CN219039627U

CN219039627U - Test platform for display control system of aircraft

Info

Publication number: CN219039627U
Application number: CN202223474520.5U
Authority: CN
Inventors: 李宁
Original assignee: Beijing Runke General Technology Co Ltd
Current assignee: Beijing Runke General Technology Co Ltd
Priority date: 2022-12-26
Filing date: 2022-12-26
Publication date: 2023-05-16
Anticipated expiration: 2032-12-26

Abstract

The embodiment of the utility model provides a test platform for an aircraft display control system. The platform comprises a first protocol terminal device, an onboard switch, a second protocol terminal device, a second protocol tandem box, a third protocol terminal device and a third protocol tandem box; the first protocol terminal equipment is connected with the aircraft display through the airborne switch, and the conversion of the integrated test mode and the parallel test mode is realized by switching the routing table of the airborne switch; the second protocol terminal equipment is connected with the aircraft display through a second protocol tandem box, and conversion between an integrated test mode and a parallel test mode is realized through pulling and inserting a connecting wire between the second protocol tandem boxes; the third protocol terminal equipment is connected with the aircraft display through a third protocol tandem box, and the conversion of the integrated test mode and the parallel test mode is realized by changing the terminal connection mode on the third protocol tandem box. The utility model can realize the conversion of IDU integrated test and parallel test, and improves the utilization rate of the test platform.

Description

Test platform for display control system of aircraft

Technical Field

The utility model relates to the technical field of testing of display and control systems of aircrafts, in particular to a testing platform of a display and control system of an aircraft.

Background

Ground testing of an aircraft, such as an aircraft, whose display control system is conducted around 5 IDUs (IntegratedDisplay Unit, integrated display), is divided into two tests and a single device test. During integrated test, an integrated test platform is built on the ground according to the real connection relation on the machine, and bus excitation signals of ARINC664, ARINC429, ARINC825 and DIO (discrete quantity) are simulated to 5 IDUs. During single device testing, ARINC664, ARINC429, ARINC825, and DIO are simulated to a single IDU.

At present, an integrated test platform is occupied during single-equipment test, and an integrated test platform for originally testing 5 IDUs is used for single-equipment test, so that test resources are wasted greatly.

Disclosure of Invention

The embodiment of the utility model aims to provide a test platform for an aircraft display control system, which can realize the conversion of IDU integrated test and parallel test and can improve the utilization rate of the test platform. The specific technical scheme is as follows:

the utility model provides a test platform of an aircraft display control system, which comprises:

the system comprises a first protocol terminal device, an onboard switch, a second protocol terminal device, a second protocol tandem box, a third protocol terminal device and a third protocol tandem box;

the first protocol terminal equipment is connected with an aircraft display through the airborne switch, and the conversion of an integrated test mode and a parallel test mode is realized by switching a routing table of the airborne switch;

the second protocol terminal equipment is connected with the aircraft display through the second protocol tandem box, and conversion between an integrated test mode and a parallel test mode is realized through pulling and inserting a connecting wire between the second protocol tandem boxes;

the third protocol terminal equipment is connected with the aircraft display through the third protocol tandem box, and the conversion of the integrated test mode and the parallel test mode is realized by changing the terminal connection mode on the third protocol tandem box.

Alternatively to this, the method may comprise,

in an integrated test mode, a plurality of first protocol terminal devices are respectively connected with interfaces of the same first protocol terminal device connecting end through a routing table of the airborne switch;

and in a parallel test mode, enabling the plurality of first protocol terminal devices to be respectively connected with interfaces of different first protocol terminal device connection ends through the routing table of the airborne switch.

Alternatively to this, the method may comprise,

in an integrated test mode, the second protocol tandem boxes are connected through connecting wires, and one second protocol terminal device is connected with a plurality of aircraft displays;

in the parallel test mode, connecting lines between two adjacent second protocol junction boxes are disconnected, and different second protocol terminal devices are connected with different aircraft displays.

Alternatively to this, the method may comprise,

in an integrated test mode, connecting the third protocol terminal equipment with the aircraft display on the same connecting line through the third protocol junction box upper terminal;

and in a parallel test mode, the third protocol terminal equipment is respectively connected with the aircraft display on different connecting lines through the third protocol junction box upper terminal.

Optionally, the on-board switch includes:

the system comprises at least two first protocol terminal equipment connecting ends and a plurality of display interfaces, wherein each first protocol terminal equipment connecting end is provided with a plurality of interfaces connected with the first protocol terminal equipment, and each display interface is connected with one aircraft display;

the test signals transmitted by the interfaces of the same first protocol terminal equipment connection end are the same, and the test signals transmitted by the interfaces of different first protocol terminal equipment connection ends are different.

Alternatively to this, the method may comprise,

the second protocol tandem box comprises a signal input end, a signal output end and an equipment port, wherein the signal input end is respectively connected with the signal output end and the equipment port, and the equipment port of the second protocol tandem box is used for connecting the aircraft display;

in the integrated test mode, the plurality of second protocol tandem boxes are sequentially connected, the signal input end of the second protocol tandem box at the head end is connected with the second protocol terminal equipment, the signal output end of the second protocol tandem box at the head end is connected with the signal input end of the second protocol tandem box at the rear end, the signal input end of the second protocol tandem box at the tail end is connected with the signal output end of the second protocol tandem box at the front end, and the test signals of the second protocol terminal equipment transmitted by the plurality of second protocol tandem boxes are identical;

in the parallel test mode, the second protocol junction boxes are divided into at least two groups, the second protocol junction boxes of the same group are sequentially connected, the signal input end of the second protocol junction box of each group of head end is connected with the second protocol terminal equipment, the signal input end of the second protocol junction box of each group of tail end is connected with the signal output end of the previous second protocol junction box, and the test signals of the second protocol terminal equipment transmitted by the second protocol junction boxes of different groups are different.

Optionally, the second protocol tandem box further includes:

a terminal block and a connection terminal pair;

the first end of the terminal strip is connected with the signal input end, the second end of the terminal strip is connected with the signal output end, the third end of the terminal strip is connected with the first end of the connecting terminal pair, and the second end of the connecting terminal pair is connected with the equipment interface;

the connection terminal pair is provided with two connection terminals, and when the two connection terminals are connected, test signals of the second protocol terminal equipment are transmitted to the aircraft display.

Alternatively to this, the method may comprise,

the number of the terminal rows and the number of the connecting terminal pairs are multiple, and the terminal rows and the connecting terminal pairs are in one-to-one correspondence;

and in an integrated test mode or a parallel test mode, the number of the connected connection terminal pairs is one, and when different connection terminal pairs are connected, test signals sent by different second protocol terminal devices are transmitted to the aircraft display.

Optionally, the third protocol tandem box includes:

a first switching terminal, a second switching terminal, a third switching terminal, a fourth switching terminal, a first resistor, a second resistor, a third resistor, a fourth resistor, and a display terminal;

the first switching terminal is connected with the first resistor, the second switching terminal is connected with the second resistor, the third switching terminal is connected with the third resistor, and the fourth switching terminal is connected with the fourth resistor; the display terminal is connected with the first resistor and the second resistor respectively, and the aircraft display is connected to the display terminal.

Alternatively to this, the method may comprise,

in an integrated test mode, the first switching terminal is connected with the second switching terminal, the first resistor is connected with the second resistor, and the third protocol terminal equipment transmits a test signal to the aircraft display through a connecting wire of the first resistor and the second resistor;

in the parallel test mode, the second switching terminal is connected with the third switching terminal, the first switching terminal is connected with the fourth switching terminal, one group of third protocol terminal equipment transmits test signals to the aircraft display through the connecting wires of the second resistor and the third resistor, the other group of third protocol terminal equipment transmits test signals to the aircraft display through the connecting wires of the first resistor and the fourth resistor, and the test signals transmitted by the third protocol terminal equipment are different.

The utility model provides a test platform of an aircraft display control system, which comprises a first protocol terminal device, an onboard switch, a second protocol terminal device, a second protocol tandem box, a third protocol terminal device and a third protocol tandem box, wherein the first protocol terminal device is connected with an aircraft display through the onboard switch, and the conversion between an integrated test mode and a parallel test mode is realized by switching a routing table of the onboard switch; the second protocol terminal equipment is connected with the aircraft display through a second protocol tandem box, and conversion between an integrated test mode and a parallel test mode is realized through pulling and inserting a connecting wire between the second protocol tandem boxes; the third protocol terminal equipment is connected with the aircraft display through a third protocol tandem box, and the conversion of the integrated test mode and the parallel test mode is realized by changing the terminal connection mode on the third protocol tandem box. The utility model can realize the conversion between the integrated test and the parallel test for the three protocol terminal devices respectively, and improves the utilization rate of the test platform.

Of course, it is not necessary for any one product to practice the utility model to achieve all of the advantages set forth above at the same time.

Drawings

In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a diagram of a test platform of an aircraft display and control system according to an embodiment of the present utility model;

fig. 2 is a schematic diagram of an on-board switch according to an embodiment of the present utility model;

FIG. 3 is a schematic diagram of an on-board ARINC 664-linked configuration according to an embodiment of the present utility model;

FIG. 4 (a) is a schematic diagram of ARINC664 connection configuration in an integrated test mode according to an embodiment of the present utility model;

FIG. 4 (b) is a schematic diagram of ARINC664 connection configuration in parallel test mode according to an embodiment of the present utility model;

FIG. 5 is a schematic diagram of an on-board ARINC429 or DIO connection configuration provided by an embodiment of the utility model;

FIG. 6 (a) is a schematic diagram of ARINC429 or DIO connection configuration in an integrated test mode according to an embodiment of the present utility model;

FIG. 6 (b) is a schematic diagram of ARINC429 or DIO connection configuration in a parallel test mode according to an embodiment of the utility model;

fig. 7 (a) is a schematic diagram of a second protocol tandem box according to an embodiment of the present utility model;

FIG. 7 (b) is a schematic diagram of another second protocol tandem box according to an embodiment of the present utility model;

FIG. 8 (a) is a schematic diagram of ARINC429 or DIO connection configuration in another integrated test mode according to an embodiment of the utility model;

FIG. 8 (b) is a schematic diagram of ARINC429 or DIO connection configuration in another integrated test mode according to an embodiment of the utility model;

FIG. 9 is a schematic diagram of an on-board ARINC825 coupling configuration according to an embodiment of the present utility model;

FIG. 10 (a) is a schematic diagram showing the ARINC825 coupling configuration under test according to the embodiment of the utility model;

FIG. 10 (b) is a schematic diagram of ARINC825 connection configuration during integrated testing according to an embodiment of the present utility model;

FIG. 10 (c) is a schematic diagram of ARINC825 coupling configuration for parallel testing according to an embodiment of the utility model.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

The utility model provides a test platform of an aircraft display control system, as shown in figure 1, which comprises: the system comprises a first protocol terminal device 1, an onboard exchange 2, a second protocol terminal device 3, a second protocol junction box 4, a third protocol terminal device 5 and a third protocol junction box 6.

The first protocol terminal device 1 is connected with the aircraft display 7 through the onboard switch 2, and the conversion between the integrated test mode and the parallel test mode is realized by switching the routing table of the onboard switch.

The second protocol terminal device 3 is connected with the aircraft display 7 through the second protocol junction box 4, and the conversion between the integrated test mode and the parallel test mode is realized through plugging and unplugging the connecting wire between the second protocol junction boxes.

The third protocol terminal equipment 5 is connected with the aircraft display 7 through the third protocol junction box 6, and the conversion between the integrated test mode and the parallel test mode is realized by changing the terminal connection mode on the third protocol junction box.

For the first protocol end device 1, the first protocol end device 1 may be an ARINC664 end device. The ARINC664 terminal device may be an RDIU (remotedatainterface unit), and the ARINC664 terminal device may also be an IMA (IntegratedModule Avionics, modular integrated avionics).

As shown in fig. 2, the on-board exchange 2 includes: at least two first protocol terminal device connections 11 and a plurality of display interfaces 12, each first protocol terminal device connection 11 having a plurality of interfaces 111 for connecting to the first protocol terminal device 1, each display interface 12 for connecting to one of the aircraft displays 7.

The test signals transmitted by the interfaces of the same first protocol terminal equipment connection end are the same, and the test signals transmitted by the interfaces of different first protocol terminal equipment connection ends are different. The interface of the first protocol terminal equipment and the display interface are switched in connection relation through a routing table.

The on-board ARINC664 connection configuration is shown in fig. 3, the first protocol termination device 1 being connected to the aircraft display 7 via the on-board exchange 2. In fig. 3, the number of flight displays 7 is 5, and is represented by IDU1, IDU2, IDU3, IDU4, and IDU5, respectively. The first protocol terminal equipment can be ARINC664 terminal equipment, the aircraft display can be an aircraft display, the connection configuration of the ARINC664 protocol bus on the aircraft is a star topology structure, different types of ARINC664 terminal equipment are connected to an onboard switch, and data transmission of each ARINC664 terminal equipment is realized by configuring an onboard switch route.

In the integrated test mode, a plurality of first protocol terminal devices are respectively connected with interfaces of the same first protocol terminal device connecting ends through a routing table of the onboard switch.

As an alternative embodiment, as shown in fig. 4 (a), a plurality of display interfaces 12 are represented by Port1, port2, port3, port4, and Port5, respectively, one display interface is connected to one aircraft display 7, and a plurality of aircraft displays 7 are represented by IDU1, IDU2, IDU3, IDU4, and IDU5, respectively. A plurality of first protocol terminal devices 1 are respectively represented by

devices

1, 2 and 3, interfaces 111 of the first protocol terminal device connection terminals 11 are respectively represented by

ports

6, 7, 8, 9, 10 and 11, each first protocol terminal device is connected with a Port interface, and arrows in fig. 4 indicate data transmission directions. In the integrated test mode, the connection relation between the interface of the first protocol terminal device and the display interface in the routing table of the on-board switch is that Port6 is connected with Port1 and Port2 respectively, port7 is connected with Port3 and Port4 respectively, and Port8 is connected with Port 5. The first protocol terminal equipment is connected with the aircraft displays only through the same first protocol terminal equipment connecting end 11, and test signals transmitted by three first protocol terminal equipment corresponding to the same first protocol terminal equipment connecting end are the same, so that integrated test of the five aircraft displays is realized.

In the parallel test mode, a plurality of first protocol terminal devices are respectively connected with interfaces of different first protocol terminal device connecting ends through a routing table of an onboard switch.

As an alternative implementation manner, as shown in fig. 4 (b), in the parallel test model, the connection relationship between the interface of the first protocol terminal device and the interface of the display in the routing table of the on-board switch is that Port6 is connected with Port1 and Port2 respectively, port8 is connected with Port5, port10 is connected with Port3 and Port4 respectively, port6 is two interfaces of the same first protocol terminal device connection end 11 with Port8, port10 is an interface of two different first protocol terminal device connection ends 11 with Port6, and the test signals transmitted by the interfaces of the different first protocol terminal device connection ends are different, so that parallel test can be implemented, that is, IDU1, IDU2 and IDU5 are tested in one group, IDU3 and IDU4 are tested in the other group, IDU1, IDU2 and IDU5 are tested in the same, IDU3 and IDU4 are tested in the same, and the test signals of IDU1 and IDU3 are different.

When the bus test signal of ARINC664 is simulated to IDU, the utility model can realize the switching between IDU integrated test and parallel test by changing the interface connection relation of the routing table, thereby improving the utilization rate of the test platform of the display control system of the aircraft.

For the second protocol terminal device, the second protocol terminal device may be an ARINC429 terminal device or a DIO terminal device. The connection configuration of the ARINC429 or the DIO bus on the aircraft is shown in fig. 5, and the connection configuration of the ARINC429 or the DIO bus on the aircraft is point-to-point, namely, a second protocol terminal device is connected with a plurality of aircraft displays. In fig. 5, five aircraft displays are IDU1, IDU2, IDU3, IDU4, and IDU5, respectively, and the second protocol terminal device has three types, which are respectively distinguished by IRU (InertialReference Unit, inertial reference device), CCD (cursor control device), and FCM (flight control module), wherein the IRU can be used as ARINC429 terminal device, the CCD can be used as DIO terminal device, and the FCM can be used as ARINC429 terminal device. The arrow in fig. 5 indicates the transmission direction of the test signal. The number of the second protocol terminal devices with the IRU type is three, namely IRU1, IRU2 and IRU3, the IRU1 is respectively connected with IDU1, IDU2, IDU3, IDU4 and IDU5, the IRU2 is respectively connected with IDU1, IDU2, IDU3, IDU4 and IDU5, and the IRU3 is respectively connected with IDU1, IDU2, IDU3, IDU4 and IDU5. The number of the second protocol terminal devices with the type of CCD is two, namely CCD1 and CCD2, the CCD1 is respectively connected with IDU1, IDU2, IDU3, IDU4 and IDU5, and the CCD2 is respectively connected with IDU1, IDU2, IDU3, IDU4 and IDU5. The number of the second protocol terminal devices with the type of FCM is 3, the second protocol terminal devices are respectively FCM1, FCM2 and FCM3, test signals transmitted by the FCM1, FCM2 and FCM3 are the same, the FCM1 is connected with IDU1 and IDU2, the FCM2 is connected with IDU3 and IDU4, and the FCM3 is connected with IDU5.

The second protocol terminal 3 is connected to the aircraft display 7 via a second protocol junction box 4, as shown in fig. 6, the second protocol junction box 4 comprising a signal input 52, a signal output 53 and an equipment port 54, the signal input being connected to the signal output and the equipment port, respectively, the equipment port of the second protocol junction box being used for connecting to the aircraft display.

In the integrated test mode, as shown in fig. 6 (a), the plurality of second protocol tandem boxes are sequentially connected in a group, the signal input end of the second protocol tandem box at the head end is connected with the second protocol terminal device 3, the signal output end of the second protocol tandem box at the head end is connected with the signal input end of the second protocol tandem box at the rear end, the signal input end of the second protocol tandem box at the tail end is connected with the signal output end of the first second protocol tandem box, and the test signals of the second protocol terminal devices transmitted by the plurality of second protocol tandem boxes are the same.

In the parallel test mode, as shown in fig. 6 (b), the plurality of second protocol tandem boxes are divided into at least two groups, the plurality of second protocol tandem boxes of the same group are sequentially connected, the signal input end of the second protocol tandem box of each group head end is connected with the second protocol terminal device 3, the signal input end of the second protocol tandem box of each group tail end is connected with the signal output end of the previous second protocol tandem box, and the test signals of the second protocol terminal devices transmitted by the second protocol tandem boxes of different groups are different.

As an alternative embodiment, as shown in fig. 7 (a), the second protocol tandem box 4 further includes: a terminal block 61 and a connection terminal pair 62. The first end of the terminal strip is connected with the signal input end, the second end of the terminal strip is connected with the signal output end, the third end of the terminal strip is connected with the first end of the connecting terminal pair, and the second end of the connecting terminal pair is connected with the equipment interface; the connection terminal pair has two connection terminals, which when connected transmit test signals of the second protocol terminal to the aircraft display. The arrow in fig. 7 (a) indicates the signal transmission direction, and the terminal block may transmit the test signal transmitted from the signal input terminal to the connection terminal pair and the signal output terminal, respectively.

Optionally, in fig. 7 (a), a signal collecting line may be further provided, where a signal transmission direction of the signal collecting line is that a signal is transmitted from the terminal strip to the signal input end, and the signal collecting line is used to transmit a signal of the aircraft display to the second protocol terminal device connected to the signal input end through the device interface, the connection terminal pair, the terminal strip and the signal input end.

As another alternative embodiment, as shown in fig. 7 (b), the number of the terminal rows and the connection terminal pairs is plural, and the terminal rows and the connection terminal pairs are in one-to-one correspondence; in the integrated test mode or the parallel test mode, the number of the connected connection terminal pairs is one, and when different connection terminal pairs are connected, test signals sent by different second protocol terminal devices are transmitted to an aircraft display. The arrow in fig. 7 (b) indicates the signal transmission direction.

In fig. 7 (b), the number of terminal rows and connection terminal pairs is 3, and two connection terminals of the middle connection terminal pair are connected to each other among the three connection terminal pairs, and the other two connection terminals of the other two connection terminal pairs are not connected to each other. The test signal of the second protocol terminal device is input to the device port 54 through the signal input terminal 52 via the terminal block at the intermediate position to the intermediate conductive connection terminal pair.

The aircraft displays to which the device interfaces can be connected are IDU1, IDU2, IDU3, IDU4, IDU5 in fig. 5, the second protocol terminal devices to which the signal input end can be connected are respectively IRU1, IRU2, IRU3 shown in fig. 5, and the second protocol terminal devices to which the signal input end can be connected are respectively CCD1 and CCD2 shown in fig. 5. Since the second protocol terminal devices of the IRU and CCD type are connected to the five IDUs, respectively, the transmission of the test signal can be realized through a set of terminal blocks and connection terminal pairs.

The number of second protocol terminal devices to which the signal input end 52 can be connected is 3, the different second protocol terminal devices transmit test signals through different terminal rows, if the connection terminal pair connected with the terminal rows is turned on, the test signals can be transmitted to the aircraft display connected with the device interface through the device port, the aircraft display connectable with the device interface is IDU1, IDU2, IDU3, IDU4, IDU5 in fig. 5, and if the three second protocol terminal devices are FCM1, FCM2, FCM3 shown in fig. 5 respectively, the FCM1 is connected with IDU1, IDU2, the FCM2 is connected with IDU3, IDU4, and the FCM3 is connected with IDU5. If the uppermost terminal row and connection terminal in fig. 7 transmit the test signal of FCM1, the middle terminal row and connection terminal transmit the test signal of FCM2, and the lowermost terminal row and connection terminal transmit the test signal of FCM3, then when the device port is connected to IDU1 or IDU2, two connection terminals of the uppermost connection terminal pair are connected and conducted, the other two connection terminal pairs are not conducted, and the test signal of FCM1 is transmitted to IDU1 or IDU2. When the device ports are connected with IDU3 and IDU4, two connection terminals of the middle connection terminal pair are connected and conducted, and the other two connection terminal pairs are not conducted, and the test signal of FCM2 is transmitted to IDU3 or IDU4. When the device port is connected with the IDU5, two connection terminals of the lowest connection terminal pair are connected and conducted, and the other two connection terminal pairs are not conducted, and the test signal of the FCM3 is transmitted to the IDU5. According to the utility model, by changing different conductive connection terminal pairs, different second protocol terminal devices can transmit test signals to different aircraft displays, and the flexibility of the test is improved.

Of course, the function of transmitting test signals of the second protocol terminal device of the type IRU and CCD to five IDUs in fig. 7 (a) can be also implemented by adopting the three sets of terminal rows and the connection terminal pairs of fig. 7 (b).

In the integrated test, as shown in fig. 8 (a), a plurality of second protocol terminal devices may be connected to the emulation board 71, if the number of the second protocol terminal devices is 3, the test signals transmitted by the 3 second protocol terminal devices enter different terminal rows through the signal input ends respectively, the test signals are transmitted to the corresponding IDU through connection or disconnection of the connection terminal pairs, and the test signals transmitted by the 3 second protocol terminal devices are input to the signal output ends through different terminal rows, so that the test signals are transmitted from one second protocol junction box to another second protocol junction box, and the integrated test of the display control system of the aircraft is realized.

In fig. 8 (a), if FCM1, FCM2, FCM3 are connected to the simulation board card 71, the second protocol junction boxes connected to the simulation board card are the first group of junction boxes, and the second group of junction boxes, the third group of junction boxes, the fourth group of junction boxes, and the fifth group of junction boxes are sequentially connected. The first group of junction boxes are connected with the IDU1, and the test signals of the FCM1 are transmitted to the IDU1 through the connection relation of the uppermost connection terminal pair in the first group of junction boxes. The second group of junction boxes are connected with IDU2, and the test signals of FCM2 are transmitted to IDU2 through the connection relation of the uppermost connection terminal pair in the second group of junction boxes. The third group of junction boxes are connected with the IDU5, and the test signals of the FCM3 are transmitted to the IDU5 through the connection relation of the lowest connection terminal pair in the third group of junction boxes. The fourth group of junction boxes are connected with the IDU3, and the test signals of the FCM2 are transmitted to the IDU3 through the connection relation of the middle connection terminal pairs in the fourth group of junction boxes. The fifth group of junction boxes are connected with the IDU4, and the test signals of the FCM2 are transmitted to the IDU4 through the connection relation of the middle connection terminal pairs in the fifth group of junction boxes.

Of course, if the IDU connected to the device interface 54 is IDU1, and the connection terminal pair is the uppermost two connection terminals, the IDU1 of the aircraft connected to the device interface 54 may be changed to IDU3, and when the IDU connected to the device interface of the first group of junction boxes is changed to IDU3, the connection relationship of the connection terminal pair is also changed from the uppermost two connection terminals to the middle two connection terminals. If the flying display IDU1 is converted to IDU2, the connection relationship of the connection terminal pair is not changed, and the uppermost two connection terminals are still connected. It can be seen that the present utility model can change the aircraft display IDU to which the device interfaces by switching the connection relationship of the connection terminal pairs.

In fig. 8 (a), if IRU1, IRU2 and IRU3 are connected to the dummy board 71, or if CCD1 and CCD2 are connected to the dummy board 71, the connection relationship of the connection terminal pairs in the five sets of junction boxes may be any one of the uppermost two connection terminal connections, the middle two connection terminal connections and the lowermost two connection terminal connections, and the connection terminal pairs having the connection relationship in the five sets of junction boxes may be the same in position, that is, may be all the uppermost connection terminal pairs, or may be the middle connection terminal pairs or the lowermost connection terminal pairs.

In parallel test, as shown in fig. 8 (b), if the test signals of the first group of junction boxes, the second group of junction boxes and the third group of junction boxes are the same, the test signals of the fourth group of junction boxes and the fifth group of junction boxes are the same, the test signals of the first group of junction boxes and the fourth group of junction boxes are different, and different test signals can be transmitted by arranging two simulation boards 71, only the connection line between the signal output end of the third group of junction boxes and the signal input end of the fourth group of junction boxes in fig. 8 (a) is pulled out, and the signal input end of the fourth group of junction boxes is connected with one simulation board 81, wherein the test signals transmitted by the second protocol terminal equipment connected by the two simulation boards are different, so that the parallel test of the display control system of the aircraft is realized.

For the third protocol terminal device, the third protocol terminal device may be an ARINC825 terminal device. The ARINC825 terminal device may be a CCD (cursor control device), and the ARINC825 terminal device may also be an MKB (Multi-function keyboard).

As shown in fig. 9, the ARINC825 protocol bus is connected to the aircraft in a bus-type manner, the connection between the two resistors R is a bus-type, the aircraft displays 7 are respectively indicated by IDU1, IDU2, IDU3, IDU4, IDU5, and these aircraft displays and the third protocol terminal device 5 are suspended in the form of branches from the trunk. The test signals transmitted by the third protocol terminal are transmitted via the bus to one or more aircraft displays, although the signals of the aircraft displays can also be transmitted via the bus to the third protocol terminal. The arrow direction of fig. 9 indicates the transmission direction of the signal.

In order to realize switching between the integrated test and the parallel test, as shown in fig. 10 (a), the third protocol tandem box includes: the first switching terminal A, the second switching terminal B, the third switching terminal C, the fourth switching terminal D, the first resistor R1, the second resistor R2, the third resistor R3, the fourth resistor R4 and the display terminal, the aircraft displays IDU1, IDU2, IDU3, IDU4 and IDU5 are connected to the display terminals, the display terminals corresponding to IDU1, IDU2 and IDU5 are connected with the first resistor R1, and the display terminals corresponding to IDU3 and IDU4 are connected with the second resistor R2. The first switching terminal is connected with the first resistor, the second switching terminal is connected with the second resistor, the third switching terminal is connected with the third resistor, and the fourth switching terminal is connected with the fourth resistor.

In the integrated test mode, as shown in fig. 10 (B), the first switching terminal a and the second switching terminal B are connected, the first resistor R1 and the second resistor R2 are connected, and the third protocol terminal device 5 transmits a test signal to the aircraft displays IDU1, IDU2, IDU3, IDU4, IDU5 through the connection line of the first resistor R1 and the second resistor R2.

In the parallel test mode, as shown in fig. 10 (C), the second switch terminal B is connected to the third switch terminal C, the first switch terminal a is connected to the fourth switch terminal D, one group of third protocol terminal devices 5 transmits test signals to the aircraft displays IDU1, IDU2, IDU5 through the connection lines of the second resistor R2 and the third resistor R3, the other group of third protocol terminal devices 5 transmits test signals to the aircraft displays IDU3, IDU4 through the connection lines of the first resistor R1 and the fourth resistor R4, and the test signals transmitted by the different groups of third protocol terminal devices are different.

The utility model can conveniently realize IDU integrated test and parallel test switching, increases the use scene of the test platform of the display and control system of the aircraft, improves the utilization rate of the test platform of the display and control system of the aircraft, and improves the test efficiency.

It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, article or apparatus that comprises an element.

In this specification, each embodiment is described in a related manner, and identical and similar parts of each embodiment are all referred to each other, and each embodiment mainly describes differences from other embodiments.

The foregoing is merely exemplary of the present application and is not intended to limit the present application. Various modifications and changes may be made to the present application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc. which are within the spirit and principles of the present application are intended to be included within the scope of the claims of the present application.

Claims

1. An aircraft display and control system test platform, comprising:

2. The aircraft display and control system test platform of claim 1,

3. The aircraft display and control system test platform of claim 1,

4. The aircraft display and control system test platform of claim 1,

5. The aircraft display and control system test platform of claim 2, wherein the on-board switch comprises:

6. The aircraft display and control system test platform of claim 3,

7. The aircraft display and control system test platform of claim 6, wherein the second protocol junction box further comprises:

a terminal block and a connection terminal pair;

8. The aircraft display and control system test platform of claim 7,

9. The aircraft display and control system test platform of claim 4, wherein the third protocol junction box comprises:

10. The aircraft display and control system test platform of claim 9,