CN202632099U - Changeable direct-current functional template for flying management and computer testing control - Google Patents
Changeable direct-current functional template for flying management and computer testing control Download PDFInfo
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- CN202632099U CN202632099U CN 201220255870 CN201220255870U CN202632099U CN 202632099 U CN202632099 U CN 202632099U CN 201220255870 CN201220255870 CN 201220255870 CN 201220255870 U CN201220255870 U CN 201220255870U CN 202632099 U CN202632099 U CN 202632099U
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- direct current
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- current module
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- 238000012360 testing method Methods 0.000 title claims abstract description 11
- 238000001514 detection method Methods 0.000 abstract description 8
- 230000004044 response Effects 0.000 abstract description 3
- 238000007726 management method Methods 0.000 description 9
- 230000008859 change Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000004308 accommodation Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
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Abstract
The utility model discloses a changeable direct-current functional template for flying management and computer testing control. The changeable direct-current functional template comprises a first changeable direct-current module and a second changeable direct-current module which are connected in parallel between a controller and an output port. The first changeable direct-current module comprises a digital potential meter and a first amplifier which are connected in series. The second changeable direct-current module comprises a digital-to-analog converter and a second amplifier which are connected in series. The changeable direct-current functional template has the advantages of being simple in structure, capable of achieving output of multi-way direct current signals, high in detection efficiency, fast in response speed, high in accuracy, wide in application range, and reliable and convenient to use.
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 direct current functional template; Use this template can provide many group direct current signals to supply to detect simultaneously to use; And can switch different direct current 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 direct current functional template; It comprises the first variable direct current module and the second variable direct current module that is connected in parallel between controller and the output port; Wherein the first variable direct current module comprises the digital regulation resistance and first amplifier that series connection is provided with, and the second variable direct current module comprises the digital to analog converter and second amplifier that series connection is provided with.
Digital regulation resistance can be used the change of its resistance of Digital Signals, thereby realizes the output of different DC voltages, through the first amplifier amplified current; Realize the output of lower accuracy direct current signal, digital to analog converter can directly change digital signal into direct current signal, through the second amplifier amplified current; Realize the output of high precision direct current signal,, can realize that just the different direct current signal of programmed control output supplies to detect use through controller control figure potentiometer and digital to analog converter; Response speed is fast, and is easy to operate, improves detection efficiency greatly; Accuracy is also high, and accommodation is extensive.
The quantity of the said first variable direct current module is 16, and the quantity of the said second variable direct current module is four.While and di-ten tunnel variable direct current modules can be carried out the output of a plurality of direct current signals simultaneously, further improve detection efficiency, shorten detection time.
The utility model has the advantages that: simple in structure, can realize the output of multipath CD signal, detection efficiency is high, and response speed is fast, and accuracy is high, and accommodation is extensive, uses convenient and reliable.
Description of drawings
Accompanying drawing 1 is the structural representation of the utility model embodiment;
1, controller, 2, digital regulation resistance, 3, first amplifier, 4, digital to analog converter, 5, second amplifier, 6, output port, 7, the first variable direct current module, 8, the second variable direct current module.
Embodiment
Embodiment:
Consult Fig. 1; For the test of a kind of flight management and control computer with variable direct current functional template; It comprises the first variable direct current module 7 and the second variable direct current module 8 that is connected in parallel between controller 1 and the output port 6; Wherein the first variable direct current module 7 comprises that digital regulation resistance 2 and first amplifier, 3, the second variable direct current modules 8 that series connection is provided with comprise the digital to analog converter 4 and second amplifier 5 that series connection is provided with.
In the present embodiment, the first variable direct current module 7 has ten six the tunnel.The second variable direct current module 8 has four the tunnel.A reference voltage can be provided in this template, and each digital regulation resistance 2 all can behind first amplifier, 3 amplified currents, be exported the direct current signal of eight precision by the direct current signal of controller control output with the proportional coefficient relation of reference voltage.Each digital to analog converter 4 can be by the direct current signal of controller control output sixteen bit precision.
The volume of digital regulation resistance 2 is little, and cost is low, but accuracy requirement is not high, and the precision of digital to analog converter 4 is high, but cost is not low, is applicable to the output of accuracy requirement higher signal.Make up the present embodiment template of these two kinds of parts, can carry out multiple precision signal output simultaneously and detect, improved work efficiency greatly.And through controller 1 control, can realize-10V to 10V, the output of the direct current signal of 0-10V, 0-28V scope.
The present embodiment accompanying drawing is used for expressing the connection and the signal that constitute variable each equipment component of direct current template and moves towards synoptic diagram; The technology such as selection of concrete equipment component such as digital potentiometer and setting, amplifier and the reference voltage of digital to analog converter in circuit are any means known of prior art, do 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 (2)
1. the test of flight management and control computer is with variable direct current functional template; It is characterized in that: it comprises the first variable direct current module and the second variable direct current module that is connected in parallel between controller and the output port; Wherein the first variable direct current module comprises the digital regulation resistance and first amplifier that series connection is provided with, and the second variable direct current module comprises the digital to analog converter and second amplifier that series connection is provided with.
2. flight management according to claim 1 and control computer test are with variable direct current functional template, and it is characterized in that: the quantity of the said first variable direct current module is 16, and the quantity of the said second variable direct current module is four.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220255870 CN202632099U (en) | 2012-05-31 | 2012-05-31 | Changeable direct-current functional template for flying management and computer testing control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220255870 CN202632099U (en) | 2012-05-31 | 2012-05-31 | Changeable direct-current functional template for flying management and computer testing control |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202632099U true CN202632099U (en) | 2012-12-26 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220255870 Expired - Lifetime CN202632099U (en) | 2012-05-31 | 2012-05-31 | Changeable direct-current functional template for flying management and computer testing control |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202632099U (en) |
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2012
- 2012-05-31 CN CN 201220255870 patent/CN202632099U/en not_active Expired - Lifetime
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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 |
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. |
|
| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121226 |
|
| CX01 | Expiry of patent term |