CN211543935U - A320 series aircraft cargo door position indication system tester - Google Patents
A320 series aircraft cargo door position indication system tester Download PDFInfo
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- CN211543935U CN211543935U CN201921593200.7U CN201921593200U CN211543935U CN 211543935 U CN211543935 U CN 211543935U CN 201921593200 U CN201921593200 U CN 201921593200U CN 211543935 U CN211543935 U CN 211543935U
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Abstract
A320 series aircraft cargo door position indication system tester comprises an electrical appliance control box, a first sensor and a second sensor, wherein the control box circuit is as follows: the B end and the C end of the first plug and the second plug are respectively connected in series, and a first indicator light is connected between the C end and the B end of the first plug and the second plug which are connected in series; the positive pole of the direct current power supply is output to one pin of the first double-throw switch, the other two pins of the first double-throw switch are respectively connected with the A, B end of the first third plug, and the negative pole of the direct current power supply is connected with the C ends of the first and second third plugs which are connected together in series; the B end and the C end of the third plug and the fourth plug are respectively connected in series, and a second indicator light is connected between the C end and the B end of the third plug and the fourth plug which are connected in series; the A end of the third plug is connected with one pin of the second double-throw switch, and the other two pins of the second double-throw switch are respectively connected with the A, B end of the fourth plug; the first and fourth plugs correspond to the sensors.
Description
Technical Field
The utility model relates to a A320 series aircraft cargo compartment door position indication system tester.
Background
As shown in fig. 2 and 3, the system for indicating the position of the cargo door of the a320 series aircraft comprises a cargo door 30, a first actuator 25, a second actuator 26, a first motion sensor 27, a second motion sensor 28 and a fully-open cargo door indicator lamp 31, wherein the first motion sensor and the second motion sensor are respectively arranged on the two actuators.
The first actuator 25 and the second actuator 26 simultaneously actuate to open or close the cargo door 30, and the indicator lamp 31 is lighted when the cargo door 30 is in the fully open position.
The A320 series airplane cargo door opening indicator lamp is used for indicating the fully extended and locked state of a cargo door actuator, and signals of the indicator lamp are from an internal proximity sensor of the actuator.
The fault that the pilot lamp often does not work in the aircraft operation process needs to be cleared up, and at present, a fault detector of an A320 series aircraft cargo hold door opening indicating system does not exist at home and abroad. At present, the method used for troubleshooting is to disconnect the sensor plug of the cargo hold door control actuator for jumping wires, measuring and other measures. This approach has the following disadvantages:
1. the troubleshooting work can be carried out only by electrifying the regular checking airplane at the later stage, the operation is complex, and the time consumption is long.
2. The troubleshooting work may cause the delayed release of the airplane due to the lack of parts of the flight materials and the like.
3. Inaccurate troubleshooting results in costly and labor-intensive sensor or actuator replacement.
4. The indicator light assembly and the human body are easy to damage when the jumper short circuit exists, the electric shock danger is caused, and the accuracy is low.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem of providing an A320 series tester for a position indicating system of a cargo hold door of an airplane, which aims to save labor, accurately find out a fault source for troubleshooting, ensure the airplane to be released for operation on time and ensure the safety and reliability of parts of the airplane and the safety of workers; the cost can be saved, and the safety and the reliability of the airplane and parts can be further improved.
Solve the above problem, the utility model discloses the technical scheme who adopts does:
a320 series aircraft cargo door position indication system tester, the said indication system includes cargo door 30, the first actuator 25, the second actuator 26, the first action sensor 27, the second action sensor 28, the full open indicator lamp 31 of cargo door that are equipped with correspondingly on two actuators; the method is characterized in that: the tester comprises an electric appliance control box, a first sensor 23 and a second sensor 24, wherein the first sensor 23 and the second sensor 24 are the same as action sensors of an indicating system, and an internal circuit of the control box is as follows:
the plug comprises a first third plug 10 and a second third plug 11, wherein the ends B and C of the first third plug and the second third plug are respectively connected in series, and a first indicator light 20 is connected between the ends C and B of the first third plug and the second third plug which are connected in series;
a direct current power supply 22, which is provided with an indicator light and a circuit breaker F1 connected in series on a positive output loop of a power switch, and finally outputs the positive output loop to one pin of a first double-throw switch 21, the other two pins of the first double-throw switch 21 are respectively connected with A, B ends of a first three-plug 10 and a second three-plug 11, and the negative electrode of the direct current power supply 22 is connected with C ends of the first three-plug 10 and the second three-plug 11 which are connected in series;
the B end and the C end of the third plug 12 and the fourth plug 13 are respectively connected in series, and a second indicator light 18 is connected between the C end and the B end of the third plug 12 and the fourth plug which are connected in series;
the A end of the third plug 12 is connected with one pin of the second double-throw switch 19, and the other two pins of the second double-throw switch 19 are respectively connected with the A, B end of the fourth plug;
the first third plug 10 and the fourth third plug 13 correspond to the first sensor 23 and the second sensor 24, respectively.
The direct current power supply is used for providing power for the tester, the circuit breaker is used for overload protection of the tester, and the switch and the indicator light are used for controlling and indicating the state and the result of the tester.
The utility model has the advantages of it is following:
the troubleshooting tester provided by the utility model is connected to the sensor plug of the actuator of the cargo hold door of the airplane through the electric plug, so that the tester can be used for testing whether the sensor of the actuator has a fault; or the sensor on the tester is arranged on the actuator of the cargo door of the airplane, and whether the actuator has a fault or not can be tested; or else to test whether there is a malfunction of the indicator light of the opening of the cargo door. Therefore, labor can be saved, fault sources can be found out by accurately performing troubleshooting work, the airplane is ensured to be put into operation on time, and the safety and reliability of parts of the airplane and the safety of workers are ensured. The cost can be saved, and the safety and the reliability of the airplane and parts can be further improved.
Drawings
FIG. 1 is a schematic diagram of the components and connections of the present invention (with the components of the aircraft);
FIG. 2 is a schematic circuit diagram of an embodiment of the present invention;
FIG. 3 is a schematic view of an A320 series aircraft cargo door position indicating system;
FIG. 4 is a schematic view of the first actuator 25 and the second actuator 26 of the indicating system of FIG. 3, and the corresponding first motion sensor 27 and the second motion sensor 28;
fig. 5 is a schematic diagram of two motion sensors according to the present embodiment.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 3, the front (rear) cargo door opening system for an a320 series aircraft includes a front (rear) cargo door 30, a cargo door opening first actuator 25, a second actuator 26, and a cargo door opening indicator lamp 31. The first actuator 25 and the second actuator 26 actuate to open or close the cargo door 30, and when the cargo door 30 is in the fully open position, the indicator lamp 31 is lighted.
As shown in fig. 4 and 5, the front (rear) cargo door opening actuator for an a320 series aircraft includes a first actuator 25, a second actuator 26, and first and second motion sensors 27 and 28.
As shown in fig. 1 and 2, the embodiment of the tester for indicating the position of the cargo door of the a320 series aircraft of the present invention comprises an electrical control box and a first sensor 23 and a second sensor 24, wherein the first sensor 23 and the second sensor 24 are the same as the sensors of the a320 series aircraft cargo door position indicating system, and the internal circuit of the control box is:
the plug comprises a first third plug 10 and a second third plug 11, wherein the ends B and C of the first third plug and the second third plug are respectively connected in series, and a first indicator light 20 is connected between the ends C and B of the first third plug and the second third plug which are connected in series;
a direct current power supply 22, which is provided with an indicator light and a circuit breaker F1 connected in series on a positive output loop of a power switch, and finally outputs the positive output loop to one pin of a first double-throw switch 21, the other two pins of the first double-throw switch 21 are respectively connected with the A end of a first three-plug 10 and the B end of a second three-plug 11, and the negative electrode of the direct current power supply 22 is connected with the C ends of the first three-plug 10 and the second three-plug 11 which are connected in series;
the B ends and the C ends of the third plug 12 and the fourth plug 13 are respectively connected in series, and a second indicator light 18 is connected between the C ends and the B ends of the third plug and the fourth plug which are connected in series;
the A end of the third plug 12 is connected with one pin of the second double-throw switch 19, and the other two pins of the second double-throw switch 19 are respectively connected with the A, B end of the fourth plug;
the first third plug 10 and the fourth third plug 13 correspond to the first sensor 23 and the second sensor 24.
The direct current power supply is used for providing power for the tester, the circuit breaker is used for overload protection of the tester, and the switch and the indicator light are used for controlling and indicating the state and the result of the tester.
The working process is as follows:
when the cargo door full open indicator lamp 31 needs to be checked whether to have a fault, the direct current power supply 22 is turned ON to provide direct current power, the first double-throw switch 21 and the second double-throw switch 19 are placed ON the B position, and whether the cargo door full open indicator lamp 31 is lighted is checked.
When checking whether the first and second actuation sensors 27 and 28 have faults, the first third plug 10 is mounted on the second actuation sensor 28, the second third plug 11 is mounted on the sensor connection wire of the second actuator 26, the third plug 12 is mounted on the first actuator sensor 27, and the fourth third plug 13 is mounted on the sensor connection wire of the first actuator 25; the dc power supply 22 is placed at the ON position to supply the tester dc power, the first double-throw switch 21 is placed at the a position, whether or not the second actuation sensor 28 has a failure can be determined by the first indicator light 20, the first double-throw switch 21 is placed at the B position, the second double-throw switch 19 is placed at the a position, and whether or not the first actuation sensor 27 has a failure can be determined by the second indicator light 18.
When it is checked whether or not there is a failure in the first actuator 25 or the second actuator 26, the first third plug 10 is attached to the tester first sensor 23, the second motion sensor 28 of the second actuator 26 is detached, the tester first sensor 23 is attached to the second actuator 26, the third plug 12 is attached to the tester second sensor 24, the first motion sensor 27 of the first actuator 25 is detached, the tester second sensor 24 is attached to the first actuator 25, the second third plug 11 is attached to the sensor connection lead of the second actuator 26, the fourth plug 13 is attached to the sensor connection lead of the first actuator 25, the dc power source 22 is placed in the ON position to supply the dc power, the first double throw switch 21 is placed in the a position, and it is possible to determine whether or not there is a failure in the second actuator 26 by the first indicator lamp 20, by placing the first double-throw switch 21 at position B and the second double-throw switch 19 at position a, the presence of a failure in the first actuator 25 can be determined by the second indicator light 18.
Claims (1)
1. A320 series aircraft cargo door position indication system tester comprises a cargo door (30), a first actuator (25), a second actuator (26), a first motion sensor (27) arranged on the first actuator (25), a second motion sensor (28) arranged on the second actuator (26) and a cargo door full-open indicator lamp (31); the method is characterized in that: the tester comprises an electric appliance control box, a first sensor (23) and a second sensor (24), wherein the first sensor (23) and the second sensor (24) are the same as the action sensors of the indicating system, and the internal circuit of the control box comprises:
the plug comprises a first third plug (10) and a second third plug (11), wherein the end B of the first third plug and the end B of the second third plug are connected in series, the end C of the first third plug and the end C of the second third plug are connected in series, and a first indicator lamp (20) is connected between the end C of the first third plug and the second third plug which are connected in series and the end B of the first third plug and the end B of the second third plug;
the direct current power supply (22) is provided with a positive output loop of a power switch, an indicator lamp and a circuit breaker (F1) are connected in series, the direct current power supply is finally output to one pin of the first double-throw switch (21), the other two pins of the first double-throw switch (21) are respectively connected with the A end of the first three-plug (10) and the B end of the second three-plug (11), and the negative electrode of the direct current power supply (22) is connected with the C ends of the first three-plug and the second three-plug which are connected in series;
a third plug (12) and a fourth plug (13), wherein the end B of the third plug and the end B of the fourth plug are connected in series, the end C of the third plug and the end C of the fourth plug are connected in series, and a second indicator light (18) is connected between the ends C and B of the third plug and the fourth plug which are connected in series;
the A end of the third plug (12) is connected with one pin of the second double-throw switch (19), and the other two pins of the second double-throw switch (19) are respectively connected with the A, B end of the fourth plug;
the first third plug (10) and the fourth third plug (13) correspond to the first sensor (23) and the second sensor (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921593200.7U CN211543935U (en) | 2019-09-24 | 2019-09-24 | A320 series aircraft cargo door position indication system tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921593200.7U CN211543935U (en) | 2019-09-24 | 2019-09-24 | A320 series aircraft cargo door position indication system tester |
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| Publication Number | Publication Date |
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| CN211543935U true CN211543935U (en) | 2020-09-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921593200.7U Active CN211543935U (en) | 2019-09-24 | 2019-09-24 | A320 series aircraft cargo door position indication system tester |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114313227A (en) * | 2021-12-17 | 2022-04-12 | 中国南方航空股份有限公司 | Method for improving reliability of civil aircraft undercarriage system |
-
2019
- 2019-09-24 CN CN201921593200.7U patent/CN211543935U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114313227A (en) * | 2021-12-17 | 2022-04-12 | 中国南方航空股份有限公司 | Method for improving reliability of civil aircraft undercarriage system |
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