CN203070097U - Comprehensive test device based on aviation flight management control display assembly - Google Patents
Comprehensive test device based on aviation flight management control display assembly Download PDFInfo
- Publication number
- CN203070097U CN203070097U CN 201320070949 CN201320070949U CN203070097U CN 203070097 U CN203070097 U CN 203070097U CN 201320070949 CN201320070949 CN 201320070949 CN 201320070949 U CN201320070949 U CN 201320070949U CN 203070097 U CN203070097 U CN 203070097U
- Authority
- CN
- China
- Prior art keywords
- test
- flight management
- control display
- adapter
- display module
- Prior art date
- 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 - Lifetime
Links
Images
Abstract
The utility model discloses a comprehensive test device based on an aviation flight management control display assembly. The comprehensive test device mainly consists of a test adapter which is connected with a to-be-tested member, a power source which is connected with the test adapter, and an industrial control computer, wherein the industrial computer provides the test adapter with test signals needed by the to-be-tested member and is provided with a control unit equipped with a terminal block; the test adapter is connected onto the terminal block; the industrial control computer includes a host machine equipped with a CPU circuit processing board and an input/output device, wherein the CPU circuit processing board and the input/output device are both disposed on the terminal block; and the terminal block is connected with the test adapter through the input/output device. The comprehensive test device is reasonable in design, can satisfy maintenance, troubleshooting and test requirements of the flight management control display assembly, has sound social and economic benefits and low development cost, and thus is suitable for flight management system control display assemblies disposed in mainstream airplane types such as Boeing and Airbus in national civil aviation units in the present day.
Description
Technical field
The utility model relates to aviation module testing field, specifically, is based on the integral test system of aviation flight management system control display module.
Background technology
Flight management system is the core of large aircraft digitalized electron system, it is by function and the effect of a plurality of electronics and organic electronic system on tissue, coordination, the comprehensive machine, generate flight planning, and the omnidistance enforcement that guarantees this flight planning in whole flight process, realize the automatic control of aerial mission.And in flight management system, display module also is one of them important component part, the pilot can arrange the parameter of every automatic flight of aircraft by this display module, so that aircraft can fly automatically, and pass through display interface, check every flight parameter of aircraft, also can pass through this display module, a plurality of parts on the aircraft are carried out self-checking, check the functional status of each parts, therefore, in actual application, display module is tested and safeguarded it is then very necessary, in case component wherein breaks down, can make the error of display module output parameter bigger, thereby the decision that causes the decision-maker to make making mistake gently then causes economic loss, and is heavy then cause fatal crass's accident, therefore, how accurately the performance of display module being detected also is the active demand that the aircraft navigation process is proposed.Display module broke down in the past, all was that the maintenance shop of delivering to external or OEM is repaired, and not only cost of repairs height, cycle are long, can't guarantee the natural rate of interest of airline flights.Based on this situation, the utility model proposes a kind of integral test system, whether it can meet the acceptance specification requirement to the performance of display module and test, and has many advantages such as simple in structure, that cost is low, reliability is high, function is strong.
The utility model content
The purpose of this utility model is to provide the integral test system based on aviation flight management system control display module, provide test signal by industrial computer for measured piece, can satisfy maintenance, troubleshooting and the test of flight management system control display module, can not only effectively improve synthesization, the automaticity of driving cabin, can also alleviate driver's work load, bring huge beyond measure economic benefit.
The utility model is achieved through the following technical solutions: based on the integral test system of aviation flight management system control display module, main by the test adapter that links to each other with measured piece, the power supply that links to each other with test adapter and industrial computer are formed, industrial computer is for providing the required test signal of measured piece and being provided with the control module of terminal strip to test adapter, described test adapter is connected on the terminal strip, can satisfy the maintenance of flight management system control display module, troubleshooting and test, applicable to the mainstream model Boeing of present domestic civil aviaton unit and Air Passenger etc. the flight management system of adorning control display module.
For better realizing said structure, industrial computer described in the utility model comprises main frame and the input-output apparatus that is provided with the cpu circuit disposable plates, cpu circuit disposable plates and input-output apparatus all are located on the terminal strip, terminal strip is connected with test adapter by input-output apparatus, the utility model is integrated with the required related software system of display module test in the cpu circuit disposable plates, and these software systems then mainly are made up of testing apparatus driving, test execution control, self-test and modules such as correcting device, subsidiary function.
For better realizing the utility model, described input-output apparatus comprises ARINC 429 bus cards, ARINC 568 bus cards and the discrete magnitude integrated circuit board that links to each other with test adapter respectively, be connected with telescopic backboard at described terminal strip, ARINC 429 bus cards, ARINC 568 bus cards and discrete magnitude integrated circuit board then are located on the telescopic backboard, control signal can be delivered on the terminal strip by the form of 568 yards of 429 yards of ARINC, ARINC or discrete magnitude, and carries out data transmission by test adapter and measured piece.
In the utility model, described test adapter is to be made up of interconnective adjustment circuit and signal adapter, described ARINC 429 bus cards, ARINC 568 bus cards and discrete magnitude integrated circuit board are connected with measured piece by signal adapter respectively, and described power supply then is connected to be adjusted on the circuit.
On described test adapter, also be provided with the voltage tester mechanism that is formed by oscillograph and digital multimeter, oscillograph and digital multimeter are connected to be adjusted on the circuit, in the prior art, oscillograph is a kind of application electronic measuring instrument very widely, and at the utility model, it can be used for providing the part of any needs measurement electric signal in this testing of equipment process, the invisible converting electrical signal of naked eyes is become visual image, and by digital multimeter its voltage is tested, can be used for as the test voltage of measured piece etc.
For better realizing the utility model, on described test adapter, also be provided with the interface for measured piece and power supply signal access.
The utility model also is connected with keyboard and display on described main frame, can be used for showing the desired various parameters of measured piece and failure message, and keyboard then can be imported the reference mark of measured piece, operates very simple.
In the utility model, described terminal strip is bus adapter, can insert the integrated circuit board of computing machine, server or mainframe, by fiber channel or SCSI computing machine is connected to storer or storer net, and function is very powerful.
Power supply described in the utility model is provided with gauge tap and pilot lamp for the power supply box of three-phase supply is provided at power supply box, and three-phase AC115V 400Hz, DC28V, DC14V, AC5V power supply can be provided.
The utility model compared with prior art has the following advantages and beneficial effect:
(1) the utility model is reasonable in design, can be on the cpu circuit disposable plates integrated corresponding testing software, can not only finish maintenance, troubleshooting, the performance test of airborne flight management system control display module, also have advanced automatic control function, guaranteed airborne flight management system control display module in real time, test accurately and rapidly.
(2) the utility model also can be on the cpu circuit disposable plates integrated self-test and have the test macro of calibration function, can not only improve software test, also can guarantee the reliably working of system self.
(3) the utility model also has high economic benefit, display module broke down in the past, all be that the maintenance shop of delivering to external or OEM is repaired, not only cost of repairs height, cycle are long, can't guarantee the natural rate of interest of airline flights, therefore, of the present utility model coming into operation, can not only improve domestic maintainability, for airline saves cost, also have good society and economic benefit.
(4) the utility model uses this airborne flight management system control display module test macro, can also improve maintenance, detection efficiency, guarantees the integrity of aviation airborne equipment, ensures aircraft safety, high efficiency flight.
(5) the utility model proposes the design of voltage tester mechanism, can be used for providing the part of any needs measurement electric signal in this testing of equipment process, the invisible converting electrical signal of naked eyes is become visual image, and by digital multimeter its voltage is tested, can be used for as the test voltage of measured piece etc.
Description of drawings
Fig. 1 is theory diagram of the present utility model.
Embodiment
Be described in further detail below in conjunction with the utility model of embodiment, but embodiment of the present utility model is not limited thereto.
Embodiment:
The utility model proposes the integral test system based on aviation flight management system control display module, this testing apparatus mainly is the test macro of developing at the control display unit, can effectively detect the correctness of test product work, its structure as shown in Figure 1, mainly formed by test adapter, power supply and industrial computer, wherein, test adapter is connected on the measured piece (as: 166891-XX-XX/167550-XX-XX/167550-XX-XX etc.); Power supply is connected on the test adapter, and provides unidirectional AC115V400Hz, 28VDC, 14VDC, 220VAC, 5VAC power supply for it; Industrial computer is connected on the test adapter, and provides the control module of the required test signal of measured piece for it.In the utility model, whole test system can adopt the standard desktop structure, is placed in the 19 〃 standard cabinets, and realizes test function by computer control, has advantages such as maintenance is simple, easy to operate, test is reliable.
Industrial computer described in the utility model is the core cell of whole test system, as shown in Figure 1, industrial computer mainly is made up of the main frame that is provided with the cpu circuit disposable plates (that is: computing machine), terminal strip and input-output apparatus, cpu circuit disposable plates and input-output apparatus all are located on the terminal strip, and terminal strip then is connected with test adapter by input-output apparatus.In actual application, the cpu circuit disposable plates is the required related software system of display module test that is integrated with, as: testing apparatus driving, test execution control, self-test and modules such as correcting device, subsidiary function.Integrate advanced sophisticated softwares such as automatic control, self-test and calibration function and test, guaranteed airborne flight management system control display module in real time, test accurately and rapidly.In said structure, the testing apparatus of software systems drives the driver that mainly comprises all plug and play integrated circuit boards, the programming of softpanel and soft interface, and this system extension is reserved with test driver and soft interface for convenience; Test execution control in the software systems then is that testing apparatus and flow process are controlled, and loads pumping signal, and points out test process and test result in the process of implementation.
Certainly, for making things convenient for the operation and maintenance of this test macro, also can use the software of independent development, according to the different software function of design needs independent development, and by hardware the flight management system of testing is controlled display module and carry out fault diagnosis, analyze and the accurate fault location reason of energy and parts, applied range, applicable to the mainstream model Boeing of present domestic civil aviaton unit and Air Passenger etc. the flight management system of adorning control display module.
In the utility model, input-output apparatus comprises ARINC 429 bus cards that link to each other with test adapter respectively, ARINC 568 bus cards and discrete magnitude integrated circuit board, be connected with telescopic backboard at terminal strip, ARINC 429 bus cards, ARINC 568 bus cards and discrete magnitude integrated circuit board then are connected on the terminal strip by telescopic backboard, in actual test process, this flight management system control display module test macro is according to the testing requirement of measured piece UUT, provide/receive required ARINC 429 bus signals, ARINC 568 bus signals, the discrete magnitude signal, each power supply signal etc., and receive to handle the various signals of Flight Management Computer output, adopt man-machine dialog interface intuitively to finish the test of flight management system control display module.After starting flight management system control display module testing system software, enter graphic interface, click enters flight management system control display module test macro and carries out self-test and calibration, and employed equipment, bus card are carried out self-test and calibration.After system self-testing success, carry out flight management system control display module master test procedure, select the piece number of tested equipment, and after input sequence number and the repacking number, finish test automatically, and test result is stored.
For better realizing said structure, terminal strip can adopt bus adapter, can insert the integrated circuit board of computing machine, server or mainframe, by fiber channel or SCSI computing machine is connected to storer or storer net, and function is very powerful.
As shown in Figure 1, the utility model also is provided with the voltage tester mechanism that is made up of oscillograph and digital multimeter on test adapter, oscillograph and digital multimeter are connected to be adjusted on the circuit, in the prior art, oscillograph is a kind of application electronic measuring instrument very widely, and at the utility model, it can be used for providing the part of any needs measurement electric signal in this testing of equipment process, the invisible converting electrical signal of naked eyes is become visual image, and by digital multimeter its voltage is tested, can be used for as the test voltage of measured piece etc.
For better realizing said structure, the utility model also is provided with the interface for measured piece and power supply signal access on test adapter, this test adapter is to be made up of interconnective adjustment circuit and signal adapter, ARINC 429 bus cards, ARINC 568 bus cards and discrete magnitude integrated circuit board are connected with measured piece by signal adapter respectively, adjust circuit and will adjust to suitable amplitude from the alternating current-direct current signal of the next varying level of special test interface, send into terminal strip.
Because multiple different model flight management system control display module is housed on Boeing and the Air Passenger aircraft at present, by the adjustment circuit that links to each other with power supply, the flight management system control display module that can guarantee different model all can insert this test macro and need not to change the testing apparatus internal circuit, adopts the special signal adapter to connect measured piece and industrial computer.The flight management system control display module of installing for existing civil aviation aircraft all is the equipment that Smith and Honeywell produce, all satisfy the ARINC700 series of canonical in the design, this has just guaranteed that the interface of the flight management system control display module of the different piece numbers that different company produces, the signal of cable all can insert test adapter, just select different signal adapters and the supply voltage of different gears for use according to different model.
For better realizing on main frame, also being connected with keyboard and display by the utility model, can be used for showing the desired various parameters of measured piece and failure message, keyboard then can be imported the reference mark of measured piece, operates very simple.The utility model is reasonable in design, can satisfy maintenance, troubleshooting and the test of flight management system control display module, have favorable social and economic benefits, cost of development is low, applicable to the mainstream model Boeing of present domestic civil aviaton unit and Air Passenger etc. the flight management system of adorning control display module.
The above; it only is preferred embodiment of the present utility model; be not that the utility model is done any pro forma restriction, every foundation technical spirit of the present utility model all falls within the protection domain of the present utility model any simple modification, equivalent variations that above embodiment does.
Claims (9)
1. control the integral test system of display module based on the aviation flight management system, it is characterized in that: mainly formed by the test adapter that links to each other with measured piece, the power supply that links to each other with test adapter and industrial computer, industrial computer is for providing the required test signal of measured piece and being provided with the control module of terminal strip to test adapter, described test adapter is connected on the terminal strip.
2. the integral test system based on aviation flight management system control display module according to claim 1, it is characterized in that: described industrial computer comprises main frame and the input-output apparatus that is provided with the cpu circuit disposable plates, cpu circuit disposable plates and input-output apparatus all are located on the terminal strip, and terminal strip is connected with test adapter by input-output apparatus.
3. the integral test system based on aviation flight management system control display module according to claim 2, it is characterized in that: described input-output apparatus comprises ARINC 429 bus cards, ARINC 568 bus cards and the discrete magnitude integrated circuit board that links to each other with test adapter respectively, be connected with telescopic backboard at described terminal strip, ARINC 429 bus cards, ARINC 568 bus cards and discrete magnitude integrated circuit board then are located on the telescopic backboard.
4. the integral test system based on aviation flight management system control display module according to claim 3, it is characterized in that: described test adapter is for to be made up of interconnective adjustment circuit and signal adapter, described ARINC 429 bus cards, ARINC 568 bus cards and discrete magnitude integrated circuit board are connected with measured piece by signal adapter respectively, and described power supply then is connected to be adjusted on the circuit.
5. the integral test system based on aviation flight management system control display module according to claim 4, it is characterized in that: also be provided with the voltage tester mechanism that is made up of oscillograph and digital multimeter on described test adapter, oscillograph and digital multimeter are connected to be adjusted on the circuit.
6. the integral test system based on aviation flight management system control display module according to claim 5 is characterized in that: also be provided with the interface for measured piece and power supply signal access on described test adapter.
7. the integral test system based on aviation flight management system control display module according to claim 6 is characterized in that: also be connected with keyboard and display on described main frame.
8. according to the arbitrary described integral test system based on aviation flight management system control display module of claim 1～7, it is characterized in that: described terminal strip is bus adapter.
9. the integral test system based on aviation flight management system control display module according to claim 8, it is characterized in that: described power supply is provided with gauge tap and pilot lamp for the power supply box of three-phase supply is provided at power supply box.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320070949 CN203070097U (en) | 2013-02-07 | 2013-02-07 | Comprehensive test device based on aviation flight management control display assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320070949 CN203070097U (en) | 2013-02-07 | 2013-02-07 | Comprehensive test device based on aviation flight management control display assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203070097U true CN203070097U (en) | 2013-07-17 |
Family
ID=48768865
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320070949 Expired - Lifetime CN203070097U (en) | 2013-02-07 | 2013-02-07 | Comprehensive test device based on aviation flight management control display assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203070097U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106199250A (en) * | 2016-06-28 | 2016-12-07 | 国营芜湖机械厂 | A kind of aviation work card electronic system and operational approach thereof |
| CN106840720A (en) * | 2016-12-15 | 2017-06-13 | 哈尔滨飞机工业集团有限责任公司 | A kind of control display unit exerciser |
| CN107707320A (en) * | 2017-08-31 | 2018-02-16 | 王洋 | A kind of satellite comprehensive testing method and system of modularization isolation |
| CN108052088A (en) * | 2017-12-04 | 2018-05-18 | 惠州市德赛西威汽车电子股份有限公司 | A kind of automotive air-conditioning controller shows information Auto-Test System |
| CN108674690A (en) * | 2018-07-04 | 2018-10-19 | 芜湖天航装备技术有限公司 | A kind of aircraft drop in beam electric attachments automatic test equipment and its test method |
| CN109828553A (en) * | 2019-02-26 | 2019-05-31 | 中国人民解放军空军工程大学航空机务士官学校 | A kind of air data computer detection system |
| CN110963072A (en) * | 2019-12-17 | 2020-04-07 | 北京青云航空仪表有限公司 | Airborne equipment comprehensive test system |
-
2013
- 2013-02-07 CN CN 201320070949 patent/CN203070097U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106199250A (en) * | 2016-06-28 | 2016-12-07 | 国营芜湖机械厂 | A kind of aviation work card electronic system and operational approach thereof |
| CN106199250B (en) * | 2016-06-28 | 2018-12-11 | 国营芜湖机械厂 | A kind of aviation work card electronic system and its operating method |
| CN106840720A (en) * | 2016-12-15 | 2017-06-13 | 哈尔滨飞机工业集团有限责任公司 | A kind of control display unit exerciser |
| CN107707320A (en) * | 2017-08-31 | 2018-02-16 | 王洋 | A kind of satellite comprehensive testing method and system of modularization isolation |
| CN108052088A (en) * | 2017-12-04 | 2018-05-18 | 惠州市德赛西威汽车电子股份有限公司 | A kind of automotive air-conditioning controller shows information Auto-Test System |
| CN108674690A (en) * | 2018-07-04 | 2018-10-19 | 芜湖天航装备技术有限公司 | A kind of aircraft drop in beam electric attachments automatic test equipment and its test method |
| CN108674690B (en) * | 2018-07-04 | 2023-05-30 | 芜湖双翼航空装备科技有限公司 | Automatic testing equipment and testing method for electric accessories of hanging beam of certain type aircraft |
| CN109828553A (en) * | 2019-02-26 | 2019-05-31 | 中国人民解放军空军工程大学航空机务士官学校 | A kind of air data computer detection system |
| CN110963072A (en) * | 2019-12-17 | 2020-04-07 | 北京青云航空仪表有限公司 | Airborne equipment comprehensive test system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203070097U (en) | Comprehensive test device based on aviation flight management control display assembly | |
| CN201757767U (en) | General comprehensive automatic test system of airplane electronic part | |
| TW201500264A (en) | Apparatus and method for testing aircraft message trigger logics | |
| CN201072597Y (en) | Automatic detection instrument for aviation electronic flight instrument | |
| CN207258013U (en) | A kind of Mini Tele-Copter flight control system in situ detection equipment | |
| CN110884687A (en) | Semi-physical real-time simulation verification platform for PHM technology of electromechanical system | |
| CN207335757U (en) | A kind of test system of automobile combination meter | |
| CN102798759A (en) | Insulation resistance test system | |
| CN104155536A (en) | System and method for testing integrity test on an electricity network in an aircraft | |
| CN103048581A (en) | Cable testing device | |
| CN203064208U (en) | Integral test equipment applied to aircraft instrument | |
| CN105752359B (en) | A kind of airborne photoelectric gondola detection means | |
| CN102591320A (en) | Portable integrated tester for flight control system of helicopter | |
| CN106019123A (en) | RF circuit off-location detecting system of communication and navigation system | |
| CN201488749U (en) | Novel meter detection equipment | |
| CN201845188U (en) | Central comprehensive display part detecting system | |
| CN110968490A (en) | General detection platform for atmospheric data computer | |
| CN203720647U (en) | Air data computer testing system | |
| CN207346123U (en) | A kind of testboard for the test of airplane data acquisition component | |
| CN106814728A (en) | A kind of assembly detection apparatus based on product power supply interface sequential logic | |
| CN101876719A (en) | Air data computer testing device | |
| CN207352460U (en) | A kind of detection device of flight control system | |
| KR101692473B1 (en) | Inspection Apparatus for Flight Data Recording Device | |
| Liu et al. | Design of UAV avionics automatic test system based on virtual instrument | |
| CN203224587U (en) | Cable testing device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130717 |