CN220795692U - Automatic temperature regulator testing device for air-tight cabin of airplane - Google Patents
Automatic temperature regulator testing device for air-tight cabin of airplane Download PDFInfo
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- CN220795692U CN220795692U CN202321522968.1U CN202321522968U CN220795692U CN 220795692 U CN220795692 U CN 220795692U CN 202321522968 U CN202321522968 U CN 202321522968U CN 220795692 U CN220795692 U CN 220795692U
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- 238000012360 testing method Methods 0.000 title claims abstract description 40
- 239000002775 capsule Substances 0.000 claims 1
- 238000013024 troubleshooting Methods 0.000 abstract description 4
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- 230000001105 regulatory effect Effects 0.000 description 25
- 238000010586 diagram Methods 0.000 description 10
- 238000001514 detection method Methods 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 230000033001 locomotion Effects 0.000 description 3
- 230000033228 biological regulation Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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Abstract
The utility model provides a testing device for an automatic temperature regulator of an air-tight cabin of an airplane, which comprises the following components: a device socket and an integrated circuit board; the integrated circuit board is provided with an analog signal input circuit and a signal feedback circuit; the equipment socket is electrically connected with the integrated circuit board; the automatic temperature regulator of the air-tight cabin and the on-board plug are electrically connected with the equipment socket; the equipment socket is used for electrically connecting the integrated circuit with the automatic temperature regulator of the air-tight cabin of the airplane, the analog signal circuit outputs an analog signal to the automatic temperature regulator of the air-tight cabin of the airplane, and the feedback signal circuit determines whether the automatic temperature regulator of the air-tight cabin of the airplane is normal or not according to the feedback signal. The utility model achieves the purpose of testing the automatic temperature regulator of the air-tight cabin of the airplane through a simple circuit, and solves the problems of complex testing equipment, inconvenient use and adverse external field troubleshooting existing in the existing testing equipment.
Description
Technical Field
The utility model relates to the field of sensor detection, in particular to a testing device for an automatic temperature regulator of an aircraft airtight cabin.
Background
The bleed air of the airtight cabin temperature automatic regulating system of a certain type of aircraft is provided by an engine bleed air system, hot air passes through an air radiator designed by a machine body, convection cold air generated during air flight is utilized to enter the air radiator to cool the hot air, then the temperature is set through an automatic temperature regulating box, the automatic temperature regulating box is matched with a temperature sensor in an air supply pipeline to work, a temperature regulating valve motor is controlled to work, the air supply proportion of the cold air and the hot air is regulated, the average temperature in the airtight cabin is ensured to be 16-30 ℃, and the aim of automatic temperature regulation is fulfilled. However, because of organism design reason, hot air cooling device installs in fuselage wheel cabin left and right sides, and the aircraft is when taking a test on ground, and the convection air that produces can't get into this position and cool off engine bleed air, and the bleed air temperature that gets into the airtight cabin can surpass the air state greatly, because the bleed air temperature of not effective cooling is higher, when taking a test on ground and carrying out airtight cabin temperature automatically regulated system function inspection, the temperature in the bleed air pipeline can rise fast (especially in the summer that ambient temperature is higher), this just easily leads to each annex on the bleed air system pipeline to cause the performance decline because of the high temperature, perhaps even cause bigger loss (such as pipeline overtemperature damage, part overtemperature damage etc.). Therefore, when the aircraft is tested on the ground in the past, the airtight cabin automatic temperature adjusting system cannot perform bleed air starting inspection, so that the function of the system automatic temperature adjusting system cannot be verified, and only comprehensive inspection can be performed in the air when the aircraft is combined with the aircraft in flight.
Because the existing automatic temperature regulating system of the airtight cabin is not matched with a corresponding ground detection tester, and the ground detection limit of the system is added, the automatic temperature regulating system of the airtight cabin flies in the air for a plurality of times in daily work development, the flight verification field is increased after the ground is cleared of faults, the working condition of the system is continuously verified in the air, and the cost of people and material resources is greatly consumed.
Disclosure of Invention
In view of the foregoing, it is desirable to provide an apparatus for testing an automatic regulator for temperature of an aircraft cabin, which is used for solving the problems of complex testing equipment, inconvenient use and adverse external field troubleshooting of testing equipment.
In order to achieve the technical purpose, the utility model adopts the following technical scheme:
in a first aspect, the present utility model provides an aircraft cockpit temperature automatic regulator testing apparatus comprising: an equipment socket and an integrated circuit board; the integrated circuit board is provided with an analog signal input circuit and a signal feedback circuit; the equipment socket is electrically connected with the integrated circuit board; the automatic temperature regulator of the air-tight cabin and the on-board plug are electrically connected with the equipment socket;
the equipment socket is used for electrically connecting the integrated circuit with the automatic temperature regulator of the air-tight cabin of the aircraft;
the analog signal circuit is used for outputting analog signals to the automatic temperature regulator of the air-tight cabin of the aircraft;
the signal feedback circuit is used for determining whether the temperature automatic regulator of the air-tight cabin of the aircraft is normal or not according to the feedback signal and sending out a light signal.
Preferably, an automatic temperature regulator testing device for an aircraft airtight cabin is characterized in that the equipment socket module comprises: the first patch plug K1, the second patch plug K2 and the third patch plug K3; the first patch plug K1 is electrically connected with the second patch plug K2 and the third patch plug K3; the second adapter plug K2 is electrically connected with the automatic temperature regulator of the air-tight cabin of the aircraft; the third patch plug K3 is electrically connected with the on-board plug.
Preferably, the analog signal input circuit includes: a band switch S2 and a high-precision resistor R1;
a first pin of the band switch S2 is electrically connected with a first plug of the first adapter plug K1; the second pin of the band switch S2 is electrically connected with the fifth plug of the first adapter plug K1; the third pin of the band switch S2 is electrically connected with the second pin of the high-precision resistor R1; the fourth pin of the band switch S2 is electrically connected with the third pin of the first adapter plug K1;
a first pin of the high-precision resistor R1 is electrically connected with a sixth plug of the first switching plug K1; the second pin of the high-precision resistor R1 is electrically connected to the third pin of the band switch S2.
Preferably, the signal feedback circuit includes: a first switch S1, a third switch S3, a fourth switch S4, a fifth switch S5, and a sixth switch S6; the LED lamp comprises a first LED lamp L1, a second LED lamp L2, a third LED lamp L2 and a fourth LED lamp L4;
one end of the third switch S3 is electrically connected with the seventh plug of the first adapter plug K1, and the other end of the third switch S3 is electrically connected with one end of the first LED lamp L1; one end of the switch S4 is electrically connected with the seventh plug of the first adapter plug K1, and the other end of the switch S4 is electrically connected with one end of the second LED lamp L2; one end of the switch S5 is electrically connected with one end of the third LED lamp L2, and one end of the switch S6 is electrically connected with one end of the fourth LED lamp L4; one end of the first switch S1 is electrically connected with the ninth plug of the first plug K1, and one end of the first switch S1 is electrically connected with the tenth plug of the first plug K1;
the other end of the first LED lamp L1 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the second LED lamp L2 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the third LED lamp L2 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the fourth LED lamp L4 is electrically connected to the eleventh plug of the first adapter plug K1.
Preferably, the band switch S2 is a state selection band switch of model RS 25.
Preferably, the first switch S1 is a power switch model YJ-LA16.
Preferably, the third switch S3, the fourth switch S4, the fifth switch S5 and the sixth switch S6 are push-button switches, and the specific model is PBS-110B05A.
Preferably, the specific models of the first LED lamp L1, the second LED lamp L2, the third LED lamp L3 and the fourth LED lamp L4 are CL2-502G.
Preferably, the specific model of the first plug K1 is GX12.
Preferably, the specific model of the second patch plug K2 is XC27T19KH; the specific model of the third patch plug K3 is XC27T19ZH.
The beneficial effects of adopting the embodiment are as follows: the utility model provides a testing device for an automatic temperature regulator of an air-tight cabin of an airplane, which comprises the following components: a device socket and an integrated circuit board; the integrated circuit board is provided with an analog signal input circuit and a signal feedback circuit; the equipment socket is electrically connected with the integrated circuit board; the automatic temperature regulator of the air-tight cabin and the on-board plug are electrically connected with the equipment socket; the equipment socket is used for electrically connecting the integrated circuit with the automatic temperature regulator of the air-tight cabin of the airplane, the analog signal circuit outputs an analog signal to the automatic temperature regulator of the air-tight cabin of the airplane, and the feedback signal circuit determines whether the automatic temperature regulator of the air-tight cabin of the airplane is normal or not according to the feedback signal. The utility model achieves the purpose of testing the automatic temperature regulator of the air-tight cabin of the airplane through a simple circuit, and solves the problems of complex testing equipment, inconvenient use and adverse external field troubleshooting existing in the existing testing equipment.
Drawings
FIG. 1 is a schematic diagram of an embodiment of an apparatus for testing an automatic temperature regulator of an aircraft cabin according to the present utility model;
FIG. 2 is a circuit diagram of an embodiment of an analog signal input circuit according to the present utility model;
FIG. 3 is a circuit diagram of an embodiment of a signal feedback circuit according to the present utility model;
FIG. 4 is a block diagram of one embodiment of a device receptacle provided by the present utility model;
fig. 5 is a circuit configuration diagram of another embodiment of an apparatus for testing an automatic regulator for temperature of an aircraft cabin according to the present utility model.
Detailed Description
Preferred embodiments of the present utility model will now be described in detail with reference to the accompanying drawings, which form a part hereof, and together with the description serve to explain the principles of the utility model, and are not intended to limit the scope of the utility model.
In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the utility model. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly appreciate that the embodiments described herein may be combined with other embodiments.
Referring to fig. 1, fig. 1 is a schematic structural diagram of an embodiment of an automatic temperature regulator testing device for an aircraft cabin according to the present utility model, and a specific embodiment of the utility model discloses an automatic temperature regulator testing device for an aircraft cabin, which includes: a device socket 100, an integrated circuit board 200; the integrated circuit board is provided with an analog signal input circuit 201 and a signal feedback circuit 202; the device socket 100 is electrically connected with the integrated circuit board 200; the automatic temperature regulator of the air-tight cabin and the on-board plug are electrically connected with the equipment socket;
the device socket 100 is used for electrically connecting an integrated circuit with an aircraft cabin temperature automatic regulator;
the analog signal circuit 201 is configured to output an analog signal to the aircraft cabin temperature automatic regulator;
the signal feedback circuit 202 is configured to determine whether the aircraft cabin temperature automatic regulator is normal based on the feedback signal.
Compared with the prior art, the device for testing the automatic temperature regulator of the air-tight cabin of the aircraft provided by the utility model comprises the following components: an equipment socket and an integrated circuit board; the integrated circuit board is provided with an analog signal input circuit and a signal feedback circuit; the equipment socket is electrically connected with the integrated circuit board; the automatic temperature regulator of the air-tight cabin and the on-board plug are electrically connected with the equipment socket; the equipment socket is used for electrically connecting the integrated circuit with the automatic temperature regulator of the air-tight cabin of the aircraft; the analog signal circuit is used for outputting analog signals to the automatic temperature regulator of the air-tight cabin of the aircraft; the signal feedback circuit is used for determining whether the temperature automatic regulator of the air-tight cabin of the aircraft is normal or not according to the feedback signal and sending out a light signal, and is used for solving the problems that the test equipment is complex, inconvenient to use and unfavorable for external field troubleshooting.
Referring to fig. 4, fig. 4 is a block diagram of an embodiment of an equipment socket provided in the present utility model, and in some embodiments of the present utility model, the equipment socket module includes: the first patch plug K1, the second patch plug K2 and the third patch plug K3; the first patch plug K1 is electrically connected with the second patch plug K2 and the third patch plug K3; the second adapter plug K2 is electrically connected with the automatic temperature regulator of the air-tight cabin of the aircraft; the third patch plug K3 is electrically connected with the on-board plug.
Referring to fig. 2, fig. 2 is a circuit diagram of an embodiment of an analog signal input circuit according to the present utility model, and in some embodiments of the present utility model, the analog signal input circuit includes: a band switch S2 and a high-precision resistor R1;
a first pin of the band switch S2 is electrically connected with a first plug of the first adapter plug K1; the second pin of the band switch S2 is electrically connected with the fifth plug of the first adapter plug K1; the third pin of the band switch S2 is electrically connected with the second pin of the high-precision resistor R1; the fourth pin of the band switch S2 is electrically connected with the third pin of the first adapter plug K1;
a first pin of the high-precision resistor R1 is electrically connected with a sixth plug of the first switching plug K1; the second pin of the high-precision resistor R1 is electrically connected to the third pin of the band switch S2.
Referring to fig. 3, fig. 3 is a circuit diagram of an embodiment of a signal feedback circuit according to the present utility model, and in some embodiments of the present utility model, the signal feedback circuit includes: a first switch S1, a third switch S3, a fourth switch S4, a fifth switch S5, and a sixth switch S6; the LED lamp comprises a first LED lamp L1, a second LED lamp L2, a third LED lamp L2 and a fourth LED lamp L4;
one end of the third switch S3 is electrically connected with the seventh plug of the first adapter plug K1, and the other end of the third switch S3 is electrically connected with one end of the first LED lamp L1; one end of the switch S4 is electrically connected with the seventh plug of the first adapter plug K1, and the other end of the switch S4 is electrically connected with one end of the second LED lamp L2; one end of the switch S5 is electrically connected with one end of the third LED lamp L2, and one end of the switch S6 is electrically connected with one end of the fourth LED lamp L4; one end of the first switch S1 is electrically connected with the ninth plug of the first plug K1, and one end of the first switch S1 is electrically connected with the tenth plug of the first plug K1;
the other end of the first LED lamp L1 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the second LED lamp L2 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the third LED lamp L2 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the fourth LED lamp L4 is electrically connected to the eleventh plug of the first adapter plug K1.
Referring to fig. 5, fig. 5 is a circuit diagram of another embodiment of an apparatus for testing an automatic regulator of temperature of an aircraft cabin according to the present utility model, in which an on-board temperature regulating valve switch is set to be "neutral" during testing. The power supply first switch S1 is turned on, the band switch S2 is selected to be a high-temperature sensitive signal, the third switch S3 and the fifth switch S5 are turned off, the sixth switch S6 is turned off, and the fourth switch S4 is turned on. The manual control machine is used for controlling the temperature regulating valve switch to be in a hot state, so that the temperature regulating valve is moved to a hot limit position, and then the temperature regulating valve switch is in an automatic state. The output of a high-precision resistor R1 in the test device for slowly adjusting the temperature automatic regulator of the air-tight cabin of the airplane is 305.23 omega-323 omega, at the moment, because an over-temperature protection circuit in the temperature automatic regulator of the air-tight cabin of the airplane is unbalanced in a balance bridge, an over-temperature protection amplified signal is sent out, (namely, the amplified signal moves towards the cold direction), and at the moment, the circuit is divided into two paths: one path is excited by a cold path circuit from a fourteenth plug of the second adapter plug K2 to a second plug of the motor plug of the temperature regulating valve, and the motor moves in a cold direction; one path of the green signal lamp passes through a fourteenth plug of the second patchplug K2 to a seventh plug of the first patchplug K1, the fourth switch S4 moves the second LED lamp L2 of the green signal lamp in the cold direction at high temperature, and the eleventh plug of the first patchplug K1 is connected with an eighteenth plug (public negative line) of the second patchplug K2 to return to the negative state on the machine body. At the moment, whether the valve in the high-temperature sensitive signal module moves to the cold direction or not is observed, whether the fourth LED lamp L4 of the red signal lamp is lighted is judged, and if the lighting shows that the temperature overtemperature protection function of the airtight cabin is normal.
The on-board temperature regulating valve switch is arranged in the neutral state. The first switch S1 is turned on, the band switch S2 is selected to be a low-temperature sensitive signal, the third switch S3 and the fifth switch S5 are turned off, the fourth switch S4 is turned off, and the sixth switch S6 is turned on. The manual control machine is provided with a temperature regulating valve switch which is arranged at the cold state, so that the temperature regulating valve is moved to the cold limit position, and then the temperature regulating valve switch is arranged at the automatic state. The high-precision resistor R1 in the test device for the automatic regulator of the temperature of the air-tight cabin of the ground plane is regulated slowly to be lower than 270.75 omega, at the moment, because the balance bridge of the low-temperature protection circuit of the automatic regulator of the temperature of the air-tight cabin of the plane is unbalanced, a low-temperature protection amplified signal is sent out, (namely, the amplified signal moves towards the hot direction), and at the moment, the circuit is divided into two paths: one path is excited by a hot path circuit from a sixteenth plug of the second adapter plug K2 to a third plug of the temperature regulating valve motor, and the motor moves towards the hot direction; one path of the green signal lamp is connected to an eighth plug of the first plug K1 through a sixteenth plug of the second plug K2, and a switch S6, a fourth LED lamp L4 of the green signal lamp moves in the thermal direction at low temperature, and the green signal lamp is discharged from an eleventh plug of the first plug K1, is connected with an eighteenth plug (public negative line) of the second plug K2, and returns to the negative state on the machine body. At this time, whether the fourth LDE lamp L4 of the red signal lamp which moves the valve to the hot direction is lighted or not is observed, and if the fourth LDE lamp L4 is lighted, the low-temperature protection function of the airtight cabin is normal.
The on-machine temperature regulating valve switch is set in 'automatic'. The first switch S1 is turned on, the band switch S2 is selected to be a temperature adjustment signal, the fourth switch S4 and the sixth switch S6 are turned off, and the third switch S3 and the fifth switch S5 are turned on. The high-precision resistor R1 in the automatic temperature regulator testing device for the air-tight cabin is set to be 300.75 omega, the automatic temperature regulator for the air-tight cabin is set to be 20 ℃, no amplified signal is sent out at the moment, the two-way excitation voltage of the temperature regulating valve motor is not signal, the temperature regulating valve motion feedback signal lamp first LED lamp L1 and the third LED lamp L2 connected to the motor excitation circuit are not burnt.
Slowly rotating a given temperature knob of the automatic temperature regulator of the air-tight cabin of the airplane to more than 20 ℃, wherein the balance bridge circuit of the automatic temperature regulator of the air-tight cabin of the airplane is unbalanced, and sends out a signal for amplifying movement in the hot direction, and the circuit is divided into two paths: one path is excited by a hot path circuit from a sixteenth plug of the second adapter plug K2 to a third plug of the temperature regulating valve motor, and the motor moves towards the hot direction; one path of the light passes through a sixteenth plug of the second patch plug K2 to an eighth plug of the first patch plug K1, is connected with a fifth switch S5, moves a third LED lamp L2 of the red signal lamp towards the hot direction, is discharged from an eleventh plug of the first patch plug K1, is connected with an eighteenth plug (public negative line) of the second patch plug K2, and is reversed on the machine body, at the moment, whether the third LED lamp L2 of the red signal lamp which moves the test valve towards the hot direction is lighted or not is observed, and if the third LED lamp L2 is lighted, the temperature of the airtight cabin is indicated to be normal automatically towards the hot regulation function.
Slowly rotating the temperature knob of the automatic temperature regulator of the air-tight cabin to be lower than 20 ℃, wherein the balance bridge circuit of the automatic temperature regulator of the air-tight cabin is unbalanced, and sends out a signal for amplifying movement in the cold direction (and positive electricity is supplied to the hole of the control box 14), and the circuit is divided into two paths: one path is excited by a cold path circuit from a fourteenth plug of the second adapter plug K2 to a second plug of the temperature regulating valve motor, and the motor moves in a cold direction; one path is connected with a third switch S3 through a fourteenth plug of a second patch plug K2 to a seventh plug of a first patch plug K1, a first LED lamp L1 of the red signal lamp moves towards the cold direction, the eleventh plug of the first patch plug K1 is connected with an eighteenth plug (public negative line) of the second patch plug K2, the eighteenth plug (public negative line) is connected with the second patch plug K2, whether the first LED lamp L1 of the red signal lamp moves towards the cold direction or not is observed at the moment, and if the first LED lamp L1 is lighted, the temperature of the airtight cabin is automatically regulated towards the cold normally.
In some embodiments of the utility model, the band switch S2 is a state-selective band switch of model RS 25.
In some embodiments of the present utility model, the first switch S1 is a power switch model YJ-LA16.
In some embodiments of the present utility model, the third switch S3, the fourth switch S4, the fifth switch S5 and the sixth switch S6 are push-button switches, and the specific model is PBS-110B05A.
In some embodiments of the present utility model, the specific models of the first LED lamp L1, the second LED lamp L2, the third LED lamp L3 and the fourth LED lamp L4 are CL2-502G.
In some embodiments of the present utility model, the specific model number of the first adapter plug K1 is GX12.
In some embodiments of the present utility model, the specific model number of the second patch plug K2 is XC27T19KH; the specific model of the third patch plug K3 is XC27T19ZH.
The present utility model is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present utility model are intended to be included in the scope of the present utility model.
Claims (10)
1. An aircraft cockpit temperature automatic regulator testing apparatus, characterized by comprising: a device socket and an integrated circuit board; the integrated circuit board is provided with an analog signal input circuit and a signal feedback circuit; the equipment socket is electrically connected with the integrated circuit board; the automatic temperature regulator of the air-tight cabin and the on-board plug are electrically connected with the equipment socket;
the equipment socket is used for electrically connecting the integrated circuit with the automatic temperature regulator of the air-tight cabin of the aircraft;
the analog signal input circuit is used for outputting analog signals to the automatic temperature regulator of the aircraft airtight cabin;
the signal feedback circuit is used for determining whether the automatic temperature regulator of the air-tight cabin of the aircraft is normal according to the feedback signal.
2. An aircraft cockpit temperature automatic regulator testing apparatus according to claim 1 wherein said equipment socket includes: the first patch plug K1, the second patch plug K2 and the third patch plug K3; the first patch plug K1 is electrically connected with the second patch plug K2 and the third patch plug K3; the second adapter plug K2 is electrically connected with the automatic temperature regulator of the air-tight cabin of the aircraft; the third patch plug K3 is electrically connected with the on-board plug.
3. An aircraft cockpit temperature automatic regulator test device according to claim 2 wherein said analog signal input circuit includes: a band switch S2 and a high-precision resistor R1;
a first pin of the band switch S2 is electrically connected with a first plug of the first adapter plug K1; the second pin of the band switch S2 is electrically connected with the fifth plug of the first adapter plug K1; the third pin of the band switch S2 is electrically connected with the second pin of the high-precision resistor R1; the fourth pin of the band switch S2 is electrically connected with the third pin of the first adapter plug K1;
a first pin of the high-precision resistor R1 is electrically connected with a sixth plug of the first switching plug K1; the second pin of the high-precision resistor R1 is electrically connected to the third pin of the band switch S2.
4. An aircraft cockpit temperature automatic regulator test device according to claim 2 wherein said signal feedback circuit includes: a first switch S1, a third switch S3, a fourth switch S4, a fifth switch S5, and a sixth switch S6; the LED lamp comprises a first LED lamp L1, a second LED lamp L2, a third LED lamp L3 and a fourth LED lamp L4;
one end of the third switch S3 is electrically connected with the seventh plug of the first adapter plug K1, and the other end of the third switch S3 is electrically connected with one end of the first LED lamp L1; one end of the switch S4 is electrically connected with the seventh plug of the first adapter plug K1, and the other end of the switch S4 is electrically connected with one end of the second LED lamp L2; one end of the switch S5 is electrically connected with one end of the third LED lamp L3, and one end of the switch S6 is electrically connected with one end of the fourth LED lamp L4; one end of the first switch S1 is electrically connected with the ninth plug of the first plug K1, and one end of the first switch S1 is electrically connected with the tenth plug of the first plug K1;
the other end of the first LED lamp L1 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the second LED lamp L2 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the third LED lamp L3 is electrically connected with an eleventh plug of the first adapter plug K1; the other end of the fourth LED lamp L4 is electrically connected to the eleventh plug of the first adapter plug K1.
5. A test device for an aircraft cabin temperature automatic regulator according to claim 3, wherein the band switch S2 is a state selection band switch of model RS 25.
6. The device for testing an automatic temperature regulator of an aircraft cabin according to claim 4, wherein the first switch S1 is a power switch model YJ-LA16.
7. The device for testing an automatic temperature regulator of an aircraft cabin according to claim 4, wherein the third switch S3, the fourth switch S4, the fifth switch S5 and the sixth switch S6 are push-button switches, and the specific model is PBS-110B05A.
8. The device for testing the automatic temperature regulator of the air-tight cabin of the aircraft according to claim 4, wherein the specific model numbers of the first LED lamp L1, the second LED lamp L2, the third LED lamp L3 and the fourth LED lamp L4 are CL2-502G.
9. An aircraft cockpit temperature automatic regulator test device according to claim 2, wherein said first adapter plug K1 is of model GX12.
10. An aircraft capsule thermostat testing device according to claim 2, wherein the specific model of the second patch plug K2 is XC27T19KH; the specific model of the third patch plug K3 is XC27T19ZH.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321522968.1U CN220795692U (en) | 2023-06-14 | 2023-06-14 | Automatic temperature regulator testing device for air-tight cabin of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321522968.1U CN220795692U (en) | 2023-06-14 | 2023-06-14 | Automatic temperature regulator testing device for air-tight cabin of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220795692U true CN220795692U (en) | 2024-04-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321522968.1U Active CN220795692U (en) | 2023-06-14 | 2023-06-14 | Automatic temperature regulator testing device for air-tight cabin of airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN220795692U (en) |
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2023
- 2023-06-14 CN CN202321522968.1U patent/CN220795692U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant |