CN210090635U - Detector for valve of aircraft fuel system - Google Patents
Detector for valve of aircraft fuel system Download PDFInfo
- Publication number
- CN210090635U CN210090635U CN201920628426.XU CN201920628426U CN210090635U CN 210090635 U CN210090635 U CN 210090635U CN 201920628426 U CN201920628426 U CN 201920628426U CN 210090635 U CN210090635 U CN 210090635U
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- valve
- detector
- relay
- lamp
- switch
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- 239000000446 fuel Substances 0.000 title claims abstract description 41
- 238000001514 detection method Methods 0.000 claims abstract description 17
- 239000000295 fuel oil Substances 0.000 abstract description 8
- 230000004044 response Effects 0.000 description 9
- 238000012423 maintenance Methods 0.000 description 6
- 239000003921 oil Substances 0.000 description 6
- 230000008859 change Effects 0.000 description 5
- 230000002159 abnormal effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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Abstract
The utility model discloses an aircraft fuel system valve detector, wherein a detector socket is connected in series with a 10A fuse tube and a button switch SW, and the button switch SW is connected in series with a detection circuit; the detection circuit comprises a working lamp connecting circuit and a fault lamp connecting circuit which are connected in parallel, the working lamp connecting circuit comprises a resistor R1, a working lamp L1 and a relay K1 which are respectively connected with the resistor R1, the working lamp L1 is connected with an airplane valve switch, and the relay K1 is connected with a detector socket; the fault lamp connecting circuit comprises a resistor R2, a fault lamp L2 and a normally closed contact A, B of a relay K1 which are connected in sequence, and a normally closed contact A, B of the relay K1 is connected with a detector socket. The utility model discloses an on-off of detector switch to through the bright state display valve's that goes out state display valve of working light L1 and trouble lamp L2 state, in order to reach the purpose that detects the valve, realize in time maintaining aircraft valve trouble, avoid causing aircraft fuel oil system's trouble because of the trouble of valve.
Description
Technical Field
The utility model belongs to the technical field of aircraft fuel system valve fault detection device, concretely relates to aircraft fuel system valve detector.
Background
At present, in the field of domestic aircraft maintenance, a process and detection equipment for checking a valve of an onboard fuel system are not available, the area is a blind area for aircraft maintenance, but the situation that the aircraft fuel system is in failure due to the problem of short circuit or disconnection of the valve occurs every year. Therefore, the valve detector for the aircraft fuel system can make up for leaks and defects of detection equipment in the aircraft maintenance process. The invention relates to a detector for a valve of an aircraft fuel system, which changes the resistance of a solenoid coil of the valve according to the fact that the valve is in an electrical fault phenomenon, namely short circuit or open circuit, so that the current on a line changes.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft fuel system valve detector, break-make through the detector switch to through the bright state display valve's of going out state display valve of work light L1 and trouble light L2 state, in order to reach the purpose that detects the valve, realize in time maintaining aircraft valve trouble, avoid causing aircraft fuel system's trouble because of the trouble of valve.
The utility model discloses mainly realize through following technical scheme: a28 VDC socket is arranged on the detector, a 10A fuse tube and a button switch SW are connected in series with the detector socket, and the button switch SW is connected in series with a detection circuit; the detection circuit comprises a working lamp connecting circuit and a fault lamp connecting circuit which are connected in parallel, the working lamp connecting circuit comprises a resistor R1, a working lamp L1 and a relay K1 which are respectively connected with the resistor R1, the working lamp L1 is connected with an airplane valve switch, and the relay K1 is connected with a detector socket; the fault lamp connecting circuit comprises a resistor R2, a fault lamp L2 and a normally closed contact A, B of a relay K1 which are sequentially connected, wherein a normally closed contact A, B of the relay K1 is connected with a detector socket; still include the self-checking circuit, the self-checking circuit includes the self-checking button, the self-checking button is connected with work lamp L1 and trouble lamp L2 respectively, and the detector socket is connected to the self-checking button.
The utility model discloses a 28VDC socket is connected with the aircraft battery, carries out the self-checking before detecting the valve, presses the self-checking switch, and work lamp L1 and trouble lamp L2 are respectively through the negative pole of self-checking button switch-on detector socket for work lamp L1, trouble lamp L2 form closed circuit respectively, light work lamp L1 and trouble lamp L2, ensure the utility model discloses a do not have the trouble itself, loosen the self-checking switch and make work lamp L1 and trouble lamp L2 extinguish, ensure the utility model discloses the condition of the circuit of measurement valve that can be accurate.
When the valve is normal, the switch SW is switched on, the working lamp L1 is connected with the airplane through the valve to be grounded, a closed loop is realized, and the working lamp L1 is electrified and lightened; the relay K1 is energized, so that the normally closed contact A, B of the relay K1 is opened, so that the faulty lamp connection circuit is opened, so that the faulty lamp L2 is extinguished. When the valve is in short circuit, the switch SW is switched on, the working lamp L1 is connected with the airplane ground through the valve short circuit, a closed loop is realized, the working lamp L1 is electrified and lightened, the branch of the working lamp L1 connected with the valve is in short circuit, so that most of current passes through the short circuit, the short circuit cannot be achieved or only small current can be obtained, the relay K1 cannot be switched on, therefore, the normally closed contact A, B of the relay K1 is closed, the fault lamp connecting circuit is communicated with the anode and the cathode of the detector socket, the fault lamp L2 is electrified and lightened, and a valve short circuit fault alarm is sent. When the shutter is opened, the switch SW is turned on, the shutter switch is opened, so that the work lamp L1 cannot form a circuit with the aircraft ground through the shutter, and thus the work lamp L1 cannot be lit, and the relay K1 forms a complete circuit, so that the normally closed contact A, B of the relay K1 is opened, so that the fault lamp connection circuit cannot form a circuit, and thus the fault lamp L2 cannot be lit.
When the valve circuit is detected to have problems, the valve and the circuit thereof are detected immediately, if the circuit is normal, the valve is replaced, and the valve is detected again by the valve detector after being installed; if the line is damaged, the line is repaired and then passes through the valve detector again for detection; after all the valves are detected to be abnormal, the airplane fuel system can be electrified to work, and the situation that the electrical elements of the airplane fuel system are burnt out due to the short circuit of the valves or valve connecting wires is avoided.
The utility model discloses detect the valve through the valve detector before aircraft fuel system first circular telegram, through the condition of measuring valve machine valve circuit in advance, avoid valve or valve circuit short circuit to cause aircraft fuel system electrical component's damage, avoid valve or valve circuit to open circuit and cause the phenomenon that aircraft fuel system can not normally start, reduced aircraft fuel system because of the damage that the valve trouble caused, improved the utility model discloses a practicality.
In order to better realize the utility model discloses, further, a backward diode is connected in parallel to relay K1. The utility model discloses in the use, when relay K1 outage, relay K1's coil can produce a reverse response electromotive force, and reverse response electromotive force can produce the influence to other components and parts, and the reverse response electromotive force that consequently produces when connecting in parallel on relay K1 when the power-off of backward diode consumption relay K1 avoids the loss of other components and parts.
In order to better implement the present invention, further, as shown in table 2, the resistance values of the resistor R1 and the resistor R2 are 6 Ω, and the operating voltage of the relay and the push button switch is 24 VDC.
In order to better implement the present invention, as shown in table 1, a patch plug is further disposed on the detector, the patch plug is connected to a 3QXA plug of the aircraft power driving box through a patch cable, and the model of the 3QXA plug is JY 27467T 25B35 PN. The detector is provided with a plurality of valve switches corresponding to the valves of the aircraft fuel system, the valve switches are respectively connected with the aircraft valves, and the aircraft valves comprise a front group refueling valve, a right refueling valve, a wing fuel delivery valve and a standby valve switch.
The utility model discloses when using, at first break off aircraft power drive box and internal connection's 3QXA plug to through adapter cable and the adapter plug connection on the detector, make valve detector and the valve intercommunication on the aircraft, and through the valve switch that sets up on the detector, control the valve of the fuel oil system in different regions respectively, make the valve in different regions carry out solitary detection, the location area that can be quick when making aircraft fuel oil system's valve or valve circuit break down, accelerate the speed of maintenance or change, improve the utility model discloses a practicality.
For better realization the utility model discloses, it is further, reserve expansion hole is connected to reserve valve switch, be provided with three reserve expansion hole on the detector. The utility model discloses a setting in reserve extension hole makes the utility model is suitable for an any aircraft can inspect arbitrary valve or solenoid valve on the aircraft, has better practicality.
Table 1: 3QXA plug pin corresponding to airplane valve pin
| Name (R) | Pin number of adapter | 3QXA Pin number of plug | Valve resistance |
| Front group oiling valve | 1 | 11 | 48 |
| Right fuel supply valve | 2 | 12 | 50 |
| Left-side oil supply valve | 3 | 23 | 50 |
| Left wing refueling valve | 4 | 22 | 49 |
| Right wing refueling valve | 5 | 21 | 49 |
| Left wing auxiliary refueling valve (hanging rack) | 6 | 35 | 34 |
| Right wing auxiliary refueling valve (hanging rack) | 7 | 29 | 34 |
| Auxiliary refuelling valve body (hanging rack) | 8 | 26 | 34 |
| Left wing auxiliary oil delivery valve | 9 | 43 | 34 |
| Right wing auxiliary oil delivery valve | 10 | 40 | 34 |
| Oil delivery valve of auxiliary engine body | 11 | 51 | 34 |
| Wing oil delivery valve | 12 | 63 | 17 |
| Front group oil transportation valve | 13 | 60 | 36 |
| Auxiliary pressurizing electromagnetic valve of machine body | 14 | 46 | 70 |
| Electromagnetic valve for pre-inspecting fuselage and wing | 15 | 36 | 14 |
Table 2: detector element
The utility model has the advantages that:
(1) the utility model discloses detect the valve through the valve detector before aircraft fuel system first circular telegram, through the condition of measuring valve machine valve circuit in advance, avoid valve or valve circuit short circuit to cause aircraft fuel system electrical component's damage, avoid valve or valve circuit to open circuit and cause the phenomenon that aircraft fuel system can not normally start, reduced aircraft fuel system because of the damage that the valve trouble caused, improved the utility model discloses a practicality.
(2) A reverse diode is connected in parallel to the relay K1. The utility model discloses in the use, when relay K1 outage, relay K1's coil can produce a reverse response electromotive force, and reverse response electromotive force can produce the influence to other components and parts, and the reverse response electromotive force that consequently produces when connecting in parallel on relay K1 when the power-off of backward diode consumption relay K1 avoids the loss of other components and parts.
(3) Through adapter cable and the patchplug connection on the detector for valve detector and the valve intercommunication on the aircraft, and through the valve switch that sets up on the detector, control the valve of the fuel oil system in different regions respectively, make the valve in different regions carry out solitary detection, make the location area that can be quick when aircraft fuel oil system's valve or valve circuit break down, accelerate the speed of maintenance or change, improve the utility model discloses a practicality.
Drawings
FIG. 1 is an electrical schematic diagram of the present invention;
fig. 2 is a schematic structural diagram of the detector.
Detailed Description
Example 1:
a28 VDC socket is arranged on the detector, a 10A fuse tube and a button switch SW are connected in series with the detector socket, and the button switch SW is connected in series with a detection circuit; the detection circuit comprises a working lamp connecting circuit and a fault lamp connecting circuit which are connected in parallel, the working lamp connecting circuit comprises a resistor R1, a working lamp L1 and a relay K1 which are respectively connected with the resistor R1, the working lamp L1 is connected with an airplane valve switch, and the relay K1 is connected with a detector socket; the fault lamp connecting circuit comprises a resistor R2, a fault lamp L2 and a normally closed contact A, B of a relay K1 which are sequentially connected, wherein a normally closed contact A, B of the relay K1 is connected with a detector socket; still include the self-checking circuit, the self-checking circuit includes the self-checking button, the self-checking button is connected with work lamp L1 and trouble lamp L2 respectively, and the detector socket is connected to the self-checking button.
The utility model discloses a 28VDC socket is connected with the aircraft battery, carries out the self-checking before detecting the valve, presses the self-checking switch, and work lamp L1 and trouble lamp L2 are respectively through the negative pole of self-checking button switch-on detector socket for work lamp L1, trouble lamp L2 form closed circuit respectively, light work lamp L1 and trouble lamp L2, ensure the utility model discloses a do not have the trouble itself, loosen the self-checking switch and make work lamp L1 and trouble lamp L2 extinguish, ensure the utility model discloses the condition of the circuit of measurement valve that can be accurate.
When the valve is normal, the switch SW is switched on, the working lamp L1 is connected with the airplane through the valve to be grounded, a closed loop is realized, and the working lamp L1 is electrified and lightened; the relay K1 is energized, so that the normally closed contact A, B of the relay K1 is opened, so that the faulty lamp connection circuit is opened, so that the faulty lamp L2 is extinguished. When the valve is in short circuit, the switch SW is switched on, the working lamp L1 is connected with the airplane ground through the valve short circuit, a closed loop is realized, the working lamp L1 is electrified and lightened, the branch of the working lamp L1 connected with the valve is in short circuit, so that most of current passes through the short circuit, the short circuit cannot be achieved or only small current can be obtained, the relay K1 cannot be switched on, therefore, the normally closed contact A, B of the relay K1 is closed, the fault lamp connecting circuit is communicated with the anode and the cathode of the detector socket, the fault lamp L2 is electrified and lightened, and a valve short circuit fault alarm is sent. When the shutter is opened, the switch SW is turned on, the shutter switch is opened, so that the work lamp L1 cannot form a circuit with the aircraft ground through the shutter, and thus the work lamp L1 cannot be lit, and the relay K1 forms a complete circuit, so that the normally closed contact A, B of the relay K1 is opened, so that the fault lamp connection circuit cannot form a circuit, and thus the fault lamp L2 cannot be lit. When the working lamp L1 goes out and the fault lamp L2 lights up, the relay K1 is in fault, and the relay needs to be replaced or maintained.
When the valve circuit is detected to have problems, the valve and the circuit thereof are detected immediately, if the circuit is normal, the valve is replaced, and the valve is detected again by the valve detector after being installed; if the line is damaged, the line is repaired and then passes through the valve detector again for detection; after all the valves are detected to be abnormal, the airplane fuel system can be electrified to work, and the situation that the electrical elements of the airplane fuel system are burnt out due to the short circuit of the valves or valve connecting wires is avoided.
The utility model discloses detect the valve through the valve detector before aircraft fuel system first circular telegram, through the condition of measuring valve machine valve circuit in advance, avoid valve or valve circuit short circuit to cause aircraft fuel system electrical component's damage, avoid valve or valve circuit to open circuit and cause the phenomenon that aircraft fuel system can not normally start, reduced aircraft fuel system because of the damage that the valve trouble caused, improved the utility model discloses a practicality.
Example 2:
the embodiment is further optimized on the basis of the embodiment 1, and a reverse diode is connected to the relay K1 in parallel. The utility model discloses in the use, when relay K1 outage, relay K1's coil can produce a reverse response electromotive force, and reverse response electromotive force can produce the influence to other components and parts, and the reverse response electromotive force that consequently produces when connecting in parallel on relay K1 when the power-off of backward diode consumption relay K1 avoids the loss of other components and parts.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
this embodiment is further optimized based on embodiment 2, as shown in fig. 1 and fig. 2, the resistance values of the resistor R1 and the resistor R2 are 6 Ω, and the operating voltage of the relay and the push button switch is 24 VDC. The detector is also provided with a patch plug, the patch plug is connected with a 3QXA plug of the airplane power drive box through a patch cable, and the model of the 3QXA plug is JY 27467T 25B35 PN. The detector is provided with a plurality of valve switches corresponding to the valves of the aircraft fuel system, the valve switches are respectively connected with the aircraft valves, and the aircraft valves comprise a front group refueling valve, a right refueling valve, a wing fuel delivery valve and a standby valve switch. The standby valve switch is connected with the standby expansion holes, and the detector is provided with three standby expansion holes.
The utility model discloses when using, at first break off aircraft power drive box and internal connection's 3QXA plug to through adapter cable and the adapter plug connection on the detector, make valve detector and the valve intercommunication on the aircraft, and through the valve switch that sets up on the detector, control the valve of the fuel oil system in different regions respectively, make the valve in different regions carry out solitary detection, the location area that can be quick when making aircraft fuel oil system's valve or valve circuit break down, accelerate the speed of maintenance or change, improve the utility model discloses a practicality. Through the setting in reserve extension hole, make the utility model is suitable for an any aircraft can inspect arbitrary valve or solenoid valve on the aircraft, has better practicality.
The other parts of this embodiment are the same as those of embodiment 2, and thus are not described again.
Example 4:
a valve detector of an aircraft fuel system is shown in figures 1 and 2, when an aircraft is powered off, a 3QXA plug of an aircraft power driving box is disconnected and connected with a transfer cable of the detector, and the other end of the aircraft power driving box is connected with the detector. And confirming that all the switches are in the off state, and connecting the power socket with the on-board direct current socket. And connecting a power supply plug of an on-board storage battery. And the power-on switch SW of the detector is switched on, and at the moment, the two indicator lamps are both turned off. The self-test button SB is pressed, both indicator lights should be lit, and then the button is released. And sequentially switching on and off the switches corresponding to all the valves, normally lighting only the green lamp, and checking whether the valves and the circuits are normal or not by contrasting a truth table. If the fault is found, whether the valve line is a fault is determined, if the line is normal, the valve is replaced, and after the valve is installed, corresponding detection needs to be carried out again. After the check is finished, the plug on the aircraft is recovered after the power is off, and after all valves are detected to be abnormal, the aircraft fuel system can be electrified to work. In addition, the detector is provided with three standby expansion holes, and can be used for inspecting any airplane, any valve or electromagnetic valve.
The utility model discloses during the use, the valve detector must use before the first circular telegram of aircraft fuel oil system, then can avoid burning out the machine and carry the electrical product on the machine because valve or the continuous line short circuit of valve. When the valve is normal, the switch SW is switched on, and the working lamp L1 is lightened through valve grounding; meanwhile, the relay K1 is electrified to open the normally closed contact A, B, so that the fault lamp L2 is broken and extinguished. When the shutter is short-circuited, the switch SW is turned on, and the work lamp L1 is lit through the shutter short-circuited ground; meanwhile, the relay K1 does not work because the valve is short-circuited and no current flows, the normally closed contact A, B is switched on, the fault lamp L2 is lighted up, and an alarm is given. When the shutter is opened, the switch SW is turned on, and the work lamp L1 is not grounded and cannot be normally lighted, indicating that the shutter is opened. When the power is off, because the relay is that the coil can produce a reverse induced electromotive force, can produce the influence to other components and parts, so connect a backward diode in parallel on the coil limit, consume induced electromotive force.
The design principle of the fuel system valve detector is that the on-off of a line is influenced by the change of resistance, and whether the valve is normal or not is displayed through the on-off state of an indicator lamp, so that the aim of detecting the valve is fulfilled.
The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.
Claims (6)
1. The detector is characterized in that a 28VDC socket is arranged on the detector, a 10A fuse tube and a button switch SW are connected in series with the detector socket, and the button switch SW is connected in series with a detection circuit; the detection circuit comprises a working lamp connecting circuit and a fault lamp connecting circuit which are connected in parallel, the working lamp connecting circuit comprises a resistor R1, a working lamp L1 and a relay K1 which are respectively connected with the resistor R1, the working lamp L1 is connected with an airplane valve, and the relay K1 is connected with a detector socket; the fault lamp connecting circuit comprises a resistor R2, a fault lamp L2 and a normally closed contact A, B of a relay K1 which are sequentially connected, wherein a normally closed contact A, B of the relay K1 is connected with a detector socket; still include the self-checking circuit, the self-checking circuit includes the self-checking button, the self-checking button is connected with work lamp L1 and trouble lamp L2 respectively, and the detector socket is connected to the self-checking button.
2. The aircraft fuel system valve detector as claimed in claim 1, wherein a reverse diode is connected in parallel to the relay K1.
3. An aircraft fuel system valve detector as claimed in claim 1 or 2, wherein the resistance of the resistors R1 and R2 is 6 Ω, and the operating voltage of the relay and the push button switch is 24 VDC.
4. The aircraft fuel system valve detector as claimed in claim 1, wherein a patch plug is further arranged on the detector, the patch plug is connected with a 3QXA plug of an aircraft power drive box through a patch cable, and the 3QXA plug is JY 27467T 25B35 PN.
5. An aircraft fuel system valve detector as claimed in any one of claims 1, 2 and 4, wherein the detector is provided with a front group refueling valve switch, a right refueling valve switch, a wing fuel delivery valve switch and a spare valve switch.
6. An aircraft fuel system valve detector as claimed in claim 5, wherein the back-up valve switch is connected to back-up extension holes, and three back-up extension holes are provided on the detector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920628426.XU CN210090635U (en) | 2019-05-05 | 2019-05-05 | Detector for valve of aircraft fuel system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920628426.XU CN210090635U (en) | 2019-05-05 | 2019-05-05 | Detector for valve of aircraft fuel system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210090635U true CN210090635U (en) | 2020-02-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920628426.XU Expired - Fee Related CN210090635U (en) | 2019-05-05 | 2019-05-05 | Detector for valve of aircraft fuel system |
Country Status (1)
| Country | Link |
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| CN (1) | CN210090635U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112235914A (en) * | 2020-10-16 | 2021-01-15 | 中国直升机设计研究所 | Display control circuit with lamp for cabin switch plate |
| CN112379251A (en) * | 2020-10-30 | 2021-02-19 | 北京航天光华电子技术有限公司 | Relay circuit fault testing system and method |
| CN112623273A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Fault diagnosis method for aircraft fuel system accessory |
-
2019
- 2019-05-05 CN CN201920628426.XU patent/CN210090635U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112235914A (en) * | 2020-10-16 | 2021-01-15 | 中国直升机设计研究所 | Display control circuit with lamp for cabin switch plate |
| CN112235914B (en) * | 2020-10-16 | 2022-06-21 | 中国直升机设计研究所 | Display control circuit with lamp for cabin switch plate |
| CN112379251A (en) * | 2020-10-30 | 2021-02-19 | 北京航天光华电子技术有限公司 | Relay circuit fault testing system and method |
| CN112623273A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Fault diagnosis method for aircraft fuel system accessory |
| CN112623273B (en) * | 2020-12-29 | 2023-06-23 | 中国航空工业集团公司西安飞机设计研究所 | Fault diagnosis method for aircraft fuel system accessories |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200218 |
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| CF01 | Termination of patent right due to non-payment of annual fee |