CN107765113B - Method for shunting aircraft test signal - Google Patents
Method for shunting aircraft test signal Download PDFInfo
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- CN107765113B CN107765113B CN201710816959.6A CN201710816959A CN107765113B CN 107765113 B CN107765113 B CN 107765113B CN 201710816959 A CN201710816959 A CN 201710816959A CN 107765113 B CN107765113 B CN 107765113B
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- 238000012360 testing method Methods 0.000 title claims abstract description 51
- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000005259 measurement Methods 0.000 claims abstract description 10
- 238000012545 processing Methods 0.000 claims abstract description 10
- 230000008054 signal transmission Effects 0.000 claims abstract description 6
- 238000012546 transfer Methods 0.000 claims description 16
- 238000004891 communication Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 11
- 230000007547 defect Effects 0.000 abstract description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical group [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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Abstract
The invention belongs to aircraft test equipment, and particularly relates to a method for shunting aircraft test signals. The invention processes and designs the test signal of the aircraft in a shunting way, and solves the defects of the traditional test mode that the original measurement and control signal transmission channel of the aircraft is cut off, the operation difficulty is higher, and the testability design level is lower. The novel method for processing the test signal of the aircraft in the shunt way is simple in design and implementation mode, simple and convenient in field test operation, and capable of remarkably improving the testability design level of the aircraft.
Description
Technical Field
The invention belongs to aircraft test equipment, and particularly relates to a method for shunting aircraft test signals.
Background
When the ground test is performed on the aircraft, generally, a test item and a test method are firstly determined, a corresponding test interface is designed on the aircraft, a matched connecting channel is developed for the test interface, and various digital quantity signals and analog quantity signals of a measurement and control system on the aircraft are introduced into test equipment for monitoring and judging. In this process, the original signal transmission channel of the measurement and control system is often cut off, and the measured signal is introduced into the test equipment from the cut-off position for detection and processing. The design mode influences the aircraft to carry out the full-system state test to a certain extent, increases the field operation difficulty and reduces the testability design level of the aircraft.
Disclosure of Invention
The purpose of the invention is as follows:
in order to solve the problem that the measurement and control system and the ground test equipment cannot simultaneously receive and monitor various signals of the aircraft in the aircraft test process, a new method for receiving and processing the measurement and control signals of the aircraft in a shunt way needs to be designed, so that the ground test of the aircraft is realized in a full-system connection state, the field test operation difficulty is reduced, and the fault detection rate of the aircraft is improved.
The technical scheme of the invention is as follows:
a method for processing the test signal of the aircraft along separate routes, characterized by, carry on all signals in the original signal transmission channel of observing and controling of the aircraft along separate routes and process, the impedance matching of the communication interface is designed; a set of signal shunt receiving and transmitting cables are manufactured, a downlink signal of an aircraft is divided into two paths, one path is sent to ground test equipment from a transfer port, and the other path is sent to a measurement and control system.
The signal shunt receiving and transmitting cable comprises a one-to-one signal straight-through cable from the testing equipment to the transfer interface and a three-interface transfer cable dividing the port into two parts.
One end of the through cable is connected with the signal interface on the ground test equipment, and the other end of the through cable is connected to the transfer interface.
One end of the transfer cable is connected to the transfer interface, and the other two ends of the transfer cable are respectively connected with the signal outlet of the tested aircraft end and the signal inlet of the tested aircraft end.
And the plug and the socket connected with the transfer interface are selected according to the characteristics of the measured signal.
The invention has the beneficial effects that:
according to the scheme, the aircraft test signal is processed and designed in a shunting manner, and the defects that the original measurement and control signal transmission channel of the aircraft is cut off, the operation difficulty is high and the design level of the testability is low in the traditional test mode are overcome. The novel method for processing the test signal of the aircraft in the shunt way is simple in design and implementation mode, simple and convenient in field test operation, and capable of remarkably improving the testability design level of the aircraft.
Drawings
FIG. 1 is a schematic diagram of the external structure of a test cable
FIG. 2 is a schematic diagram of signal splitting design
Wherein: 1-test equipment end signal interface, 2-straight cable, 3-transfer interface, 4-three interface transfer cable, 5-aircraft end signal outlet, 6-aircraft end signal inlet, 7-tested aircraft and 8-test equipment
Detailed Description
The invention is further described below with reference to the accompanying drawings:
as shown in fig. 1 and fig. 2, all signals in the original measurement and control signal transmission channel of the aircraft are subjected to shunt processing, and the communication interface is designed for impedance matching; a set of signal shunting receiving and transmitting cable is manufactured, a downlink signal of the aircraft is divided into two paths, one path of the downlink signal is sent into the ground test equipment from the switching port, and the other path of the downlink signal is sent back to the measurement and control system, so that the aircraft is tested in the full-system connection state, and the testability design level of the aircraft is remarkably improved.
The signal shunting receiving and transmitting cable comprises: the system comprises a one-to-one signal through cable 2 from the test equipment to the transfer interface and a three-interface transfer cable 4 dividing the port into two parts, wherein one end of the through cable 2 is connected to the test equipment end signal interface 1, the other end of the through cable is connected to the transfer interface 3, one end of the cable 4 is connected to the transfer interface 3, and the other two ends of the cable are respectively connected with an aircraft end signal outlet 5 and an aircraft end signal inlet 6.
Selecting an military grade rectangular electric connector corresponding to and matched with the aircraft end signal outlet 5 and the aircraft end signal inlet 6 according to the connector types; selecting a corresponding circular aviation plug according to the socket type of the signal interface 1 at the test equipment end; and selecting a plug and a socket of the transfer interface 3 according to the characteristics of the measured signal.
After the type selection of the plug and the socket is finished, processing such as reasonable arrangement, impedance matching, interference resistance and the like is carried out according to the specific content, the number and the electrical characteristics of the aircraft test signals; the aviation silver-plated copper core insulated wire is adopted, a cable is processed and manufactured, and insulation and conduction inspection is carried out after the manufacturing is finished.
When the aircraft is tested, the one-to-one signal through cable 2 and the three-interface switching cable 4 are connected through the switching interface 3 and are respectively connected to the testing equipment end signal interface 1 on the testing equipment 8, the aircraft end signal outlet 5 on the tested aircraft 7 and the aircraft end signal inlet 6, and then product testing can be carried out.
Taking sign1 as an example, the signal trend during testing is: starting from the aircraft end signal outlet 5, one path directly flows into the aircraft end signal inlet 6, and the other path flows into the test equipment end signal interface 1 through the transit interface 3.
Claims (5)
1. A method for processing the test signal of the aircraft along separate routes, characterized by, carry on all signals in the original signal transmission channel of observing and controling of the aircraft along separate routes and process, the impedance matching of the communication interface is designed; manufacturing a set of signal shunt receiving and transmitting cables, dividing a downlink signal of the aircraft into two paths, wherein one path is sent to ground test equipment from a transfer port, and the other path is sent to a measurement and control system; when the aircraft is tested, the one-to-one signal through cable (2) and the three-interface switching cable (4) are connected through the switching interface (3) and are respectively connected to the testing equipment end signal interface (1) on the testing equipment (8), the aircraft end signal outlet (5) and the aircraft end signal inlet (6) on the tested aircraft (7), and then product testing can be carried out.
2. The method of claim 1, wherein the signal splitter receive and transmit cables include a one-to-one signal pass-through cable to the relay interface of the test equipment and a three-interface transition cable that bisects the port.
3. The method for split processing of aircraft test signals according to claim 2, wherein the through cable is connected at one end to a signal interface on ground test equipment and at another end to a relay interface.
4. The method according to claim 2 or 3, wherein one end of the adapter cable is connected to the relay interface, and the other two ends are respectively connected to the tested aircraft-side signal outlet and the tested aircraft-side signal inlet.
5. The method for processing the aircraft test signal shunt according to claim 4, wherein the plug and the socket of the relay interface connection are selected according to the tested signal characteristics.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710816959.6A CN107765113B (en) | 2017-09-12 | 2017-09-12 | Method for shunting aircraft test signal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710816959.6A CN107765113B (en) | 2017-09-12 | 2017-09-12 | Method for shunting aircraft test signal |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107765113A CN107765113A (en) | 2018-03-06 |
| CN107765113B true CN107765113B (en) | 2021-01-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710816959.6A Active CN107765113B (en) | 2017-09-12 | 2017-09-12 | Method for shunting aircraft test signal |
Country Status (1)
| Country | Link |
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| CN (1) | CN107765113B (en) |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9617396D0 (en) * | 1996-08-19 | 1996-10-02 | Stc Submarine Systems Ltd | Improvements in or relating to optical add/drop wavelength division multiplex systems |
| US7804280B2 (en) * | 2006-11-02 | 2010-09-28 | Current Technologies, Llc | Method and system for providing power factor correction in a power distribution system |
| CN101299858B (en) * | 2007-04-30 | 2011-11-30 | 大唐移动通信设备有限公司 | Signal processing device, method and intelligent antenna test system using said apparatus |
| CN101197638B (en) * | 2007-12-14 | 2012-02-01 | 上海未来宽带技术及应用工程研究中心有限公司 | hybrid passive optical network system |
| CN101697627B (en) * | 2009-10-28 | 2012-06-06 | 华为终端有限公司 | Method and system for testing reception performance of wireless terminal with function of diversity reception |
| WO2017002879A1 (en) * | 2015-06-30 | 2017-01-05 | 株式会社小糸製作所 | Foreign material removing device and vehicle provided with this foreign material removing device |
| CN206202729U (en) * | 2016-11-15 | 2017-05-31 | 北京临近空间飞行器系统工程研究所 | A kind of autonomous recording measuring system |
| JP6728089B2 (en) * | 2017-02-27 | 2020-07-22 | 三菱重工業株式会社 | Position determination device, position determination system including the same, position determination method, and position determination program |
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- 2017-09-12 CN CN201710816959.6A patent/CN107765113B/en active Active
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| CN107765113A (en) | 2018-03-06 |
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