CN204479297U - Aero Engine Testing field digital bus control device - Google Patents
Aero Engine Testing field digital bus control device Download PDFInfo
- Publication number
- CN204479297U CN204479297U CN201520016140.8U CN201520016140U CN204479297U CN 204479297 U CN204479297 U CN 204479297U CN 201520016140 U CN201520016140 U CN 201520016140U CN 204479297 U CN204479297 U CN 204479297U
- Authority
- CN
- China
- Prior art keywords
- module
- interface
- output
- circuit board
- processing unit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Abstract
The utility model relates to a kind of Aero Engine Testing field digital bus control device, comprise control system, communication interface, output interface, power supply interface, control system comprises master control circuit board, central processing unit, output module, supply module, communication module, relay module; Power supply interface connects master control circuit board; Communication interface is connected with engine testsand; Central processing unit is connected with relay module, and relay module connects output interface, and output interface is by cable connecting engine test bay site test equipment.The utility model can the state at real-time monitoring equipment scene, and safety, stable, anti-interference etc. in there is good performance while, better achieve the intellectuality of control device, complete the requirement meeting Aero Engine Testing device context and control.
Description
Technical field
The utility model relates to a kind of Aero Engine Testing field digital bus control device, for the long-distance intelligent control of Aero Engine Testing field apparatus.
Background technology
Aero Engine Testing equipment, in the special test bay system operation of aeromotor, needs to carry out scene or Long-distance Control, to meet the requirement of engine test condition.Described special test bay is provided with apparatus control system, for testing equipment provides on-the-spot or Long-distance Control.In process of the test, need to carry out opening, stop, the operation control such as the sequence that operate, to control the various duties of each testing equipment of test bay.Aero Engine Testing on-site control device, guarantee not change the long-range and on-the-spot control of finishing equipment under the prerequisite of testing equipment function, with the intelligence of warranty test equipment, stable, control overflow reliably.Current testing equipment controls, general testing equipment control device is just adopted to carry out field control, although this structure is simple, independent controlling functions can be realized, but want a large amount of control electrical equipments, control cables etc., therefore increase considerably the complexity of test bay system and cost drops into, and Systematical control precision and the safe reliability of testing equipment can be affected, and then affect engine and test normally.At present, data of literatures is not also had to do full and accurate introduction and for consulting, can still belong to blank at home to the research of on-the-spot long-distance intelligent control to testing ground number bus control device.If Aero Engine Testing plant control unit adopts general control and mode, also exist a lot of not enough from device rationality, control accuracy, security, anti-interference and structure function, can't meet to maximum likelihood the requirement of the control of Aero Engine Testing equipment real-time live digital intelligent and condition monitoring.
Summary of the invention
The purpose of this utility model is to provide a kind of device that can substitute traditional Aero Engine Testing device context and control, overcome the deficiency of traditional testing equipment field control mode, ensureing that Aero Engine Testing field control is stable, safe and reliable while, can monitoring test equipment state in real time, and control accuracy, safety, stable, anti-interference in there is good performance, better realize the on-the-spot Contrast tuned imaging of testing equipment, complete the requirement meeting Aero Engine Testing device context and control.
Concrete scheme of the present utility model is:
Aero Engine Testing field digital bus control device comprises control system, communication interface, output interface, power supply interface, and control system comprises master control circuit board and is arranged on central processing unit in master control circuit board, output module, supply module, communication module, relay module; Power supply interface is connected with power supply by signal shielding cable, and connects master control circuit board, for each electronic component is powered by supply module and feed circuit; Communication interface is connected with the control system of engine testsand by signal shielding cable, and is connected the signal input part of the central processing unit in master control circuit board with communicating circuit by module; The signal output part of central processing unit is connected with the input end of relay module, and the output terminal of relay module connects output interface by output module, and output interface is by cable connecting engine test bay site test equipment.The output terminal of relay module is also connected with communication module.Described feed circuit, communicating circuit are arranged on main control board.
The utility model does not need to increase extra pilot relay, control circuit and control cables etc., overcome traditional testing equipment deficiency functionally, while warranty test equipment is safe and reliable to operation, can the state at real-time monitoring equipment scene, and safety, stable, anti-interference etc. in there is good performance while, better achieve the intellectuality of control device, complete the requirement meeting Aero Engine Testing device context and control.
Accompanying drawing explanation
Fig. 1 is syndeton schematic diagram of the present utility model.
Embodiment
As shown in the figure, Aero Engine Testing field digital bus control device comprises control system I, communication interface II, output interface III, power supply interface IV, and control system I comprises master control circuit board 1 and is arranged on central processing unit 1a in master control circuit board, output module 1c, supply module 1d, communication module 1e, relay module 1f; Power supply interface IV is connected with power supply by signal shielding cable, and connects master control circuit board 1, for each electronic component is powered by supply module 1d and feed circuit; Communication interface II is connected with the control system of engine testsand by signal shielding cable, and is connected the signal input part of the central processing unit 1a in master control circuit board 1 with communicating circuit by module; The signal output part of central processing unit 1a is connected with the input end of relay module 1f, and the output terminal of relay module 1f connects output interface III by output module 1c, and output interface III is by cable connecting engine test bay site test equipment.The output terminal of relay module 1f is also connected with communication module 1e.Described feed circuit, communicating circuit are arranged on main control board 1.
During work, control device of the present utility model is fixed on Aero Engine Testing equipment, by establishment control program, with the co-ordination of engine testsand master control system.Operationally, testing equipment steering order signal (opens, stop, running sequence etc.) sent by test bay control system, pass through communication interface, communication module, communicating circuit enters into central processing unit, central processing unit calculates according to program prepared in advance, again the steering order signal after calculating is exported and pass through relay module, output interface enters the testing equipment of engine testsand, the various trystates carrying out testing equipment control, meet the technical requirement that engine run controls testing equipment, simultaneously, the steering order status signal that central processing unit exports (opens, stop, the status signals such as running sequence) feed back to communication module by relay module, pass through communicating circuit, communication module, the work order of communication interface back-to-back testing equipment, for the state of the real-time monitoring test equipment of test bay control system.
Claims (2)
1. an Aero Engine Testing field digital bus control device, it is characterized in that, described device comprises control system (I), communication interface (II), output interface (III), power supply interface (IV), and control system (I) comprises master control circuit board (1) and is arranged on central processing unit in master control circuit board (1a), output module (1c), supply module (1d), communication module (1e), relay module (1f); Power supply interface (IV) be connected with power supply by signal shielding cable, and connect master control circuit board (1), for each electronic component is powered by supply module (1d) and feed circuit; Communication interface (II) be connected with the control system of engine testsand by signal shielding cable, and be connected the signal input part of the central processing unit (1a) in master control circuit board (1) with communicating circuit by module (1b); The signal output part of central processing unit (1a) is connected with the input end of relay module (1f), the output terminal of relay module (1f) connects output interface (III) by output module (1c), output interface (III) is by cable connecting engine test bay site test equipment, and the output terminal of relay module (1f) is also connected with communication module (1e).
2. Aero Engine Testing field digital bus control device as claimed in claim 1, it is characterized in that, described feed circuit, communicating circuit are arranged on main control board (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520016140.8U CN204479297U (en) | 2015-01-09 | 2015-01-09 | Aero Engine Testing field digital bus control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520016140.8U CN204479297U (en) | 2015-01-09 | 2015-01-09 | Aero Engine Testing field digital bus control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204479297U true CN204479297U (en) | 2015-07-15 |
Family
ID=53635084
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520016140.8U Expired - Fee Related CN204479297U (en) | 2015-01-09 | 2015-01-09 | Aero Engine Testing field digital bus control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204479297U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104568452A (en) * | 2015-01-09 | 2015-04-29 | 哈尔滨东安发动机（集团）有限公司 | Aircraft engine test site digital bus control device |
-
2015
- 2015-01-09 CN CN201520016140.8U patent/CN204479297U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104568452A (en) * | 2015-01-09 | 2015-04-29 | 哈尔滨东安发动机（集团）有限公司 | Aircraft engine test site digital bus control device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101566849B (en) | Functional parameter test system for automobile electronic controller and test method thereof | |
| CN103869781A (en) | Non-similar three-redundancy onboard electric load management center | |
| CN105644474B (en) | A kind of car Intelligent central electrical appliance kit | |
| CN202117902U (en) | Electric automation monitoring and control system of pump station | |
| CN106553878A (en) | A kind of querying method of mine leather belt protection system locking along the line | |
| CN104052152A (en) | Intelligent power supply and distribution unit | |
| CN204479297U (en) | Aero Engine Testing field digital bus control device | |
| CN203951254U (en) | One comes off to power and disconnects control circuit | |
| CN112241138A (en) | Logic control device and train control system | |
| CN104330262B (en) | Aero-engine combustion oil system assay device | |
| CN106057783A (en) | Fuse circuit | |
| CN104568452A (en) | Aircraft engine test site digital bus control device | |
| CN103472746A (en) | Double-main-control device and redundancy control method of double-main-control device | |
| CN103605303A (en) | Injection-molding-machine digital IO switch-over terminal junction box with redundancy detection function | |
| CN204165752U (en) | Aeromotor combustion oil system test unit | |
| CN205160212U (en) | Power remote control and monitored control system | |
| CN204719474U (en) | A kind of emergent sniffing robot power source management control system | |
| CN209719279U (en) | The DC charging terminal of new intelligent | |
| CN205545672U (en) | Power supply unit of SDI mode | |
| CN202204384U (en) | Information acquisition controller for self-propelled gun integrated EIS (Electronic Information System) | |
| CN203480268U (en) | PLC-based separating test controller of multiple separate connectors | |
| CN114721358B (en) | Switching device for ground function test of flight control system | |
| CN204925759U (en) | Industry electric signal gathers communication control system | |
| CN107856890A (en) | A kind of de- slotting monitoring device of portable satellite based on cRIO frameworks | |
| CN107168235B (en) | IO network wiring system |
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: 20150715 Termination date: 20210109 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |