KR101461491B1 - Device for Checking an Existence and Nonexistence of Strangeness of Communication Channel of LCS of UAV System and Checking Method for the same - Google Patents

Abstract

The present invention provides an apparatus for checking the existence of abnormalities in a communications channel of a launch control system in an unmanned aerial vehicle system, and a method of the same. According to the present invention, the apparatus comprises: a test standard setting module that stores, in a memory, an optimal test standard for a launch control system and sets the test standard in a test; a test panel part that is coupled with the test standard setting module, electrically combines various test instruments required for the launch control system, selectively or simultaneously connects the test instruments to the launch control system through a test circuit, and performs a preset test; and a display part that is prepared in the test panel part and displays the current status of a test by using digital data or a voice signal. The present invention connects a power meter, an attenuator, etc. to a launch control system and performs a precise test by varying the characteristic value of the launch control system, therefore precisely checks the existence of abnormalities in a communications channel of the launch control system and then installs the launch control system in an unmanned aerial vehicle system, thereby maximizing the operation stability of the unmanned aerial vehicle system.

Description

TECHNICAL FIELD [0001] The present invention relates to an apparatus and a method for measuring the presence or absence of a communication channel in a launch control apparatus of an unmanned aerial vehicle system,

The present invention relates to an apparatus and method for measuring the presence or absence of a communication channel in a launch control system of an unmanned aerial vehicle system, and more particularly, to a method and apparatus for measuring a communication channel in an unmanned aerial vehicle system by connecting a power meter and an attenuator to the launch control apparatus, The present invention relates to an apparatus and method for measuring the presence or absence of a communication channel in a launch control apparatus of a unmanned aerial vehicle system that maximizes operational stability of a unmanned aerial vehicle system by performing precise testing.

In general, unmanned aerial vehicles (UAVs) are fixed-wing aircraft or helicopters that are controlled by remote remote pilots. In the past, the unmanned aerial vehicles were mainly used for reconnaissance and table applications. They perform all public activities such as airplay. Therefore, various electronic devices including a camera serving as a pilot's eye are mounted on the UAV. Due to the various advantages of the UAV, the military UAV market has been growing rapidly and the market has been expanded to the civilian market. Such a unmanned aerial vehicle (ROV) is a system that obtains and provides real-time image information through ROK operations and appropriate monitoring within the ROK ROK. ㅇ It is a system for night air reconnaissance, continuous battlefield monitoring of combat situation and moving targets, Obtain information about the target located in the square of the equipment, and fix the spot immediately. These unmanned aerial vehicles are usually composed of unmanned aerial vehicles, ground control equipment, ground tracking equipment, launch control equipment, ground relay equipment, launch equipment, support equipment and test inspection equipment.

Referring to FIG. 1, the conventional unmanned aerial vehicle system as described above may be implemented as follows. First, an unmanned flight is performed according to a remote control signal for unmanned flight, which is transmitted through a communication channel generated via the satellite 70, An unmanned flight vehicle 71 for transmitting image information and the like;

A ground control device 72 for configuring a wireless data link via the unmanned air vehicle 71 and the satellite 70 and remotely controlling the flight of the unmanned air vehicle through the formed wireless data link and receiving the acquired image information, .

Here, the ground control device 72 includes a Launch Control (LCS), a Ground Data (GDT), a Ground Control (GCS) Station), and ground relay equipment (hereinafter referred to as GRS: Ground Relay Station).

The operation of the conventional unmanned aerial vehicle as described above is such that an operator of the unmanned aerial vehicle 71 first connects the ground control device 72 and the wireless data link to the ground control device 72 via the satellite 70 The unmanned air vehicle 71 is taken off. The ground control device 72 transmits the wireless remote control signal to the flight control computer 73 of the unmanned aerial vehicle 71 through the uplink among the wireless data links as described above to control the flight. At this time, the flight control computer 73 of the unmanned air vehicle 71 transmits the acquired image information and the like to the ground control device 72 of the ground control station. At this time, the unmanned air vehicle 71 can perform landing using the launch pad and the parachute in addition to the landing, and operation using the ground relay device in the area where the radio wave from the launch control equipment or the ground tracking equipment can not be secured (CCC), ASIC, and OCC can receive real-time image information, so that it is possible to easily grasp the battlefield situation and analyze situation of the commander.

However, in the conventional unmanned aerial vehicle system as described above, since there is no means for checking the abnormality of the launch control device for controlling the launching process of the expensive unmanned aerial vehicle, precise verification of transmission sensitivity and output to the launch control device The operational stability of the unmanned aeronautical flight system is considerably degraded. Even if the operation test of the launch control equipment is performed, there is no process that is performed by the systematic test procedure, Is frequently generated.

SUMMARY OF THE INVENTION Accordingly, the present invention has been made to solve the above-mentioned problems of the prior art, and it is an object of the present invention to provide a method and system for accurately measuring operational conditions of a communication control channel of a launch control device, And to provide a measurement device and a method for measuring the presence or absence of a communication channel of a launch control device of an unmanned aerial vehicle system that maximizes the distance.

Another object of the present invention is to set the optimum test standard value verified through various studies or tests to check the transmission sensitivity and output of the launch control device, thereby maximizing the efficiency of the verification test of the launch control device And a method of measuring the presence or absence of a communication channel of the launch control device of the unmanned aerial vehicle system.

In order to accomplish the above object, the present invention provides a method of controlling a launch control device, the method comprising: setting a test reference value for an emission control device in a memory;

A test panel unit interlocked with the test reference value setting module and electrically connecting various test instruments necessary for the launch control equipment and selectively or simultaneously connecting them to the test control circuit to execute the set test;

And a display unit provided on the test panel and informing the current test situation by digital data or a voice signal, and includes a display unit. The apparatus for measuring presence or absence of a communication channel in a launch control apparatus of an unmanned aerial vehicle system is provided.

Another aspect of the present invention is a method for controlling a launch control device, comprising: a first step of electrically coupling various test instruments required for a launch control device on a test panel surface;

After the first process, either the C-BAND UP (basic communication link) transmission output measurement mode, the UHF UP (auxiliary communication link) transmission output measurement mode or the C-BAND DN (downlink) A second step of setting a measurement mode;

A third step of loading an optimal test reference value for the verified fire control equipment conforming to the measurement mode set by the test reference value setting module after the second process to a corresponding test instrument of the test panel unit and setting the reference value as a reference value;

After the third step, the diagnostic and discriminating unit compares the measured value currently measured by the test instrument with the optimal test standard value for the launch control equipment, and then determines and outputs the abnormality of the launch control equipment according to the comparison, The present invention provides a measurement method of a communication channel abnormality measuring apparatus of a launch control apparatus of an unmanned aerial vehicle system.

According to the present invention, after the power meter and the attenuator are connected to the launch control device, the characteristics of the launch control device are varied and precisely tested to precisely measure the abnormality of the communication channel of the launch control device Therefore, it is possible to maximize the operational stability of the unmanned aerial vehicle system.

In addition, since the present invention as described above sets the optimal test standard value verified through various studies or tests to check the transmission sensitivity and the output of the launch control device, it is possible to maximize the efficiency of the verification test of the launch control device There is also an effect.

1 is an explanatory view for explaining an example of a conventional unmanned flight system.
FIG. 2 is an explanatory view for explaining a communication channel abnormality measuring device of the launch control device of the unmanned aerial vehicle system according to the present invention. FIG.
3 is a flowchart of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, preferred embodiments of a communication channel abnormality measurement apparatus for a launch control device of an unmanned aerial vehicle system according to the present invention will be described with reference to the accompanying drawings.

However, the present invention is not limited to the embodiments of the communication channel abnormality measuring apparatus of the launch control apparatus of the unmanned aerial vehicle system according to the present invention described here, but may be embodied in other forms. Rather, the embodiments disclosed herein are provided so that the disclosure can be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Like reference numerals designate like elements throughout the specification. It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. In the present specification, the singular form includes plural forms unless otherwise specified in the specification. The term " comprises " And / or "comprising" does not exclude the presence or addition of one or more other elements, steps, operations, and / or elements.

Example

FIG. 2 is an explanatory view schematically illustrating an embodiment of a communication channel abnormality measurement apparatus for a launch control device of an unmanned aerial vehicle system according to the present invention, and FIG. 3 is a flowchart of the present invention.

Referring to FIG. 2, the communication channel abnormality measuring device of the launch control device of the unmanned aerial vehicle system according to an embodiment of the present invention includes:

(2) a test reference value setting module (2) in which an optimal test reference value for the launch control device (1) verified through various studies or tests is embedded in a memory and set at the time of test execution;

A spectrum analyzer 4, a power meter 5 (including a power sensor), a fixed attenuator 6, a variable attenuator 6, a variable attenuator 6, and the like, which are interlocked with the test reference value setting module 2 and necessary for the launch control device 1, A test panel for electrically connecting the attenuator 7, the digital multimeter (not shown), the attenuator adapter kit (not shown), etc., electrically connected thereto, and selectively or simultaneously connecting them to the launch control device 1 as a test circuit, (8);

And a display unit (9) provided on the test panel unit (8) and informing the current test situation by digital data or a voice signal.

The test panel unit 8 includes a wireless module 12 for converting a test procedure into digital data and transmitting the test data to the smartphone 11 designated by the mobile communication network 10, And an Ethernet converter 14 for transmitting the data to the outside via the Internet 13 are connected.

In addition, the one end of the test panel unit 8 as described above is compared with the currently measured test value for the launch control equipment 1, and then the abnormality of the launch control equipment 1 according to the comparison is determined And outputting the diagnosis result.

Here, the unmanned aerial vehicle system 16 associated with the launch control device 1 may include a launch control device 1 (or LCS) for controlling takeoff and landing of the unmanned air vehicle 17; (18: or GDT) for controlling the functions of the launch control equipment (1) and controlling the operation of the mission of the unmanned air vehicle (17), for example, a reconnaissance mission; (19: GRS) for selectively receiving frequency signals from the LCS (1) or the GDT (18) and operating the mission of the unmanned air vehicle (17) to a remote area.

The unmanned air vehicle 17 takes off using the runway by the LCS 1 interlocked with the GDT 18. At this time, in the area without the runway, takeoff takes place through separate launch equipment (not shown). The unmanned aerial vehicle 17 launched in this manner performs the maneuvering and reconnaissance mission to the operation area, for example, and transmits the obtained real-time video information. In addition, the unmanned aerial vehicle 17 that has completed the above-mentioned reconnaissance mission lands on the runway. At this time, the landing is made through the parachute in the area without the runway.

Next, the control method of the present invention having the above-described configuration will be described.

The method of the present invention includes a first step S2 of electrically connecting various test instruments necessary for the fire control equipment to the test panel in the initial state S1 as shown in FIG. 3;

After the first step S2, the C-BAND UP (basic communication link) transmission output measurement mode, the UHF UP (auxiliary communication link) transmission output measurement mode and the C-BAND DN (downlink) reception sensitivity measurement A second step (S3) of setting one of the measurement modes;

A third step of loading the optimum test reference value for the verified fire control equipment conforming to the measurement mode set through the test reference value setting module to the reference value in the test panel unit after the second process (S3) S4);

After the third step (S4), the diagnostic judging unit compares the measured value currently measured by the test instrument with the optimal test standard value for the launch control equipment, and then determines whether the launch control equipment is abnormal based on the comparison, 4 process (S5).

In the fourth step S5, the testing process is converted into digital data through the wireless module unit of the test panel unit, and then transmitted to the designated smart phone through the mobile communication network. On the other hand, And a control step.

A power meter 5, a fixed attenuator 6, a variable attenuator 7, and a variable attenuator 7 necessary for the launch control equipment 1 on the test panel unit 8 of the present invention. , A digital multimeter, an attenuator adapter kit, and the like. For example, in the case of the C-BAND UP (basic communication link) transmission output measuring mode for the launch control device 1, the communication panel 20 of the launch control device 1 is connected via the test panel section 8, The fixed attenuator 6 of the test instrument 3 is connected to the terminal J2 and the power meter 5 is connected to the output terminal of the fixed attenuator 6. [ In the case of the UHF UP (auxiliary communication link) transmission output measurement mode, the fixed attenuator 6 is connected to the terminal J2 of the UHF transmitter 21 of the fire control equipment 1 via the test panel unit 8 And the power meter 5 is connected to the output end of the fixed attenuator 6. In the case of the C-BAND DN (downlink) reception sensitivity measurement mode, the test instrument 3 (3) is connected to the terminal J5 of the image data receiver 22 of the fire control equipment 1 via the test panel unit 8 And the spectrum analyzer 4 is connected to the output terminal of the variable attenuator 7. The spectrum analyzer 4 is connected to the variable attenuator 7,

After the above combination, the C-BAND UP (basic communication link) transmission output measurement mode, the UHF UP (auxiliary communication link) transmission output measurement mode and the C-BAND DN (downlink) reception mode And the sensitivity measurement mode. When the measurement mode is determined as described above, an optimum corresponding test reference value for the verified fire control equipment 1 conforming to the measurement mode set through the test reference value setting module 2 is determined Load the test instrument and set it as a reference value. When the preparation for the measurement of the launch control apparatus is completed as described above, the diagnostic discrimination unit 15 compares the measured value currently measured by the test instrument with the optimal test standard value for the launch control apparatus 1, And determines and outputs an abnormal state of the launch control device (1) according to the comparison. At this time, during the test process, the wireless module 12 of the test panel unit 8 converts the test procedure into digital data and transmits it to the designated smartphone 11 through the mobile communication network 10, 11 and transmits the control signal to the test panel unit 8 so that the test process can be remotely controlled.

First, the C-BAND UP (basic communication link) transmission output measurement mode of the launch control device is a flight control device (1: LCS) and an unmanned aerial vehicle 17) Prepare communication channel for communication test in advance. At this time, in the preliminary preparation step, the mission file and the mission map are transmitted from the mission planning assembly (also known as NBY) to the flight steering assembly (also referred to as PBY: Pilot Bay), and the mission handling file and the initialization data are loaded And confirm that the GPS (Satellite Navigation Device) navigation message (satellite 4 or more) is released. At this time, DISH ANT 'FED (pedestal) is turned off (directional antenna pedestal power OFF) after selecting the indication value of the reception intensity of the launch control device 1 as the maximum value (PIKE SEARCH). After the preparation of the C-BAND UP (Basic Communication Link) transmission output measurement mode of the launch control device, the power meter connected to the test panel unit 8 is connected to the power meter 5, Connect the Out direction toward the power meter. At this time, if the outgoing direction of the fixed attenuator 6 is not directed to the power meter 5 during the test connection step, the output of the power amp will be bypassed to the power meter 5, resulting in a power sensor failure of the power meter It should be noted that After the test connection step, the C-BAND transmitter of the flight control assembly is turned off, the cable of the connector J2 (SUM) terminal is disconnected from the communication box 20, and the 8m RF cable is connected. - Turn ON the BAND transmitter to select the transmission output strength and strength, and check the output value of the Power Amp (high power amplifier) with the power meter (5). For example, the output measurement is -12dB, 8m RF cable 8db, and -12- (30 + 8) when the fixed attenuator is 30db. At this time, the output value of the power meter 5 can also be confirmed through the display unit 9.

On the other hand, the UHF UP (auxiliary communication link) transmission output measurement mode makes a preparation for establishing a communication channel for the communication test of the launch control device (LCS) and the air vehicle. At this time, the mission file and the mission map are transmitted from the NBY (Navigation Bay) to the flight control assembly (PBY), the mission file and the initialization data are loaded from the PBY, (More than 4 satellites) are released and select the indication value of the reception intensity of the launch control equipment (1) as the maximum value (PIKE SEARCH) and then turn off the DISH ANT 'FED (pedestal) OFF). After the preparation of the UHF UP (auxiliary communication link) transmission output measurement mode, the power meter 5 is connected to the power meter 5, and then the direction of the fixed attenuator 6 is oriented toward the power meter. At this time, if the outgoing direction of the fixed attenuator 6 is not directed to the power meter 5, the output of the power amp 5 may be bypassed to the power meter 5 to cause a power sensor failure of the power meter 5 . After the above procedure, the UHF (auxiliary communication) transmitter 21 of the PBY is turned off, the cable of the connector J2 terminal is disconnected from the UHF transmitter 21, the 8m RF cable is connected, and the UHF transmitter 21) is turned on to select the transmission output power, and then check the output value of the Power Amp with the power meter (5). For example, if the output measurement value is about 5 db, (8m RF cable + 8db fixed attenuator) = 32db (5 + 32), the result is obtained as 37db. At this time, the output value of the power meter 5 can also be confirmed through the display unit 9.

In addition, the C-BAND DN (downlink) receiving sensitivity measurement mode is prepared to establish a communication channel for the communication control of the launch control device (1: LCS) and the vehicle. At this time, the mission planning assembly (hereinafter referred to as NBY) transmits the mission file and the mission map to the flight control assembly (PBY), loads the mission file and the initialization data from the PBY, 4 or more) is released and select the indication value of the reception intensity of the launch control device (1) as the maximum value (PIKE SEARCH) and then turn it off (pedestal of the directional antenna pedestal). Then, RF Cable (1.8m) 2EA is connected to the variable attenuator 7 (IN: 10 step upper left, OUT: 1 step lower right) after the preparation process of the C-BAND DN ), Disconnect the DN Link by turning off the DN LINK (downlink) transmitter of the PBY, connect the RF cable in the direction of the output of the variable attenuator 7 to the spectrum analyzer 4 and connect the N-type connector to the variable attenuator 7 ) Connect the RF cable in the IN direction to the cable connected to the VTR DN IN J5 terminal (AV signal). Also, turn on the DN LINK (downlink) transmitter of the PBY to confirm the Ref signal measurement with the spectrum analyzer 4 (record the signal value of the Ref value in the AV (flight), ex) measure the Ref value value of -45 dB. Further, after measuring the Ref signal, the DN LINK (downlink) transmitter of the PBY is turned off to disconnect the N-type RF cable from the spectrum analyzer 4, and then connected to the DN IN J5 terminal of the image data receiver 22 (7) 10 steps and 1 step varying by turning ON the DN LINK (downlink) transmitter of the PBY and changing the variable attenuator to the time of occurrence of the message "no object response" on the AVTE (Air Vehicle Test Equipment) Is recorded and measured. For example, if the Ref value is -45db and the attenuation value is -41db, -45 + -41 is calculated and the result is obtained as -86db. Here, the reference sensitivity value of the C-Band DN (basic communication link) of the launch control device 1 is -78db or less when there is no response of the flight, but the reference value is less than -78db when the response of the flight is absent. (Difference between TM Data and Image Data is 4dB), and there is no abnormality in the mission, and the measurement value of image cracking should be -78dB.

1: Launch control equipment 2: Test reference setting module
3: Test instrument 4: Spectrum analyzer
5: Power meter 6: Fixed attenuator
7: Variable attenuator 8: Test panel section
9: Display unit 10: Mobile communication network
11: smartphone 12: wireless module part
13: Internet 14: Ethernet converter
15: diagnostic judgment unit 16: unmanned aerial vehicle system
17: Unmanned Vehicle 18: Ground Tracking Equipment
19: Ground relay equipment 20: Communication box
21: UHF transmitter 22: image data receiver

Claims (5)

A test reference value setting module in which a test reference value for the launch control device is embedded in a memory and set at the time of test execution;
A test panel unit interlocked with the test reference value setting module and electrically connecting various test instruments necessary for the launch control equipment and selectively or simultaneously connecting them to the test control circuit to execute the set test;
And a display unit provided on the test panel and informing the current test situation by digital data or a voice signal;
A wireless module unit for converting a test procedure into digital data and transmitting the test data to a smart phone designated through a mobile communication network, an Ethernet converter for converting a test procedure into digital data and transmitting the test data to the outside via the Internet,
Wherein the test panel unit further comprises a diagnostic discrimination unit for comparing the test standard value for the launch control device with the currently measured value and for discriminating and outputting the abnormality of the launch control equipment according to the comparison, A device for measuring the presence or absence of a communication channel in the launch control equipment of the system. delete delete A first step of electrically coupling various test instruments necessary for the launch control device to the test panel surface;
After the first process, either the C-BAND UP (basic communication link) transmission output measurement mode, the UHF UP (auxiliary communication link) transmission output measurement mode or the C-BAND DN (downlink) A second step of setting a measurement mode;
A third step of loading the test reference value for the verified fire control equipment conforming to the measurement mode set through the test reference value setting module to the test instrument of the test panel unit and setting the test reference value to the reference value after the second process;
And a fourth step of comparing the measurement value currently measured by the diagnostic gauge with the test standard value for the launch control device after the third process and then determining whether the launch control device is abnormal based on the comparison, Constitute;
In the fourth step, the test process is converted into digital data through the wireless module of the test panel unit and transmitted to the designated smart phone through the mobile communication network. On the contrary, the remote control step is performed to remotely control the test process by receiving the control signal And measuring the communication channel abnormality measurement device of the launch control device of the unmanned aerial vehicle system. delete

Images