KR101693005B1 - Tester mother box apparatus - Google Patents

Abstract

Discloses a tester mother box device for performing testing through the avionics equipment integration of the present invention. The apparatus comprising: a test base component for simulating verification of the equipment under test, the test base component comprising a configuration for a computing host, power supply and monitoring, and a plurality of at least one line replaceable unit (LRU) Wherein the connection port of the SDC is configured to be detachably connectable with at least one connection member whose termination is connected to the LRU, and the SDC And a plurality of connection ports, one end of which is connected to the SDC connection port and the other end of which is connected to a first connection member connected to the LRU, The first surface and the second surface both including a detachable connection port, the detachable connection port including a second surface, By changing the arrangement of the connecting member between the access port from the second side is connected to the relationship between LRU connected to the connection port of the first surface it is arbitrarily changed.

Description

[0001] TESTER MOTHER BOX APPARATUS [0002]

The present invention relates to a tester mother box device which physically and functionally separates the inside of a test equipment, thereby shortening the development period.

Testing of avionics equipment involves developing a flight operating program, conducting software testing, verifying in an integrated system incorporating actual avionics equipment, and then conducting ground and flight tests. This will be described in detail in FIG.

1 is a conceptual diagram showing an aviation electronic equipment development process.

Referring to FIG. 1, firstly, the need for development of avionics equipment is grasped. If you find out what parts are needed for actual flight and the demand is derived, the system is designed according to the demand and equipped with the hardware equipment. Also develop and test the flight operation program for the designed system and develop the test station. At this time, a SIC (Simulation Interface Console), a SCC (Simulation Computer Complex) and an OTC (Operator Test Console) are provided. SIC is a device for developing an avionics system in an LAB, not an aircraft, and for developing an OFP (Flight Operation Program) in a mission computer. Currently, most aircraft are tested in LAB, It proceeds.

The system can be integrated to test the developed and verified software along with the actual avionics equipment, and once the verification is completed with the integrated system, the final verification can be completed via ground and flight tests.

However, since the flight test equipment is developed as one giant all-in-one equipment at the time of system integration, it is necessary to acquire all the signal interface information in order to develop one test equipment, so that the design can be completed, There is a problem that it takes a considerable time to manufacture.

FIG. 2 is a view showing an integrated testing apparatus using a tester mother box apparatus according to an embodiment of the present invention.

Referring to FIG. 2, in the actual appearance of the SIL, each avionics equipment is directly connected to each other through an interlocking cable, and there are many entangled devices connected to each other. Therefore, there is a problem that the design of the SIL itself is difficult, and the use of the test equipment is not possible when the test equipment is added because of the addition of the requirement of the test equipment. When the user of the test equipment changes the test environment There is a problem that it takes a long time to construct the environment because the test is interrupted in order to construct the required environment.

An object of the present invention to solve the above-mentioned problems is to provide a tester mother box device for simplifying / modularizing a system by using a funtional partitioning technology and grouping the functions into a detachable configuration .

In order to accomplish the above object, there is provided a tester mother box device for performing a test through integration of avionics equipment of the present invention is a test basic component for simulation verification of a test target device. The test basic components include a computing host, And a signal distribution console (SDC) including a plurality of connection ports to which at least one LRU (Line Replaceable Units) are connected, wherein the connection port of the SDC includes: Wherein at least one connection member whose end is connected to the LRU is detachably connectable and a first connection member whose one end is connected to the SDC connection port and the other end is connected to the LRU is connected A second surface for interfacing between a first surface comprising a plurality of connection ports and the plurality of connection ports of the SDC, Wherein the first surface and the second surface both include a detachable connection port and the first surface and the second surface are connected to the connection port of the first surface by changing the arrangement of the connection members between the connection ports on the second surface including the detachable connection port The connection relationship between the connected LRUs can be arbitrarily changed.

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The SDC may be divided into a first connection port region connecting the test basic component, a second connection port region connecting the at least one LRU, and a third connection port region connecting the test common support device.

The test base component may include a computing host component, a power supply component, a monitoring component, a simulation matrix component, a repeater matrix component, and a multiplexing interface component.

The LRU may include at least one of an avionics equipment group and an avionics equipment integration console group.

Wherein the avionics equipment group comprises aircraft mounted equipment and the avionics equipment integrated console group includes console type equipment in which aviation equipment is mounted on the console and information is exchanged with the SDC through the console's relay, Group and the avionics console integrated console group can be independently interlocked with the SDC through the connecting member for each equipment or console.

The avionics equipment group may include Mission Computer (MC) and actual avionics equipment.

The connecting member may include an interlocking cable.

The SDC may be a circuit board.

According to the tester mother box device of the present invention, it is possible to make the design determination and start production before securing all the interface information, thereby shortening the development period.

Further, according to the tester mother box apparatus of the present invention, sufficient time can be secured for verifying the test equipment, and the time required for the test equipment user to stop the test in order to establish a specific test environment between tests is shortened, So that the construction can be performed quickly.

FIG. 1 is a conceptual view showing an aviation electronic equipment development process,
FIG. 2 is a view showing an integrated testing apparatus using a tester mother box apparatus according to an embodiment of the present invention;
3 is a schematic view of a configuration of an integrated testing apparatus using a tester mother box apparatus according to an embodiment of the present invention,
FIG. 4 is a block diagram schematically illustrating a connection relationship between a tester mother box device and an LRU device according to an embodiment of the present invention. FIG.
5 is a view showing both sides of a tester mother box device according to an embodiment of the present invention,
FIG. 6 is a detailed block diagram specifically illustrating a connection relationship between an LRU device connected to a tester mother box device according to an embodiment of the present invention,
7 is a block diagram illustrating the relationship between the system integration utility, aviation equipment and test common support equipment and a signal distribution console (SDC).

While the invention is susceptible to various modifications and alternative forms, specific embodiments thereof are shown by way of example in the drawings and will herein be described in detail.

It is to be understood, however, that the invention is not to be limited to the specific embodiments, but includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.

The terms first, second, etc. may be used to describe various components, but the components should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from another. For example, without departing from the scope of the present invention, 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. And / or < / RTI > includes any combination of a plurality of related listed items or any of a plurality of related listed items.

It is to be understood that when an element is referred to as being "connected" or "connected" to another element, it may be directly connected or connected to the other element, . On the other hand, when an element is referred to as being "directly connected" or "directly connected" to another element, it should be understood that there are no other elements in between.

The terminology used in this application is used only to describe a specific embodiment and is not intended to limit the invention. The singular expressions include plural expressions unless the context clearly dictates otherwise. In the present application, the terms "comprises" or "having" and the like are used to specify that there is a feature, a number, a step, an operation, an element, a component or a combination thereof described in the specification, But do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

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

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In order to facilitate the understanding of the present invention, the same reference numerals are used for the same constituent elements in the drawings and redundant explanations for the same constituent elements are omitted.

FIG. 3 is a view schematically showing a configuration of an integrated testing apparatus using a tester mother box apparatus according to an embodiment of the present invention.

Referring to FIG. 3, the SIL includes a real-time operating system, and may include an operating system and an analysis system. The SIL can be connected to external equipment such as Mission Computer (MC), Multi-Function Display System (MFDS), and the like as an avionics network. Also, it can transmit and receive data to and from a radar system, a weapon system, an EW system, a navigation system (including GPS / INS), and a communication system.

The real-time operating system included in the SIL includes a plurality of subsystem models and may include a signal database. The operating system may also include a flight model, an operating program, a graphical user interface (GUI), and an operating console.

The analysis system may include a data analysis tool and a system network analysis tool. Data Analysis and Systems Network analysis tools can monitor, record and analyze data sent and received between LRUs.

The avionics network may include a MIL-STD-1553 network, an ARINC, a UART, and the like.

This SIL establishes the interface between the mission computer and the actual LRU (Line Replaceable Unit) equipment, and constructs the test environment system so that the signal of the simulation model is reflected in the actual equipment in the correct time. Here, the LRU may include avionics as an replaceable external unit. For example, radar, peer identification equipment, data transmission devices, horizontal status indicators, engine status computers, integrated digital engine production equipment, and the like.

In addition, the SIL can configure the avionics equipment model and provide its signals to mission computers and LRUs, and can be linked to user operating programs.

FIG. 4 is a block diagram schematically illustrating a connection relationship between a tester mother box device and an LRU device according to an embodiment of the present invention. Referring to FIG.

Referring to FIG. 4, the tester mother box device includes a system integration utility for simulating verification of the device under test and a signal distribution console (SDC) including a plurality of connection ports to which at least one line replaceable unit (LRU) Console).

The SDC has a flexible structure and can include a plurality of connection ports. A power distribution panel (PDP), a wired matrix (WMX), a relay matrix matrix (MCP), a mux interface panel (MIP) , LRU, etc., can be interconnected.

The PDP is a power distribution panel that serves to supply power to each WMX, RMP, MIP, and LRU.

WMX adjusts the wiring matrix and the signal to provide discrete / analog signals to each LRU.

RMP is a relay matrix panel, and MIP is a MUX interface panel, and can perform a role of multiplexing a signal coming from an LRU.

At least one LRU operates by receiving power from the PDP, and can transmit and receive video, audio, and data signals through the SDC.

5 is a view showing both sides of a tester mother box device according to an embodiment of the present invention.

Referring to FIG. 5, the first surface includes a plurality of connection ports connectable with the interlocking cable, and the second surface may include a surface for interfacing between connection ports of the first surface.

The first side is a space for connecting the LRU to the SDC connection port, wherein the end of the interlocking cable is respectively connected to the LRU and the connection port, and one of the ends of the interlocking cable is connected to the connection port of the SDC. The connection of the interlocking cable and connection port is possible by detachable.

The second side may also be configured to include a removable connection port and the user can easily change the connection relationship between the connection ports of the first side to which the LRU is connected by differently arranging the connection members between the connection ports.

The connection ports of the first surface and the second surface may be different from each other and need not necessarily be composed of two surfaces of the first surface and the second surface.

Also, the interface on the second side does not necessarily have to use the interlocking cable that was used on the first side, but other types of cables or other types of interconnection schemes (e.g., microelectrode use, etc.) may be used.

The advantage is that the SIL configuration can be modularized through a connection scheme in which each of these LRUs and external equipment is connected to the connection port of the SDC. That is, the LRUs are fixed in a single connection relationship, and each LRU is directly connected to each other in only one manner.

In other words, SIL modularization refers to designing, fabricating, and assembling the module by function without directly mounting the individual components on the rack or console. This allows for flexible adaptation to the frequent modification of the SIL.

The SIL modularization method can be simplified to the process of developing the requirements by modularizing each functional unit and the process of integrating the modules of the SIL system development. In addition, all modules may have an identification number and may exist as part of the SIL system. In SIL standardization, even if a single wire is used, it can be a single module having a unique identification number if it is separated and has independent functions.

In this case, since it is designed for each module, the system structure can be simplified, and the development can be concentrated on each module, thereby improving the overall SIL level. In addition, it can be produced professionally and concurrently for each module, and it is easy to combine the latest technology and equipment. In addition, it is possible to shorten the test environment construction time due to various demands of the user and the diversification of the aviation system, and maintenance after the system integration is facilitated.

FIG. 6 is a detailed block diagram illustrating a connection relationship between a tester mother box device and an LRU device according to an exemplary embodiment of the present invention. Referring to FIG.

6, the SDC 620 may be coupled to the computing host 610. The computing host 610 may be connected to the SDC via an MMP (Monitoring Matrix Panel) and an SMP (Simulation Matrix Panel). In addition, the computing host 610 may be connected to the workstation 1 to configure a PC workstation. That is, it can perform the VME bus function. The workstation 1 may include a window, and may include a user interface system and a flight model. The computing host 610 can send a processable signal from the avionics equipment, receive simulation data and the like from the avionics equipment, and perform processing such as analysis.

The computing host 610 and the workstation 1 as basic equipment connected to the SDC 620, as well as a monitor connected to the workstation. It also includes a loader PC, including a server and a window, including Windows, electronic equipment, and a SIL source, including MC / LAD OFP and SIL software, and the server and loader PC can be interconnected via Ethernet have. It may also include the SM555, which manages the flight image PC and video overlay and merge. Loader PC and SM555 can be connected to different monitors respectively. Further, the PDP may further include a PDP for power supply, and may further include a BBP (Blower Box Panel), a VIP (Video Interface Panel), an RMP and a MIP. ). ≪ / RTI > It may also include workstation 1 and a respected stick / throttle, which may be connected to the SDC to provide control commands to the LRU.

 The SDC 620 can be connected to the basic components (test equipment) of the MMP, SMP, RMP, MIP, SIP, SPP, SMP, PDP, Misc.P, BBP and VIP via detachable connection ports.

The SDC 620 can also be used as a part of an airplane part and can be connected to a plurality of common support stations 640, a plurality of LRUs 630-1 to 630-N and a plurality of benches 632-1 to 632- And can be connected through a connection port. Here, at least one of the plurality of LRUs 630-1 to 630-N may be a mission computer. Mission computers can operate as real-time workstations. That is, a VME-PC workstation. The equipment of the aircraft part may come with other equipment. Here, the bench (632-1 to 632-N) is an LRU integrated console, which means an integrated console in which the LRU equipment is integrated with other basic components such as PD and MIP.

7 is a block diagram showing the relationship between the system integration utility, the aviation equipment and the test common support equipment and the signal distribution console (SDC).

Referring to FIG. 7, the SDC 740 may be included in the system integration utility 710. That is, the system integration utility 710 is a main utility of the SIL, including a test basic component (see FIG. 6) and an SDC 740. In other words, it is a utility for basic tests for controlling avionics and test support equipment, receiving and monitoring sensing information, and analyzing it.

The system integration utility 710 can be broadly divided into a test basic component and an SDC 740. The test basic component may include various utility panels such as a computing host, PDP, MMP, SMP, RMP, MIP, The test basic components provide power to various devices connected to the SDC 740 via the SDC 740, drive the simulation program, control the switching (repeater), block the circuit, do. The SDC 740 can also monitor and analyze the sensing information and the status information received from the aviation equipment 720.

The aviation equipment 720 may include at least one LRU (Avionics Equipment Group) and LIC (Avionics Consolidated Console Group) and may receive control and display signals via the SDC 740. The status and sensed information may also be transmitted to the SDC 740.

Here, the LRU (avionics equipment group) refers to aircraft mounted equipment and may include MC, EGL, APP, and the like. In addition, each device can be interlocked with the SDC 740 independently through an interlocking cable, and can exchange information with other systems (LRU, LIC, JSE, SIL) through the SDC 740.

The LIC (Consolidated Console Group of Avionics Equipment) collectively refers to console-type equipment where avionics equipment is mounted on the console to exchange information with the SDC (740) through the console's relay. For example, RTB. These LICs can be commonly used in many SILs depending on the frequency of use. The LIC can also be interlocked with the SDC 740 independently through an interworking cable for each device and can exchange information with other systems (LRU, LIC, JSE, SIL) through the SDC 740.

The test joint support equipment (730) collectively refers to common equipment for testing support without including avionics equipment, and is stand alone in order to utilize various functions excluded from the scope of the main function of SIL due to its low frequency of use, It is a device that is provided as a support for the test of the form. It can also exchange information with other systems (LRU, LIC, JSE, SIL) via the SDC 740.

The interworking cable group that performs the connection function with the SDC 740 may have an independent shape for each equipment and can accommodate a wire for each signal type.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit or scope of the inventions as defined by the following claims It will be understood that various modifications and changes may be made thereto without departing from the spirit and scope of the invention.

Claims (9)

A tester mother box device for performing testing through integration of avionics equipment,
Test base components for simulation verification of the equipment under test - The test base components include the configuration for computing host, power supply and monitoring - and a plurality of connection ports to which at least one LRU (Line Replaceable Unit) And a signal distribution console (SDC)
Wherein the connection port of the SDC is configured to be detachably connectable to at least one connection member whose end is connected to the LRU,
A first surface including a plurality of connection ports to which one end of the SDC connection port and the other end of which are connected to a first connection member connected to the LRU; And
A second side for an interface between the plurality of connection ports of the SDC,
Wherein the first surface and the second surface both include a removable connection port,
Wherein the connection relationship between the LRUs connected to the connection port of the first surface is arbitrarily changed by changing the arrangement of the connection members between the connection ports on the second surface including the detachable connection port. delete The method according to claim 1,
Wherein the SDC is divided into a first connection port region for connecting the test basic component, a second connection port region for connecting the at least one LRU, and a third connection port region for connecting the test common support device Tester mother box device. The method according to claim 1,
Wherein the test base component comprises a computing host component, a power supply component, a monitoring component, a simulation matrix component, a repeater matrix component, and a multiplexing interface component. The method according to claim 1,
Wherein the LRU comprises at least one of an avionics equipment group and an avionics equipment integrated console group. 6. The method of claim 5,
The avionics equipment group includes aircraft mounted equipment,
The avionics console integrated console group includes console type equipment in which avionics equipment is mounted on the console to exchange information with the SDC through the console's relay,
Wherein the avionics equipment group and the avionics console integrated console group independently interlock with the SDC through the connecting member for each equipment or console. The method according to claim 6,
Wherein the avionics equipment group comprises a mission computer (MC) and actual avionics equipment. The method according to claim 1,
Wherein the connecting member comprises an interlocking cable. The method according to claim 1,
Wherein the SDC is a circuit board.

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