CN202632098U - Variable alternating current function template for flight management and control computer testing - Google Patents
Variable alternating current function template for flight management and control computer testing Download PDFInfo
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- CN202632098U CN202632098U CN 201220255869 CN201220255869U CN202632098U CN 202632098 U CN202632098 U CN 202632098U CN 201220255869 CN201220255869 CN 201220255869 CN 201220255869 U CN201220255869 U CN 201220255869U CN 202632098 U CN202632098 U CN 202632098U
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- alternating current
- control computer
- flight management
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Abstract
The utility model discloses a variable alternating current function template for flight management and control computer testing. The template comprises a plurality of groups of variable alternating current modules connected between a controller and an output port in parallel, wherein each variable alternating current module comprises a digital to analog converter, an amplifier and an isolation transformer, which are connected in series. The template has the advantages that the template can quickly realize output of variable alternating current signals, is convenient for simultaneously carrying out a plurality of retrievals, has high whole detection process efficiency, is safe and reliable in application and has wide range of application.
Description
Technical field
The utility model relates to flight management and control computer checkout equipment on a kind of civil aircraft.
Background technology
Flight Management Computer is mainly used in atmosphere data, navar, engine and fuel oil parameter and the internal database system of handling; Accomplish Navigation Control, flight planning, execution management; Functions such as display process, outside connection signal is more, and its main function relies on software to accomplish.Flight-control computer is mainly accomplished the control command of flight attitude, direction, speed; Respectively with A/T (auto-throttle computing machine); FMC (Flight Management Computer), ADC (air data computer), DME (range finder), (IRU) inertial reference assembly etc. are connected, and outside connection signal is also more.
Along with science and technology development, it is more and more advanced that these air environments become, and needs the parameter of test many, and precision is high, makes supporting with it test job become and become increasingly complex that development difficulty constantly increases, and safeguards after the payment that the guarantee expense also constantly increases.And there is certain difference in the signal kinds of the Flight Management Computer of different model and control computer, if adopt manual type to test, different detection signals need be provided manually; It is longer to expend time in, and poor stability, if make special testing apparatus to different models; For checking maintenance unit, its required specialized detection quantity is more, and the place area occupied is big; Investment is high, and the cost recovery cycle is long, can't promote the use of.
Summary of the invention
The purpose of the utility model provides a kind of flight management and control computer is tested with variable communication function template; Use this template can provide many group AC signals to supply to detect simultaneously to use; And can switch different AC signals fast, effectively raise detection efficiency, applied widely.
The technical solution of the utility model is: a kind of flight management and control computer test are with variable communication function template; It comprises that parallel connection is arranged on some groups of variable interchange modules between controller and the output port, and every group of variable interchange module comprises digital to analog converter, amplifier and the isolating transformer that series connection is provided with.
Digital to analog converter can benchmark voltage, through controller control, exports variable AC signal; Switch rapidly, Digital Control, precision is high; Exported after the AC signal that produces advances the amplifier amplified current, isolating transformer can be realized the safety isolation of signal output part and test lead, parallelly connected some groups of variable interchange modules in the whole template; Just output that can the multiple AC signal of Rapid Realization is conveniently carried out a plurality of detections simultaneously, and whole process can be carried out with programmed control automatically; Improved detection efficiency greatly, safety easy to use.
Also be provided with the short circuit relay with normal open switch in each said variable interchange module, said isolating transformer and normal open switch are connected in parallel, and the short circuit relay connects said controller.Short circuit through short circuit relay realization isolating transformer also can be convenient to use in the place that does not need isolation signals, has increased the popularity that is suitable for.
Between each said variable interchange module and output port, be provided with and exchange phase conversion.Can realize exchanging commutation easily, further improve the scope that test adapts to.
The utility model has the advantages that: output that can the variable AC signal of Rapid Realization, conveniently carry out a plurality of retrievals simultaneously, whole testing process efficient is high, is suitable for safe and reliablely, and the scope of application is extensive.
Description of drawings
Accompanying drawing 1 is the structural representation of the utility model embodiment;
1, controller, 2, digital to analog converter, 3, the reference voltage module, 4, amplifier, 5, isolating transformer, 6, exchange phase conversion, 7, output port, 8, the short circuit relay, 9, normal open switch, 10, variable interchange module.
Embodiment
Embodiment:
Consult Fig. 1: for the test of a kind of flight management and control computer with variable communication function template; It comprises that parallel connection is arranged on some groups of variable interchange modules 10 between controller 1 and the output port 7; Every group of variable interchange module 10 comprises digital to analog converter 2, amplifier 4 and the isolating transformer 5 that series connection is provided with; Also be provided with the short circuit relay 8 with normal open switch 9 in each variable interchange module 10, isolating transformer 5 is connected in parallel with normal open switch 9, and short circuit relay 8 connects controller 1.Between each variable interchange module 10 and output port 7, be provided with and exchange phase conversion 6.Band arrow dotted line is the control signal trend among the figure.
In the present embodiment, variable interchange module 10 is provided with eight altogether, can provide octuple variable AC signal simultaneously.Reference voltage module 3 is arranged on the template, and each variable interchange module 10 shared reference voltage module 3 also can be separately positioned on reference voltage module 3 in each variable interchange module 10, thereby increases the scope that is suitable for signal.
The present embodiment accompanying drawing; Be used to express each equipment component connection and the signal that constitute variable interchange template and move towards synoptic diagram; The concrete element that adopts all can adopt existing device of the prior art; For example exchange phase conversion 6 and utilize relay to realize the conversion of input AC phase place, concrete connected mode is means known in the state of the art between its principle and each element, does not repeat them here.
Above-listed detailed description is specifying to one of the utility model possible embodiments; This embodiment is not the claim in order to restriction the utility model; Allly do not break away from the equivalence that the utility model does and implement or change, all should be contained in the claim of this case.
Claims (3)
1. the test of flight management and control computer is with variable communication function template; It is characterized in that: it comprises that parallel connection is arranged on some groups of variable interchange modules between controller and the output port, and every group of variable interchange module comprises digital to analog converter, amplifier and the isolating transformer that series connection is provided with.
2. flight management according to claim 1 and control computer test are with variable communication function template; It is characterized in that: also be provided with short circuit relay in each said variable interchange module with normal open switch; Said isolating transformer and normal open switch are connected in parallel, and the short circuit relay connects said controller.
3. the test of flight management according to claim 1 and 2 and control computer is characterized in that with variable communication function template: between each said variable interchange module and output port, be provided with and exchange phase conversion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220255869 CN202632098U (en) | 2012-05-31 | 2012-05-31 | Variable alternating current function template for flight management and control computer testing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220255869 CN202632098U (en) | 2012-05-31 | 2012-05-31 | Variable alternating current function template for flight management and control computer testing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202632098U true CN202632098U (en) | 2012-12-26 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220255869 Expired - Lifetime CN202632098U (en) | 2012-05-31 | 2012-05-31 | Variable alternating current function template for flight management and control computer testing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202632098U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2799166C1 (en) * | 2023-02-27 | 2023-07-04 | Акционерное общество "ЭЙРБУРГ" | Aircraft motion simulation device for flight controller software and hardware training |
-
2012
- 2012-05-31 CN CN 201220255869 patent/CN202632098U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2799166C1 (en) * | 2023-02-27 | 2023-07-04 | Акционерное общество "ЭЙРБУРГ" | Aircraft motion simulation device for flight controller software and hardware training |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee |
Owner name: HNA TECHNIK CO., LTD. Free format text: FORMER NAME: GRAND CHINA AVIATION TECHNIK LIMITED COMPANY |
|
| CP03 | Change of name, title or address |
Address after: 571924 Hainan province Chengmai County Old Town Economic Development Zone South Road 69, Haikou Comprehensive Bonded Zone Inspection Building Room 802 Patentee after: HNA Technik Co., Ltd. Address before: 570105 Haikou Free Trade Zone office building, No. 168 Nanhai Road, Hainan, Haikou, 126A Patentee before: Grand China Aviation Technik Limited Company |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 570216 East 103, Haikou Free Trade Zone, No. 168, Nanhai Road, Haikou, Hainan Patentee after: HNA aviation technology Limited by Share Ltd Address before: 571924 Hainan province Chengmai County Old Town Economic Development Zone South Road 69, Haikou Comprehensive Bonded Zone Inspection Building Room 802 Patentee before: HNA Technik Co., Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121226 |