An auxiliary device for an aircraft bleed air leak detection system

Abstract

The utility model relates to a vehicle door and window frame technical field discloses a kind of supplementary device of aircraft bleed air leakage detection system, and aircraft bleed air leakage detection system includes aircraft bleed air leakage detection loop, equipment rack socket and loop measuring instrument, supplementary device includes: shell;Cover body, detachably installed in shell;Relay matrix, relay matrix includes circuit board and multiple relays on circuit board;Control module, control module is electrically connected with the first input end of circuit board;Touch screen, touch screen is electrically connected with control module;Input interface, input interface is electrically connected with the second input end of circuit board, and input interface is used to be electrically connected with the output end of equipment rack socket;And output interface, output interface is electrically connected with the output end of circuit board, and output interface is used to be electrically connected with loop measuring instrument.The supplementary device of aircraft bleed air leakage detection system of the utility model can switch the signal of multiple aircraft bleed air leakage detection loop, improve detection efficiency.

Description

TECHNICAL FIELD

[0001] The utility model relates to an aircraft bleed air system technical field especially relates to an auxiliary device of aircraft bleed air leakage detection system. BACKGROUND

[0002] At present, for aircraft bleed air leakage detection, a plurality of aircraft bleed air leakage detection loops are erected at each part of the aircraft to obtain detection signals, then the detection signals are transmitted to the equipment rack socket, finally the equipment rack socket is connected with the loop measuring instrument, the detection signals are analyzed and tested through the loop measuring instrument to determine the condition of the aircraft bleed air leakage. At this time, the equipment rack socket is installed in the equipment rack of the aircraft electronic cabin, the space is small, the number of interfaces on the equipment rack socket is large, which leads to the inconvenience of connection between the loop measuring instrument and the equipment rack socket, and the signal switching function is not provided, so that the loop measuring instrument can only analyze and test the detection signals of a single aircraft bleed air leakage detection loop, resulting in low detection efficiency. SUMMARY

[0003] The utility model discloses a kind of auxiliary devices of aircraft bleed air leakage detection system, the signal of multiple aircraft bleed air leakage detection loops can be switched, and detection efficiency is improved.

[0004] In order to achieve the above purpose, the utility model provides a kind of auxiliary device of aircraft bleed air leakage detection system, the aircraft bleed air leakage detection system includes aircraft bleed air leakage detection loop, equipment rack socket and loop measuring instrument, the aircraft bleed air leakage detection loop has multiple and is respectively connected with the input end of equipment rack socket, auxiliary device includes:

[0005] Shell, with opening;

[0006] Cover, detachable installation in the shell, for opening or closing the opening;

[0007] Relay matrix, in the shell, the relay matrix includes circuit board and multiple relays on the circuit board;

[0008] Control module, in the shell, the control module is electrically connected with the first input end of the circuit board;

[0009] Touch screen, installation in the shell, the touch screen is electrically connected with the control module;

[0010] Input interface, installation in the shell, the input interface is electrically connected with the second input end of the circuit board, and the input interface is used to be electrically connected with the output end of the equipment rack socket;And

[0011] An output interface is mounted on the shell and electrically connected with the output end of the circuit board, and the output interface is used for electrical connection with the loop measuring instrument.

[0012] In some embodiments, a plurality of mounting pieces are fixed to the inner wall of the shell, and the cover is detachably connected to the mounting pieces.

[0013] In some embodiments, a plurality of fixing bolts are provided in one-to-one correspondence with the mounting pieces, and the cover is detachably connected to the mounting pieces through the fixing bolts.

[0014] In some embodiments, a handle is mounted on the shell.

[0015] In some embodiments, the shell has oppositely arranged first and second end plates, the input interface is mounted on the first end plate, and the touch screen and the output interface are mounted on the second end plate.

[0016] In some embodiments, the first end plate has a first through hole, the input interface includes a mounting seat mounted on the inner wall of the first end plate and an aviation plug arranged inside the first through hole, the aviation plug is electrically connected with the second input end of the circuit board, and the aviation plug is used for electrical connection with the output end of the equipment rack socket.

[0017] In some embodiments, the mounting seat has a receiving groove on the outer side, a plurality of aviation plugs are arranged on the inner side of the mounting seat, the receiving groove is arranged in correspondence with the first through hole, and the outer side of the aviation plug extends into the receiving groove.

[0018] In some embodiments, the width of the receiving groove is equal to the width of the first through hole, and the length of the receiving groove is equal to the length of the first through hole.

[0019] The auxiliary device of the aircraft bleed air leakage detection system provided by the utility model has the advantages that compared with the prior art, the auxiliary device of the aircraft bleed air leakage detection system has the advantages that:

[0020] A relay matrix is arranged in the shell, the relay matrix comprises a circuit board and a plurality of relays arranged on the circuit board, a control module is arranged in the shell, the control module is electrically connected with a first input end of the circuit board, a touch screen is mounted on the shell, the touch screen is electrically connected with the control module, an input interface is mounted on the shell, the input interface is electrically connected with a second input end of the circuit board, the input interface is used for being electrically connected with an output end of the equipment rack socket, and an output interface is mounted on the shell, the output interface is electrically connected with an output end of the circuit board, and the output interface is used for being electrically connected with the loop measuring instrument, so that the relay matrix can realize multi-way signal switching, the loop measuring instrument is convenient to connect, and therefore the detection efficiency is improved. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 A top view structural schematic diagram of an auxiliary device of an aircraft bleed air leakage detection system is provided in the embodiment of the utility model.

[0022] Figure 2 For Figure 1 A structural schematic diagram of removing the cover body.

[0023] Figure 3 A first shaft side structural schematic diagram of an auxiliary device of an aircraft bleed air leakage detection system is provided in the embodiment of the utility model.

[0024] Figure 4 A second shaft side structural schematic diagram of an auxiliary device of an aircraft bleed air leakage detection system is provided in the embodiment of the utility model.

[0025] Figure 5 An input interface amplification structural schematic diagram of an auxiliary device of an aircraft bleed air leakage detection system is provided in the embodiment of the utility model.

[0026] Figure 6 A principle connection diagram of an auxiliary device of an aircraft bleed air leakage detection system is provided in the embodiment of the utility model.

[0027] In the drawing: 1, shell; 2, cover body; 3, relay matrix; 4, control module; 5, touch screen; 6, input interface; 61, mounting seat; 611, containing groove; 62, aviation plug; 627, output interface; 11, mounting piece; 12, fixing bolt; 13, handle; 14, first end plate; 141, first through hole; 15, second end plate; 100, auxiliary device; 200, aircraft bleed air leakage detection loop; 300, equipment rack socket; 400, loop measuring instrument. DETAILED DESCRIPTION

[0028] With reference to the accompanying drawings, the technical solutions in the embodiments of the present application will be clearly and completely described below. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application.

[0029] It should be understood that, in the description of the present application, the terms "upper", "lower", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements indicated must be in a particular orientation, constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. The terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. That is, the features with "first", "second" can explicitly or implicitly include one or more features. In addition, unless otherwise stated, the meaning of "multiple" is two or more.

[0030] In addition, the technical features involved in different embodiments of the present application described below can be combined with each other as long as there is no conflict between them.

[0031] As Figures 1-6 shown, the auxiliary device of the aircraft bleed air leakage detection system includes a shell 1, a cover 2, a relay matrix 3, a control module 4, a touch screen 5, an input interface 6 and an output interface 7.

[0032] The shell 1 has an opening. The cover 2 is detachably mounted on the shell 1, and is used to open or close the opening.

[0033] The relay matrix 3 is arranged in the shell 1, and the relay matrix 3 includes a circuit board 31 and a plurality of relays 32 arranged on the circuit board 31. In this way, the relay matrix 3 is used to realize flexible switching, routing and control of multiple signals, and a dynamic electrical connection path is constructed through the on-off state of each relay 32. In the present embodiment, the relay matrix 3 can select the input signals of the plurality of aircraft bleed air leakage detection loops 200, generate an output signal, and realize flexible configuration of the signal path.

[0034] The control module 4 is housed within the housing 1 and is electrically connected to the first input terminal of the circuit board 31. For example, the control module 4 is a programmable microcontroller. The touchscreen 5 is mounted on the housing 1 and is electrically connected to the control module 4. Thus, the control signals generated by the touchscreen 5 are processed by the control module 4 to configure the output signals of the relay matrix 3.

[0035] Input interface 6 is mounted on housing 1 and is electrically connected to the second input terminal of circuit board 31. Input interface 6 is used for electrical connection to the output terminal of device rack socket 300. Output interface 7 is mounted on housing 1 and is electrically connected to the output terminal of circuit board 31. Output interface 7 is used for electrical connection to loop measuring instrument 400.

[0036] Based on the above structural setup, the control signal generated by the touch screen 5 is processed by the control module 4 to configure the output signal of the relay matrix 3. The relay matrix 3 can select the input signals of multiple aircraft bleed air leakage detection loops 200 and generate an output signal, realizing flexible configuration of the signal path. In this way, the loop measuring instrument 400 only needs to be connected to the output interface 7 to detect and analyze the detection signals of multiple aircraft bleed air leakage detection loops, realize multi-channel signal switching, make the loop measuring instrument wiring convenient, and thus improve detection efficiency.

[0037] like Figure 2 As shown, in some embodiments, the auxiliary device 100 includes: a plurality of mounting pieces 11, the mounting pieces 11 being fixed to the inner wall of the housing 1, and the cover 2 being detachably connected to the mounting pieces 11. Thus, the mounting pieces 11 ensure the stability of the cover 2's mounting structure.

[0038] like Figure 2 As shown, in some embodiments, the auxiliary device 100 includes a plurality of fixing bolts 12, each fixing bolt 12 corresponding to a plurality of mounting pieces 11, and the cover 2 is detachably connected to the mounting pieces 11 via the fixing bolts 12. Thus, the fixing bolts 12 ensure convenient installation and removal of the cover 2.

[0039] like Figure 1 and 2 As shown, in some embodiments, the auxiliary device 100 includes a handle 13, which is mounted on the housing 1. Thus, the handle 13 makes the auxiliary device 100 easy to carry.

[0040] like Figure 3 and 4 As shown, in some embodiments, the housing 1 has a first end plate 14 and a second end plate 15 disposed opposite to each other. The input interface 6 is mounted on the first end plate 14, and the touch screen 5 and the output interface 7 are mounted on the second end plate 15. In this way, the entire auxiliary device 100 can be installed in the equipment rack of the aircraft's electronics bay, facilitating wiring.

[0041] like Figure 3 As shown, in some embodiments, the first end plate 14 has a first through hole 141. The input interface 6 includes a mounting base 61 and an aviation plug 62 disposed on the mounting base 61. The mounting base 61 is mounted on the inner wall of the first end plate 14, and the aviation plug 62 is correspondingly disposed inside the first through hole 141. The aviation plug 62 is electrically connected to the second input terminal of the circuit board 31 and is used to electrically connect to the output terminal of the device rack socket 300. In this way, the input interface 6 is convenient to install and remove.

[0042] like Figure 5 As shown, in some embodiments, the outer side of the mounting base 61 has a receiving groove 611, and multiple aviation plugs 62 are provided and all are installed on the inner side of the mounting base 61. The receiving groove 611 is in communication with the first through hole 141, and the outer side of the aviation plug 62 extends into the receiving groove 611. Thus, multiple aviation plugs 62 are provided to facilitate electrical connection with multiple aircraft bleed air leakage detection loops 200 via the equipment rack socket 300.

[0043] like Figure 5 As shown, in some embodiments, the width of the receiving groove 611 is equal to the width of the first through hole 141, and the length of the receiving groove 611 is equal to the length of the first through hole 141. Thus, the receiving groove 611 provides space for installation with the equipment rack socket 300, ensuring a stable installation structure.

[0044] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present utility model, and these improvements and substitutions should also be considered within the protection scope of the present utility model.

Claims

1. An auxiliary device for an aircraft bleed air leak detection system, the aircraft bleed air leak detection system comprising an aircraft bleed air leak detection loop, an equipment rack socket, and a loop measuring instrument, wherein the aircraft bleed air leak detection loop has multiple loops, each electrically connected to an input terminal of the equipment rack socket, characterized in that, include: The shell has an opening; A cover, detachably mounted to the housing, is used to open or close the opening; A relay matrix is ​​disposed within the housing, the relay matrix comprising a circuit board and a plurality of relays disposed on the circuit board; A control module is disposed inside the housing, and the control module is electrically connected to the first input terminal of the circuit board. A touch screen is installed in the housing and is electrically connected to the control module; An input interface is mounted on the housing and is electrically connected to the second input terminal of the circuit board. The input interface is also used to electrically connect to the output terminal of the device rack socket. as well as An output interface is installed in the housing and is electrically connected to the output terminal of the circuit board. The output interface is used to electrically connect to the loop measuring instrument.

2. The auxiliary device for the aircraft bleed air leakage detection system according to claim 1, characterized in that, It includes multiple mounting pieces, which are fixed to the inner wall of the housing, and the cover is detachably connected to the mounting pieces.

3. The auxiliary device for the aircraft bleed air leakage detection system according to claim 2, characterized in that, It includes multiple fixing bolts, each of which corresponds to one of the mounting pieces. The cover is detachably connected to the mounting pieces via the fixing bolts.

4. The auxiliary device for the aircraft bleed air leakage detection system according to claim 1, characterized in that, Includes a handle, which is mounted on the housing.

5. The auxiliary device for the aircraft bleed air leakage detection system according to claim 1, characterized in that, The housing has a first end plate and a second end plate disposed opposite to each other, the input interface is mounted on the first end plate, and the touch screen and the output interface are mounted on the second end plate.

6. The auxiliary device for the aircraft bleed air leakage detection system according to claim 5, characterized in that, The first end plate has a first through hole. The input interface includes a mounting base and an aviation plug disposed on the mounting base. The mounting base is installed on the inner wall of the first end plate. The aviation plug is disposed on the inner side of the first through hole. The aviation plug is electrically connected to the second input terminal of the circuit board. The aviation plug is used to electrically connect to the output terminal of the device rack socket.

7. The auxiliary device for the aircraft bleed air leakage detection system according to claim 6, characterized in that, The mounting base has a receiving groove on its outer side. Multiple aviation plugs are provided and are all installed on the inner side of the mounting base. The receiving groove is connected to the first through hole. The outer side of the aviation plug extends into the receiving groove.

8. The auxiliary device for the aircraft bleed air leakage detection system according to claim 7, characterized in that, The width of the receiving groove is equal to the width of the first through hole, and the length of the receiving groove is equal to the length of the first through hole.

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