CN204359879U - A kind of helicopter instrumentation system cable original position switching test device - Google Patents
A kind of helicopter instrumentation system cable original position switching test device Download PDFInfo
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- CN204359879U CN204359879U CN201520002059.4U CN201520002059U CN204359879U CN 204359879 U CN204359879 U CN 204359879U CN 201520002059 U CN201520002059 U CN 201520002059U CN 204359879 U CN204359879 U CN 204359879U
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- cable
- original position
- test device
- position switching
- testing apparatus
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Abstract
The utility model belongs to helicopter design of electrical system technical field, relates to a kind of helicopter instrumentation system cable original position switching test device.Described cable original position switching test device (2) is board instrument system cable bundle (3) tested in test process and the stube cable between testing apparatus fabric interface (1): one end that described cable original position switching test device (2) is connected with testing apparatus fabric interface (1) is normal end, its each electric connector heart yearn pin numerical value is fixed, identical with testing apparatus fabric interface (1) pin number; Each terminal heart yearn sum of described tested board instrument system cable bundle (3) is not more than normal end heart yearn numerical value.Adopt the utility model position large to board instrument system cable in situ detection difficulty can accomplish conveniently, test flexibly.
Description
Technical field
The utility model belongs to helicopter design of electrical system technical field, relates to a kind of helicopter instrumentation system cable original position switching test device.
Background technology
Certain type helicopter instrumentation system cable home position testing method existing uses multimeter, conducting bell, the testing tools such as insulation tester, on ground first to the electrical specification of the board instrument system cable wire harness made as resistance value, capacitance, diode etc., insulation characterisitic is tested by root, at least need more than 3 people, and then carry out in situ detection by the method to laying to board instrument system cable, test process is numerous and diverse easily makes mistakes, be unfavorable for searching the damage that board instrument system cable produces in laid processes, the finished product energising work after installation of giving brings great potential safety hazard.
Because the airborne finished product of instrument system mainly distributes the position such as electronic equipment rack, driving cabin instrument panel by space constraint, it is large especially that the instrument system core of a cable made completes in situ detection difficulty on machine, has a strong impact on aircraft general assembly manufacturing schedule and delivery cycle.
Utility model content
The purpose of this utility model is: provide a kind of helicopter instrumentation system cable original position switching test device; under guaranteeing that the whole high-quality and high-efficiency of board instrument system cable accomplishes the prerequisite of in situ detection; the destruction of electrical specification that board instrument system cable causes due to extraneous factor in laid processes, insulation characterisitic can be found in time; guarantee board instrument system cable lay after reliability; the hidden danger avoiding Aircraft Cables to exist and the damage that likely occurs during energising after the airborne finished product installation that causes, ensure carrying out smoothly of helicopter general assembly energising work.
The technical solution of the utility model is: a kind of helicopter instrumentation system cable original position switching test device, it is characterized by: described cable original position switching test device 2 is tested board instrument system cable bundle 3 and the stube cable between testing apparatus fabric interface 1 in test process: the connector one end at described cable original position switching test device 2 two ends is connected with the plug and socket in tested board instrument system cable bundle 3, and the other end is connected with testing apparatus fabric interface 1; One end that described cable original position switching test device 2 is connected with testing apparatus fabric interface 1 is normal end, and its each electric connector heart yearn pin numerical value is fixed, identical with testing apparatus fabric interface 1 pin number; Each terminal heart yearn sum of described tested board instrument system cable bundle 3 is not more than normal end heart yearn numerical value.
The beneficial effects of the utility model are: adopt the utility model position large to board instrument system cable in situ detection difficulty can accomplish conveniently, test flexibly.According to the crosslinked relation of mission system cable transmission signal each on machine, the test data of every root cable is provided by autotest program in testing apparatus, judge the reliability on machine after cable laying thus, adopt the board instrument system cable in-situ test of the utility model energy complete independently system separately, in-situ test on the crosslinked machine of multiple system cable can be carried out again.The utility model meets in-situ test requirement on certain type helicopter instrumentation system cable machine completely, adopt the utility model can not be subject to the restriction of helicopter narrow space, only need 1 people just can facilitate, complete cable in situ detection work on instrument system machine flexibly, efficiently, has reference to in-situ test work on the machine of different type of machines helicopter instrumentation system cable.
Accompanying drawing explanation
Fig. 1 is in situ detection line schematic diagram on helicopter instrumentation system cable machine;
Wherein, 1-testing apparatus fabric interface, 2-cable original position switching test device, 3-tested board instrument system cable bundle.
Embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is described further.
See Fig. 1, a kind of helicopter instrumentation system cable original position switching test device, described cable original position switching test device 2 is tested board instrument system cable bundle 3 and the stube cable between testing apparatus fabric interface 1 in test process: the connector one end at described cable original position switching test device 2 two ends is connected with the plug and socket in tested board instrument system cable bundle 3, and the other end is connected with testing apparatus fabric interface 1; One end that described cable original position switching test device 2 is connected with testing apparatus fabric interface 1 is normal end, and its each electric connector heart yearn pin numerical value is fixed, identical with testing apparatus fabric interface 1 pin number; Each terminal heart yearn sum of described tested board instrument system cable bundle 3 is not more than normal end heart yearn numerical value.
Helicopter instrumentation system more than 50 is planted the position that 80 crosslinked mutually bundle cables of airborne finished product all or have as required been laid by 60 bundle Splices cable devices from machine to transfer out, form a test macro with 60 groups of addressing interfaces special in ATE (automatic test equipment).High by test resistance value by the corresponding relation of helicopter instrumentation system wiring figure and measured point, test resistance value is low, test output point misconnection, test output point are that these four kinds of states of ignore write an autotest program, when arrange ATE (automatic test equipment) export a 0.2A exciting current and specify response time 0.3S in receive an impedance be less than the signal of 3 Ω time, ATE (automatic test equipment) start autotest program judge tested point conduction status; When arrange ATE (automatic test equipment) export 500V high pressure time, and specify response time 0.25S in receive one be greater than the resistance signal of 10M Ω time, ATE (automatic test equipment) start autotest program judge tested point insulation status.After meters under test bunch of cables all completes the test of point-to-point or 1 point-to-multipoint, electrical specification, the insulation characterisitic of board instrument system cable bundle also complete in situ detection simultaneously.
Cable original position switching test device 2 is stube cables between tested board instrument system cable bundle 3 and testing apparatus fabric interface 1 in test process, the connector one end at its two ends is connected with the plug and socket of various model in tested board instrument system cable bundle 3, and the other end is connected with testing apparatus fabric interface 1.
The one end be connected with testing apparatus fabric interface 1 each electric connector heart yearn pin numerical value is fixed, be called normal end, it is identical with testing apparatus fabric interface 1 pin number, cable original position switching test device 2 other end is connected with tested board instrument system cable bundle 3, the cable interface of the core number negligible amounts disperseed by tested board instrument system cable bundle 3 gathers together, decomposed by cable interface large for core number quantity, after making decomposition, each terminal heart yearn sum is less than or equal to normal end heart yearn numerical value.Electrically be cross-linked relation and the concrete installation site of airborne equipment by analyzing in tested board instrument system cable bundle 3 between each system, instrument transit cable device by normal end address is: 3000 ~ 5949 distribute.
Tested board instrument system cable bundle 3 is divided into the part such as electronic equipment rack, instrument panel according to installation site concrete on machine, instrument system is according to bunch of cables on relevant tested machine on installation site statistics native system machine on machine, and after statistics, each system carries out distribution making cable original position switching test device 2 in conjunction with instruments subsystems according to normal end address again.
The system of cable original position switching test device 2 correspondence mainly comprises: synthetical display control system, automated driving system, backup flight displays, fuel system, Atmosphere System, backup aviation attitude system, FDR system, horizon instrument.
The multi-tap that finished product attachment plug on tested board instrument system cable bundle 3 is corresponding with on cable original position switching test device 2 is connected, again the normal end of cable original position switching test device 2 is connected with testing apparatus fabric interface 1, by on cable original position switching test device 2 one to one patchplug by the electrical specification of tested board instrument system cable bundle 3, insulation characterisitic is transferred in testing apparatus main frame and automatically completes the organic cable in situ detection that powers on of instrument system by test procedure, according to the resistance value of the every root wire shown on testing apparatus main frame, judge the reliability on machine after cable laying, select testing apparatus host stores or printing test result, namely the in situ detection of all finished product stube cables of instrument system is completed.
Claims (1)
1. a helicopter instrumentation system cable original position switching test device, it is characterized by: described cable original position switching test device (2) is board instrument system cable bundle (3) tested in test process and the stube cable between testing apparatus fabric interface (1): the connector one end at described cable original position switching test device (2) two ends is connected with the plug and socket in tested board instrument system cable bundle (3), and the other end is connected with testing apparatus fabric interface (1); One end that described cable original position switching test device (2) is connected with testing apparatus fabric interface (1) is normal end, and its each electric connector heart yearn pin numerical value is fixed, identical with testing apparatus fabric interface (1) pin number; Each terminal heart yearn sum of described tested board instrument system cable bundle (3) is not more than normal end heart yearn numerical value.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520002059.4U CN204359879U (en) | 2015-01-04 | 2015-01-04 | A kind of helicopter instrumentation system cable original position switching test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520002059.4U CN204359879U (en) | 2015-01-04 | 2015-01-04 | A kind of helicopter instrumentation system cable original position switching test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204359879U true CN204359879U (en) | 2015-05-27 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520002059.4U Expired - Fee Related CN204359879U (en) | 2015-01-04 | 2015-01-04 | A kind of helicopter instrumentation system cable original position switching test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204359879U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108021122A (en) * | 2017-12-12 | 2018-05-11 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine vibration-testing trouble-shooter and diagnostic method |
-
2015
- 2015-01-04 CN CN201520002059.4U patent/CN204359879U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108021122A (en) * | 2017-12-12 | 2018-05-11 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine vibration-testing trouble-shooter and diagnostic method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170606 Address after: 150066 Heilongjiang Province, Harbin city Youxie Street Pingfang District No. 15 Patentee after: Harbin Hafei Aviation Industry Co. Ltd. Address before: 150066 Heilongjiang Province, Harbin city Youxie Street Pingfang District No. 15 Patentee before: Harbin Aircraft Industrial (Group) Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150527 Termination date: 20180104 |