CN2869838Y - Vehicle-carried apparatus comprehensive detecting system - Google Patents

Vehicle-carried apparatus comprehensive detecting system Download PDF

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Publication number
CN2869838Y
CN2869838Y CNU2006200400522U CN200620040052U CN2869838Y CN 2869838 Y CN2869838 Y CN 2869838Y CN U2006200400522 U CNU2006200400522 U CN U2006200400522U CN 200620040052 U CN200620040052 U CN 200620040052U CN 2869838 Y CN2869838 Y CN 2869838Y
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CN
China
Prior art keywords
test
detection
card
bus
adapter
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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
Application number
CNU2006200400522U
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Chinese (zh)
Inventor
李世民
张斌
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SHANGHAI AIRLINES ESTABLISHED AIRCRAFT PARTS MAINTENANCE Co
Original Assignee
SHANGHAI AIRLINES ESTABLISHED AIRCRAFT PARTS MAINTENANCE Co
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Priority to CNU2006200400522U priority Critical patent/CN2869838Y/en
Application granted granted Critical
Publication of CN2869838Y publication Critical patent/CN2869838Y/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Abstract

The utility model relates to a skyborne detection device. The past skyborne detection device that is provided by the skyborne equipment manufacturer has a complicated operation, a single function, a long test period, and a high expense, far from meeting the requirement of civil aviation, air force, land navigating, and sea navigating. The utility model is designed to provide an integrative detection system for the large-scale and integrative skyborne equipment, able to provide a complete service, trouble-shooting, and detecting, and able to satisfy manifold types such as Boeing and Airbus, etc. The utility model provides an airborne equipment comprehensive detection system which is also called airborne aircraft instrument exclusive-use detection device. The utility model comprises a main casing, a terminal board, a test adapter and an interface receptacle measured piece, etc. which can complete the service, trouble-shooting and performance detecting of the aircraft instruments of a plurality of aircraft types, guaranteeing a safety of plane, and a high efficiency of flying, furthermore, improving domestic service ability greatly, economizing a great deal foreign exchange, and having a favorable social and economic benefits.

Description

The airborne equipment comprehensive detection system
Technical field
The utility model relates to a kind of checkout equipment, relates in particular to a kind of airborne equipment comprehensive detection system.
Background technology
The serviceability rate of airborne equipment is the key factor that ensures the aircraft normal flight.Past is that airborne equipment production firm directly provides relevant detection equipment always, and main product is the manual checkout equipment of single cover still.The major defect that exists in the use is that complicated operation, function singleness, test period are long, and expense is higher, can not satisfy the demand of present civil aviaton, air force, Lu Hang, Hainan Airlines far away.
The airborne equipment comprehensive detection system at home and abroad is an emerging project, and its purpose is exactly the problems that exist in the checkout equipment of will solving over.At present, resemble large-scale synthesis checkout equipments such as ATEC6000 in the world, it adopts the vxi bus technology, uses supporting software, the detection of finishing multiple airborne equipment that can be automatic/semi-automatic.Advantage is that test item is many, efficient is high, but also have price high, the maintenance troubleshooting in problems such as service efficiency is low.At home, the development work of comprehensive detection system is in the starting stage.
Summary of the invention
The purpose of this utility model is to provide the airborne equipment comprehensive detection system of a kind of maximization, synthesization, can complete maintenance, troubleshooting and detection is provided and can satisfy different types of machines such as Boeing, visitor airborne equipment.
The utility model provides a kind of airborne equipment comprehensive detection system, also claims airborne instrument special inspecting equipment, and the main technology that adopts has ARINC429 bus, ARINC568 bus, PXI bus, vxi bus etc.Concrete tested object has piece number: 2083-11-1,2055/56/57-01-1,4034559-901, H341ANM1, H150AKM1, H321AKM1, H140ATM1,4019700,4038930,777-1397-XXX etc.This integrated test system is simulated its required ARINC429 bus signals, ARINC568 bus signals, synchronous/as to revolve varied angle signal, discrete magnitude signal etc., and is received the various signals of handling instrument output according to the testing requirement of UUT.Adopt interactive operation interface to finish automatic (semi-automatic) test function of mode control panel system.
The utility model been has mainly has been researched and developed automatic control, has been detected the maintenance process of software systems, ARINC429 bus signals simulator, ARINC568 bus signals simulator, the exploitation of synchronizing signal simulator, automatic control circuit and airborne instrument.
The utility model provides a kind of airborne equipment comprehensive detection system, and it comprises mainframe box, terminal strip, test adapter and interface socket measured piece etc.; Mainframe box comprises keyboard, mouse, central processing unit, display, printer, ARINC429 bus card, ARINC568 bus card, SDDS synchronizing signal card etc.; Terminal strip comprises bus adapter etc.; Test adapter comprises signal adapter circuit (relay switch array) and modulate circuit; Keyboard wherein, mouse, display, printer, ARINC429 bus card, ARINC568 bus card, SDDS synchronizing signal card all link to each other with central processing unit, ARINC429 bus card wherein, ARINC568 bus card, SDDS synchronizing signal card link to each other with bus adapter again, bus adapter links to each other with test adapter, and test adapter links to each other with the interface socket measured piece.
ARINC429 bus card wherein, ARINC568 bus card, SDDS synchronizing signal cartoon are crossed the multiple-grooved telescopic backboard and are linked to each other with central processing unit.
For the signal that guarantees system's distinct interface, cable all can insert general purpose test equipment and need not to change the general purpose test equipment circuit, test macro adopts test adapter to connect measurand and general purpose test equipment.Test adapter comprises signal adapter circuit (relay switch array) and modulate circuit, the signal adapter circuit switches by relay, each parts of system both can be interconnected by former complete machine connected mode, arbitrary parts can be inserted test circuit separately again.When switch arrays n-1 and switch arrays n '-1 closure and switch arrays n-2 and switch arrays n '-2 open, can directly connect by one group of lead between parts n and the n ', by this mode each parts is connected by former complete machine connected mode.If when the switch arrays n-1 of only closed certain parts n and switch arrays n-2, the cable of these parts is connected to the signal adapter output interface by the signal adapter input interface, can make the interface of unit under test be connected to modulate circuit by universal test interface by the pilot relay action like this.Modulate circuit will be adjusted to suitable amplitude from the straight signal of friendship of the next varying level of special test interface, send into circuitry for signal measurement.
Interface socket measured piece: be 2083-11-1,2055/56/57-01-1,4034559-901, H341ANM1, H150AKM1, H321AKM1, H140ATM1,4019700,4038930,777-1397-XXX etc.
The utility model matches with software systems in use, and software systems mainly are made up of testing apparatus driving, test execution control, self check and modules such as self calibration equipment, subsidiary function.Testing apparatus drives: comprise the programming of driver of modules, softpanel and the soft interface of all plug and play integrated circuit boards, for making things convenient for system extension, also reserve some test drivers and soft interface.Test execution control: be that testing apparatus and flow process are controlled, load pumping signal, and point out test process and test result in the process of implementation.Self check and self calibration equipment: be used for test macro itself is carried out self check (BIT) and calibration.The utility model uses switch matrix to provide each test and excitation source to the link circuit between the module related measurement devices.1. self check and calibration process: the test and excitation source of drive system, export specific self-test signal, measure by the measuring equipment of response, thereby whether the check system function is normal, and carries out self calibration.2. Measuring and testing interface: switch matrix provides each driving source of system and the testing apparatus interface with external unit, thereby carries out Measuring and testing by external canonical measure equipment and standard signal source.Modules such as subsidiary function: mainly comprise help document etc.
The beneficial effects of the utility model are: the utility model can be finished maintenance, troubleshooting, the Performance Detection of instrument, its advanced person's automatic control function, sophisticated software system, guaranteed real-time, accurate, the accurate detection of airborne instrument, the utlity model has self-checking function, can guarantee that system self works reliably.Use airborne equipment comprehensive detection system of the present utility model, can improve maintenance, detection efficiency, guarantee the integrity of army, civil aviaton's equipment, ensure aircraft safety, high efficiency flight.Native system extends to Civil Aviation System, system of air force or the like.Can satisfy air unit, maintenance depot of air force, civil aviaton's engineering, civil aviaton's boat and repair the maintenance demand of unit such as factory airborne instrument.Particularly airborne instrument extensively equips our troops, the various aircraft of civil aviaton, is airborne High Value Unit, and annual maintenance cost is very high.Past is sent in a large number and repaiies abroad, cost of repairs height, and the cycle is long, repaiies the back service and is difficult to guarantee.Of the present utility model succeeding in developing can be improved domestic maintainability, saves a large amount of foreign exchanges, has good society and economic benefit.
Description of drawings
Fig. 1 is the system software block diagram
Fig. 2 is a software flow pattern
Fig. 3 is an instrument test system configurations schematic diagram
Fig. 4 is the structural representation of test adapter
Embodiment
Test product by the test of this testing apparatus has: the test of 2055/56/57-01-1,2083-11-1,4034559-901, H341ANM1, H150AKM1, H321AKM1, H140ATM1,4019700,4038930,777-1397-XXX.
After entering system test software, at first enter from detecting: by ARINC568 bus card, switch matrix, digital I/O card, ARINC429 I/O card, SDDS I/O card etc., and call testing software self-checking function module, realize the detection certainly of test macro, and after the System self-test success, automatically access main test procedure,, finish test automatically with reference to the test procedure of instrument CMM.
Embodiment 1
When measured piece 777-1397-XXX carries out fault diagnosis with the test procedure of HIS (the Horizontal Situation Indicator) CMM of instrument integrated test system, its failure code is shown as:
The input of 1 road ARINC568 data, the output of 2 road ARINC568 data have fault.
With reference to the requirement of CMM test procedure, software calls the ARINC568 function by the ARINC568 bus controller card, make test product 777-1397-XX very quick service return to work do normal.
Embodiment 2
When measured piece 4034559-901 carries out fault diagnosis with the test procedure of ADI (Attitude5Director Indicator) CMM of instrument integrated test system, its failure code is shown as:
The input of 2 tunnel synchronizing signals, the output of 1 tunnel synchronizing signal has fault.
When reprocessing, according to the CMM test procedure, software transfer synchronizing signal transmitting-receiving control function, and under the cooperation of synchronizing signal card feeding-discharging, realize the synchronizing signal input of instrument and the function that output is tested simultaneously.What make that test product 4034559-901 guarantees both quality and quantity finishes maintenance task on time, and reaches the requirement of instrument CMM.
Embodiment 3
When measured piece 2083-11-1 carries out fault diagnosis with the test procedure of " DME sends test " CMM of instrument integrated test system, its failure code is shown as:
1 road ARINC429 input, 1 road ARINC429 export fault.
With the detection of desired ARINC429 input/output signal in the CMM test procedure, testing software imports by switch matrix by the ARINC429 bus card control program signal that instrument is required, receives the ARINC429 signal of test product output simultaneously.Reprocess product thereby finish very soon, satisfy the requirement of instrument CMM.
Embodiment 4
When the test procedure of " horizon instrument test " CMM of measured piece 4019700 usefulness instrument combined test stands carries out fault diagnosis, failure code is shown as:
The fault of the output of 2 road GND/OPEN discrete magnitudes, the output of 1 road 28VDC/OPEN discrete magnitude, 2 road 28/19/12VDC discrete magnitude outputs etc.
Adopt the detection of desired discrete magnitude output signal in the CMM test procedure etc., testing software imports by switch matrix by the DI/O control program signal that instrument is required, finishes the automatic detection of output signal simultaneously.Make measured piece 4019700 fulfil the task of reprocessing ahead of schedule.
By the example of above several test products test, comprehensive, advanced, the trouble diagnosibility that has embodied the instrument integrated test system by force, the automaticity advantages of higher, test result satisfies the requirement of CMM fully.

Claims (2)

1, a kind of airborne equipment comprehensive detection system is characterized in that it comprises mainframe box, terminal strip, test adapter and interface socket measured piece; Mainframe box comprises keyboard, mouse, central processing unit, display, printer, ARINC429 bus card, ARINC568 bus card, SDDS synchronizing signal card; Terminal strip comprises bus adapter; Test adapter comprises signal adapter circuit and modulate circuit; Keyboard wherein, mouse, display, printer, ARINC429 bus card, ARINC568 bus card, SDDS synchronizing signal card all link to each other with central processing unit, ARINC429 bus card wherein, ARINC568 bus card, SDDS synchronizing signal card link to each other with bus adapter again, bus adapter links to each other with test adapter, and test adapter links to each other with the interface socket measured piece.
2, a kind of airborne equipment comprehensive detection system according to claim 1 is characterized in that wherein ARINC429 bus card, ARINC568 bus card, SDDS synchronizing signal cartoon cross the multiple-grooved telescopic backboard and link to each other with central processing unit.
CNU2006200400522U 2006-03-09 2006-03-09 Vehicle-carried apparatus comprehensive detecting system Expired - Fee Related CN2869838Y (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CNU2006200400522U CN2869838Y (en) 2006-03-09 2006-03-09 Vehicle-carried apparatus comprehensive detecting system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CNU2006200400522U CN2869838Y (en) 2006-03-09 2006-03-09 Vehicle-carried apparatus comprehensive detecting system

Publications (1)

Publication Number Publication Date
CN2869838Y true CN2869838Y (en) 2007-02-14

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CNU2006200400522U Expired - Fee Related CN2869838Y (en) 2006-03-09 2006-03-09 Vehicle-carried apparatus comprehensive detecting system

Country Status (1)

Country Link
CN (1) CN2869838Y (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102508814A (en) * 2011-09-19 2012-06-20 北京航空航天大学 Extendable core system for universal avionics system
CN105913754A (en) * 2016-06-21 2016-08-31 中国民航大学 Circuit-level virtual maintenance teaching platform for aviation airborne electronic equipment
CN106200622A (en) * 2016-08-18 2016-12-07 四川泛华航空仪表电器有限公司 Fuel On Board observing and controlling online detection instrument

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102508814A (en) * 2011-09-19 2012-06-20 北京航空航天大学 Extendable core system for universal avionics system
CN102508814B (en) * 2011-09-19 2014-07-02 北京航空航天大学 Extendable core system for universal avionics system
CN105913754A (en) * 2016-06-21 2016-08-31 中国民航大学 Circuit-level virtual maintenance teaching platform for aviation airborne electronic equipment
CN106200622A (en) * 2016-08-18 2016-12-07 四川泛华航空仪表电器有限公司 Fuel On Board observing and controlling online detection instrument

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CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20070214

Termination date: 20150309

EXPY Termination of patent right or utility model