be a narrower space than a typical airport runway. However, the present invention is not limited to this and can be applied to a wider space than a more general airport runway.

Receiving satellite navigation information from a GPS satellite, transmitting the received satellite navigation information, calculating first information and second information of the aircraft in response to the satellite navigation information, And transmitting the calculated first information and second information of the aircraft to the aircraft.

A computer-readable recording medium storing a program for an aircraft landing assistance ground system according to an embodiment, the program comprising: a set of instructions for receiving satellite navigation information from a GPS satellite; A set of instructions, a set of instructions for wirelessly receiving the satellite navigation information and calculating first information and second information of the aircraft, and a set of instructions for transmitting the first information and the second information of the calculated aircraft to the aircraft And may be a computer-readable recording medium.

According to one embodiment, there is provided a method of receiving satellite navigation information, comprising: receiving satellite navigation information from a GPS satellite; transmitting the received satellite navigation information; calculating first information and second information of the aircraft in response to the satellite navigation information; And transmitting the calculated first information and second information of the aircraft to the aircraft.

According to one embodiment, there is provided a computer-readable recording medium having recorded thereon a program for an aircraft landing aiding ground system, the program comprising: a set of instructions for receiving satellite navigation information from GPS satellites; A set of instructions for wirelessly receiving the satellite navigation information and calculating first information and second information of the aircraft, and a set of instructions for transmitting the first information and the second information of the calculated aircraft to the aircraft A computer-readable recording medium is disclosed.

1 is a diagram of a ground system in accordance with one embodiment.
2 is a communication simulation of a receiver and a computation unit according to an embodiment.
3 is a diagram illustrating an external operation of the overall system according to one embodiment.
4 is a diagram illustrating an internal system of an airplane according to an exemplary embodiment of the present invention.
5 is a diagram illustrating the internal operation of the overall system in accordance with one embodiment.

Specific structural or functional descriptions of embodiments are set forth for illustration purposes only and may be embodied with various changes and modifications. Accordingly, the embodiments are not intended to be limited to the specific forms disclosed, and the scope of the disclosure includes changes, equivalents, or alternatives included in the technical idea.

The terms first or second, etc. may be used to describe various elements, but such terms should be interpreted solely for the purpose of distinguishing one element from another. For example, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component.

It is to be understood that when an element is referred to as being "connected" to another element, it may be directly connected or connected to the other element, although other elements may be present in between.

The singular expressions include plural expressions unless the context clearly dictates otherwise. In this specification, the terms "comprises ", or" having ", and the like, are used to specify one or more of the described features, numbers, steps, operations, elements, But do not preclude the presence or addition of steps, operations, elements, parts, or combinations thereof.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art. Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the meaning of the context in the relevant art and, unless explicitly defined herein, are to be interpreted as ideal or overly formal Do not.

1 is a diagram of a ground system in accordance with one embodiment. The terrestrial system 100 of the satellite navigation system reinforcement system includes a GPS reference station receiver 110, a ground station calculation unit 120, and a third wireless communication module 130. The GPS reference station receiver receives the satellite navigation information of the aircraft from the satellite. The calculation unit can calculate the differential position correction information and the integrity information from the GPS navigation information received by the GPS reference station receiver. However, the present invention is not limited thereto, and information about the takeoff and landing of an airplane can be calculated. The transmitting unit receives the information calculated from the calculating unit and transmits the information to the airplane.

2 is a communication simulation of a receiver and a computation unit according to an embodiment. A detailed information transfer method between the GPS reference station receiver 210 and the calculation unit 240 is shown. Conventionally, information is transmitted between a GPS reference station receiver and a calculation unit through a wired connection, but the present invention transmits information through the first wireless communication module and the second wireless communication module.

In order to ensure the independence of the error between each GPS reference station receiver, there is an installation restriction condition that 100-200m or more should be installed separately. Therefore, to install two or more GPS reference station receivers in a satellite navigation system reinforcement system in a general situation installed in an airport, it is necessary to install a power source and a communication line of several hundred meters and to manage accordingly. Also, the cable installed in the pipeline causes electromagnetic induction when the lightning occurs in the environment of the airport, which is vulnerable to lightning, due to the characteristics of the open space, thereby damaging the circuit of the calculation unit as well as the GPS reference station receiver. Therefore, the first wireless communication module 220 may be installed in each receiver of the GPS reference station, and the second wireless communication module 230 may be installed in the calculation unit to reduce unnecessary burial of the pipeline. A concrete method of transmitting information between wireless communication modules will be described later.

3 is a diagram illustrating an external operation of the overall system according to one embodiment. The satellite navigation system reinforcement system 300 includes ground station systems 330 and 340 and an aircraft mounting system 310. The satellite 320 transmits GPS information to the aircraft mounting system 310 and to each GPS reference station receiver 330. Each of the reference station receivers transmits GPS information received from the satellite 320 to the calculation unit 340 of the ground station system. The calculation unit transmits the differential correction information and the integrity information calculated using the third wireless communication module to the aircraft mounting system. In this case, the transmission method of the third wireless communication module may be a VHF data broadcasting method. However, it is not limited to this method. The aircraft mounting system 310 calculates the aircraft precision position value based on the GPS signal received from the satellite 320, the differential correction information received from the ground station system, and the integrity information. The aircraft performs an instrument landing flight based on the deviation calculation based on the precise approach path from the aircraft to the runway.

4 is a diagram illustrating an aircraft mounting system according to one embodiment. The airplane mounting system 400 includes a wireless communication module 410, an airplane calculation unit 420, and an airplane GPS receiver 430. The fourth wireless communication module 410 is responsible for wireless communication with the ground station system. Specifically, it serves to receive differential correction information and integrity information from the ground station system. The airplane GPS receiver 430 receives GPS signals from satellites. Finally, the calculation unit 420 of the airplane calculates an accurate position value of the aircraft based on the received GPS signal, the difference correction information, and the integrity information, and performs the instrument landing based on the deviation based on the precision approach route to the runway To be calculated. When the calculated value of the airplane computation unit exceeds the predetermined threshold value, the time point information value and the data value thereof can be fed back to the terrestrial system through the fourth wireless communication module. This will allow the ground station system to detect that the navigation performance of the aircraft has deteriorated and take action.

5 is a diagram illustrating the internal operation of the overall system in accordance with one embodiment. Specifically, the operation of the entire system including the ground station system 510 of the satellite navigation area reinforcement system and the aircraft mounting system 520 is shown. As described above, the ground station system 510 calculates the first information and the second information and transmits them to the aircraft mounting system 520 through the third wireless communication module. The aircraft mounting system 520 receives the first information and the second information transmitted through the fourth wireless communication module.

The first to fourth wireless communication modules may transmit information to each other using a communication interface. The communication interface may be a wireless interface such as a wireless LAN (WLAN), a wireless fidelity (WiFi) direct, a DLNA (Digital Living Network Alliance), a Wibro (Wireless broadband), a Wimax (World Interoperability for Microwave Access), HSDPA (High Speed Downlink Packet Access) May include an Internet interface and a short range communication interface such as Bluetooth (TM), Radio Frequency Identification (RFID), Infrared Data Association (IrDA), UWB (Ultra Wideband), ZigBee, NFC . In addition, the communication interface may represent all interfaces capable of performing communication, except for communication using a wired connection.

There is a merit that when the ground station system is operated using the first wireless communication module and the second wireless communication module, the GPS ground station receiver can be moved freely due to the wireless connection. The ground station system of the existing satellite navigation system reinforcement system is not free to move the GPS ground station receiver because the long - distance channel due to the wired connection is already buried. Therefore, it is not easy to move the GPS receiver or construct a new GPS receiver even if radio interference or multi-path error occurs due to the expansion or contraction of a building or other obstacle in an airport area. However, there is a merit that the GPS ground station receiver can be easily installed when the ground station system is operated using wireless communication.

The monitoring portion of the satellite navigation area enhancement system, which is present according to one embodiment, can predict the system performance of the satellite navigation area enhancement system over time and transmit a message related to the anomaly to the user. The user can anticipate emergency situations in advance according to the predicted system performance, so that it is expected to operate the aircraft landing facility more stably.

The embodiments described above may be implemented in hardware components, software components, and / or a combination of hardware components and software components. For example, the devices, methods, and components described in the embodiments may be implemented within a computer system, such as, for example, a processor, a controller, an arithmetic logic unit (ALU), a digital signal processor, such as an array, a programmable logic unit (PLU), a microprocessor, or any other device capable of executing and responding to instructions. The processing device may execute an operating system (OS) and one or more software applications running on the operating system. The processing device may also access, store, manipulate, process, and generate data in response to execution of the software. For ease of understanding, the processing apparatus may be described as being used singly, but those skilled in the art will recognize that the processing apparatus may have a plurality of processing elements and / As shown in FIG. For example, the processing unit may comprise a plurality of processors or one processor and one controller. Other processing configurations are also possible, such as a parallel processor.

The software may include a computer program, code, instructions, or a combination of one or more of the foregoing, and may be configured to configure the processing device to operate as desired or to process it collectively or collectively Device can be commanded. The software and / or data may be in the form of any type of machine, component, physical device, virtual equipment, computer storage media, or device , Or may be permanently or temporarily embodied in a transmitted signal wave. The software may be distributed over a networked computer system and stored or executed in a distributed manner. The software and data may be stored on one or more computer readable recording media.

The method according to an embodiment may be implemented in the form of a program command that can be executed through various computer means and recorded in a computer-readable medium. The computer-readable medium may include program instructions, data files, data structures, and the like, alone or in combination. The program instructions to be recorded on the medium may be those specially designed and configured for the embodiments or may be available to those skilled in the art of computer software. Examples of computer-readable media include magnetic media such as hard disks, floppy disks and magnetic tape; optical media such as CD-ROMs and DVDs; magnetic media such as floppy disks; Magneto-optical media, and hardware devices specifically configured to store and execute program instructions such as ROM, RAM, flash memory, and the like. Examples of program instructions include machine language code such as those produced by a compiler, as well as high-level language code that can be executed by a computer using an interpreter or the like. The hardware devices described above may be configured to operate as one or more software modules to perform the operations of the embodiments, and vice versa.

Although the embodiments have been described with reference to the drawings, various technical modifications and variations may be applied to those skilled in the art. For example, it is to be understood that the techniques described may be performed in a different order than the described methods, and / or that components of the described systems, structures, devices, circuits, Lt; / RTI > or equivalents, even if it is replaced or replaced.

Claims (10)

A GPS reference station receiver designed to be mobile and receiving satellite navigation information from GPS satellites;
A first wireless communication module for transmitting the satellite navigation information received by the GPS reference station receiver to a calculation unit;
A second wireless communication module for receiving the satellite navigation information from the first wireless communication module;
A calculation unit for receiving the satellite navigation information from the second wireless communication module and calculating first information and second information; And
A third wireless communication module for transmitting the first information and the second information to an aircraft,
/ RTI >
Wherein the third wireless communication module receives the precision position data of the aircraft when the precision position value calculated in the aircraft exceeds a predetermined threshold distance to the landing point,
The calculation unit calculates satellite navigation information received from the three GPS reference station receivers
Ground navigation system for satellite navigation system. The method according to claim 1,
Wherein the calculation unit includes a monitoring unit for monitoring a current state of the satellite navigation area reinforcement system according to the first information and the second information. The method according to claim 1,
Wherein the first information and the second information are differential position correction information or integrity information of the aircraft. delete delete delete The method according to claim 1,
Wherein said aircraft is an unmanned aerial vehicle. The method according to claim 1,
Wherein the ground system device of the satellite navigation area reinforcement system is installed in an open space instead of a runway. Receiving GPS navigation information from a GPS satellite, the GPS reference station receiver being designed to be mobile;
The GPS reference station receiver transmitting the received satellite navigation information to a calculation unit;
The calculation unit receiving the satellite navigation information and calculating first information and second information;
The wireless communication module transmitting the first information and the second information to the aircraft;
The third wireless communication module is configured to receive the fine position data of the aircraft when the fine position value calculated in the aircraft exceeds a predetermined threshold distance to the landing point; And
The calculation unit calculates satellite navigation information received from the three GPS reference station receivers
A method of operation of a satellite navigation area reinforcement system including. A computer-readable recording medium containing a program for an aircraft landing aiding ground system, said program comprising:
A set of GPS base station receivers designed to be mobile capable of receiving satellite navigation information from GPS satellites:
And the GPS reference station receiver wirelessly transmits the received satellite navigation information to the calculation unit:
Wherein the calculation unit wirelessly receives the satellite navigation information and calculates first information and second information:
Wherein the wireless communication module transmits the first information and the second information to the aircraft:
The third wireless communication module receiving the fine position data of the aircraft when the fine position value calculated in the aircraft exceeds a predetermined threshold distance to the landing point:
Wherein the calculation unit comprises a set of instructions for calculating satellite navigation information received from the three GPS reference station receivers
Readable recording medium.

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