CN102981474A - Central control unit for aircraft's skin digitizing multi-point flexible tool - Google Patents
Central control unit for aircraft's skin digitizing multi-point flexible tool Download PDFInfo
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- CN102981474A CN102981474A CN2012104811478A CN201210481147A CN102981474A CN 102981474 A CN102981474 A CN 102981474A CN 2012104811478 A CN2012104811478 A CN 2012104811478A CN 201210481147 A CN201210481147 A CN 201210481147A CN 102981474 A CN102981474 A CN 102981474A
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- control unit
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- skin
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Abstract
The invention discloses a central control unit for an aircraft's skin digitizing multi-point flexible tool. The central control unit comprises a casing in a sealed and shielded structure, an alternating current (AC)/direct current (DC) power supply module and a control circuit, the AC/DC power supply module and the control circuit are arranged in the casing, the control circuit comprises a 32-bit microprocessor, the 32-bit microprocessor is in a communication connection with an upper computer through an asynchronous serial port and with a plurality of communication modules respectively through a synchronous serial port, the plurality of communication modules are in the communication connection through the synchronous serial port, and the plurality of communication modules are in the communication connection with corresponding motor drive controllers respectively through six paths of controller area network (CAN) buses. The central control unit for the aircraft's skin digitizing multi-point flexible tool has the advantages that high control accuracy and control real-time performance can be achieved in an industrial site with numerous control parameters and data interfaces and extremely complicated electromagnetic interference environments, and the central control unit is economical.
Description
Technical field
The present invention relates to central controller, especially relate to aircraft skin digitizing flexible multipoint tool central controller.
Background technology
Aircraft skin digitizing flexible multipoint tool is to large thin-wall part tool for processing, in the thin-walled parts of aircraft is made, no matter be the heavy parts productions such as wallboard class part or fuselage wing, until the finally docking of each large parts, all use a large amount of flexible frocks, greatly improved production efficiency, shortened the manufacturing cycle, reduce the aircraft manufacturing cost, improved product quality.At present, in aircraft skin processing adopt establishment simple programs control hydraulic systems to realize in the anchor clamps location and step up, the deficiency of its existence is that Flexible Control is relatively poor, and this has just limited the kind scope to covering processing.
Summary of the invention
The object of the invention is to provide a kind of aircraft skin digitizing flexible multipoint tool central controller applied widely.
For achieving the above object, the present invention takes following technical proposals:
Aircraft skin digitizing flexible multipoint tool central controller of the present invention comprises the housing of closed shield structure, is arranged on AC/DC power module and control circuit in the described housing; Described control circuit comprises 32-bit microprocessor, and described 32-bit microprocessor is connected with upper machine communication by asynchronous serial port, and is connected with a plurality of communication module communications respectively by synchronous serial interface; Connect by the synchronous serial interface communication between described a plurality of communication module; A plurality of communication modules are respectively by 6 road CAN buses and corresponding motor drive controller communication connection.
Beneficial effect major embodiment of the present invention is: the industry spot of and electromagnetic interference environment very complex more at control parameter and data-interface, also can realize higher precise control and realtime control, and have good economy.
Description of drawings
Fig. 1 is contour structures synoptic diagram of the present invention.
Fig. 2 is schematic block circuit diagram of the present invention.
Fig. 3 is program operation logic block diagram of the present invention.
Embodiment
As shown in Figure 1, 2, aircraft skin digitizing flexible multipoint tool central controller of the present invention comprises the housing 1 of closed shield structure, is arranged on AC/DC power module and control circuit in the described housing 1; Described control circuit comprises 32-bit microprocessor (adopting SI8421 electromagnetic isolation chip), and described 32-bit microprocessor is connected with upper machine communication by asynchronous serial port, and is connected with four communication module communications respectively by synchronous serial interface; Connect by the synchronous serial interface communication between described four communication modules; These four communication modules are respectively by 6 road CAN buses and corresponding motor drive controller communication connection.
As shown in Figure 3, carry out self check after system powers on, by the address that each communication module is obtained in self check, go again to carry out corresponding steering order after the deciphering address information; 32-bit microprocessor is understood host computer information, and sends instruction to each communication module; After four communication modules receive instruction, behind extraction rate and the position signalling, send corresponding motor drive controller to by 6 road CAN buses and carry out.
Claims (1)
1. aircraft skin digitizing flexible multipoint tool central controller comprises the housing (1) of closed shield structure being arranged on AC/DC power module and control circuit in the described housing (1); It is characterized in that: described control circuit comprises 32-bit microprocessor, and described 32-bit microprocessor is connected with upper machine communication by asynchronous serial port, and is connected with a plurality of communication module communications respectively by synchronous serial interface; Connect by the synchronous serial interface communication between described a plurality of communication module; A plurality of communication modules are respectively by 6 road CAN buses and corresponding motor drive controller communication connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104811478A CN102981474A (en) | 2012-11-23 | 2012-11-23 | Central control unit for aircraft's skin digitizing multi-point flexible tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104811478A CN102981474A (en) | 2012-11-23 | 2012-11-23 | Central control unit for aircraft's skin digitizing multi-point flexible tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102981474A true CN102981474A (en) | 2013-03-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012104811478A Pending CN102981474A (en) | 2012-11-23 | 2012-11-23 | Central control unit for aircraft's skin digitizing multi-point flexible tool |
Country Status (1)
| Country | Link |
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| CN (1) | CN102981474A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010042306A1 (en) * | 1998-03-12 | 2001-11-22 | Robert B. Crocker | Flexible fixture system and method |
| CN101339427A (en) * | 2008-08-13 | 2009-01-07 | 北京航空航天大学 | Multiple DC motor shape adjusting control unit for multi-point mould shape adjustment |
| CN203012460U (en) * | 2012-11-23 | 2013-06-19 | 郑州飞机装备有限责任公司 | Central controller for digital multi-point flexible tool of airplane skin |
-
2012
- 2012-11-23 CN CN2012104811478A patent/CN102981474A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010042306A1 (en) * | 1998-03-12 | 2001-11-22 | Robert B. Crocker | Flexible fixture system and method |
| CN101339427A (en) * | 2008-08-13 | 2009-01-07 | 北京航空航天大学 | Multiple DC motor shape adjusting control unit for multi-point mould shape adjustment |
| CN203012460U (en) * | 2012-11-23 | 2013-06-19 | 郑州飞机装备有限责任公司 | Central controller for digital multi-point flexible tool of airplane skin |
Non-Patent Citations (3)
| Title |
|---|
| 徐晓东等: "基于MCP2515的多路CAN总线接口及驱动程序设计", 《应用天地》 * |
| 邹方: "飞机数字化柔性装配关键技术及其发展", 《航空制造技术》 * |
| 郇极等: "CNC SYSTEM OF FLEXIBLE FIXTURE IN AIRCARAFT COMPONENT MANUFACTURING AND ASSEMBLY", 《TRANSACTIONS OF UNIVERSITY OF AERONAUTICS & ASTRONAUTICS》 * |
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Application publication date: 20130320 |