CN202771256U - Aircraft zone temperature controller automatic simulation test desk - Google Patents
Aircraft zone temperature controller automatic simulation test desk Download PDFInfo
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- CN202771256U CN202771256U CN 201220485236 CN201220485236U CN202771256U CN 202771256 U CN202771256 U CN 202771256U CN 201220485236 CN201220485236 CN 201220485236 CN 201220485236 U CN201220485236 U CN 201220485236U CN 202771256 U CN202771256 U CN 202771256U
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Abstract
The utility model discloses an aircraft zone temperature controller automatic simulation test desk which comprises a casing which is internally provided with a PCB circuit board. A front end of the casing is provided with an automatic test panel which is characterized in that the automatic test panel comprises an indicating lamp display area, a potentiometer adjusting area, a wave band switch selection area, a test instrument interface circuit, a plug area, a power supply switch area and a reserved interface.
Description
Technical field
The utility model relates to aircraft automatic analog test field, specifically, relates to a kind of aircraft area temperature controller automatic analog test platform.
Background technology
Area temperature controller (English name Pack/zone Temperature Controller) is installed on the Boeing 737 airplane, be used for controlling whole air-conditioning system, realizing the temperature control and adjusting of driving cabin, main cabin, front and back, freight house, is the important component part of aircraft air-conditioning system.The test condition of area temperature controller is complicated, need a large amount of fine resistive elements to carry out the simulation of component working environment, the test system structure that the former factory of HONEYWELL produces is complicated, it all is manual test, it is very inconvenient to operate, and 20 time-limited operations are arranged in test process nearly, and (restriction reset operation process was finished in 2 minutes, need repeatedly to move more than ten Test Switchboards in 2 minutes), if operation overtime, test crash then, requirement to worker's dexterity and operative skill is all very high, and whole test process is longer, if manual test probably needs 5-8 hour, work efficiency is low, does not also have the test board that the area temperature controller of Boeing 737 airplane is tested automatically in the prior art.This is the deficiencies in the prior art part.
The summary of the invention the technical problems to be solved in the utility model provides a kind of aircraft area temperature controller automatic analog test platform, allows test process become simple, has improved work efficiency, and test result is accurate, has saved human cost and time cost.
The utility model adopts following technical scheme to realize goal of the invention:
A kind of aircraft area temperature controller automatic analog test platform, comprise shell, be provided with the PCB circuit board in the described shell, described shell front end is provided with automatic test panel, it is characterized in that: described automatic test board comprises that pilot lamp viewing area, pot control band, waver are selected zone, test instrumentation interface circuit, connector zone, power switch is regional and spare interface.
As the further restriction to the technical program, be provided with FPGA control circuit, I/O interface circuit, automatic measurement circuit and working environment mimic channel on the described PCB circuit board, described FPGA control circuit connects discrete switch circuit and described automatic measurement circuit.
Compared with prior art, advantage of the present utility model and good effect are: pilot lamp of the present utility model viewing area shows the I/O state of each pin of unit under test; The pot control band is the part of working environment mimic channel, the failure condition when pot and inner discharge circuit can analog component work; Waver selects the zone to realize test or the measurement of the different channel functions of parts by the gear that switches waver; The test instrumentation interface circuit provides connecting interface for test instrumentation and inner PCB; The connector zone provides connecting interface for unit under test and testing apparatus; The switch residue interface of power switch zone and spare interface control DC, AC and AC/DC power supply is reserved, and can be used as the expansion measurement function and uses.Use this test board to make whole test process foreshorten to 1 hour by 8 hours, greatly improved work efficiency, measuring accuracy improves greatly, all test volumes are by computer automatic analysis and record, and automatically convert by software, not only improved efficient, and data recording mistake and the deviation of having avoided human factor to cause.
Description of drawings
Fig. 1 is structural representation of the present utility model.
Fig. 2 is functional-block diagram of the present utility model.
Embodiment
Below in conjunction with accompanying drawing and preferred embodiment the utility model is done further to describe in detail.
Referring to Fig. 1 and Fig. 2, the utility model comprises shell 1, automatic test panel 2, pilot lamp viewing area 3, pot control band 4, waver is selected zone 5, test instrumentation interface circuit 6, connector zone 7, power switch zone 8 and spare interface 9, be provided with the PCB circuit board in the described shell 1, described shell 1 front end is provided with automatic test panel 2, and described automatic test board 2 comprises pilot lamp viewing area 3, pot control band 4, waver is selected zone 5, test instrumentation interface circuit 6, connector zone 7, power switch zone 8 and spare interface 9.
Be provided with FPGA control circuit, I/O interface circuit, automatic measurement circuit and working environment mimic channel on the described PCB circuit board, described FPGA control circuit connects discrete switch circuit and described automatic measurement circuit.FPGA control circuit receiving computer sends order, through after decoding, computing and the Error detection, accurately control discrete signal output, finish the control to the discrete magnitude switch, what directly link to each other with it is the discrete switch circuit, mainly finishes the switching of unit under test internal discrete amount and the passage handoff functionality between unit under test and the test instrumentation; The I/O interface circuit provides interconnecting channel for unit under test afterbody joint and testing apparatus, realizes that the fully coupling between unit under test and the testing apparatus connects, and all I/O signals all carry out I/O by the I/O interface circuit; Automatic measurement circuit is measured resistance, voltage, frequency, the current parameters of unit under test automatically by FPGA control circuit control, and test data is transferred to computing machine by the RS232 communication port carries out calculation process; The working environment mimic channel is comprised of one group of precision resistance, switch, pot and discharge circuit, and the system environments that is connected with unit under test on the main simulated aircraft allows unit under test in the situation that break away from aircraft, realize the workshop test.
Certainly; above-mentioned explanation is not limitation of the utility model; the utility model also is not limited only to above-mentioned giving an example, and the variation that those skilled in the art make in essential scope of the present utility model, remodeling, interpolation or replacement also belong to protection domain of the present utility model.
Claims (2)
1. aircraft area temperature controller automatic analog test platform, comprise shell, be provided with the PCB circuit board in the described shell, described shell front end is provided with automatic test panel, it is characterized in that: described automatic test board comprises that pilot lamp viewing area, pot control band, waver are selected zone, test instrumentation interface circuit, connector zone, power switch is regional and spare interface.
2. aircraft area temperature controller automatic analog test platform according to claim 1, it is characterized in that: be provided with FPGA control circuit, I/O interface circuit, automatic measurement circuit and working environment mimic channel on the described PCB circuit board, described FPGA control circuit connects discrete switch circuit and described automatic measurement circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220485236 CN202771256U (en) | 2012-09-21 | 2012-09-21 | Aircraft zone temperature controller automatic simulation test desk |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220485236 CN202771256U (en) | 2012-09-21 | 2012-09-21 | Aircraft zone temperature controller automatic simulation test desk |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202771256U true CN202771256U (en) | 2013-03-06 |
Family
ID=47777819
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220485236 Expired - Fee Related CN202771256U (en) | 2012-09-21 | 2012-09-21 | Aircraft zone temperature controller automatic simulation test desk |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202771256U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112462735A (en) * | 2020-11-11 | 2021-03-09 | 中国电子科技集团公司第二十九研究所 | Universal automatic test system for environment control unit |
-
2012
- 2012-09-21 CN CN 201220485236 patent/CN202771256U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112462735A (en) * | 2020-11-11 | 2021-03-09 | 中国电子科技集团公司第二十九研究所 | Universal automatic test system for environment control unit |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130306 Termination date: 20180921 |