CN109335018B - Automatic wire harness detection system and wire harness box for aircraft auxiliary power device - Google Patents
Automatic wire harness detection system and wire harness box for aircraft auxiliary power device Download PDFInfo
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- CN109335018B CN109335018B CN201811276994.4A CN201811276994A CN109335018B CN 109335018 B CN109335018 B CN 109335018B CN 201811276994 A CN201811276994 A CN 201811276994A CN 109335018 B CN109335018 B CN 109335018B
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- 238000001514 detection method Methods 0.000 title claims abstract description 28
- 238000012360 testing method Methods 0.000 claims abstract description 36
- 210000001503 joint Anatomy 0.000 claims description 42
- 239000000758 substrate Substances 0.000 claims description 9
- 238000005259 measurement Methods 0.000 abstract description 10
- 238000000034 method Methods 0.000 abstract description 5
- 238000005299 abrasion Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 3
- 229920001342 Bakelite® Polymers 0.000 description 1
- 239000004637 bakelite Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Short-Circuits, Discontinuities, Leakage, Or Incorrect Line Connections (AREA)
Abstract
The automatic detection system for the wire harness of the auxiliary power device of the aircraft comprises a test bench and a wire harness box; the wire harness box is used for connecting aviation connectors at two ends of a wire harness to be tested, and under the control of the test bench, the two ends of each wire in the wire harness to be tested are respectively output to the test bench in a divided manner; and the test bench performs on-off or resistance measurement on each input wire. The automatic detection system can replace manual work to automatically complete detection of the on-off and resistance ranges of the APU wire harness, can greatly reduce labor cost in the detection process of the APU wire harness, improves detection efficiency, does not need to distinguish the numbers of all wires in the wire harness, avoids false detection risks caused by abrasion of the pin numbers, and improves accuracy.
Description
Technical Field
The invention belongs to the technical field of aircraft maintenance, and particularly relates to an automatic detection system for an Auxiliary Power Unit (APU) wire harness of an aircraft, and a wire harness box applied to the system.
Background
An aircraft Auxiliary Power Unit (APU) wire harness is one of basic equipment for normal operation of the APU, and mainly comprises signal acquisition and actuator control circuits for assisting in monitoring the working performance of the APU and controlling the working state of the APU.
Current APU harness detection requires two workers to measure each wire in the harness one by using a multimeter in accordance with a manual or work card to obtain the on/off condition or resistance range of each wire.
The current APU models available for repair by the southern Sangan APU repair center include APS3200/APS2300/APS2600 and 131-9A, 131-9B, with annual repair volume predicted to break through 200 in 2018, where APS3200 and 131-9B are predicted to be around 150. APS3200 has 108 wires and 131-9B has 129 wires.
The existing wire harness detection device is used for finishing wire harness measurement, at least two workers are required to work together and take a long time, for example, the average finishing time of APS3200 is 40min, the average finishing time of 131-9B is 50min, the working efficiency is low, and the labor is consumed. In addition, the interpolation needles of aviation connectors (connectors at two ends of a wire harness) are densely arranged and are generally numbered by white small words, but after the wire harness is used for a long time, the numbers are easy to wear and lead to difficult discrimination, so that the problems of misdetection and the like are brought to the measurement of workers, reworking is caused when the later further detection results are inconsistent, the time cost and the labor cost are further increased, the repair period of an APU (auxiliary unit) is delayed, and a new scheme is needed to be explored to replace the scheme to improve the efficiency and the accuracy of the wire harness detection of the APU, and the labor cost is reduced.
Disclosure of Invention
The first invention provides an automatic detection system for the APU wire harness, which can detect the on-off or resistance of each wire in the APU wire harness, can greatly reduce the labor cost in the detection process of the APU wire harness and can also improve the detection efficiency and accuracy.
A second object of the present invention is to provide an aircraft auxiliary power unit harness box for use in the above system.
The first invention is realized by the following technical scheme: an automatic detection system for a wire harness of an aircraft auxiliary power device comprises a test bench and a wire harness box;
the wire harness box is used for connecting aviation connectors at two ends of a wire harness to be tested, and under the control of the test bench, the two ends of each wire in the wire harness to be tested are respectively output to the test bench in a divided manner;
the test bench is used for measuring the on-off or resistance of each input wire; the measuring circuit for the on-off or resistance of the lead in the test board comprises a tester, a power supply, a first relay and a second relay, wherein the power supply is connected in series with the first relay and then connected in parallel with the second relay, and finally connected in series between two input ends of the same lead with the tester, the test board further comprises a PLC (programmable logic controller) which is connected with the first relay and the second relay, when the on-off of the lead is detected, the first relay is controlled to be closed, the second relay is opened, then the circuit voltage is detected by the tester to judge, when the resistance of the lead is detected, the first relay is controlled to be opened, the second relay is controlled to be closed, and then the circuit resistance is detected by the tester to judge.
The tester recommends the use of a programmable multimeter.
The wire harness box includes:
as a base plate for mounting the panel, more than one group each group comprises a butt joint A, B for being respectively and uniquely connected with aviation joints at two ends of a to-be-tested wire harness (the existing aviation joints are commonly provided with limiting designs so as to be connected with the butt joints thereof in a unique manner, thereby avoiding the problem of misconnection), the butt joints A, B are internally provided with joints corresponding to corresponding aviation joint interpolation pins, and the butt joints are mounted on the base plate;
the relay set comprises an input relay set and an output relay set;
each contact in each butt joint A is respectively connected with the input end of an input relay, and is output to n public output ends after passing through the input relay;
each contact in each butt joint B is respectively connected with an output end of an output relay, and is connected with n common input ends after passing through the input relay.
The relay group also comprises an input control relay group and an output control relay group;
each public output end is respectively connected with an input end of an input control relay, and is output to a total output end after passing through the input control relay;
and each common input end is respectively connected with an output end of an output control relay, and is connected to a total input end after passing through the output control relay.
The input relay group and the output relay group respectively comprise more than one sub-relay group; each sub-relay group comprises n relays, the relays in each sub-relay group are numbered in sequence, the output ends of the input relays with the same number in each input sub-relay group are connected in parallel to form n common output ends, and the input ends of the output relays with the same number in each output sub-relay group are connected in parallel to form n common input ends.
The corresponding arrangement positions of the input sub-relay groups and the output sub-relay groups are corresponding.
The second object of the invention is achieved by the following technical scheme: an aircraft auxiliary power unit harness box for use with the system described above, comprising:
as a substrate for mounting the panel, more than one group of the boards comprises butt joints A, B for being respectively and correspondingly connected with aviation joints at two ends of a to-be-tested beam in a unique mode, the butt joints A, B are internally provided with joints corresponding to corresponding aviation joint interpolation pins, and the butt joints are mounted on the substrate;
the relay set comprises an input relay set and an output relay set;
each contact in each butt joint A is respectively connected with the input end of an input relay, and is output to n public output ends after passing through the input relay;
each contact in each butt joint B is respectively connected with an output end of an output relay, and is connected with n common input ends after passing through the input relay.
The relay group also comprises an input control relay group and an output control relay group;
each public output end is respectively connected with an input end of an input control relay, and is output to a total output end after passing through the input control relay;
and each common input end is respectively connected with an output end of an output control relay, and is connected to a total input end after passing through the output control relay.
As a preferred embodiment of the present invention: the input relay group and the output relay group respectively comprise more than one sub-relay group; each sub-relay group comprises n relays, the relays in each sub-relay group are numbered in sequence, the output ends of the input relays with the same number in each input sub-relay group are connected in parallel to form n common output ends, and the input ends of the output relays with the same number in each output sub-relay group are connected in parallel to form n common input ends.
The corresponding arrangement positions of the input sub-relay groups and the output sub-relay groups are corresponding.
According to the invention, the wire harness box is designed and used, the APU wire harness aviation connector is connected with the butt joint in the wire harness box, which is matched with the APU wire harness aviation connector, the APU wire harness is connected with the test bench through the inner circuit of the wire harness box in a number-by-number manner through the control of the relay group by the PLC, so that a test loop is formed, the automatic measurement of the APU wire harness in a number-by-number manner is automatically realized, the working efficiency of staff is effectively improved, the numbers of all wires in the wire harness are not required to be distinguished, the false detection risk caused by the abrasion of the pin numbers is avoided, the labor cost in the detection process of the APU wire harness can be reduced, the maintenance period of the APU is shortened, and the accuracy is improved.
The PLC and multimeter test program is designed according to a CMM manual as a standard, and the design software is Labview and OPC.
The beneficial effects are that:
1) The automatic detection system can replace manual work to automatically complete detection of the on-off and resistance range of the APU wire harness, can greatly reduce the labor cost in the detection process of the APU wire harness, and improves the detection efficiency: if more than 100 wires to be measured are divided into 15 groups through a wire harness box, one of the 15 groups is measured each time, measurement of all the wires is completed, the average measurement time of APS3200 is 2min, and the average measurement time of 131-9B is 5min; by using the invention to finish the APU wire harness test, only the APU wire harness aviation connector is correspondingly spliced with the corresponding butt joint connector in the wire harness box, and each wire number in the wire harness is not required to be distinguished, so that the false detection risk caused by abrasion of the pin number is avoided, and the accuracy is improved.
2) According to the invention, each sub-relay group of the wire harness box divides more than 100 wires to be tested into 15 groups, 1 group is measured each time, all measurements are completed, compared with the case that all wires are connected into the test box at one time, only 1 connecting wire harness is led out to be connected with a test bench after grouping, so that the number of plugs connected into the test box is reduced, the equipment maintenance time is reduced, the consumption of consumables is reduced, the time for replacing the wire harness box by workers is reduced (one type of wire harness box, only the connecting wires of the wire harness box and the test box are disconnected each time, and only the wire harness box of another type is replaced, if more than 100 wires are connected into the test box, and when the wire harness box is replaced each time, more than 100 wires are required to be disconnected, so that the time is very consumed;
3) The relays in each sub-relay group of the wire harness box are sequentially numbered, the output ends of the input relays with the same number in each input sub-relay group are connected in parallel, and the input ends of the output relays with the same number in each output sub-relay group are connected in parallel, so that the on-off of the corresponding input sub-relay group and the output sub-relay group are sequentially controlled, and the wire grouping connection of the wire to the test bench can be realized, so that the control process is simpler.
Drawings
FIG. 1 is a schematic block diagram of an aircraft auxiliary power unit harness automatic detection system according to a first embodiment;
FIG. 2 is a schematic circuit diagram of an aircraft auxiliary power unit harness box according to one embodiment;
fig. 3 is a layout diagram of an input relay set and an output relay set in a harness box of an aircraft auxiliary power unit according to a first embodiment;
fig. 4 is a layout diagram of a second scheme of an input relay set and an output relay set in a harness box of an auxiliary power unit for an aircraft according to the first embodiment.
Detailed Description
Example 1
An automatic detection system for an aircraft auxiliary power unit wire harness according to the first embodiment is as shown in fig. 1, and includes a test bench and a wire harness box.
The wire harness box is used for connecting aviation connectors at two ends of a wire harness to be tested, and under the control of the test bench, the two ends of each wire in the wire harness to be tested are respectively output to the test bench in a divided manner. In this embodiment, the wire harness box outputs two ends of one wire in the wire harness to be tested to the test bench respectively each time.
The test bench is used for carrying out on-off or resistance measurement on each input wire. The measuring circuit of wire break-make or resistance in the testboard includes programmable universal meter G, 24VDC power and first, second relay, and the power is established ties the back with first relay, again parallelly connected with the second relay, and finally establish ties between two input of same root wire together with G, the testboard still includes PLC, PLC connects with first, second relay, when detecting wire break-make, controls first relay closure, and the second relay disconnection, then detects line voltage through the tester and judges, when detecting wire resistance, controls first relay disconnection and controls second relay closure, then detects line resistance through the tester and judges. In other embodiments, more than two circuits of the measuring circuits for the on-off or the resistance of the wires can be configured, and the measuring circuits are specifically determined according to the number of wires which are connected to the test board through the wire harness box at a time.
The wire harness box comprises a substrate serving as a mounting panel, more than one group of wire harness boxes comprises butt joints A, B which are used for being correspondingly connected with aviation joints at two ends of a wire harness to be tested in a unique mode respectively, the butt joints A, B are internally provided with joints corresponding to corresponding aviation joint interpolation pins, the substrate is made of an insulating material such as bakelite, and the butt joints are mounted on the substrate.
The wire harness box further comprises a relay set, wherein the relay set comprises an input relay set, an output relay set, an input control relay set and an output control relay set. In this embodiment, the input relay group and the output relay group include 16 sub-relay groups, respectively. The 16 input sub-relay groups are numbered S1-S16, and the 16 output sub-relay groups are numbered S17-S32. In this embodiment, S16 and S32 are each used as a backup sub-relay group. Each sub-relay group consists of 16 relays. The input control relay group and the output control relay group are also respectively composed of 16 relays.
For each set of butt joints A, B, as shown in fig. 1, the butt joint a sequentially passes through S1-S16, the input control relay set outputs to the test bench, and the butt joint B sequentially passes through S17-S32, the output control relay set outputs to the test bench.
Specifically, as shown in fig. 2, the relays in each sub-relay group are numbered 1-16 in sequence, each contact in each butt joint a is connected with an input end of an input sub-relay respectively, then, the output ends of the input sub-relays with the same number in each input sub-relay group are connected in parallel, for example, the output ends of the S1-1 and the S16-1 are connected in parallel, so that 16 common output ends are formed, likewise, each contact in each butt joint B is connected with an output end of an output sub-relay respectively, and the input ends of the output sub-relays with the same number in each output sub-relay group are connected in parallel, so that 16 common input ends are formed. The PLC is used for switching on the corresponding input sub-relay group and the corresponding output sub-relay group in sequence, connecting two ends of 16 wires into each relay in the input control relay group and the output control relay group at one time, and selecting two ends of one wire to be respectively output to a total output end and a total input end through controlling the input control relay group and the output control relay so as to be output to a test bench.
As can be seen from the above, the wire harness box of the embodiment outputs only two ends of one wire in the wire harness to be tested to the test bench at a time. When the wire harness box only comprises the input relay group and the output relay group, the two ends of 16 wires can be simultaneously output to the test bench at one time. At this time, the test bench can be internally provided with 16 circuits for measuring the on-off or resistance of the wires, and the on-off or resistance measurement of 16 wires can be completed in a separated way by only arranging one circuit for measuring the on-off or resistance of the wires by additionally arranging the input and output control relay groups.
Fig. 3 and 4 show two arrangements of the input relay set and the output relay set in the harness box of the auxiliary power unit of the aircraft. S1 corresponds to S17, and forms a corresponding group of input sub-relay groups and output sub-relay groups, S2 and S18, S3 and S19 and so on.
The rated voltage of the relay employed in this embodiment is 24vDC. The PLC adopts Siemens s7-200.
Claims (4)
1. An automatic detection system for a wire harness of an aircraft auxiliary power device is characterized by comprising a test bench and a wire harness box;
the wire harness box is used for connecting aviation connectors at two ends of a wire harness to be tested, and under the control of the test bench, the two ends of each wire in the wire harness to be tested are respectively output to the test bench in a divided manner;
the test bench is used for measuring the on-off or resistance of each input wire; the measuring circuit for the on-off or resistance of the lead in the test board comprises a tester, a power supply, a first relay and a second relay, wherein the power supply is connected in series with the first relay and then connected in parallel with the second relay, and finally connected in series between two input ends of the same lead together with the tester;
the wire harness box includes: as a substrate for mounting the panel, more than one group of the boards comprises butt joints A, B for being respectively and correspondingly connected with aviation joints at two ends of a to-be-tested beam in a unique mode, the butt joints A, B are internally provided with joints corresponding to corresponding aviation joint interpolation pins, and the butt joints are mounted on the substrate;
the relay set comprises an input relay set and an output relay set;
each contact in each butt joint A is respectively connected with the input end of an input relay, and is output to n public output ends after passing through the input relay;
each contact in each butt joint B is respectively connected with the output end of an output relay, and is connected to n common input ends after passing through the input relay;
the relay group also comprises an input control relay group and an output control relay group;
each public output end is respectively connected with an input end of an input control relay, and is output to a total output end after passing through the input control relay;
each common input end is respectively connected with an output end of an output control relay, and is connected to a total input end after passing through the output control relay;
the input relay group and the output relay group respectively comprise more than one sub-relay group; each sub-relay group comprises n relays, the relays in each sub-relay group are numbered in sequence, the output ends of the input relays with the same number in each input sub-relay group are connected in parallel to form n common output ends, and the input ends of the output relays with the same number in each output sub-relay group are connected in parallel to form n common input ends.
2. The aircraft auxiliary power unit harness automatic detection system according to claim 1, wherein the respective input sub-relay groups and output sub-relay groups are arranged in correspondence with each other.
3. An aircraft auxiliary power unit harness box, comprising:
as a substrate for mounting the panel, more than one group of the boards comprises butt joints A, B for being respectively and correspondingly connected with aviation joints at two ends of a to-be-tested beam in a unique mode, the butt joints A, B are internally provided with joints corresponding to corresponding aviation joint interpolation pins, and the butt joints are mounted on the substrate;
the relay set comprises an input relay set and an output relay set;
each contact in each butt joint A is respectively connected with the input end of an input relay, and is output to n public output ends after passing through the input relay;
each contact in each butt joint B is respectively connected with the output end of an output relay, and is connected to n common input ends after passing through the input relay;
the relay group also comprises an input control relay group and an output control relay group;
each public output end is respectively connected with an input end of an input control relay, and is output to a total output end after passing through the input control relay;
each common input end is respectively connected with an output end of an output control relay, and is connected to a total input end after passing through the output control relay;
the input relay group and the output relay group respectively comprise more than one sub-relay group; each sub-relay group comprises n relays, the relays in each sub-relay group are numbered in sequence, the output ends of the input relays with the same number in each input sub-relay group are connected in parallel to form n common output ends, and the input ends of the output relays with the same number in each output sub-relay group are connected in parallel to form n common input ends.
4. An aircraft auxiliary power unit wiring harness box as claimed in claim 3 wherein the respective input and output sub-relay sets are arranged in respective positions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811276994.4A CN109335018B (en) | 2018-10-30 | 2018-10-30 | Automatic wire harness detection system and wire harness box for aircraft auxiliary power device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811276994.4A CN109335018B (en) | 2018-10-30 | 2018-10-30 | Automatic wire harness detection system and wire harness box for aircraft auxiliary power device |
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| CN109335018A CN109335018A (en) | 2019-02-15 |
| CN109335018B true CN109335018B (en) | 2024-02-23 |
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| CN201811276994.4A Active CN109335018B (en) | 2018-10-30 | 2018-10-30 | Automatic wire harness detection system and wire harness box for aircraft auxiliary power device |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111413557B (en) * | 2020-02-25 | 2024-02-06 | 中国南方航空股份有限公司 | Portable ID module reading testing arrangement of auxiliary power device |
| CN113009381A (en) * | 2021-03-10 | 2021-06-22 | 中国人民解放军海军航空大学青岛校区 | Aviation wire ground setting device |
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| CN209321287U (en) * | 2018-10-30 | 2019-08-30 | 中国南方航空股份有限公司 | Aircraft auxiliary power plant harness automatic checkout system and harness case |
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2018
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|---|---|---|---|---|
| EP0103971A1 (en) * | 1982-08-18 | 1984-03-28 | LUCAS INDUSTRIES public limited company | Apparatus for testing wiring harnesses |
| US4859953A (en) * | 1988-07-08 | 1989-08-22 | General Motors Corporation | Modular test assembly for wiring harnesses |
| CN201740833U (en) * | 2010-05-13 | 2011-02-09 | 三一重机有限公司 | Wiring harness detection table |
| JP2015134543A (en) * | 2014-01-17 | 2015-07-27 | 矢崎総業株式会社 | Disconnection detection device |
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| Publication number | Publication date |
|---|---|
| CN109335018A (en) | 2019-02-15 |
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