CN104568452A - Aircraft engine test site digital bus control device - Google Patents
Aircraft engine test site digital bus control device Download PDFInfo
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- CN104568452A CN104568452A CN201510012244.6A CN201510012244A CN104568452A CN 104568452 A CN104568452 A CN 104568452A CN 201510012244 A CN201510012244 A CN 201510012244A CN 104568452 A CN104568452 A CN 104568452A
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Abstract
The invention relates to an aircraft engine test site digital bus control device. The aircraft engine test site digital bus control device comprises a control system, a communication interface, an output interface and a power supply interface, and the control system comprises a main control circuit board, a central processing unit, an output module, a power supply module, a communication module and a relay module; the power supply interface is connected with the main control circuit board; the communication interface is connected with an engine test bed; the central processing unit is connected with the relay module which is connected with the output interface, and the output interface is connected with engine test bed site test equipment through a cable. The aircraft engine test site digital bus control device can monitor the status of an equipment site in real time and has good performance of safety, stability and anti-interference, intelligence of the control device is achieved better, and the requirement for aircraft engine test equipment site control is met.
Description
Technical field
The present invention 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 object of this invention 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 invention 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 present invention 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 invention.
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 1b; 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 invention 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 |
|---|---|---|---|
| CN201510012244.6A CN104568452A (en) | 2015-01-09 | 2015-01-09 | Aircraft engine test site digital bus control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510012244.6A CN104568452A (en) | 2015-01-09 | 2015-01-09 | Aircraft engine test site digital bus control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104568452A true CN104568452A (en) | 2015-04-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510012244.6A Pending CN104568452A (en) | 2015-01-09 | 2015-01-09 | Aircraft engine test site digital bus control device |
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| CN (1) | CN104568452A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105223893A (en) * | 2015-11-02 | 2016-01-06 | 沈阳航天新光集团有限公司 | Aeromotor ground stand trystate supervisory system |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201174049Y (en) * | 2008-03-28 | 2008-12-31 | 徐州徐挖挖掘机械有限公司 | Remote intelligent management apparatus for digging machine |
| US20090088892A1 (en) * | 2007-10-01 | 2009-04-02 | Hitachi, Ltd. | Control system of electric actuator and control method thereof |
| JP4715676B2 (en) * | 2006-08-11 | 2011-07-06 | 株式会社ジェイテクト | Circuit board for I / O controller |
| CN202886104U (en) * | 2012-11-09 | 2013-04-17 | 东风汽车股份有限公司 | Fault diagnosis system for electric control engine bench test process |
| CN103235568A (en) * | 2013-04-03 | 2013-08-07 | 电子科技大学 | Wireless detecting device for monitoring nuclear power plant equipment |
| CN203374932U (en) * | 2013-07-17 | 2014-01-01 | 合肥三益江海智能科技有限公司 | Explosion-proof electric valve control device for mine |
| CN203394646U (en) * | 2013-06-14 | 2014-01-15 | 南车玉柴四川发动机股份有限公司 | Electrical control system for ship engine |
| CN203433363U (en) * | 2013-09-11 | 2014-02-12 | 广东保达动力技术有限公司 | Detection apparatus for electrical control of generating set |
| CN204479297U (en) * | 2015-01-09 | 2015-07-15 | 哈尔滨东安发动机（集团）有限公司 | Aero Engine Testing field digital bus control device |
-
2015
- 2015-01-09 CN CN201510012244.6A patent/CN104568452A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4715676B2 (en) * | 2006-08-11 | 2011-07-06 | 株式会社ジェイテクト | Circuit board for I / O controller |
| US20090088892A1 (en) * | 2007-10-01 | 2009-04-02 | Hitachi, Ltd. | Control system of electric actuator and control method thereof |
| CN201174049Y (en) * | 2008-03-28 | 2008-12-31 | 徐州徐挖挖掘机械有限公司 | Remote intelligent management apparatus for digging machine |
| CN202886104U (en) * | 2012-11-09 | 2013-04-17 | 东风汽车股份有限公司 | Fault diagnosis system for electric control engine bench test process |
| CN103235568A (en) * | 2013-04-03 | 2013-08-07 | 电子科技大学 | Wireless detecting device for monitoring nuclear power plant equipment |
| CN203394646U (en) * | 2013-06-14 | 2014-01-15 | 南车玉柴四川发动机股份有限公司 | Electrical control system for ship engine |
| CN203374932U (en) * | 2013-07-17 | 2014-01-01 | 合肥三益江海智能科技有限公司 | Explosion-proof electric valve control device for mine |
| CN203433363U (en) * | 2013-09-11 | 2014-02-12 | 广东保达动力技术有限公司 | Detection apparatus for electrical control of generating set |
| CN204479297U (en) * | 2015-01-09 | 2015-07-15 | 哈尔滨东安发动机（集团）有限公司 | Aero Engine Testing field digital bus control device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105223893A (en) * | 2015-11-02 | 2016-01-06 | 沈阳航天新光集团有限公司 | Aeromotor ground stand trystate supervisory system |
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Application publication date: 20150429 |
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