CN209043227U - A kind of aircraft anti-icing valve position instruction test equipment - Google Patents
A kind of aircraft anti-icing valve position instruction test equipment Download PDFInfo
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- CN209043227U CN209043227U CN201821783563.2U CN201821783563U CN209043227U CN 209043227 U CN209043227 U CN 209043227U CN 201821783563 U CN201821783563 U CN 201821783563U CN 209043227 U CN209043227 U CN 209043227U
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- indicator light
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- indicating circuit
- test equipment
- position indicating
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Abstract
The utility model discloses a kind of aircraft anti-icing valve position instruction test equipments, are related to the service technique field of commercial aircraft gas circuit control.Including testing indicating circuit, testing indicating circuit includes: power supply, switch and the indicator light of parallel connection L4, L5, L6, L7, L8, wherein, indicator light L4 and indicator light L5 is connect with the off-position indicating circuit of components interior respectively, off-position indicating circuit control instructions lamp L4 and indicator light L5 light and OFF state；Indicator light L7 and indicator light L8 is connect with the open position indicating circuit of components interior respectively, open position indicating circuit control instructions lamp L7 and indicator light L8 light and OFF state, indicator light L6 are connect with off-position indicating circuit and open position indicating circuit respectively；Test equipment can be monitored and indicate to the position of valve according to the light on and off state of indicator light, and realization is accurately monitored and indicated to the actuation situation of its valve plate when the anti-icing valve of a variety of different models is repaired and tested.
Description
Technical field
The utility model relates to the service technique field of commercial aircraft gas circuit control more particularly to a kind of aircraft anti-icings
Valve position instruction test equipment.
Background technique
In aircraft operational process, to external wing out of aircraft cabin, in all pneumatic systems for using valve, all
It is that the opening and closing degree of the valve plate inside the valve is adjusted accordingly, therefore the folding condition of valve plate is to the reality of aircraft
Operation conditions has vital adjustment effect.
When carrying out practical maintenance to valve, generally require to access valve body in gas circuit, by applying certain gas
It presses and its behavior in service is judged, but in this case, Maintenance Engineer cannot observe enclosure interior valve plate
Rotation situation and present position, then Maintenance Engineer cannot accurately recognize the actuation situation of valve, thus also with regard to nothing
Method makes corresponding adjusting to valve plate, strong influence repair quality and efficiency.
Utility model content
The purpose of this utility model is to provide a kind of aircraft anti-icing valve position instruction test equipments, to solve existing
Foregoing problems present in technology.
To achieve the goals above, the technical solution adopted in the utility model is as follows:
A kind of aircraft anti-icing valve position instruction test equipment, including test indicating circuit, the test indicating circuit packet
It includes: power supply, switch and the indicator light of parallel connection L4, L5, L6, L7, L8, wherein indicator light L4 and indicator light L5 is respectively and in component
The off-position indicating circuit in portion connects, the off-position indicating circuit control instructions lamp L4 and indicator light L5 light and OFF state；
Indicator light L7 and indicator light L8 is connect with the open position indicating circuit of components interior respectively, the open position indicating circuit control instructions lamp
L7 and indicator light L8 light and OFF state, indicator light L6 connect with the off-position indicating circuit and open position indicating circuit respectively
It connects；Indicator light L5 is connected with indicator light L7, and indicator light L4 is connected with indicator light L8.
Preferably, isolation circuit is additionally provided on each indicator light and the connection circuit of components interior.
Preferably, current-limiting circuit is additionally provided between each indicator light and the isolation circuit.
It preferably, further include the starting or stopping control circuit of components interior solenoid valve, the zener diode in the solenoid valve connects
It connects in the starting or stopping control circuit.
Preferably, the test equipment includes shell, and indicator light L4, L5, L6, L7, L8 are respectively positioned on the panel of the shell
On, the switch of the test indicating circuit and the switch of solenoid valve starting or stopping control circuit are respectively positioned on the panel of the shell, institute
The connecting interface for stating test equipment and components interior circuit is located on the panel of the shell.
The beneficial effects of the utility model are: aircraft anti-icing valve position instruction test provided by the embodiment of the utility model
Equipment, including multiple indicator lights, by different indicator lights respectively with the off-position indicating circuit of components interior and open position indicating circuit
Connection, according to component valve plate in different location, the state of internal off-position indicating circuit and open position indicating circuit, using referring to
Show lamp to be shown, so that during the test, test equipment can be according to the light on and off state of indicator light come to valve
Position be monitored and indicate, thus effectively help Maintenance Engineer actually maintenance in can accurately recognize valve
Actuation situation, and make corresponding adjusting, substantially increase repair quality and efficiency；Moreover, the test equipment analog component
Actual conditions when running aboard can connect in use according to the different replacement private cables of physical unit interface
It is connected to test equipment, to realize the actuation for when the anti-icing valve of a variety of different models being repaired and being tested to its valve plate
Situation is accurately monitored and is indicated.
Detailed description of the invention
Fig. 1 is the circuit diagram of aircraft anti-icing valve position instruction test equipment provided by the utility model；
Fig. 2 is the external structure schematic diagram of aircraft anti-icing valve position instruction test equipment provided by the utility model.
In figure, the meaning of each symbol is as follows:
1 shell, the 2 test switches of indicating circuit, the switch of 3 solenoid valve starting or stopping control circuits, 4 connecting interfaces.
Specific embodiment
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, below in conjunction with attached drawing, to this reality
It is further elaborated with novel.It should be appreciated that the specific embodiments described herein are only used to explain that this is practical
It is novel, it is not used to limit the utility model.
As shown in Figs. 1-2, the utility model embodiment provides a kind of aircraft anti-icing valve position instruction test equipment, packet
Including test indicating circuit, the test indicating circuit includes: power supply, switch and the indicator light of parallel connection L4, L5, L6, L7, L8,
In, indicator light L4 and indicator light L5 are connect with the off-position indicating circuit of components interior respectively, and the off-position indicating circuit control refers to
Show lamp L4 and indicator light L5 light and OFF state；Indicator light L7 and indicator light L8 indicates electricity with the open position of components interior respectively
Road connection, the open position indicating circuit control instructions lamp L7 and indicator light L8 light and OFF state, indicator light L6 respectively with
The off-position indicating circuit is connected with open position indicating circuit；Indicator light L5 is connected with indicator light L7, indicator light L4 and indicator light L8
Connection.
The aircraft anti-icing valve position instruction test equipment of above structure, its working principle is that:
The test equipment is attached by private cable and test equipment when in use, by the parts to be tested.
When the valve plate of the parts to be tested completely closes, the off-position indicating circuit of components interior have voltage output (if this
When component is installed aboard, for corresponding off-position indicator actuation on aircraft), the control of off-position indicating circuit is connected thereto
Indicator light L5 light, indicator light L4 extinguish (i.e. when off-position indicating circuit has voltage output, indicator light L5 is lighted, indicator light
L4 extinguishes, and when off-position indicating circuit does not have voltage output, indicator light L5 extinguishes, and indicator light L4 is lighted), simultaneously as instruction
Lamp L6 is connect with off-position indicating circuit, then indicator light L6 is lighted, in addition, then indicating since indicator light L5 is connect with indicator light L7
Lamp L7 is also lighted, i.e., when the valve plate of the parts to be tested completely closes, indicator light L5, indicator light L7, indicator light L6 are lighted, remaining
Indicator light goes out entirely；
When the valve plate of the parts to be tested fully opens, the open position indicating circuit of components interior have voltage output (if this
When component is installed aboard, for corresponding position indicator actuation on aircraft), the control of open position indicating circuit is connected thereto
Indicator light L8 light, indicator light L7 extinguish (i.e. when open position indicating circuit has voltage output, indicator light L8 is lighted, indicator light
L7 extinguishes, and when open position indicating circuit does not have voltage output, indicator light L8 extinguishes, and indicator light L7 is lighted), simultaneously as instruction
Lamp L6 is connect with open position indicating circuit, then indicator light L6 is lighted, in addition, then indicating since indicator light L8 is connect with indicator light L4
Lamp L4 is also lighted, i.e., when the valve plate of the parts to be tested fully opens, indicator light L4, indicator light L8, indicator light L6 are lighted, remaining
Indicator light goes out entirely；
The state for then lighting and extinguishing according to above-mentioned indicator light can make Service Technician refer to the position of the component
When showing that circuit places under repair, two extreme positions can be found well, so as to fast and accurately to the established angle of electric switch
Degree is adjusted.
In addition, indicator light L4 and indicator light L8 are lighted when the valve plate of the parts to be tested is in by reaching during pass,
Remaining indicator light can knock out, and when valve plate is in by closing to during opening, indicator light L5 and indicator light L7 is bright, and remaining refers to
Show that lamp can knock out, in this way when technician tests valve plate, can recognize the current state of valve plate completely, and
When a certain indicator light breaks down, can also be judged accordingly according to the state of other lamps.
As it can be seen that the utility model solves the monitoring and instruction that valve is directed to its position in maintenance process, it is for work
The comprehensive repairing auxiliary device that door actuation situation carries out real-time monitoring and indicates, to effectively help Maintenance Engineer in reality
It can accurately recognize that the actuation situation of valve substantially increases repair quality to make corresponding adjusting in the maintenance of border
And efficiency.
Actual conditions when the test equipment analog component is run aboard, and all purpose aircraft socket is housed, it can root
The factually different replacement private cables of border unit interface, to realize that the anti-icing valve of a variety of different models is repaired and tested
When the actuation situation of its valve plate is accurately monitored and is indicated.
In the present embodiment, isolation circuit is also provided on the connection circuit of each indicator light and components interior.
It, can be to avoid when testing, because instruction modulation characteristic causes component circuitry by shadow using foregoing circuit structure
Component circuitry is damaged when loud or indicator light damages.
In a preferred embodiment, current limliting is also provided between each indicator light and the isolation circuit
Circuit.
Using above-mentioned circuit structure, in uncertain unit status, can be used for control unit internal current can be protected
It holds in 7mA or less.
Aircraft anti-icing valve position instruction test equipment provided by the embodiment of the utility model can also include components interior
The starting or stopping control circuit of solenoid valve, the zener diode in the solenoid valve are connected in the starting or stopping control circuit.
In the present embodiment, which can carry out start-up and shut-down control to the solenoid valve on component using 18VDC power supply, lead to
It crosses and the zener diode in solenoid valve is linked into the starting or stopping control circuit, can prevent components interior damage when test from causing
Transient voltage increases to burn component.
The test equipment provided by the embodiment of the utility model includes shell 1, indicator light L4, L5, L6, L7, L8
To be located on the panel of the shell 1, the switch 2 of the test indicating circuit and the switch 3 of solenoid valve starting or stopping control circuit are equal
It can be located on the panel of the shell 1, the connecting interface 4 of the test equipment and components interior circuit can be located at described outer
On the panel of shell 1.
Using the above structure, not only can be very good to realize to apparatus circuit for testing from the influence of extraneous factor and by
Damage, also can engineer easy to repair carry out operation and viewing lamp light on and off situation.
By using above-mentioned technical proposal disclosed by the utility model, following beneficial effect: the utility model has been obtained
The aircraft anti-icing valve position instruction test equipment that embodiment provides, including multiple indicator lights, by different indicator lights respectively with
The off-position indicating circuit of components interior is connected with open position indicating circuit, internal to close according to component valve plate in different location
The state of position indicating circuit and open position indicating circuit, is shown using indicator light, so that during the test, test
Equipment can be monitored and indicate to the position of valve according to the light on and off state of indicator light, to effectively help maintenance mans
Cheng Shi can accurately recognize the actuation situation of valve in actually maintenance, and make corresponding adjusting, substantially increase dimension
Repair quality and efficiency；Moreover, the actual conditions when test equipment analog component is run aboard in use can
It is connected to test equipment according to the different replacement private cables of physical unit interface, to realize to the anti-icing of a variety of different models
The actuation situation of its valve plate is accurately monitored and indicated when valve is repaired and tested.
The above is only the preferred embodiment of the utility model, it is noted that for the common skill of the art
For art personnel, without departing from the principle of this utility model, several improvements and modifications can also be made, these improve and
Retouching should also regard the protection scope of the utility model.
Claims (5)
1. a kind of aircraft anti-icing valve position instruction test equipment, which is characterized in that including testing indicating circuit, the test refers to
Show that circuit includes: power supply, switch and the indicator light of parallel connection L4, L5, L6, L7, L8, wherein indicator light L4 and indicator light L5 difference
It is connect with the off-position indicating circuit of components interior, the off-position indicating circuit control instructions lamp L4's and indicator light L5 lights and put out
It goes out state；Indicator light L7 and indicator light L8 is connect with the open position indicating circuit of components interior respectively, the open position indicating circuit control
Indicator light L7 and indicator light L8 processed light and OFF state, indicator light L6 are indicated with the off-position indicating circuit and open position respectively
Circuit connection；Indicator light L5 is connected with indicator light L7, and indicator light L4 is connected with indicator light L8.
2. aircraft anti-icing valve position instruction test equipment according to claim 1, which is characterized in that each instruction
Isolation circuit is additionally provided on lamp and the connection circuit of components interior.
3. aircraft anti-icing valve position instruction test equipment according to claim 2, which is characterized in that each instruction
Current-limiting circuit is additionally provided between lamp and the isolation circuit.
4. aircraft anti-icing valve position instruction test equipment according to claim 1, which is characterized in that further include in component
The starting or stopping control circuit of portion's solenoid valve, the zener diode in the solenoid valve are connected in the starting or stopping control circuit.
5. aircraft anti-icing valve position instruction test equipment according to claim 4, which is characterized in that the test equipment
Including shell, indicator light L4, L5, L6, L7, L8 are respectively positioned on the panel of the shell, it is described test indicating circuit switch and
The switch of solenoid valve starting or stopping control circuit is respectively positioned on the panel of the shell, the company of the test equipment and components interior circuit
Connection interface is located on the panel of the shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821783563.2U CN209043227U (en) | 2018-10-31 | 2018-10-31 | A kind of aircraft anti-icing valve position instruction test equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821783563.2U CN209043227U (en) | 2018-10-31 | 2018-10-31 | A kind of aircraft anti-icing valve position instruction test equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209043227U true CN209043227U (en) | 2019-06-28 |
Family
ID=67040306
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821783563.2U Active CN209043227U (en) | 2018-10-31 | 2018-10-31 | A kind of aircraft anti-icing valve position instruction test equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209043227U (en) |
-
2018
- 2018-10-31 CN CN201821783563.2U patent/CN209043227U/en active Active
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