KR20170023574A - Multi-function test equipment for input and output modules of the avionics - Google Patents

Multi-function test equipment for input and output modules of the avionics Download PDF

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Publication number
KR20170023574A
KR20170023574A KR1020150118887A KR20150118887A KR20170023574A KR 20170023574 A KR20170023574 A KR 20170023574A KR 1020150118887 A KR1020150118887 A KR 1020150118887A KR 20150118887 A KR20150118887 A KR 20150118887A KR 20170023574 A KR20170023574 A KR 20170023574A
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port
computer
test
input
control monitoring
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KR1020150118887A
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Korean (ko)
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서정배
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(주) 에어로매스터
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/005—Testing of electric installations on transport means
    • G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/28—Testing of electronic circuits, e.g. by signal tracer
    • G01R31/2832—Specific tests of electronic circuits not provided for elsewhere
    • G01R31/2834—Automated test systems [ATE]; using microprocessors or computers
    • G—PHYSICS
    • G08—SIGNALLING
    • G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
    • G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
    • G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
    • G—PHYSICS
    • G08—SIGNALLING
    • G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
    • G08C19/00—Electric signal transmission systems
    • G08C19/02—Electric signal transmission systems in which the signal transmitted is magnitude of current or voltage

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Maintenance And Management Of Digital Transmission (AREA)

Abstract

The present invention relates to a multi-function test device for input and output modules of avionics equipment, and is to provide a multi-function test device for input and output modules of avionics equipment, capable of providing a communication interface according to each communication method among input/output modules (SRU), a control monitoring computer (SBC) and/or a function test computer (laptop computer) of avionics equipment performing data communication in communication methods different from each other. The multi-function test device according to the present invention comprises: a communication interface; a first communication port which is connected to the communication interface to communicate with a control monitoring computer; a second communication port which is connected to the communication interface to communicate with input and output modules of avionics equipment; and a plurality of third communication ports which are connected to the communication interface to transmit communication signals with methods different from each other.

Description

[0001] Multi-function test equipment for input and output modules of avionics [

The present invention relates to a multifunctional test apparatus for input / output modules of avionics equipment.

In general, avionics (Avionics, abbreviation of AVI-ation electr-ONICS, avionics) is a combination of aviation and electronics. It is a system that provides functions to process and display data received from various sensors, which is related to the brain, nervous system, and senses of an aircraft, and related electronic equipments and various sensors.

The configuration of the avionics system is composed of mission computer, armed computer, communication, identification (IFF), navigation system, autopilots, electronic flight management systems (FMS) (TCAS), a radar, and the like.

Airborne electronic equipment, such as a video system for passengers, and electronic equipment not associated with aircraft operations, are often considered to be avionics components. The development of the equipment for mounting can be divided into hardware and software, and it is developed with a procedure according to the specification of the airplane and encourages the installation of the approved components.

Korean Patent Registration No. 10-1016812 (Feb. 21, 2011) Korean Patent Publication No. 10-2014-0137324 (Feb. Korean Patent Publication No. 10-2014-0137325 (Feb.

SUMMARY OF THE INVENTION The present invention is directed to an I / O module (e.g., SRU), a control monitoring computer (e.g., SBC) and / or a functional testing computer Output module of an avionics device having a communication interface according to each communication method between a mobile phone and a notebook computer.

Another object of the present invention is to provide a multifunctional test apparatus for an input / output module of an avionics device capable of checking the state of a communication line between an input / output module of an avionics device and a control monitoring computer and / .

A multifunctional test apparatus for an input / output module of an avionics device according to an embodiment of the present invention includes: a communication interface for mediating a communication signal; A first communication port coupled to the communication interface to enable communication with the control monitoring computer; A second communication port connected to the communication interface for communicating with the input / output module of the avionic device; And a plurality of third communication ports connected to the communication interface for selectively transmitting different types of communication signals.

The third plurality of communication ports may include at least an RS-232 port, an RS-422/485 port, an ARINC 429 port, a DISCRETE port, an ANALOG port, a PWM port, or an I2C port.

And a function test computer communicably connected to the control monitoring computer.

And the functional test computer may be communicably connected to the third communication port.

When RS-232 or RS-422/485 transmission / reception data is tested, a USB to RS-232 port is connected between the RS-232 port or RS-422/485 port of the third port and the USB port of the functional testing computer. Converter or a RS-232 to RS-422/485 converter is further connected to the USB to RS-232 converter, and the transmission data is transmitted to the functional testing computer, the multifunctional testing device, the input / output module, the multifunctional testing device, The transmission data is output through the control monitoring computer or after the received data is transmitted in the order of the control monitoring computer, the multifunctional test apparatus, the input / output module, the multifunctional test apparatus and the function test computer, The received data may be output through the functional test computer.

When the ARINC 429 method transmission / reception data is tested, an ENET to ARINC 429 converter is connected between the ARINC 429 port of the third port and the Ethernet port of the functional test computer, and transmission data is transmitted to the control monitoring computer, , The input / output module, the multifunction test device, and the function test computer, the transmission data is output through the function test computer, or the received data is transmitted to the function test computer, the multifunction test device, the input / output module, A control monitoring computer, a multifunction test apparatus, an input / output module, a multifunction test apparatus, and a function test computer, and then the received data can be output through the function test computer.

When DISCRETE type input / output data is tested, DISCRETE type input data is input by the multifunction test apparatus after the control monitoring computer is driven, input data of DISCRETE type is output through the control monitoring computer, After the control monitoring computer is driven, the DISCRETE output data is output by the multifunction test apparatus, and the DISCRETE output data is output through the LED connected to the DISCRETE port.

When the GPIO output state value is changed by the control monitoring computer, the LED connected to the DISCRETE port is turned on or when the input state value of the input switch connected to the DISCRETE port changes, the GPIO input The status value can be changed and displayed.

In the ANALOG input unit interlocking test, when the ANALOG input state value is changed by the multifunctional test apparatus after the control monitoring computer is driven, the ANALOG input state value may be changed and displayed through the control monitoring computer.

During the PWM signal test, the brightness of the lamp connected to the PWM port may vary as the PWM duty ratio is varied by the multifunction test apparatus.

During the I2C communication test, the I2C communication test is performed by the control monitoring computer, and the I2C communication result value may be output through the control monitoring computer.

The present invention relates to an I / O module (e.g., SRU), a control monitoring computer (e.g., SBC) and / or a functional testing computer (e.g., a notebook computer The present invention provides a multifunctional test apparatus for an input / output module of an avionics device having a communication interface according to each communication method. That is, the present invention allows the multifunctional test apparatus to mediate various communication signals of UART (RS-232, RS-422/485), ARINC 429, DISCRETE, ANALOG, PWM and / It is possible to test various communication signals between the input / output module of the equipment and the functional test computer.

The present invention also provides a multifunctional test apparatus for an input / output module of an avionics device capable of checking the state of a communication line between an input / output module of an avionics device and a control monitoring computer and / or a functional test computer. That is, the present invention provides a method and system for monitoring and / or diagnosing, via a control monitoring computer and / or a computer for functional testing, whether a communication line status of whether a communication signal between a control monitoring computer and an input / output module of an avionics device is normally transmitted and / Be monitored.

1 is a block diagram showing a state in which a control monitoring computer and an input / output module of an avionics device are connected by a multifunction test apparatus according to an embodiment of the present invention.
2 is a block diagram illustrating the configuration of a multifunctional test apparatus for an input / output module of an avionics device according to an embodiment of the present invention.
FIG. 3A is a block diagram illustrating a connection configuration of an RS-232/422/485 test equipment using a multifunctional test apparatus for an input / output module of an avionics device according to an embodiment of the present invention, And a flow chart of a received signal.
4A is a block diagram showing a connection configuration of an ARINC 429 test equipment using a multifunctional test apparatus for an input / output module of an avionics device according to an embodiment of the present invention, and FIGS. 4B and 4C are diagrams showing a flow of a transmitted signal and a received signal Fig.
5 is a block diagram illustrating a connection configuration of a DISCRETE / GPIO / ANALOG test apparatus using a multifunction test apparatus for an input / output module of an avionics device according to an embodiment of the present invention.
6 is a block diagram illustrating a PWM / I2C communication connection and test state using a multifunction test apparatus for an input / output module of an avionics device according to an embodiment of the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

The embodiments of the present invention are described in order to more fully explain the present invention to those skilled in the art, and the following embodiments may be modified into various other forms, The present invention is not limited to the embodiment. Rather, these embodiments are provided so that this disclosure will be more faithful and complete, and will fully convey the scope of the invention to those skilled in the art.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the singular forms "a," "an," and "the" include singular forms unless the context clearly dictates otherwise. Also, " comprise "and / or" comprising "when used herein should be interpreted as specifying the presence of stated shapes, numbers, steps, operations, elements, elements, and / And does not preclude the presence or addition of one or more other features, integers, operations, elements, elements, and / or groups.

Also, in the present specification and / or drawings, the control monitoring computer may be referred to as "SBC (Single Board Computer) " as occasion demands, and the functional testing computer may be referred to as" And may be referred to as "Shop Replacement Unit (SRU)"

Here, the SBC includes, for example, an I7 CPU, which basically serves to control and monitor the SRU. In general, the SRU is installed in an LRU (Line Replacement Unit) inside an aircraft using an aircraft communication (UART, ARINC 429, DISCRETE, ANALOG and / or I2C) method and processes the communication signal of the LRU.

In addition, the SRU means a factory maintenance exchange item, which may be a piece of equipment that is exchanged for the parts that make up the equipment during the repair of the equipment at the aircraft equipment repair shop. Furthermore, the LRU means a flight maintenance exchange item, which may be an equipment that can restore the condition of the aircraft to normal by exchanging parts during flight maintenance.

1 is a block diagram illustrating a state in which a control monitoring computer 150 and an input / output module 160 are connected by a multifunction test apparatus 100 for an input / output module of an avionics device according to an embodiment of the present invention.

1, a multifunctional test apparatus 100 according to the present invention includes a control monitoring computer 150 (e.g., SBC) and an input / output module 160 (e.g., SRU) And is communicably connected. For example, the multifunctional test apparatus 100 and the control monitoring computer 150 may be communicably connected in a PCIe manner and the multifunction test apparatus 100 and the input / output module 160 may be connected to a UART (RS-232, / 422/455 ), ARINC 429, DISCRETE, ANALOG, and / or I2C.

In this way, the multifunctional test apparatus 100 enables a unit test on the input / output module 160 of the aviation electronic equipment. That is, the multifunctional test apparatus 100 serves as an interface board for providing a communication test for controlling and monitoring the control monitoring computer 150 for the input / output module 160 to be mounted on the aircraft.

2 is a block diagram showing the configuration of a multifunctional test apparatus 100 for an input / output module of an avionics device according to an embodiment of the present invention.

2, the multifunctional test apparatus 100 includes a communication interface 110, a first communication port 120, a second communication port 130, and a plurality of third communication ports 140. As shown in FIG. Optionally, the multifunction test apparatus 100 may be a concept that includes the control monitoring computer 150 and / or the input / output module 160.

Here, the control monitoring computer 150 may further include a monitor 151 connected via an RGB port. Further, a functional test computer 170 may be further connected between the control monitoring computer 150 and the multifunctional test apparatus 100 through, for example, an Ethernet port. Accordingly, the multifunctional test apparatus 100 according to the present invention may be a concept including the monitor 151 and the functional test computer 170 as occasion demands.

The communication interface 110 mediates various types of communication signals, communication data, and / or input / output data. The communication interface 110 mainly includes a function test computer 170, an input / output module 160, a control monitoring computer 150, Or the received signal Rx between the transmission signal Tx and the reception signal Rx. The communication interface 110 may be, for example, a circuit pattern formed on a circuit board or a circuit board, and it functions to electrically connect the various ports to be described below.

The first communication port 120 is basically connected to the communication interface 110, which allows the multifunctional test apparatus 100 to communicate with the control monitoring computer 150. For example, the PCIe communication data can be transmitted and received through the first communication port 120, but the present invention is not limited thereto.

The second communication port 130 is basically connected to the communication interface 110, which allows the multifunctional test apparatus 100 to communicate with the input / output module 160. 2, a Con terminal and a DSUB terminal are illustrated as the second communication port 130, but the present invention is not limited thereto. The Con terminal and the DSUB terminal are simple connectors for connecting the multifunctional test apparatus 100 and the input / output module 160 so that they can communicate with each other.

The third communication port 140 is basically connected to the communication interface 110, which can transmit various communication signals in different ways. For example, the third communication port 140 allows the function test computer 170 to communicate with the multifunction test apparatus 100 with different types of communication signals. For example, the third communication port 140 may include an RS-232 port 141, an RS-422 port 142, an RS-485 port (not shown) and an ARINC 429 port 143, The functional test computer 170 can communicate with the multifunctional test apparatus 100 through a communication method such as RS-232, RS-422, RS-485, or ARINC 429. [ In addition, the third communication port 140 may further include a DISCRETE port 144, an ANALOG port 145, a PWM port 146, and an I2C port 147. The DISCRETE port 144, the ANALOG port 145, 145, and a switch / LED, a knob, and a lamp may be connected to the PWM port 146, respectively.

The USB port of the function test computer 170 may be connected to the RS-232 port 141 of the third communication port 140 via the USB to RS 232 converter 181 and may be connected to the USB port of the function test computer 170 Port may be connected to the RS-422 port 142 of the third communication port 140 via the USB to RS 422 converter 182 and the Ethernet port of the functional testing computer 170 may be connected to the ENET to ARINC 429 converter 183, To the ARINC 429 port 143 of the third communication port 140 via the second communication port 140.

In this way, in the present invention, the functional test computer 170 can basically transmit and receive transmission signals and / or reception signals of the RS-232/422/425 and ARINC 429 systems to and from the multifunctional test apparatus 100. Of course, it is a matter of course that the multifunctional test apparatus 100 allows the control monitoring computer 150 to send and receive transmission signals and / or reception signals of the RS-232/422/425 and ARINC 429 systems to and from the input / output module 160 . Moreover, the multifunctional test apparatus 100 allows the control monitoring computer 150 to send and receive DISCRETE, ANALOG, PWM and / or I2C transmission and / or reception signals to and from the input / output module 160.

3A is a block diagram showing a connection configuration of an RS-232/422/485 test equipment using a multifunctional test apparatus 100 for an input / output module of an aviation electronic equipment according to an embodiment of the present invention, and FIGS. 3B and 3C Is a flowchart showing a flow of a transmission signal and a reception signal.

As shown in FIG. 3A, the transmission / reception data of the RS-232 or RS-422/485 scheme is tested by the control monitoring computer 150 and / or the function testing computer 170, 150) and / or a computer 170 for functional testing. For this, for example, the following test procedure can be performed.

First, when the RS-232 or RS-422/485 transmission / reception data is tested, the RS-232 port 141 or RS-422/485 port 142 of the third communication port 140 and the function test computer RS 232 converter 181 is connected between the USB ports of the USB-to-RS 232 converter 170 and the RS-232 to RS 422/485 converter 182 is connected to the USB to RS 232 converter 181.

That is, the description will be sequentially described as follows.

1) The Ethernet port of the function test computer 170 and the Ethernet port of the control monitoring computer 150 are connected by an Ethernet cable.

2) The USB to RS 232 converter 181 is connected to the USB port of the function test computer 170.

3) When the RS-422/485 communication signal is tested, an RS 232 to RS 422/485 converter 182 is additionally connected to the USB to RS 232 converter 181.

4) When the RS-232 communication signal is tested, the UART cable of the USB to RS 232 converter 181 is connected to the RS-232 port 141 of the multifunction test apparatus 100, for example, the UART 1-16 terminal .

5) When the RS-422/485 communication signal is tested, the RS 232 to RS 422/485 converter 182 is additionally connected to the USB to RS 232 converter 181 and the RS-422 / 485 port 142, for example, UART 17 to 20 terminals.

In such a connection state, the following operation is performed. Here, this operation is only an example for understanding the present invention, and the present invention is not limited to the terms and methods used herein.

1) In the control monitoring computer 150, the test program is executed in a state defined as 'RS232 (422/485) _TEST'.

2) In the function test computer 170, the 'Open Com' button is clicked after ComMaster is executed and the Baudrate of the setting panel is set to the same value as the Baudrate value displayed on the monitor 151 of the control monitoring computer 150. (In this way, the transmission signal (Tx) data is transmitted.)

3) Check whether the RS-232/422/485 message transmitted from the UART test program is normally output to the monitor 151 via the ComMaster's Received Data window (ie, the received signal (Rx) data is transmitted).

4) Check whether the message transmitted from the TestView through the monitor 151 of the control monitoring computer 150 is normally output to the monitor 151.

5) Repeat the above 3) and 4) test procedure for each channel while changing the RS-232/422/485 terminal of SRU.

3B, the transmission data Tx is transmitted from the functional test computer 170 to the multifunctional test apparatus 100, the input / output module 160, the multifunctional test apparatus 100, After the control monitoring computer 150 is transmitted in this order, it is finally confirmed that the transmission data Tx is outputted through the monitor 151 of the control monitoring computer 150. [ That is, the state of the communication line related to the transmission is checked.

3C, received data Rx is transmitted from the control monitoring computer 150 to the multifunctional test apparatus 100, the input / output module 160, the multifunctional test apparatus 100, Function test computer 170, and it is finally confirmed that the received data Rx is outputted through the function test computer 170. [ That is, the line status related to reception is checked.

4A is a block diagram showing a connection configuration of an ARINC 429 test equipment using a multifunction test apparatus 100 for an input / output module of an avionics device according to an embodiment of the present invention, Fig. 3 is a flow chart showing the received signal flow. Fig.

As shown in FIG. 4A, the transmission / reception data of the ARINC 429 scheme is tested by the control monitoring computer 150 and / or the functional testing computer 170, and the transmission / reception data is transmitted to the control monitoring computer 150 and / May be identified by the computer 170.

That is, when the transmission / reception data of the ARINC 429 scheme is tested, an ENET to ARINC 429 converter 183 is connected between the ARINC 429 port 143 of the third communication port 140 and the Ethernet port of the functional test computer 170 .

 The following explains this in turn.

1) The Ethernet port of the function test computer 170 and the Ethernet port of the control monitoring computer 150 are connected by an Ethernet cable.

2) The ENET-A429 input / output cable is connected to the J1 terminal of the ENET to ARINC 429 converter (183), and the Ethernet port and the USB port on the opposite side of the cable are respectively connected to the corresponding port of the function test computer (170). It is possible to use USB LAN card equipment if necessary.)

3) The ENET to ARINC 429 converter 183 is connected once to the ARINC 429 port 143 of the multifunction test apparatus 100, that is, ARINC_CN1 or ARINC_CN2

In such a connection state, the following operation is performed. Here, this operation is only an example for understanding the present invention, and the present invention is not limited to the terms and methods used herein.

First, the test of the ARINC 429 transmission data will be described.

1) At the control monitoring computer 150, the ARINC 429 test program is called 'TX ... _TEST '.

2) On the functional test computer 170, the AltaView Bus Analyzer is executed.

3) In the Device Open menu, the board type is set to 'ENET-A429'. For example, 'This System IP Address' is set to '192.168.0.10'.

4) The Start RX button is clicked on the Rx Control Panel. (Here, in the functional test computer 170, the received signal Rx becomes the transmitted signal Tx in the input / output module 160.)

5) The monitoring screen of the Rx Control Panel confirms that the ARINC 429 data transmitted from the ARINC 429 test program has been received.

6) As the Tx terminal of the ARINC 429 port 143 is changed, the test procedure of 4) and 5) is repeated for each channel 1-4.

Next, the test of the ARINC 429 received data will be described.

1) At the control monitoring computer 150, the ARINC 429 test program is called 'RX ... _TEST '.

2) After the ARINC 429 Tx unit interlocking test, the TX Control Panel is opened in the AltaView Bus Analyzer and the Add Label button is clicked on the channel item to be tested to add the label data to be transmitted. (In the functional test computer 170, Output module 160 becomes the received signal Rx.)

3) Start ALL button is clicked to start TX data transmission.

4) Check whether the ARINC 429 data transmitted from the AltaView Bus Analyzer is normally output through the monitor 151 of the control monitoring computer 150.

5) As the ARINC 429 RX terminal of the SRU is changed, the test procedure of 3) and 4) is repeated for each channel 1-8.

4B, the transmission data Tx is transmitted from the control monitoring computer 150 and transmitted to the multifunctional test apparatus 100, the input / output module 160, the multifunctional test apparatus 100, and the function test computer 100. As described above, (170), and finally, the transmission data (Tx) is outputted through the function test computer (170). That is, the state of the communication line related to the transmission is checked.

4C, the received data Rx is transferred from the function test computer 170 to the multifunction test apparatus 100, the input / output module 160, the multifunction test apparatus 100, the control monitoring computer 150 ), The multifunctional test apparatus 100, the input / output module 160, the multifunctional test apparatus 100 and the function test computer 170 are transmitted in this order and eventually the received data Rx is transmitted through the function test computer 170 . That is, the state of the communication line related to reception is checked.

5 is a block diagram showing a connection configuration of a DISCRETE / GPIO / ANALOG test equipment using a multifunction test apparatus 100 for an input / output module of avionics equipment according to an embodiment of the present invention.

The Ethernet port of the function test computer 170 and the Ethernet port of the control monitoring computer 150 are connected to an Ethernet cable (not shown) through an LED, a lamp, and / or a control monitoring computer 150. [ Lt; / RTI > In practice, no other connection is required. However, a connection between the control monitoring computer 150 and the function test computer 170 may not be required when a separate stable power source can be input to the control monitoring computer 150.

After this connection configuration, a DISCRETE input / output test can be performed. That is, when the DISCRETE type input / output data is tested, after the control monitoring computer 150 is driven, the DISCRETE type input data is input by the multifunction test apparatus 100, and the DISCRETE type input data is input to the control monitoring computer 150 or the control monitoring computer 150 is driven, output data of the DISCRETE format is output by the multifunction test device 100, and output data of the DISCRETE format is output to the DISCRETE port 144 It can be confirmed that it is output through connected LED. That is, the DISCRETE input / output signal can be checked.

First, the DISCRETE input test will be described.

1) At the control monitoring computer 150, the test program is executed in a state defined as 'DISCRETE_IN_TEST'.

2) The DIS_IN switch of the multifunctional test apparatus 100 is turned on.

3) It is confirmed through the monitor 151 of the control monitoring computer 150 that the corresponding DISCRETE input channel value changes from 0 to 1.

4) As the DIS_IN switch is changed, the test procedures of 2) and 3) above are repeated for each channel of input 1-8.

Next, DISCRETE output test is explained.

1) At the control monitoring computer 150, the test program is executed in a state defined as 'DISCRETE_OUT_TEST'.

2) When the status value of the DISCRETE output channel item on the monitor 151 of the control monitoring computer 150 changes from 0 to 1, it is confirmed that the corresponding DIS_OUT LED of the test fixture lights up.

3) Output Whether or not light is on for each channel 1-16 is checked.

Next, GPIO unit interlocking test will be described. That is, when the GPIO output state value is changed by the control monitoring computer 150 during the GPIO unit interlock test, the LED connected to the DISCRETE port 144 is turned on or the input state value of the input switch connected to the DISCRETE port 144 is changed The GPIO input state value of the control monitoring computer 150 is changed and displayed. That is, the communication line of the GPIO is checked.

The following explains this in turn.

1) In the control monitoring computer 150, the test program is executed in a state defined as 'GPIO_TEST'.

2) When the GPIO output status value changes from 0 to 1 in the monitor 151 of the control monitoring computer 150, it is confirmed that the GPIO output LED of the multifunctional test apparatus is turned on.

3) When the GPIO input switch is turned on in the multifunction test device, it is checked whether the GPIO input state value of DDC-I monitor screen changes from 0 to 1.

4) In the multifunctional test equipment, when the encoder switch of the Encoder is turned clockwise, the encoder input value of DDC-I's Video Stream screen changes from 0x00 to> 0x01 -> 0x11 -> 0x10 Is confirmed.

Next, the ANALOG input unit interlocking test will be described. That is, when the ANALOG input unit is interlocked and the ANALOG input status value is changed by the multifunctional test apparatus 100 after the control monitoring computer 150 is driven, the ANALOG input status value is changed via the control monitoring computer 150 Is displayed. That is, the communication line of the ANALOG is checked.

The following explains this in turn.

1) In the control monitoring computer 150, the test program is executed in a state defined as 'ANALOG_TEST'.

2) The VR1 dial switch of the multifunctional test apparatus 100 is turned.

3) It is confirmed through the monitor 151 of the control monitoring computer 150 whether the state value of the corresponding analog 1-channel item changes from a minimum value of 0 to a maximum value of 2DB or less.

4) The dial switch is changed to VR2, and the test procedures of 2) and 3) are repeated for the analog 2 channels

6 is a block diagram illustrating a PWM / I2C communication connection and test state using the multifunction test apparatus 100 for an input / output module of an avionics device according to an embodiment of the present invention.

During the PWM signal test, the multifunction test apparatus 100 determines whether the brightness of the lamp connected to the PWM port 146 changes as the PWM duty ratio changes.

That is, the PWM test proceeds in the following order.

1) The ethernet port of the functional test computer 170 and the ethernet port of the computer for the control monitor 151 are connected by an Ethernet cable.

2) The PWM signal level can be confirmed by the brightness change of the lamp. (For checking the PWM output duty ratio of the multifunction test apparatus 100, the oscilloscope 184 is connected to the multifunction test apparatus 100, It can be.

In the I2C communication test, the I2C communication test is performed by the control monitoring computer 150, and it is confirmed through the control monitoring computer 150 that the I2C communication result value is output.

That is, the I2C test is performed in the following order.

1) In the control monitoring computer 150, the test program is executed in a state defined as 'I2C_TEST'.

2) Check whether the I2C communication result value is displayed on the monitor 151 of the control monitoring computer 150 as 'ACK'.

Thus, the present invention allows the multifunctional test apparatus 100 to interrogate various communication signals of RS-232, RS-422/485, ARINC 429, DISCRETE, ANALOG, PWM and / 150, the input / output module 160, and / or the functional test computer 170, as described above.

The present invention also allows for checking and monitoring the status of the communication line between the control monitoring computer 150 and the input / output module 160 of the avionics equipment through the control monitoring computer 150 and / or the function testing computer 170 .

The present invention is not limited to the above-described embodiment, but may be applied to various types of test apparatuses, It will be understood by those of ordinary skill in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined in the appended claims.

100; The multifunctional test apparatus
110; Communication interface 120; The first communication port
130; A second communication port 140; Third communication port
141; RS-232 port 142; RS-422 port
143; ARINC 429 port 144; DISCRETE port
145; ANALOG port 146; PWM port
147; I2C port 150; Control monitoring computer
151; Monitor 160; I / O module
170; Function test computer 181; USB to RS 232 converter
182; USB to RS 422 variant 183; ENET to ARINC 429 Converter
184; oscilloscope

Claims (11)

A communication interface for mediating a communication signal;
A first communication port coupled to the communication interface to enable communication with the control monitoring computer;
A second communication port connected to the communication interface for communicating with the input / output module of the avionic device; And
And a plurality of third communication ports connected to the communication interface for selectively transmitting different types of communication signals. The method according to claim 1,
Wherein the plurality of third communication ports includes at least an RS-232 port, an RS-422/485 port, an ARINC 429 port, a DISCRETE port, an ANALOG port, a PWM port or an I2C port. Multifunction test equipment. The method according to claim 1,
Further comprising a functional test computer communicatively coupled to the control monitoring computer. ≪ RTI ID = 0.0 > [0002] < / RTI > The method of claim 3,
And the functional test computer is communicably connected to the third communication port. 5. The method of claim 4,
When the RS-232 or RS-422/485 transmission / reception data is tested,
A USB to RS-232 converter is connected between the RS-232 port or RS-422/485 port of the third port and a USB port of the functional test computer, or RS-232 to RS- The -422/485 converter is further connected,
After the transmission data is transmitted in the order of the functional testing computer, the multifunctional testing device, the input / output module, the multifunctional testing device and the control monitoring computer, the transmission data is outputted through the control monitoring computer,
Wherein the received data is transmitted through the functional test computer after the received data is transmitted in the order of the control monitoring computer, the multifunctional test device, the input / output module, the multifunctional test device and the functional test computer. Multifunction test equipment. 5. The method of claim 4,
When the ARINC 429 transmission / reception data is tested,
An ENET to ARINC 429 converter is connected between the ARINC 429 port of the third port and the Ethernet port of the functional test computer,
After the transmission data is transmitted in the order of the control monitoring computer, the multifunctional test apparatus, the input / output module, the multifunctional test apparatus, and the function test computer, the transmission data is outputted through the function test computer,
After the received data is transmitted in the order of the functional test computer, the multifunctional test device, the input / output module, the multifunctional test device, the control monitoring computer, the multifunctional test device, the input / output module, the multifunctional test device and the functional test computer, And outputting it through a test computer. The method according to claim 1,
When DISCRETE input / output data is tested,
After the control monitoring computer is driven, DISCRETE input data is input by the multifunction test apparatus, the DISCRETE input data is output through the control monitoring computer,
Outputting data of the DISCRETE method is output by the multifunctional test apparatus after the control monitoring computer is driven, and output data of the DISCRETE method is outputted through an LED connected to the DISCRETE port. Multifunction test equipment. The method according to claim 1,
In the GPIO unit interlock test,
The LED connected to the DISCRETE port is turned on when the GPIO output state value is changed by the control monitoring computer,
And the GPIO input state value of the control monitoring computer is changed and displayed when the input state value of the input switch connected to the DISCRETE port is changed, so that the multifunctional test apparatus for the input / output module of the avionics device. The method according to claim 1,
When the ANALOG input unit is interlocked,
When the ANALOG input state value is changed by the multifunctional test apparatus after the control monitoring computer is driven,
Wherein the ANALOG input state value is changed and displayed through the control monitoring computer. The method according to claim 1,
When testing the PWM signal,
Wherein the brightness of the lamp connected to the PWM port is changed as the PWM duty ratio is changed by the multifunctional test apparatus. The method according to claim 1,
In the I2C communication test,
The I2C communication test is performed by the control monitoring computer,
And the I2C communication result value is outputted through the control monitoring computer.
KR1020150118887A 2015-08-24 2015-08-24 Multi-function test equipment for input and output modules of the avionics KR20170023574A (en)

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KR20200029782A (en) 2018-09-11 2020-03-19 한국항공우주산업 주식회사 Bench test system for aviation equipment
KR102107111B1 (en) * 2019-09-19 2020-05-06 한화시스템 주식회사 Lru combined sru testing apparatus and method

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KR20140137325A (en) 2013-05-22 2014-12-02 에어 차이나 리미티드 Apparatus and method for testing aircraft message trigger logics
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Publication number Priority date Publication date Assignee Title
KR20200029782A (en) 2018-09-11 2020-03-19 한국항공우주산업 주식회사 Bench test system for aviation equipment
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