CN204439805U - Aircraft power supply module failure diagnostic equipment - Google Patents
Aircraft power supply module failure diagnostic equipment Download PDFInfo
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- CN204439805U CN204439805U CN201520065905.7U CN201520065905U CN204439805U CN 204439805 U CN204439805 U CN 204439805U CN 201520065905 U CN201520065905 U CN 201520065905U CN 204439805 U CN204439805 U CN 204439805U
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- supply module
- data acquisition
- interface
- module
- acquisition board
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Abstract
The utility model discloses aircraft power supply module failure diagnostic equipment, comprise supply module, power module, fictitious load, data acquisition board, cpci bus and flush bonding processor, described supply module, power module, fictitious load, data acquisition board connect successively, flush bonding processor and data acquisition board all access cpci bus, and data acquisition board is connected with supply module, power module; Described flush bonding processor is connected to USB interface, audio input output interface, VGA output interface, blue tooth interface and Man Machine Interface; Described Man Machine Interface is connected with human-machine exchange module.The utility model is applicable to the maintenance support work of power-supply device in aircraft, change the problem of the weak and maneuverability difference of existing diagnostic device on-the-spot in-situ diagnostics ability, simple to operate, be convenient to tester's operation and check result, there is the good movability being adapted to on-the-spot test, there is good economic benefit.
Description
Technical field
The utility model relates to a kind of airplane fault diagnostic equipment, specifically aircraft power supply module failure diagnostic equipment.
Background technology
In test and diagnostic field, many main equipment builds are huge, especially the power module on aircraft, it is dispersed in each position of aircraft, because general diagnostic instrments volume is larger, turnover for the most of testing apparatus of narrow and small volume in cabin also has very large restriction, and many test signal cables cannot have been extracted test.Therefore, very large difficulty is brought to the daily servicing of these specific installations, bring many difficulties to management and maintenance department simultaneously.
Utility model content
The purpose of this utility model is to provide a kind of mobility strong, simple to operate, has the aircraft power supply module failure diagnostic equipment of good economic benefit, to solve the problem proposed in above-mentioned background technology.
For achieving the above object, the utility model provides following technical scheme:
Aircraft power supply module failure diagnostic equipment, comprise supply module, power module, fictitious load, data acquisition board, cpci bus and flush bonding processor, described supply module, power module, fictitious load, data acquisition board connect successively, flush bonding processor and data acquisition board all access cpci bus, and data acquisition board is connected with supply module, power module; Described flush bonding processor is connected to USB interface, audio input interface, VGA output interface, blue tooth interface and Man Machine Interface; Described Man Machine Interface is connected with human-machine exchange module.
Further: described data acquisition board is provided with multichannel I/O mouth.
Further: described USB interface is provided with two.
Further: described human-computer interaction module comprises key input unit and display screen unit.
Compared with prior art, the beneficial effects of the utility model are: the utility model is applicable to the maintenance support work of power-supply device in aircraft, change the problem of the weak and maneuverability difference of existing diagnostic device on-the-spot in-situ diagnostics ability, simple to operate, be convenient to tester's operation and check result, there is the good movability being adapted to on-the-spot test, there is good economic benefit.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft power supply module failure diagnostic equipment.
Fig. 2 is that in aircraft power supply module failure diagnostic equipment, data acquisition board realizes block diagram.
In figure: 1-supply module, 2-power module, 3-fictitious load, 4-data acquisition board, 5-CPCI bus, 6-flush bonding processor, 7-Man Machine Interface, 8-USB interface, 9-audio input interface, 10-VGA output interface, 11-blue tooth interface, 12-human-computer interaction module.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, be clearly and completely described the technical scheme in the utility model embodiment, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
Refer to figure, in the utility model embodiment, aircraft power supply module failure diagnostic equipment, comprise supply module 1, power module 2, fictitious load 3, data acquisition board 4, cpci bus 5 and flush bonding processor 6, described supply module 1, power module 2, fictitious load 3, data acquisition board 4 connect successively, flush bonding processor 6 and data acquisition board 4 all access cpci bus 5, and data acquisition board 4 is also connected with supply module 1, power module 2; Supply module 1 and fictitious load 3 do suitable amendment according to the difference of detected power module 2, and the content wherein related to comprises the output class of tested power module 2, power, interface shape, power supply mode and magnitude; Data acquisition board 4 can gather single channel, multichannel data, and data acquisition can synchronously be carried out also can asynchronously carrying out, and simultaneously data acquisition board 4 has multichannel I/O mouth, and this mouthful can be used for realizing the controlling functions of external testing annex; Described flush bonding processor 6 is connected to USB interface 8, audio input interface 9, VGA output interface 10, blue tooth interface 11 and Man Machine Interface 7, described USB interface 8 is provided with two, use when wherein VGA output interface 10 and audio input port 9 are mainly used in the demonstration of these functions of the equipments, blue tooth interface 11 can provide simple and easy mobile device to connect; Described Man Machine Interface 7 is connected with human-machine exchange module 12, and human-computer interaction module 12 comprises key input unit and display screen unit.
To those skilled in the art, obvious the utility model is not limited to the details of above-mentioned one exemplary embodiment, and when not deviating from spirit of the present utility model or essential characteristic, can realize the utility model in other specific forms.Therefore, no matter from which point, all should embodiment be regarded as exemplary, and be nonrestrictive, scope of the present utility model is limited by claims instead of above-mentioned explanation, and all changes be therefore intended in the implication of the equivalency by dropping on claim and scope are included in the utility model.Any Reference numeral in claim should be considered as the claim involved by limiting.
In addition, be to be understood that, although this instructions is described according to embodiment, but not each embodiment only comprises an independently technical scheme, this narrating mode of instructions is only for clarity sake, those skilled in the art should by instructions integrally, and the technical scheme in each embodiment also through appropriately combined, can form other embodiments that it will be appreciated by those skilled in the art that.
Claims (4)
1. aircraft power supply module failure diagnostic equipment, comprise supply module (1), power module (2), fictitious load (3), data acquisition board (4), cpci bus (5) and flush bonding processor (6), it is characterized in that: described supply module (1), power module (2), fictitious load (3), data acquisition board (4) connect successively, flush bonding processor (6) and data acquisition board (4) all access cpci bus (5), and data acquisition board (4) is also connected with supply module (1), power module (2); Described flush bonding processor (6) is connected to USB interface (8), audio input interface (9), VGA output interface (10), blue tooth interface (11) and Man Machine Interface (7); Described Man Machine Interface (7) is connected with human-machine exchange module (12).
2. aircraft power supply module failure diagnostic equipment according to claim 1, is characterized in that: described data acquisition board (4) is provided with multichannel I/O mouth.
3. aircraft power supply module failure diagnostic equipment according to claim 1, is characterized in that: described USB interface (8) is provided with two.
4. aircraft power supply module failure diagnostic equipment according to claim 1, is characterized in that: described human-computer interaction module (12) comprises key input unit and display screen unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520065905.7U CN204439805U (en) | 2015-01-30 | 2015-01-30 | Aircraft power supply module failure diagnostic equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520065905.7U CN204439805U (en) | 2015-01-30 | 2015-01-30 | Aircraft power supply module failure diagnostic equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204439805U true CN204439805U (en) | 2015-07-01 |
Family
ID=53607655
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520065905.7U Expired - Fee Related CN204439805U (en) | 2015-01-30 | 2015-01-30 | Aircraft power supply module failure diagnostic equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204439805U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105334471A (en) * | 2015-10-21 | 2016-02-17 | 中国人民解放军海军航空工程学院青岛校区 | Portable airplane power supply quality test system and method |
| CN108037469A (en) * | 2017-10-23 | 2018-05-15 | 上海科梁信息工程股份有限公司 | Aircraft power supply characteristic test system and method |
-
2015
- 2015-01-30 CN CN201520065905.7U patent/CN204439805U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105334471A (en) * | 2015-10-21 | 2016-02-17 | 中国人民解放军海军航空工程学院青岛校区 | Portable airplane power supply quality test system and method |
| CN108037469A (en) * | 2017-10-23 | 2018-05-15 | 上海科梁信息工程股份有限公司 | Aircraft power supply characteristic test system and method |
| CN108037469B (en) * | 2017-10-23 | 2020-06-16 | 上海科梁信息工程股份有限公司 | Airplane power supply characteristic testing system and method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150701 Termination date: 20180130 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |