CN201497912U - Plane cabin pressure controller test system - Google Patents
Plane cabin pressure controller test system Download PDFInfo
- Publication number
- CN201497912U CN201497912U CN2009202264992U CN200920226499U CN201497912U CN 201497912 U CN201497912 U CN 201497912U CN 2009202264992 U CN2009202264992 U CN 2009202264992U CN 200920226499 U CN200920226499 U CN 200920226499U CN 201497912 U CN201497912 U CN 201497912U
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- pressure controller
- cabin pressure
- interface
- test board
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Abstract
The utility model discloses a plane cabin pressure controller test system, which comprises a computer, wherein an RS 422 receiving-transmitting board and an ARINC 429 receiving-transmitting board are arranged on the computer, the computer is respectively connected with a test bench and a digital multimeter, the test bench is connected with the digital multimeter, and a cabin pressure controller interface is arranged on the test bench. The plane cabin pressure controller test system realizes the automation of cabin pressure controller tests under the control of test software, and improves the test efficiency.
Description
Technical field
The utility model relates to a kind of aircraft cabin pressure controller test device, specifically, relates to a kind of aircraft cabin pressure controller test system.
Background technology
In aircraft manufacturing and maintenance job, usually need the aircraft cabin pressure controller is tested and keeped in repair, whether testing airplane cockpit pressure controller can operate as normal, find out the trouble spot, the aircraft cabin pressure controller is keeped in repair, and existing to cockpit pressure controller test system, automaticity is not high, testing efficiency is lower, and this is the deficiencies in the prior art part.
The utility model content
The technical problems to be solved in the utility model provides a kind of aircraft cabin pressure controller automatic test system, and this system realizes the automatic test to the cockpit pressure controller, and testing efficiency is higher.
The utility model adopts following technical scheme to realize goal of the invention:
A kind of aircraft cabin pressure controller test system, comprise computing machine, wherein, described computing machine is provided with RS422 transceiver boards and ARINC429 transceiver boards, described computing machine also connects test board and digital multimeter respectively, described test board is connected with digital multimeter, and described test board is provided with the cockpit pressure control unit interface.
As the technical program is further limited, described test board comprises CPLD control module, relay matrix and USB control module, and described CPLD control module can be according to the test access of the automatic selective relay matrix of test procedure.
As the technical program is further limited, described test board is provided with RS422 interface, ARINC429 interface and USB interface.
Compared with prior art, advantage of the present utility model with good effect is: test board of the present utility model is connected the passenger cabin pressure controller, simultaneously respectively by the RS422 interface, ARINC429 interface and USB interface are connected on the interface of computing machine correspondence, the testing software of computing machine sends test massage for the cockpit pressure controller by test board, the CPLD control module is by USB control module and computer testing software communication, the CPLD control module can be according to the test access of the automatic selective relay matrix of test procedure, digital multimeter is used for the measurement of some magnitudes of voltage, the magnitude of voltage that records is delivered to computing machine, call for test software programs.The test results platform of cockpit pressure controller is delivered to computer testing software, carries out analyzing and processing by testing software, and the display process result.The utility model is realized the robotization of cockpit pressure controller test under testing software control, improved testing efficiency.
Description of drawings
Fig. 1 is the structural representation of the utility model preferred embodiment.
Fig. 2 is the process flow diagram of the utility model preferred embodiment.
Among the figure, 1, computing machine, 2, the RS422 transceiver boards, 3, the ARINC429 transceiver boards, 4, test board, 5, digital multimeter, 6, the CPLD control module, 7, relay matrix, 8, the USB control module, 9, the cockpit pressure controller.
Embodiment
Below in conjunction with accompanying drawing and preferred embodiment the utility model is done further to describe in detail.
Referring to Fig. 1, computing machine 1 is provided with RS422 transceiver boards 2 and ARINC429 transceiver boards 3, and computing machine 1 also connects test board 4 and digital multimeter 5 respectively, and test board 4 is connected with digital multimeter 5, and test board 4 is provided with cockpit pressure controller 9 interfaces.Test board 4 comprises CPLD control module 6, relay matrix 7 and USB control module 8.CPLD control module 6 is a programmable logic device (PLD), realizes two big functions by programming: meter relay matrix 7 information, i.e. row and column; The control information of meter relay matrix 7.Determine some relays in the relay matrix 7 according to control information work thus, thereby reached the function that commutation circuit is provided and the passage of receiving and sending messages is provided.6 of CPLD control modules provide commutation circuit and the function of the passage of receiving and sending messages are provided, and are to carry out according to the requirement of cockpit pressure controller CMM verification of product documentation part.The relay matrix of this preferred embodiment amounts to 41 relays and forms, by the darlington transistor array driving of 6 big electric currents of MC1413.Wherein 17 relays are used for the driving of discrete magnitude signal; 4 relays are used for 28V discrete magnitude drive controlling; 7 are used for load driving; 10 ARINC429 signals that are used for pressure controller drive; 3 are used for standby.
Testing software comprises visual examination module, overlap resistance test module, megger test module, acquiescence input response test module, power supply test module, input discrete magnitude test module, output discrete magnitude test module, ARINC429 interface testing module, RS422 control module, pressure sensor interface test module, nonvolatile memory test module.What testing software adopted is the CVI software platform exploitation of America NI company, and test result can generate text automatically or printer prints is arranged, and can judge by test result whether the cockpit pressure controller meets the installation requirement.
Referring to Fig. 2, workflow of the present utility model is: computing machine 1 connects test board 4, test board 4 connects passenger cabin pressure controller 9, testing software sends test massage for cockpit pressure controller 9 by test board 4, relay matrix 7 sends discrete signal for cockpit pressure controller 9, send digital signal for cockpit pressure controller 9 by ARINC429 integrated circuit board and RS422 integrated circuit board, digital multimeter 5 is measured the magnitude of voltage of passenger cabin pressure controller 9 by test board 4, the magnitude of voltage that records is delivered to computing machine 1, call for the testing software test procedure.The test results platform 4 of cockpit pressure controller 9 is delivered to computer testing software, carries out analyzing and processing by testing software, and shows test results.Test software programs designs according to cockpit pressure controller CMM handbook standard, a plurality of testing procedures in the testing software are that order is carried out, and the input signal in each step is all different, therefore the staff can select whole steps to carry out complete functional test, also can select proper step to carry out the test of emphasis as required, and the signal of input and output measured and monitor, conveniently carry out troubleshooting and repair.
Certainly; above-mentioned explanation is not to restriction of the present utility model; the utility model also is not limited only to above-mentioned giving an example, and variation, remodeling, interpolation or replacement that those skilled in the art are made in essential scope of the present utility model also belong to protection domain of the present utility model.
Claims (3)
1. aircraft cabin pressure controller test system, comprise computing machine, it is characterized in that: described computing machine is provided with RS422 transceiver boards and ARINC429 transceiver boards, described computing machine also connects test board and digital multimeter respectively, described test board is connected with digital multimeter, and described test board is provided with the cockpit pressure control unit interface.
2. according to the described test macro of claim 1, it is characterized in that: described test board comprises CPLD control module, relay matrix and USB control module, and described CPLD control module can be according to the test access of the automatic selective relay matrix of test procedure.
3. according to the described test macro of claim 1, it is characterized in that: described test board is provided with RS422 interface, ARINC429 interface and USB interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202264992U CN201497912U (en) | 2009-09-17 | 2009-09-17 | Plane cabin pressure controller test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202264992U CN201497912U (en) | 2009-09-17 | 2009-09-17 | Plane cabin pressure controller test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201497912U true CN201497912U (en) | 2010-06-02 |
Family
ID=42441115
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202264992U Expired - Fee Related CN201497912U (en) | 2009-09-17 | 2009-09-17 | Plane cabin pressure controller test system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201497912U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103424231A (en) * | 2013-09-02 | 2013-12-04 | 成都飞亚航空设备应用研究所有限公司 | Air leakage testing bed and detection method using same |
| CN106094785A (en) * | 2016-06-01 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Cabin Pressure Control System ground experiment device |
-
2009
- 2009-09-17 CN CN2009202264992U patent/CN201497912U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103424231A (en) * | 2013-09-02 | 2013-12-04 | 成都飞亚航空设备应用研究所有限公司 | Air leakage testing bed and detection method using same |
| CN106094785A (en) * | 2016-06-01 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Cabin Pressure Control System ground experiment device |
| CN106094785B (en) * | 2016-06-01 | 2018-07-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Cabin Pressure Control System ground experiment device |
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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 |
Granted publication date: 20100602 Termination date: 20150917 |
|
| EXPY | Termination of patent right or utility model |