CN203606875U - Digital history recorder of aero-engine - Google Patents
Digital history recorder of aero-engine Download PDFInfo
- Publication number
- CN203606875U CN203606875U CN201320729373.3U CN201320729373U CN203606875U CN 203606875 U CN203606875 U CN 203606875U CN 201320729373 U CN201320729373 U CN 201320729373U CN 203606875 U CN203606875 U CN 203606875U
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- circuit
- aeromotor
- history recorder
- interface
- dsp microprocessor
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Abstract
The utility model discloses a digital history recorder of an aero-engine. The digital history recorder comprises a DSP (Digital Signal Processor) microprocessor; the DSP microprocessor is connected with a USB (Universal Serial Bus) communication interface and an RS422 bus interface; the RS422 bus interface is used for being communicated with an electronic controller of the aero-engine; the USB communication interface is used for being communicated with a PC (Personal Computer) for ground detection. The digital history recorder of the aero-engine, which is disclosed by the utility model, is compatible with the RS422 bus interface and the USB communication interface and flexible in communication mode; furthermore, more operation parameters can be collected in a digital storage manner; the data storage capacity is high; the practical life loss condition of the aero-engine can be accurately detected, therefore, the service life of the aero-engine can be utilized to the most extent; the flight safety performances of the aero-engine are improved.
Description
Technical field
The utility model relates to aeromotor field of electric control, especially, relates to the digital history recorder of a kind of aeromotor.
Background technology
History recorder is the important component part of aeromotor Digital electronic control system, and history recorder, for recording the course parameter of aeromotor truly, reflects life-span and the use state of aeromotor.
Generally speaking, history recorder mostly is analog history recorder, by driving the counter of digital wheel to form based on stepper motor, by receiving the pumping signal response action of aeromotor Digital electronic control system, indicate the number of the course parameter that represents aeromotor.Although analog history recorder principle of work is simple, intuitive display, also met to a certain extent the data recording demand of aeromotor, but its recording parameters limited amount, mode machinery are single, and cannot realize digital information storage, can not reflect exactly aeromotor Expenditure Levels actual life, easily waste the serviceable life of aeromotor and may cause flight safety hidden danger.
At present, comparatively rare digital history recorder, its addressing mode generally adopts the data line of processor, address wire direct-connected with data line, the address wire of external memory storage respectively, this mode has solved the problem of digital information storage, but data storage capacity is limited, and communication interface is single, cannot meet the demand that aeromotor on-line operation detects and ground maintenance detects.
Utility model content
The utility model object is to provide a kind of aeromotor digital history recorder, to solve the technical matters that recording parameters is limited and communication interface is single of existing history recorder.
For achieving the above object, the technical solution adopted in the utility model is as follows:
The digital history recorder of a kind of aeromotor, comprises DSP microprocessor, and DSP microprocessor is connected with usb communication interface and RS422 bus interface, and RS422 bus interface is for communicating with the electronic controller of aeromotor; Usb communication interface is for communicating with ground detection PC.
Further, DSP microprocessor is TMS320F2812 chip.
Further, DSP microprocessor connects RS422 bus interface through serial communication interface.
Further, DSP microprocessor connects usb communication interface through universal input/output interface.
Further, DSP microprocessor is connected with and extends out RAM circuit and/or extend out FLASH circuit through external memory storage expansion interface.
Further, it is multiple extending out FLASH circuit, and the multiple FLASH of extending out circuit are connected to DSP microprocessor through external memory storage expansion interface respectively.
Further, DSP microprocessor is provided with peripheral circuit, and peripheral circuit comprises power-switching circuit, reset circuit, clock circuit, self-checking circuit and jtag interface circuit.
The utlity model has following beneficial effect:
The digital history recorder of the utility model aeromotor, by adopting DSP microprocessor and connect usb communication interface and RS422 bus interface on DSP microprocessor, while making history recorder presence, communicate the operational factor of real-time online record aeromotor through the electronic controller of RS422 bus interface and aeromotor by DSP microprocessor; And when aeromotor is during in ground detection maintenance state, DSP microprocessor is connected with ground detection PC through usb communication interface, makes ground detection PC to read relevant historical data and the failure message in history recorder, stored by usb communication interface.The digital history recorder of the utility model is compatible RS422 bus interface and usb communication interface not only, communication mode is flexible, and the operational factor gathering by digital storage mode is many, memory data output is large, can detect exactly the loss actual life situation of aeromotor, thereby maximally utilise the serviceable life of aeromotor and improve its flight safety performance.
Except object described above, feature and advantage, the utility model also has other object, feature and advantage.Below with reference to figure, the utility model is described in further detail.
Accompanying drawing explanation
The accompanying drawing that forms the application's a part is used to provide further understanding of the present utility model, and schematic description and description of the present utility model is used for explaining the utility model, does not form improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the electrical block diagram of the digital history recorder of the utility model preferred embodiment aeromotor.
Embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is elaborated, but the multitude of different ways that the utility model can be defined by the claims and cover is implemented.
With reference to Fig. 1, preferred embodiment of the present utility model provides a kind of aeromotor digital history recorder, comprise DSP microprocessor 201, DSP microprocessor 201 is connected with usb communication interface 203 and RS422 bus interface 202, and RS422 bus interface 202 is for communicating with the electronic controller of aeromotor; Usb communication interface 203 is for communicating with ground detection PC.In the time that history recorder is in line states, DSP microprocessor 201 communicates by RS422 bus interface 202 and the electronic controller of aeromotor, the electronic controller real-time online of aeromotor sends the normal operation of various control instruction with manipulation aeromotor, DSP microprocessor 201 carrys out through RS422 bus interface 202 steering order that Real-time Collection electronic controller sends, to realize the operational factor such as status information, failure diagnosis information of real-time online record aeromotor life-span course parameter, engine operating parameter and engine and digital control system; When aeromotor is during in ground detection maintenance state, micro-processing 201 devices of DSP are connected with ground detection PC through usb communication interface 203, make ground detection PC to read relevant historical data and the failure message in history recorder, stored by usb communication interface 203.The digital history recorder of the utility model is compatible RS422 bus interface and usb communication interface not only, communication mode is flexible, and the operational factor gathering by digital storage mode is many, memory data output is large, can detect exactly the loss actual life situation of aeromotor, thereby maximally utilise the serviceable life of aeromotor and improve its flight safety performance.
In the present embodiment, preferably, DSP microprocessor 201 is TMS320F2812 chip.The present embodiment adopts TMS320F2812 chip as development platform, and on TMS320F2812 chip by peripheral hardware serial communication interface (SCI in sheet, Serial Communication Interface) connection RS422 bus interface 202, wherein, SCI is the asynchronous serial communication interface of two signal wires of a kind of employing, it is UART interface, comprise two group communication modules: SCIA module and SCIB module, the receiver of two group communication modules and transmitter are all with the FIFO of 16 grades of degree of depth, and receiver and transmitter have and independently enable and interrupt bit, can operation simultaneously under independent operation under semiduplex mode or full-duplex mode.
In the present embodiment, connect usb communication interface 203 as the TMS320F2812 chip of DSP microprocessor 201 through universal input/output interface (GPIO).The realization of usb communication interface 203 is the microprocessor CY7C68013A that adopt USB2.0, it is directly connected with the TMS320F2812 chip as DSP microprocessor 201, data are mainly from DSP microprocessor and controlled by it, use the Slave fifo interface of CY7C68013A as from equipment, asynchronous read and write, automatic mode.DSP microprocessor can be read and write by the multilayer buffering FIFO to CY7C68013A inside as the common FIFO of read-write.The control program of CY7C68013A microprocessor is from I
2in C compatibility interface E2PROM, download, the sheet of CY7C68013A selects SLCS signal by the choosing of DSP sheet and address wire encoded control.
Due to DSP microprocessor 201 to carry data space limited, in order to realize the memory requirement of large capacity Nonvolatile data, DSP microprocessor 201 is connected with and extends out RAM circuit and/or extend out FLASH circuit through external memory storage expansion interface (XINTF).Preferably, it is multiple extending out FLASH circuit, and the multiple FLASH of extending out circuit are connected to DSP microprocessor 201 through external memory storage expansion interface (XINTF) respectively.With reference to Fig. 1, in the present embodiment, TMS320F2812 chip connects respectively through XINTF and extends out RAM circuit 401, extends out FLASH circuit 402 and extend out FLASH circuit 403, wherein extends out the memory capacity >=4GByte of FLASH circuit 402, and the memory capacity that extends out FLASH circuit 403 is 1MByte.
With reference to Fig. 1, DSP microprocessor 201 is provided with peripheral circuit, and peripheral circuit comprises power-switching circuit 301, reset circuit 302, clock circuit 303, self-checking circuit 304 and jtag interface circuit 305.Wherein, JTAG (Joint TestAction Group, combined testing action group) interface circuit 305 is a kind of international standard test protocols, is mainly used in chip internal test, comprise TMS, TCK, TDI, TDO, i.e. model selection, clock, data input, DOL Data Output Line.
The digital history recorder of the utility model, not only change the recording mode of analog history recorder, realize digital information storage, and compatible RS422 bus interface and usb communication interface, communication mode is flexible, and the operational factor gathering by digital storage mode is many, and memory data output is large, can detect exactly the loss actual life situation of aeromotor, thereby maximally utilise the serviceable life of aeromotor and improve its flight safety performance.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (7)
1. the digital history recorder of aeromotor, comprises DSP microprocessor (201), it is characterized in that,
Described DSP microprocessor (201) is connected with usb communication interface (203) and RS422 bus interface (202), and described RS422 bus interface (202) is for communicating with the electronic controller of aeromotor; Described usb communication interface (203) is for communicating with ground detection PC.
2. the digital history recorder of aeromotor according to claim 1, is characterized in that,
Described DSP microprocessor (201) is TMS320F2812 chip.
3. the digital history recorder of aeromotor according to claim 1, is characterized in that,
Described DSP microprocessor (201) connects described RS422 bus interface (202) through serial communication interface.
4. the digital history recorder of aeromotor according to claim 1, is characterized in that,
Described DSP microprocessor (201) connects described usb communication interface (203) through universal input/output interface.
5. the digital history recorder of aeromotor according to claim 1, is characterized in that,
Described DSP microprocessor (201) is connected with and extends out RAM circuit and/or extend out FLASH circuit through external memory storage expansion interface.
6. the digital history recorder of aeromotor according to claim 5, is characterized in that,
The described FLASH of extending out circuit is multiple, extends out FLASH circuit described in multiple to be connected to described DSP microprocessor (201) through external memory storage expansion interface respectively.
7. the digital history recorder of aeromotor according to claim 1, is characterized in that,
Described DSP microprocessor (201) is provided with peripheral circuit, and described peripheral circuit comprises power-switching circuit (301), reset circuit (302), clock circuit (303), self-checking circuit (304) and jtag interface circuit (305).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320729373.3U CN203606875U (en) | 2013-11-18 | 2013-11-18 | Digital history recorder of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320729373.3U CN203606875U (en) | 2013-11-18 | 2013-11-18 | Digital history recorder of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203606875U true CN203606875U (en) | 2014-05-21 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320729373.3U Expired - Fee Related CN203606875U (en) | 2013-11-18 | 2013-11-18 | Digital history recorder of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203606875U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108510618A (en) * | 2018-03-30 | 2018-09-07 | 安徽航瑞航空动力装备有限公司 | A kind of implementation method of data logger for aviation controller |
| CN109597402A (en) * | 2018-12-07 | 2019-04-09 | 中国航发南方工业有限公司 | The data storage and management device and engine of engine |
| CN109598814A (en) * | 2018-11-21 | 2019-04-09 | 中国航发西安动力控制科技有限公司 | A kind of small aero status data storage system |
| CN109616150A (en) * | 2018-12-07 | 2019-04-12 | 中国航发南方工业有限公司 | The data storage and management device and its power-off protection method of engine |
-
2013
- 2013-11-18 CN CN201320729373.3U patent/CN203606875U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108510618A (en) * | 2018-03-30 | 2018-09-07 | 安徽航瑞航空动力装备有限公司 | A kind of implementation method of data logger for aviation controller |
| CN109598814A (en) * | 2018-11-21 | 2019-04-09 | 中国航发西安动力控制科技有限公司 | A kind of small aero status data storage system |
| CN109597402A (en) * | 2018-12-07 | 2019-04-09 | 中国航发南方工业有限公司 | The data storage and management device and engine of engine |
| CN109616150A (en) * | 2018-12-07 | 2019-04-12 | 中国航发南方工业有限公司 | The data storage and management device and its power-off protection method of engine |
| CN109597402B (en) * | 2018-12-07 | 2020-11-27 | 中国航发南方工业有限公司 | Data storage and management device of engine and engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
|
| CP01 | Change in the name or title of a patent holder | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140521 Termination date: 20201118 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |