CN203720647U - Air data computer testing system - Google Patents
Air data computer testing system Download PDFInfo
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- CN203720647U CN203720647U CN201420013432.1U CN201420013432U CN203720647U CN 203720647 U CN203720647 U CN 203720647U CN 201420013432 U CN201420013432 U CN 201420013432U CN 203720647 U CN203720647 U CN 203720647U
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Abstract
The utility model discloses an air data computer testing system. The air data computer testing system comprises a discrete function interface unit which is configured to be in communication connection with an air data computer and used for forwarding or processing signals received by the discrete function interface unit, a temperature simulation unit which is configured to be in communication connection with the air data computer and used for setting temperature signals received by the air data computer testing system, and an air data test device which is configured to be in communication connection with the air data computer and used for transmitting air data signals to the air data computer. The air data computer testing system can adopt general standard test equipment and can simulate the work environment of the air data computer (ADC) on a plane, and therefore, the air data computer testing system is advantageous in universality and high accuracy.
Description
Technical field
The utility model relates to avionics testing apparatus field, the especially a kind of equipment that can test air data computer (Air Data Computer, ADC).
Background technology
Air data computer is an important avionic device assembly, and it is mainly arranged in the glass cockpit of aircraft.Be different from common personal computer, ADC can by from input data from sensor as aircraft pressure detection system, gyroscope, GPS and accelerometer, determine calibrated air speed, Mach number, height and trend highly.
Degree of taking place frequently in view of avionics system fault, and the consideration of maintenance cost, according to an international practice and research ARJ21 airplane fault statistics, and the importance of equipment in aircraft system, avionics system finished parts needs to detect by Aerial Electronic Equipment test board before packing aircraft into.Therefore research and develop Aerial Electronic Equipment test board and be very important, need to design such Aerial Electronic Equipment test board.
The equipment that external ADC-3000 Aerial Electronic Equipment is tested is mainly comprised of signal condition panel (SIGNAL DISTRIBUTION PANEL), test point conditioning case, computer and 429 analysers and source of the gas.This testing apparatus is derivative by other avionics testing apparatus expansions, in other Aerial Electronic Equipments of test, takes into account ADC-3000 Aerial Electronic Equipment.Therefore, do not have special-purposely, define understandable special test platform.In concrete test, not only waste time and energy, and operating personnel's skill level is had to very high requirement.
Utility model content
Based on above consideration, if propose a kind of, can, to air data computer standard, the system of testing reliably, will be very favorable.
According to one side of the present utility model, a kind of test macro of air data computer has been proposed, it is characterized in that, comprising: discrete functionality interface unit, is configured to and described air data computer communication connection, for forwarding or process its received signal; Temperature simulation unit, is configured to and described air data computer communication connection, the temperature signal receiving for described air data computer test macro is set; Atmosphere data proving installation, is configured to and described air data computer communication connection, for transmitting atmosphere data signal to described air data computer.
According to an embodiment of the present utility model, also comprise, power supply, be configured to be coupled to described air data computer, for described air data computer is powered, wherein, the voltage of described power supply output is identical with described air data computer operating voltage aboard, to simulate described air data computer power supply environment aboard.
According to an embodiment of the present utility model, described test macro also comprises atmosphere data Bus simulator analytic unit, be configured to and the communication connection of described air data computer, for reception and graphically to show the output signal from described air data computer.
According to an embodiment of the present utility model, described temperature simulation unit communicates to connect by described discrete functionality interface unit and described air data computer.
According to an embodiment of the present utility model, described temperature simulation unit is resistance box, changes the temperature signal of simulation by changing effective resistance value.
According to an embodiment of the present utility model, described test macro also comprises supplementary interface unit, be configured to communication connection to described air data computer, wherein, described supplementary interface unit cannot process or process for receiving or input because described discrete functionality interface unit and described air data computer cannot mating to cause completely the signal not meeting the demands.
According to an embodiment of the present utility model, described supplementary interface unit communicates to connect by described discrete functionality interface unit and described air data computer.
According to an embodiment of the present utility model, described supplementary interface unit is configured to supplement discrete signal to described air data computer input, and draws the output signal corresponding with described supplementary discrete signal for described atmosphere data Bus simulator analytic unit test.
According to an embodiment of the present utility model, described power supply is coupled to described air data computer by described discrete functionality interface unit, to power to described air data computer.
Compared to current external similar testing apparatus, test macro of the present utility model, can complete the test that finished parts enters factory's performance/function, and simple to operate.In addition, this test macro can adopt universal standard testing apparatus and this test macro can simulate ADC working environment aboard, thereby this test macro has versatility and accuracy widely, and can test all technical of ADC, and can failure judgement place, and be not only the concluding result of PASS/FAIL and so on.
Various aspects of the present utility model are by the explanation of the specific embodiment by hereinafter and more clear.
Accompanying drawing explanation
By reading the following detailed description to non-limiting example with reference to accompanying drawing, it is more obvious that other features, objects and advantages of the present utility model will become.
Fig. 1 is the configuration diagram according to the test macro of the utility model embodiment;
Fig. 2 is the ADC discrete signal interface panel schematic diagram according to the utility model embodiment.
Embodiment
In the specific descriptions of following preferred embodiment, with reference to the appended accompanying drawing that forms the utility model part.Appended accompanying drawing shows by way of example can realize specific embodiment of the present utility model.The embodiment of example is not intended to limit according to all embodiment of the present utility model.Be appreciated that not departing under the prerequisite of scope of the present utility model, can utilize other embodiment, also can carry out the modification of structural or logicality.Therefore, following specific descriptions are also nonrestrictive, and scope of the present utility model is limited by appended claim.
In order to make test result can reflect ADC working condition aboard, the utility model provides the various signals of normal need of work, such as ADC power module, atmosphere data Bus simulator analyser etc. by relevant other mobile systems that are connected with ADC on pertinent instruments simulated aircraft that use to ADC.Under real work state, by corresponding control command and input signal are set, use the property indices parameter of corresponding testing tool test ADC, thereby differentiate this ADC, whether be certified products.
Below the products A DC-3000 of Yi Dui Collins company type ADC tests as example, sets forth the framework of test macro of the present utility model.
Fig. 1 is the configuration diagram according to the test macro of the utility model embodiment.The test macro of the present embodiment comprises atmosphere data tester, discrete functionality interface unit 12, temperature simulation unit 13, atmosphere data Bus simulator analyser 14, direct supply 15 and ADC to be measured.
Discrete functionality interface unit 12, for the input/output signal of ADC16 to be measured is drawn, carries out connecting test for other equipment.Discrete functionality interface unit 12 is also for providing test necessary discrete input signal.For discrete functionality interface unit 12, the signal of its reception or forwarding mainly comprises that discrete input signal, ARINC429 input/output signal and temperature input signal form.Wherein, discrete functionality interface unit 12 is connected to atmosphere data Bus simulator analyser 14 by ARINC429 input/output signal, and temperature signal is connected to temperature simulation unit 13.
While normally using aboard due to ADC16 to be measured, need to power by the power module on aircraft, therefore, in the present embodiment, in test macro, adopt the 15 couples of ADC16 to be measured of direct supply that are coupled to discrete functionality interface unit 12 to power, with the power module to ADC16 power supply to be measured on simulated aircraft, wherein direct supply 15 is output as the DC voltage of 28V.Equally, because ADC16 on aircraft need to analyze air pressure signal, so the utility model adopts atmosphere data tester 11 to provide air pressure signal for ADC16 to be measured.In the present embodiment, that atmosphere data tester adopts is the testing apparatus ADTS-405 of General Electric Co. Limited, for measured piece provides required move/static pressure signal.
Atmosphere data Bus simulator analyser 14 communicates to connect with ADC to be measured by discrete functionality interface unit 12, be used for sending ARINC429 signal command to ADC to be measured, and the output signal that receives ADC16 to be measured, and then analyze the ARINC429 signal that ADC16 to be measured exports.
Temperature simulation unit 13 is coupled to discrete functionality interface unit 12, for providing temperature signal to ADC16 to be measured.Preferably, temperature simulation unit 13 is resistance box, by selecting the resistance of each place in circuit, to simulate the output signal of different temperatures.Resistance box Main Function is analog temperature signal, and because the tested Aerial Electronic Equipment of ADC-3000 decides Current Temperatures by inductive reactance resistance, so the utility model selects precision resistance case model ZX98E to be used for analog temperature signal.
Atmosphere data Bus simulator analyser 14 provides graphical operation interface for testing ADC-3000 Aerial Electronic Equipment.This analyser is comprised of PXI-429 board and PXI cabinet, and wherein, PXI-429 board, for gathering, is analyzed 429 signals, and PXI cabinet provides operating system and platform, and built-in testing software is for tester's operation simultaneously.
The utility model also provides supplementary interface unit 17 (not shown)s, for the discrete control command of test use is provided.Supplement interface unit 17 and can be connected directly to ADC16, also can communicate with ADC16 by discrete functionality interface unit 12.Equally, atmosphere data Bus simulator analyser 14 can be connected directly to discrete functionality interface unit 12, also can establish a communications link with discrete functionality interface unit 12 by supplementing interface unit 17.
In addition, supplement interface unit 17 and can also cannot process or process the signal not meeting the demands for receiving or input because discrete functionality interface unit 12 cannot mating to cause with ADC16 completely.Supplement interface unit 17 and be configured to supplement discrete signal to ADC16 input, and draw the output signal confession corresponding to described supplementary discrete signal.
For discrete functionality interface unit 12, because it will be sent to respectively a plurality of connected equipment by the signal of tissue, processing, therefore, for the ease of test, the utility model also provides ADC discrete signal interface panel.
Fig. 2 is the ADC discrete signal interface panel schematic diagram according to the utility model embodiment.This panel comprises temperature signal input field 21, ARINC signal output area 22, ARINC signal input field 23.This panel is connected with discrete signal interface unit 12 by the interface at the back side, to ADC input signal to be measured, draw the signals such as ARINC429 to atmosphere data Bus simulator analyser 14 simultaneously, thereby test result is presented to user in patterned mode, and without tester, remove to read the ARINC429 signal of 2 carry system codes.
Compared to current external similar testing apparatus, test macro of the present utility model, can complete the test that finished parts enters factory's performance/function, and simple to operate.In addition, this test macro can adopt universal standard testing apparatus and this test macro can simulate ADC working environment aboard, thereby this test macro has versatility and accuracy widely, and can test all technical of ADC, and can failure judgement place, and be not only the concluding result of PASS/FAIL and so on.
Those skilled in the art are understandable that, the utility model can also be for the test of other ADC, according to parameters such as the I/O signal kinds of ADC to be measured, number, functions, determine its input/output signal, if discrete functionality interface unit cannot meet the testing requirement of ADC to be measured, as long as select the corresponding interface unit that supplements.
To those skilled in the art, obviously the utility model is not limited to the details of above-mentioned one exemplary embodiment, and in the situation that not deviating from spirit of the present utility model or essential characteristic, can realize the utility model with other concrete form.Therefore, in any case, all should regard embodiment as exemplary, and be nonrestrictive.In addition, significantly, " comprising ", other elements and step do not got rid of in a word, and wording " one " is not got rid of plural number.A plurality of elements of stating in device claim also can be realized by an element.The first, the second word such as grade is used for representing title, and does not represent any specific order.
Claims (9)
1. a test macro for air data computer, is characterized in that, comprising:
Discrete functionality interface unit, is configured to and described air data computer communication connection, for forwarding or process its received signal;
Temperature simulation unit, is configured to and described air data computer communication connection, the temperature signal receiving for described air data computer test macro is set;
Atmosphere data proving installation, is configured to and described air data computer communication connection, for transmitting atmosphere data signal to described air data computer.
2. test macro according to claim 1, is characterized in that, also comprises:
Power supply, be configured to be coupled to described air data computer, for described air data computer is powered, wherein, the voltage of described power supply output is identical with described air data computer operating voltage aboard, to simulate described air data computer power supply environment aboard.
3. test macro according to claim 1, it is characterized in that, described test macro also comprises atmosphere data Bus simulator analytic unit, is configured to and the communication connection of described air data computer, for reception and graphically to show the output signal from described air data computer.
4. test macro according to claim 1, is characterized in that, described temperature simulation unit communicates to connect by described discrete functionality interface unit and described air data computer.
5. test macro according to claim 4, is characterized in that, described temperature simulation unit is resistance box, changes the temperature signal of simulation by changing effective resistance value.
6. test macro according to claim 1, is characterized in that, also comprises:
Supplement interface unit, be configured to communication connection to described air data computer, wherein, described supplementary interface unit cannot process or process for receiving or input because described discrete functionality interface unit and described air data computer cannot mating to cause completely the signal not meeting the demands.
7. test macro according to claim 6, is characterized in that, described supplementary interface unit communicates to connect by described discrete functionality interface unit and described air data computer.
8. test macro according to claim 6, it is characterized in that, described supplementary interface unit is configured to supplement discrete signal to described air data computer input, and draws the output signal corresponding with described supplementary discrete signal for described atmosphere data Bus simulator analytic unit test.
9. test macro according to claim 2, is characterized in that, described power supply is coupled to described air data computer by described discrete functionality interface unit, to power to described air data computer.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420013432.1U CN203720647U (en) | 2014-01-09 | 2014-01-09 | Air data computer testing system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420013432.1U CN203720647U (en) | 2014-01-09 | 2014-01-09 | Air data computer testing system |
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| CN203720647U true CN203720647U (en) | 2014-07-16 |
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| CN201420013432.1U Expired - Lifetime CN203720647U (en) | 2014-01-09 | 2014-01-09 | Air data computer testing system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107525521A (en) * | 2017-09-07 | 2017-12-29 | 国营芜湖机械厂 | A kind of atmosphere data exciting bank |
| CN110455331A (en) * | 2019-07-22 | 2019-11-15 | 成都飞机工业（集团）有限责任公司 | Aircraft intelligence atmosphere data exerciser and test method |
| CN111024895A (en) * | 2019-12-18 | 2020-04-17 | 成都飞机工业（集团）有限责任公司 | Interactive atmosphere test system |
-
2014
- 2014-01-09 CN CN201420013432.1U patent/CN203720647U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107525521A (en) * | 2017-09-07 | 2017-12-29 | 国营芜湖机械厂 | A kind of atmosphere data exciting bank |
| CN110455331A (en) * | 2019-07-22 | 2019-11-15 | 成都飞机工业（集团）有限责任公司 | Aircraft intelligence atmosphere data exerciser and test method |
| CN111024895A (en) * | 2019-12-18 | 2020-04-17 | 成都飞机工业（集团）有限责任公司 | Interactive atmosphere test system |
| CN111024895B (en) * | 2019-12-18 | 2022-11-18 | 成都飞机工业（集团）有限责任公司 | Interactive atmosphere testing system |
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Granted publication date: 20140716 |
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