Multi-channel avionic equipment testing instrument

Abstract

The utility model relates to the technical field of avionic equipment testing, in particular to a multi-channel avionic equipment testing instrument, which comprises a box body, a connecting assembly, a testing module, a power supply assembly and an auxiliary assembly, the connecting assembly comprises a male head, first female heads, second female heads, change-over switches and connecting banana sockets, the male head is connected with the box body, the six first female heads are connected with the box body, the eight second female heads are connected with the box body, the multiple change-over switches are connected with the box body, and the multiple connecting banana sockets are connected with the box body. The test modules are divided into six groups, the power supply assembly and the auxiliary assembly are respectively connected with the box body, a plurality of original devices, a power distribution device and an RS485 bus switching device are integrated on the same device, frequent replacement and use by testers in the test process are avoided, and the test efficiency is improved. Meanwhile, a plurality of devices are integrated into one device, so that the occupied space of the device can be reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of avionics test, especially to a multi-channel avionics test instrument. BACKGROUND

[0002] The laboratory tests electronic equipment, needs power supply system main spare power supply switching, multiway equipment simultaneously power on control, multiway equipment function switching test, and the market does not have multiway equipment simultaneously power on control, power supply system main spare power supply switching, multiway equipment function switching test simultaneously, needs to develop a test instrument with power supply system main spare power supply, multiway equipment simultaneously power on control, multiway equipment function switching. UTILITY MODEL CONTENTS

[0003] The utility model discloses a kind of multi-channel avionics test instruments, the original multiple equipment, power distribution equipment and RS485 bus switching equipment are concentrated on the same equipment, avoid test personnel frequently change use in the testing process, simultaneously, multiple equipment is concentrated into a device, which can reduce the equipment occupied space.

[0004] To achieve the above object, the utility model provides a kind of multi-channel avionics test instruments, including box, connecting component, test module, power supply component and auxiliary component;The connecting component includes male head, first female head, second female head, switching switch and connecting banana socket, the male head is connected with the box, and located at the front of the box, the number of the first female head is six, six first female head is connected with the box respectively, and is located at the right side of the male head respectively, the number of the second female head is eight, eight second female head is connected with the box respectively, and is located at the front of the box respectively, the number of the switching switch is multiple, multiple switching switch is connected with the box respectively, and is located above the male head and the first female head respectively, the number of the connecting banana socket is multiple, multiple connecting banana socket is connected with the box respectively, and is located at the right side of the second female head respectively, the test module is divided into six groups, the power supply component and the auxiliary component are connected with the box respectively.

[0005] Among them, the test module includes six ammeters, six test switches and twelve test banana sockets, six ammeters are connected with the box respectively, and are located at the front of the box, six test switches are connected with the box respectively, and are located at the front of the box, twelve test banana sockets are connected with the box respectively, and are located at the front of the box.

[0006] The test module further comprises six potentiometers, forty-two button switches, six aviation connectors and test lamps, the six potentiometers are connected with the box respectively and are located on the front face of the box, the forty-two button switches are connected with the box respectively and pass through the box, the six aviation connectors are connected with the box respectively and are located on the top of the box, and the test lamps are connected with the box respectively and are located on the front face of the box.

[0007] The power supply assembly comprises four binding posts and an air switch, the four binding posts are connected with the box respectively and are located on the top of the box, and the air switch is connected with the box and is located on the left side of the binding posts.

[0008] The auxiliary assembly comprises two heat dissipation plates and two handles, the two heat dissipation plates are connected with the box respectively and are located on the two sides of the box, and the handle is connected with the top of each heat dissipation plate.

[0009] The multi-channel avionics equipment test instrument of the utility model not only can realize power supply system main and standby power supply switching, multi-channel equipment simultaneous power-on control, multi-channel equipment function switching test, but also has the advantages of small size, light weight, voltage and current display, can satisfy test demand, the original multiple equipment, power distribution equipment and RS485 bus switching equipment are concentrated on the same equipment, avoid the test personnel frequently change in the test process, simultaneously, the multiple equipment is concentrated into one equipment, and the equipment occupied space can be reduced. BRIEF DESCRIPTION OF DRAWINGS

[0010] In order to more clearly illustrate the technical scheme in the embodiment of the present application or prior art, the drawings needed to be used in the embodiment or prior art description will be briefly introduced.

[0011] Figure 1 It is the overall structure schematic diagram of the multi-channel avionics equipment test instrument of the first embodiment of the utility model.

[0012] Figure 2 It is the electrical schematic diagram of the power-on control part of the first embodiment of the utility model.

[0013] Figure 3 It is the electrical schematic diagram of the DB50 public part of the first embodiment of the utility model.

[0014] Figure 4 It is the principle diagram of the power supply system of the first embodiment of the utility model.

[0015] Figure 5 It is the principle diagram of the multi-channel equipment switching of the first embodiment.

[0016] In the figure: 101 - box, 102 - male head, 103 - first female head, 104 - second female head, 105 - switch, 106 - connecting banana socket, 107 - ammeter, 108 - test switch, 109 - test banana socket, 110 - potentiometer, 111 - button switch, 112 - aviation connector, 113 - test lamp, 114 - terminal post, 115 - air switch, 116 - heat sink, 117 - handle. DETAILED DESCRIPTION

[0017] The embodiments of the present application are described in detail below, examples of which are shown in the accompanying drawings, the embodiments described below by referring to the accompanying drawings are exemplary, and are intended to explain the present application, and cannot be understood as a limitation of the present application.

[0018] The first embodiment of the present application is:

[0019] Please refer to Figures 1 to 5 , wherein, Figure 1 is the overall structure schematic diagram of the multi-channel avionics equipment test instrument of the first embodiment of the present application, Figure 2 is the electrical schematic diagram of the power-on control part of the first embodiment of the present application, Figure 3 is the electrical schematic diagram of the DB50 public part of the first embodiment of the present application, Figure 4 is the principle diagram of the power supply system of the first embodiment of the present application, Figure 5 is the principle diagram of the multi-channel equipment switching of the first embodiment, the present application provides a kind of multi-channel avionics equipment test instrument, including box 101, connecting assembly, test module, power supply component and auxiliary assembly, the connecting assembly includes male head 102, first female head 103, second female head 104, switch 105 and connecting banana socket 106, the test module includes ammeter 107, test switch 108, test banana socket 109, potentiometer 110, button switch 111, aviation connector 112, test lamp 113, the power supply component includes terminal post 114 and air switch 115, the auxiliary assembly includes heat sink 116 and handle 117;Through the foregoing scheme, the original multiple devices, power distribution equipment and RS485 bus switching equipment are concentrated on the same device, avoid test personnel frequently change in the test process Use, while the multiple devices are concentrated into a device, which can reduce the equipment occupied space.

[0020] For this specific embodiment, the male head 102 is connected to the box 101 and located on the front of the box 101, the number of the first female head 103 is six, six first female heads 103 are respectively connected to the box 101 and respectively located on the right side of the male head 102, the number of the second female head 104 is eight, eight second female heads 104 are respectively connected to the box 101 and respectively located on the front of the box 101, the number of the switch 105 is multiple, multiple switches 105 are respectively connected to the box 101 and respectively located above the male head 102 and the first female head 103, the number of the connection banana socket 106 is multiple, multiple connection banana sockets 106 are respectively connected to the box 101 and respectively located on the right side of the second female head 104, the test module is divided into six groups, the power supply component and the auxiliary component are respectively connected to the box 101, the box 101 provides support for the device, the male head 102 is connected with the external DB50 cable, and the device to be tested is connected to the public channel for testing, the first female head 103 can be connected with the external six DB50 cables, and each device is respectively connected to the box 101, the second female head 104 can be connected with the external eight devices through the DB9 cable, so that each device is respectively connected to the device, and the connection banana socket 106 is used for connecting the external device.

[0021] Among them, six ammeters 107 are respectively connected to the box 101 and respectively located on the front of the box 101, six test switches 108 are respectively connected to the box 101 and respectively located on the front of the box 101, twelve test banana sockets 109 are respectively connected to the box 101 and respectively located on the front of the box 101, the ammeter 107 is a Hall voltage and current meter, which is used for displaying the power-on current and voltage of each test module, the test switch 108 is used for opening or closing each test module, and the test banana socket 109 is used for connecting the test module with the device to be tested.

[0022] Secondly, six potentiometers 110 are respectively connected to the box 101 and respectively located on the front of the box 101, forty-two button switches 111 are respectively connected to the box 101 and respectively pass through the box 101, six aviation connectors 112 are respectively connected to the box 101 and respectively located on the top of the box 101, multiple test lamps 113 are respectively connected to the box 101 and respectively located on the front of the box 101, the potentiometer 110 is a double 6-pin potentiometer 110, which is used for connecting with the external device, and the test lamp 113 is used for prompting the test.

[0023] Again, the number of the terminal posts 114 is four, four terminal posts 114 are connected with the box 101 respectively and are located at the top of the box 101, the air switch 115 is connected with the box 101 and is located at the left side of the terminal posts 114, the terminal posts 114 are connected with the external power supply, and the air switch 115 is convenient for the power supply and power-off of the whole equipment.

[0024] Finally, the number of the heat dissipation plates 116 is two, two heat dissipation plates 116 are connected with the box 101 respectively and are located at the two sides of the box 101, and one handle 117 is connected with the top of each heat dissipation plate 116 respectively, the heat dissipation plates 116 are convenient for the heat dissipation of the device, and the handles 117 are convenient for the transfer of the device.

[0025] Using the multi-channel avionics test instrument of the embodiment, not only the power supply system main and standby power supply switching, multi-channel equipment simultaneous power-on control, multi-channel equipment function switching test can be realized, but also the volume is small, the weight is light, the voltage and current display and other points can be realized, the test demand can be met, the original multiple devices, power distribution equipment and RS485 bus switching equipment are concentrated on the same device, the test personnel in the test process is avoided to frequently change and use, at the same time, multiple devices are concentrated into one device, the device occupied space can be reduced.

[0026] The above only discloses one or more preferred embodiments of the application, and cannot limit the scope of the application, and those skilled in the art can understand that all or part of the above-mentioned embodiments can be implemented, and equivalent changes made according to the claims of the application still belong to the scope of the application.

Claims

1. A multi-channel avionics test instrument comprising a box, characterized in that, It also includes a connection assembly, a test module, a power supply assembly and an auxiliary assembly; The connection assembly includes a male head, a first female head, a second female head, a switch and a connection banana socket, the male head is connected with the box and located on the front of the box, the number of the first female head is six, six first female heads are respectively connected with the box and respectively located on the right side of the male head, the number of the second female head is eight, eight second female heads are respectively connected with the box and respectively located on the front of the box, the number of the switch is multiple, multiple switches are respectively connected with the box and respectively located above the male head and the first female head, the number of the connection banana socket is multiple, multiple connection banana sockets are respectively connected with the box and respectively located on the right side of the second female head, the test module is divided into six groups, the power supply assembly and the auxiliary assembly are respectively connected with the box.

2. The multi-channel avionics test instrument of claim 1, characterized in that, The test module includes six ammeters, six test switches and twelve test banana sockets, six ammeters are respectively connected with the box and respectively located on the front of the box, six test switches are respectively connected with the box and respectively located on the front of the box, twelve test banana sockets are respectively connected with the box and respectively located on the front of the box.

3. The multi-channel avionics test instrument of claim 2, characterized in that, The test module further includes six potentiometers, forty-two button switches, six aviation connectors and multiple test lamps, six potentiometers are respectively connected with the box and respectively located on the front of the box, forty-two button switches are respectively connected with the box and respectively pass through the box, six aviation connectors are respectively connected with the box and respectively located on the top of the box, multiple test lamps are respectively connected with the box and respectively located on the front of the box.

4. The multi-channel avionics test instrument of claim 1, characterized in that, The power supply assembly includes binding posts and an air switch, the number of the binding posts is four, four binding posts are respectively connected with the box and respectively located on the top of the box, the air switch is connected with the box and located on the left side of the binding posts.

5. The multi-channel avionics test instrument of claim 1, characterized in that, The auxiliary assembly includes heat sinks and handles, the number of the heat sinks is two, two heat sinks are respectively connected with the box and respectively located on both sides of the box, the top of each heat sink is respectively connected with a handle.

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