CN201072597Y - Automatic detection instrument for aviation electronic flight instrument - Google Patents
Automatic detection instrument for aviation electronic flight instrument Download PDFInfo
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- CN201072597Y CN201072597Y CNU2007200722696U CN200720072269U CN201072597Y CN 201072597 Y CN201072597 Y CN 201072597Y CN U2007200722696 U CNU2007200722696 U CN U2007200722696U CN 200720072269 U CN200720072269 U CN 200720072269U CN 201072597 Y CN201072597 Y CN 201072597Y
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Abstract
The utility model relates to an automatic detection instrument for an avionics flight instrument, which comprises an industrial control computer, a signal simulating and controlling device, an interface device, a power supply device and a monitoring device; the industrial control computer is communicated and connected with the signal simulating and controlling device, the signal simulating and controlling device and the power supply device are both communicated and connected with the interface device, the monitoring device is communicated and connected with the industrial control computer, the signal simulating and controlling device and the interface device. Compared with the prior art, the utility model has the advantages of simple operation, stable and reliable working performance and convenient maintenance, etc.
Description
Technical field
The utility model relates to the instrument pick-up unit, particularly relates to a kind of automatic tester that is used for the aviation electronics flying instruments.
Background technology
Electronic Flight Instrument is the aircraft airborne equipment of offshore company's development and production, but domestic present stage do not have the relevant detection service equipment, make and check before the instrument installation and the prophylactic repair maintenance can't normally be carried out.The fault part that occurs in directly causing using can only return offshore company's diagnosis or repair.Increase cost, production cycle greatly and influenced the attendance rate of aircraft.
The ATS400 aviation proving installation of U.S. Goodrich company can be carried out Electronic Flight Instrument and detect.But too numerous and diverse because of its hardware, software is more outmoded, belongs to semi-automatic product, and operation is inconvenience very.
Summary of the invention
The purpose of this utility model is exactly that a kind of simple to operate, stable and reliable working performance, the automatic tester that is used for the aviation electronics flying instruments easy to maintenance are provided in order to overcome the defective that above-mentioned prior art exists.
The purpose of this utility model can be achieved through the following technical solutions: the automatic tester that is used for the aviation electronics flying instruments, it is characterized in that, comprise industrial control computer, signal imitation and control device, interface arrangement, electric supply installation, monitoring device, described industrial control computer is connected with signal imitation and control device communication, described signal imitation and control device, electric supply installation all are connected with the interface arrangement communication, and described monitoring device is connected with industrial control computer, signal imitation and control device, interface arrangement communication.
Be inserted with 488 communication modules, PXI communication module one, 429 communication modules in the bus slot of described industrial control computer, described 488 communication modules, PXI communication module one all are inserted in the PCI slot of industrial control computer, and described 429 communication modules are inserted in the ISA slot of industrial control computer; Described signal imitation and control device comprise PXI communication module two, D/A module, multi-way switch module, selsyn module, relay module, PXI cabinet, and described PXI communication module two, D/A module, multi-way switch module, selsyn module, relay module interconnect by the PXI bus in the PXI cabinet; Described electric supply installation comprises power control, ups power, intermediate frequency power supply, and described ups power, intermediate frequency power supply are connected with power control respectively, and this power control is connected with the feeder ear of interface arrangement; Described monitoring device comprises digital multimeter, oscillograph.
488 communication modules in the described industrial control computer are connected with digital multimeter by communication cable.
PXI communication module one in the described industrial control computer is connected with PXI communication module two in signal imitation and the control device by communication cable.
429 communication modules in the described industrial control computer are connected with relay module in signal imitation and the control device by communication cable.
Relay module in described signal imitation and the control device is connected with digital multimeter by communication cable.
Described oscillograph is connected with interface arrangement by communication cable.
Compared with prior art, the utlity model has following advantage:
One, simple to operation: as to adopt WINDOWS operating system, perfect operation interface, friendly dialog box.Can select multiple trace routine and execution pattern, simulation model can be used to user training or software debugging; Automatic mode can be used to detect; The diagnostic mode major failure is isolated and fault analysis; Development mode is applicable to the trace routine exploitation.
Two, reliable operation: utility model takes into full account the functional reliability of automatic checkout system, guarantees that detected device parameter is errorless, index is accurate, and can not damage equipment under test, takes corresponding measure from hardware, software.Hardware uses the PXI bussing technique, and is embedded, can expand the standalone feature module, mainly contains ARINC429 module, three-phase synchronizer module, DC quantity module and switching value module.All output analog quantity parameters, status signals have only normally, accurately after, could export through relay control; Carry out modularized program on the software, be divided into user command executive routine, data base administrator, resource allocator, device driver and trace routine collection.Real time monitoring function in addition, by digital watch, SDC module, Rx passage, real-time EF monitoring S40 automatic checkout system duty.
Three, stable performance: utility model is considered environment for use, service condition, and hardware aspect components and parts process is screened and test, and constructs in strict accordance with technology; The various modes operation of software aspect, comprehensive test, the checking of equipment joint-trial.
Four, easy to maintenance: utility model has self-checking function.When the user can or think that detection system has fault in the equipment calibrating, the operation self-check program, the automatic prompt facility module of system or interface OK or FAIL, the user is as long as check, get rid of or change defective device such as module, interface according to prompting.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
Wherein: 1-industrial control computer, 2-488 communication module, 3-PXI communication module one, the 4-429 communication module, 5-signal imitation and control device, 6-PXI communication module two, the 7-D/A module, 8-multi-way switch module, 9-selsyn module, the 10-relay module, 11-interface arrangement, 12-power control, the 13-UPS power supply, the 14-intermediate frequency power supply, 15-digital multimeter, 16-oscillograph.
Embodiment
The utility model is described in further detail below in conjunction with accompanying drawing.
As shown in Figure 1, the automatic tester that is used for the aviation electronics flying instruments, comprise industrial control computer 1, signal imitation and control device 5, interface arrangement 11, electric supply installation, monitoring device, described industrial control computer 1 is connected with signal imitation and control device 5 communications, described signal imitation and control device 5, electric supply installation all are connected with interface arrangement 11 communications, and described monitoring device is connected with industrial control computer 1, signal imitation and control device 5, interface arrangement 11 communications.
Be inserted with 488 communication modules 2, PXI communication module one 3,429 communication modules 4 in the bus slot of described industrial control computer 1, described 488 communication modules 2, PXI communication module 1 all are inserted in the PCI slot of industrial control computer 1, and described 429 communication modules 4 are inserted in the ISA slot of industrial control computer 1; Described signal imitation and control device 5 comprise PXI communication module 26, D/A module 7, multi-way switch module 8, selsyn module 9, relay module 10, PXI cabinet, and described PXI communication module 26, D/A module 7, multi-way switch module 8, selsyn module 9, relay module 10 interconnect by the PXI bus in the PXI cabinet; Described electric supply installation comprises power control 12, ups power 13, intermediate frequency power supply 14, and described ups power 13, intermediate frequency power supply 14 are connected with power control 12 respectively, and this power control 12 is connected with the feeder ear of interface arrangement 11; Described monitoring device comprises digital multimeter 15, oscillograph 16; 488 communication modules 2 in the described industrial control computer 1 are connected with digital multimeter 15 by communication cable; PXI communication module 1 in the described industrial control computer is connected with PXI communication module 26 in signal imitation and the control device by communication cable; 429 communication modules 4 in the described industrial control computer are connected with relay module 10 in signal imitation and the control device by communication cable; Relay module 10 in described signal imitation and the control device is connected with digital multimeter 15 by communication cable; Described oscillograph 16 is connected with interface arrangement 11 by communication cable.
When the aviation electronics flight instrument system detects, the power supply of interface arrangement control EFIS.By digital display meter or digital multimeter, carry out video voltage measurement and effective status and measure; Oscillograph carries out vision signal and measures.
When automatic or single step detected, by industrial computer operation trace routine, crosslinked airborne equipment and sensor dynamic or quiescent operation state and parameter were simulated in the work of control PXI apparatus function module.Input channel is with digital quantity, ac analog, DC analogue quantity and switching value signal, flow to EFIS, control and show AHS heading and attitude system, ADF wireless compass system, VOR landing system, ILS instrument landing system (ILS), MLS microwave landing system (MLS), TACAN navigational system, RNAV navigational system, LNAV/VNAV navigational system, FMS flight management system, HOVER bank position, HOMING make a return voyage state and CABLE state respective picture and duty.According to ED461 display and ED462 display picture displayed, state, detect the flying instruments serviceability, analyze, isolate cross-linking apparatus and SG465 symbol generator, ED461 display, ED462 display components fault; Digital multimeter can be used to carry out video voltage and measures and System self-test; Power control is switched on or switched off civil power AC220V power supply, and DC 28V and AC 26V 400Hz power supply are provided; Interface arrangement provides the input/output signal passage and measures interface; The PXI cabinet is equipped with selsyn module, 8 tunnel 16 analog modules, multi-way switch module, SPST relay module, and three-phase synchronizer signal, DC quantity signal and gauge tap amount signal are provided; Install software and ARINC429 module on the industrial computer, the system core provides ARINC 429 signals.
Present embodiment adopts HP34401A digital multimeter, KTS-8341 power control, KTS-8342 interface arrangement, WS-855AW industrial computer, 2670 PXI cabinets, C1K ups power, KT-26 intermediate frequency power supply and FLUKE196B oscillograph to form.
Wherein KTS-8341 power control, C1K ups power, the major control of KT-26 intermediate frequency power supply, provide the AC 220V of system, DC 28V and AC 26V 400Hz power supply.
WS-855AW industrial computer, 2670 PXI cabinets, KTS-8342 interface arrangement are the automatic checkout system main portions.WS-855AW industrial computer and 2670 PXI cabinets connect by the pci bus bridging; 2670 PXI cabinets are connected by interface I/O signalling channel with the KTS-8342 interface arrangement.488 communication modules, PXI communication module, 429 modules are mounted in the industrial computer bus slot in the WS-855AW industrial computer; The PXI cabinet communication module of installing in the 2670 PXI cabinets, D/A module, multi-way switch module, selsyn module I, selsyn module II, relay module I, relay module II connect by the PXI internal bus, and D/A module, multi-way switch module, selsyn module I, selsyn module II, 429 module I/O are sent I/O signalling channel through relay module I, relay module II control.
The HP34401A digital multimeter is connected with the AS-855AW industrial computer by 488 communication cables, by industrial computer control survey or monitoring video voltage; The FLUKE196B oscillograph links to each other with the KTS-8342 interface arrangement, mainly measures or monitoring video signal.
When flying instruments detects automatically, the DC28V of energized control device 12, AC26V power switch, intermediate frequency power supply 14 output AC26V are to power control 12, power control 12 output DC28V, AC26V are to interface arrangement 20, connect DC28V, the AC26V power switch of interface arrangement 20, Electronic Flight Instrument is given in power supply through sense channel (being telecommunication cable); The operation autotest, control 488 communication modules 2, PXI communication module 3,429 modules 4, by 488 communication cables 2, ARINC429 signalling channel (telecommunication cable), pci bus bridge (telecommunication cable), PXI cabinet communication module 6, drive the D/A module 7 of PXI cabinet, multi-way switch module 8, selsyn module I and selsyn module II 9, through relay passage I and relay passage II 10 controls, from I/O signalling channel (communication cable), output to interface arrangement 11, pass through sense channel then, be input to the receiving interface of EFIS, EFIS shows respective picture and state according to the signal data and the state of a control that receive through resolving.Simultaneously, data such as the video voltage of EFIS, vision signal, by sense channel, interface arrangement 11, available oscillograph 16 measures or I/O signalling channel, 15 measurements of relay passage I conveying digital multimeter or monitoring.
When the detection system self check with when safeguarding, DC28V on the energized control device 12, the AC26V power switch, intermediate frequency power supply 14 output AC26V are to power control 12, power control 12 output DC28V, AC26V is to interface arrangement 11, connect the DC28V of interface arrangement 11, the AC26V power switch, the operation self-check program, control 488 communication modules 2, PXI communication module 3,429 modules 4, by 488 communication cables 2, the ARINC429 signalling channel, the pci bus bridge, PXI communication module 6, drive the D/A module 7 of PXI cabinet, multi-way switch module 8, selsyn module I and selsyn module II9, through relay passage I and relay passage II 10 controls, from the I/O signalling channel, output to interface arrangement 11, form closed loop, process I/O signalling channel return relay passage I and relay passage II 10 are by selsyn module I and selsyn module II 9, digital multimeter 15 and ARINC429 signalling channel, 429 modules 4 are measured, reading of data is finished the detection system self check, safeguard.
Claims (7)
1. the automatic tester that is used for the aviation electronics flying instruments, it is characterized in that, comprise industrial control computer, signal imitation and control device, interface arrangement, electric supply installation, monitoring device, described industrial control computer is connected with signal imitation and control device communication, described signal imitation and control device, electric supply installation all are connected with the interface arrangement communication, and described monitoring device is connected with industrial control computer, signal imitation and control device, interface arrangement communication.
2. the automatic tester that is used for the aviation electronics flying instruments according to claim 1, it is characterized in that, be inserted with 488 communication modules, PXI communication module one, 429 communication modules in the bus slot of described industrial control computer, described 488 communication modules, PXI communication module one all are inserted in the PCI slot of industrial control computer, and described 429 communication modules are inserted in the ISA slot of industrial control computer; Described signal imitation and control device comprise PXI communication module two, D/A module, multi-way switch module, selsyn module, relay module, PXI cabinet, and described PXI communication module two, D/A module, multi-way switch module, selsyn module, relay module interconnect by the PXI bus in the PXI cabinet; Described electric supply installation comprises power control, ups power, intermediate frequency power supply, and described ups power, intermediate frequency power supply are connected with power control respectively, and this power control is connected with the feeder ear of interface arrangement; Described monitoring device comprises digital multimeter, oscillograph.
3. the automatic tester that is used for the aviation electronics flying instruments according to claim 2 is characterized in that, 488 communication modules in the described industrial control computer are connected with digital multimeter by communication cable.
4. the automatic tester that is used for the aviation electronics flying instruments according to claim 2 is characterized in that, the PXI communication module one in the described industrial control computer is connected with PXI communication module two in signal imitation and the control device by communication cable.
5. the automatic tester that is used for the aviation electronics flying instruments according to claim 2 is characterized in that, 429 communication modules in the described industrial control computer are connected with relay module in signal imitation and the control device by communication cable.
6. the automatic tester that is used for the aviation electronics flying instruments according to claim 2 is characterized in that, the relay module in described signal imitation and the control device is connected with digital multimeter by communication cable.
7. the automatic tester that is used for the aviation electronics flying instruments according to claim 2 is characterized in that described oscillograph is connected with interface arrangement by communication cable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200722696U CN201072597Y (en) | 2007-07-06 | 2007-07-06 | Automatic detection instrument for aviation electronic flight instrument |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200722696U CN201072597Y (en) | 2007-07-06 | 2007-07-06 | Automatic detection instrument for aviation electronic flight instrument |
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| CN201072597Y true CN201072597Y (en) | 2008-06-11 |
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| CNU2007200722696U Expired - Fee Related CN201072597Y (en) | 2007-07-06 | 2007-07-06 | Automatic detection instrument for aviation electronic flight instrument |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101980041A (en) * | 2010-10-25 | 2011-02-23 | 南车戚墅堰机车有限公司 | Intelligent calibration system for instrument |
| CN102829797A (en) * | 2012-08-22 | 2012-12-19 | 广州航新航空科技股份有限公司 | PXI synthetic instrument-based TACAN simulator |
| CN102102990B (en) * | 2009-12-18 | 2013-06-19 | 上海凯迪克航空工程技术有限公司 | Direct-current sine and cosine azimuth indicator |
| CN103454522A (en) * | 2013-08-08 | 2013-12-18 | 中国人民解放军总装备部军械技术研究所 | Electronic replacement part technology state automatic detection system and method based on PXI bus |
| CN103616560A (en) * | 2013-11-29 | 2014-03-05 | 中国航空无线电电子研究所 | Automatic power consumption parameter testing device and method applied to avionics device |
| CN104808087A (en) * | 2015-05-05 | 2015-07-29 | 江西洪都航空工业集团有限责任公司 | Power supply testing system for onboard advanced training equipment |
| CN105099816A (en) * | 2015-07-02 | 2015-11-25 | 北京航空航天大学 | Universal comprehensive detection device and method for aviation mission electronic systems |
| CN105137960A (en) * | 2015-07-24 | 2015-12-09 | 余江 | Small multi-rotor-type unmanned aerial equipment and self detection method thereof |
| CN109733643A (en) * | 2019-02-22 | 2019-05-10 | 中国人民解放军空军工程大学航空机务士官学校 | A kind of aircraft navigation attitude device test system |
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2007
- 2007-07-06 CN CNU2007200722696U patent/CN201072597Y/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102102990B (en) * | 2009-12-18 | 2013-06-19 | 上海凯迪克航空工程技术有限公司 | Direct-current sine and cosine azimuth indicator |
| CN101980041A (en) * | 2010-10-25 | 2011-02-23 | 南车戚墅堰机车有限公司 | Intelligent calibration system for instrument |
| CN102829797B (en) * | 2012-08-22 | 2015-04-15 | 广州航新航空科技股份有限公司 | PXI synthetic instrument-based TACAN simulator |
| CN102829797A (en) * | 2012-08-22 | 2012-12-19 | 广州航新航空科技股份有限公司 | PXI synthetic instrument-based TACAN simulator |
| CN103454522B (en) * | 2013-08-08 | 2016-02-03 | 中国人民解放军总装备部军械技术研究所 | Based on electronics spare part state of the art automatic checkout system and the method for PXI bus |
| CN103454522A (en) * | 2013-08-08 | 2013-12-18 | 中国人民解放军总装备部军械技术研究所 | Electronic replacement part technology state automatic detection system and method based on PXI bus |
| CN103616560A (en) * | 2013-11-29 | 2014-03-05 | 中国航空无线电电子研究所 | Automatic power consumption parameter testing device and method applied to avionics device |
| CN104808087A (en) * | 2015-05-05 | 2015-07-29 | 江西洪都航空工业集团有限责任公司 | Power supply testing system for onboard advanced training equipment |
| CN105099816A (en) * | 2015-07-02 | 2015-11-25 | 北京航空航天大学 | Universal comprehensive detection device and method for aviation mission electronic systems |
| CN105099816B (en) * | 2015-07-02 | 2018-08-24 | 北京航空航天大学 | A kind of aviation mission electronic system general comprehensive detection device and detection method |
| CN105137960A (en) * | 2015-07-24 | 2015-12-09 | 余江 | Small multi-rotor-type unmanned aerial equipment and self detection method thereof |
| CN105137960B (en) * | 2015-07-24 | 2018-03-27 | 余江 | A kind of small-sized more rotary wind type unmanned flight equipment and its self checking method |
| CN109733643A (en) * | 2019-02-22 | 2019-05-10 | 中国人民解放军空军工程大学航空机务士官学校 | A kind of aircraft navigation attitude device test system |
| CN109733643B (en) * | 2019-02-22 | 2024-04-02 | 中国人民解放军空军工程大学航空机务士官学校 | Airplane attitude equipment testing system |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080611 Termination date: 20100706 |