CN203601583U - System for testing performance of airplane porthole assembly - Google Patents
System for testing performance of airplane porthole assembly Download PDFInfo
- Publication number
- CN203601583U CN203601583U CN201320771559.5U CN201320771559U CN203601583U CN 203601583 U CN203601583 U CN 203601583U CN 201320771559 U CN201320771559 U CN 201320771559U CN 203601583 U CN203601583 U CN 203601583U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- assembly
- plc
- proofing box
- electromagnetic valve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model discloses a system for testing the performance of an airplane porthole assembly. The system comprises an industrial personal computer, a PLC, a testing device of the airplane porthole assembly and an air source used for providing air for the testing device of the airplane porthole assembly, wherein the industrial personal computer is used for being connected with the PLC, transmitting a pulse signal for controlling the testing device of the airplane porthole assembly and receiving a current signal of the testing device of the airplane porthole assembly processed by the PLC, and the PLC is used for receiving the pulse signal for the industrial personal computer to control the testing device of the airplane porthole assembly and receiving and processing the current signal of the testing device of the airplane porthole assembly. The system can effectively simulate temperature and pressure parameters of an airplane under the working conditions of flying and really reflect the physical performance of airplane porthole glass in the actual work and influences of assembled components on the performance of the of airplane porthole glass, testing data in the performance testing process can be automatically intercepted and saved in the industrial personal computer, and the testing functions can be expanded.
Description
Technical field
The utility model relates to a kind of test macro, especially relates to a kind of test macro of aircraft porthole assembly property.
Background technology
For the test of aircraft porthole assembly property, at present both at home and abroad generally based on material mechanical performance test method, to aerial organic glass print under different temperatures, stretch, distortion and destruction after tension and compression research and analyse, there is larger difference in its test environment and aircraft flight operating mode, can not truly reflect the physical property in the real work of aircraft side of a ship window assembly, its research object all concentrates on air port glass material itself simultaneously, has ignored the impact that air port glass load module produces its performance.
Aircraft side of a ship window assembly must be prolonged and repeated be exposed under the harsh environment that the residing temperature of aircraft flight process, air pressure are changeable, and because of its physical property difference, crazing, crackle, the even phenomenon of explosion easily appear in aircraft side of a ship window assembly in flight course.Therefore the test method that, adopts the test of temperature, pressure bonding simulated aircraft side of a ship window assembly flight operating mode aircraft porthole assembly property is tested more effectively.
Summary of the invention
For the problem existing in existing test method, the purpose of this utility model is to provide a kind of test macro of aircraft porthole assembly property, and simulated aircraft flight work condition environment carries out the test of aircraft porthole assembly property.
The utility model is achieved through the following technical solutions:
The utility model comprises industrial computer, for the also impulse singla of transfer control aircraft porthole assembly test device that is connected with programmable logic controller (PLC), and receives the current signal through programmable logic controller (PLC) aircraft porthole after treatment assembly test device;
Comprise programmable logic controller (PLC), for receiving the impulse singla of industrial computer control aircraft porthole assembly test device, and the current signal of reception & disposal aircraft porthole assembly test device;
Comprise aircraft porthole assembly test device and be used to aircraft porthole assembly test device that the source of the gas of air is provided.
The current signal of described aircraft porthole assembly test device comprises the deformation current signal of temperature current signal, air pressure current signal and aircraft side of a ship window assembly.
Described aircraft porthole assembly test device comprises proofing box, aircraft side of a ship window assembly, two temperature sensors for detection of proofing box temperature, two for detection of the pressure sensor of proofing box air pressure, displacement pickup, air inlet switch electromagnetic valve, air discharge cook electromagnetic valve, electric Proportion valve and high-low temperature controller for detection of the deformation of aircraft side of a ship window assembly, in proofing box, be divided into upper chambers and lower chamber, aircraft side of a ship window assembly is contained between the upper chambers and lower chamber of proofing box, aircraft side of a ship window assembly is by upper chambers and lower chamber isolation, source of the gas is successively through electric Proportion valve, after air inlet switch electromagnetic valve, be connected with the upper chambers of proofing box, the upper chambers of proofing box is connected with air discharge cook electromagnetic valve, the upper chambers of proofing box is respectively connected with temperature sensor and pressure sensor with lower chamber, in the lower chamber of proofing box, high-low temperature controller is housed, displacement pickup is contained in the lower chamber under aircraft side of a ship window assembly, the thimble of displacement pickup contacts with the center of aircraft side of a ship window assembly, two temperature sensors, two pressure sensors, displacement pickup, air inlet switch electromagnetic valve, air discharge cook electromagnetic valve and electric Proportion valves are connected with industrial computer through described programmable logic controller (PLC).
Described programmable logic controller (PLC) comprises digital I/O mouth, analog output module and analog input module, described air inlet switch electromagnetic valve, air discharge cook electromagnetic valve are all connected with digital I/O mouth, described electric Proportion valve is connected with analog output module, and described two temperature sensors, two pressure sensors, displacement pickups are all connected with analog input module.
Between described source of the gas and electric Proportion valve, be connected with manual ball valve.
Between described air inlet switch electromagnetic valve and the upper chambers of proofing box, be connected with check valve.
The air pressure positive differential pressure of the upper chambers of described proofing box and lower chamber is 0～6bar, and upper chambers temperature is normal temperature, and lower chamber temperature is-55 ~ 80 degrees Celsius.
Described aircraft side of a ship window assembly comprises the load module of air port glass and air port glass periphery.
Between described industrial computer and programmable logic controller (PLC), connect by serial transmission mouth.
The beneficial effect the utlity model has is:
The utility model temperature, pressure parameter that effectively simulated aircraft flies under operating mode, truly reflect physical property and the impact of load module on its performance generation in the real work of aircraft air port glass.The utility model comprises the test of aircraft porthole assembly property: extreme pressure test, fatigue test, Work condition analogue test, can automatically intercept and be saved in the data bank of industrial computer the test data in performance testing process.The utility model can be realized the expansion of test function.
Accompanying drawing explanation
Fig. 1 is connection structure graph of a relation of the present utility model.
Fig. 2 is control structure figure of the present utility model.
In figure: 1, industrial computer, 2, programmable logic controller (PLC), 3, aircraft porthole assembly test device, 4, source of the gas, 5, proofing box, 6, air discharge cook electromagnetic valve, 20, digital I/O mouth, 21, analog input module, 22, analog output module, 31, temperature sensor, 32, pressure sensor, 33, displacement pickup, 34, air inlet switch electromagnetic valve, 35, electric Proportion valve, 36, aircraft side of a ship window assembly, 37, manual ball valve, 38, check valve, 39, high-low temperature controller.
The specific embodiment
Below in conjunction with drawings and the specific embodiments, the utility model is described in further detail.
As shown in Figure 1 and Figure 2, the utility model comprises industrial computer 1, for the also impulse singla of transfer control aircraft porthole assembly test device 3 that is connected with programmable logic controller (PLC) 2, and receive the current signal through programmable logic controller (PLC) 2 aircraft porthole after treatment assembly test device 3;
Comprise programmable logic controller (PLC) 2, control the impulse singla of aircraft porthole assembly test device 3 for receiving industrial computer 1, and the current signal of reception & disposal aircraft porthole assembly test device 3;
Comprise aircraft porthole assembly test device 3 and be used to aircraft porthole assembly test device 3 that the source of the gas 4 of air is provided.
The current signal of described aircraft porthole assembly test device 3 comprises the deformation current signal of temperature current signal, air pressure current signal and aircraft side of a ship window assembly.
As shown in Figure 2, described aircraft porthole assembly test device 3 comprises proofing box 5, aircraft side of a ship window assembly 36, two temperature sensors 31 for detection of proofing box temperature, two for detection of the pressure sensor 32 of proofing box air pressure, displacement pickup 33, air inlet switch electromagnetic valve 34, air discharge cook electromagnetic valve 6, electric Proportion valve 35 and high-low temperature controller 39 for detection of the deformation of aircraft side of a ship window assembly, in proofing box 5, be divided into upper chambers and lower chamber, aircraft side of a ship window assembly 36 is contained between the upper chambers and lower chamber of proofing box 5, aircraft side of a ship window assembly 36 is by upper chambers and lower chamber isolation, source of the gas 4 is successively through electric Proportion valve 35, after air inlet switch electromagnetic valve 34, be connected with the upper chambers of proofing box 5, the upper chambers of proofing box 5 is connected with air discharge cook electromagnetic valve 6, the upper chambers of proofing box 5 is respectively connected with temperature sensor 31 and pressure sensor 32 with lower chamber, high-low temperature controller 39 is housed in the lower chamber of proofing box 5, displacement pickup 33 is contained in the lower chamber under aircraft side of a ship window assembly 36, the thimble of displacement pickup 33 contacts with the center of aircraft side of a ship window assembly 36, two temperature sensors 31, two pressure sensors 32, displacement pickup 33, air inlet switch electromagnetic valve 34, air discharge cook electromagnetic valves 6 are connected with industrial computer 1 through described programmable logic controller (PLC) 2 with electric Proportion valve 35.
As shown in Figure 2, described programmable logic controller (PLC) 2 comprises digital I/O mouth 20, analog output module 22 and analog input module 21, described air inlet switch electromagnetic valve 34, air discharge cook electromagnetic valve 6 are all connected with digital I/O mouth 20, described electric Proportion valve 35 is connected with analog output module 22, and described two temperature sensors 31, two pressure sensors 32, displacement pickups 33 are all connected with analog input module 21.
Between described source of the gas 4 and electric Proportion valve 35, be connected with manual ball valve 37.
Between described air inlet switch electromagnetic valve 34 and the upper chambers of proofing box 5, be connected with check valve 38.
The upper chambers of described proofing box 5 and the air pressure positive differential pressure of lower chamber are 0～6bar, and upper chambers temperature is normal temperature, and lower chamber temperature is-55 ~ 80 degrees Celsius.
Described aircraft side of a ship window assembly 36 comprises the load module of air port glass and air port glass periphery.
Between described industrial computer 1 and programmable logic controller (PLC) 2, connect by serial transmission mouth.
Source of the gas 4 can adopt pneumatics unit, and pneumatics unit comprises the parts such as pressure source, freeze drier, filter, storage tank and regulator, for aircraft porthole assembly test device provides the air of uniform temperature, pressure and clean dried.
The exhausr port of pneumatics unit connects electric Proportion valve 35 after manual ball valve to be realized the adjusting of pressure and stablizes; Displacement pickup 33 is the deformation quantity under temperature, pressure load for testing airplane side of a ship window assembly 36.In the concrete enforcement of the utility model, programmable logic controller (PLC) 2 adopts S7-224CPU, and analog output module 22 adopts EM232, and analog input module 21 adopts EM231, and temperature sensor 31 adopts PT100 type.
Described industrial computer 1 is obtained the current signal of temperature sensor 31, pressure sensor 32 and displacement pickup 33 that analog input module 21 collects from programmable logic controller (PLC) 2, and this measurement signal is processed, to obtain every supplemental characteristic that needs test, computer operating system and aircraft porthole assembly property software system are installed simultaneously, for user provides operation interface, and all observed datas that measure are shown and stored in data bank.
Concrete implementation process of the present utility model (how complete test process being described in detail in detail in conjunction with beneficial effect):
In enforcement, the test of aircraft porthole assembly property is comprised: extreme pressure test, fatigue test, Work condition analogue test.
Extreme pressure test process is as follows: first connect the working power of whole test macro, setting high-low temperature controller 39 is a certain temperature value, waits for that the bottom cavity temperature of proofing box 5 reaches this temperature value; Start source of the gas 4, industrial computer 1, reach after test requirements document scope until source of the gas 4 air pressure, open manual ball valve 37; Exporting high level by the digital I/O mouth 20 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1 makes air inlet switch electromagnetic valve 34 be held open state; By the analog output module 22 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1 export 4 ~ 20mA standard current signal make electric Proportion valve 35 export air pressure from 1bar by set speed raise, until aircraft side of a ship window assembly 36 lost efficacy, show and preserve force value, temperature value, the deformation values of inefficacy eve; Close manual ball valve 37, export high level by the digital I/O mouth 20 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1 air discharge cook electromagnetic valve 6 is opened, system exhaust pressure release.Revise the temperature value of high-low temperature controller 39, repeat above-mentioned steps.
Fatigue test process is as follows: first connect the working power of whole test macro, setting high-low temperature controller 39 is a certain temperature value, waits for that the bottom cavity temperature of proofing box 5 reaches this temperature value; Start source of the gas 4, industrial computer 1, reach after test requirements document scope until source of the gas 4 air pressure, open manual ball valve 37; Exporting 4 ~ 20mA standard current signal by the analog output module 22 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1, to make electric Proportion valve 35 export air pressure constant in test requirements document pressure; Export low and high level by the digital I/O mouth 20 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1 air inlet switch electromagnetic valve 34 and air discharge cook electromagnetic valve 6 are carried out to switch control, make the upper chambers internal gas pressure of proofing box 5 by the sine curve cyclical variation of setting, until aircraft side of a ship window assembly 36 lost efficacy or completed the cycle number of requirement, preserve temperature, pressure, deformation change curve in this process of the test; Close manual ball valve 37, export high level by the digital I/O mouth 20 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1 air discharge cook electromagnetic valve 6 is opened, system exhaust pressure release.Revise the temperature value of high-low temperature controller 39, repeat above-mentioned steps.
Work condition analogue process of the test is as follows: first connect the working power of whole test macro, start source of the gas 4, industrial computer 1, reach after test requirements document scope until source of the gas 4 air pressure, open manual ball valve 37; Exporting 4 ~ 20mA standard current signal by the analog output module 22 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1, to make electric Proportion valve 35 export air pressure constant in test requirements document pressure; Export low and high level by the digital I/O mouth 20 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1 air inlet switch electromagnetic valve 34 and air discharge cook electromagnetic valve 6 are carried out to switch control, the upper chambers internal gas pressure of proofing box 5 is changed by the step curve of setting, the temperature of simultaneously setting high-low temperature controller 39 changes by setting curve, preserves temperature, pressure, deformation change curve in process of the test; Close manual ball valve 37, export high level by the digital I/O mouth 20 in the operation interface control programmable logic controller (PLC) 2 of industrial computer 1 air discharge cook electromagnetic valve 6 is opened, system exhaust pressure release.
The above-mentioned specific embodiment is used for the utility model of explaining; rather than the utility model is limited; in the protection domain of spirit of the present utility model and claim, any modification and change that the utility model is made, all fall into protection domain of the present utility model.
Claims (9)
1. a test macro for aircraft porthole assembly property, is characterized in that:
Comprise industrial computer (1), for the also impulse singla of transfer control aircraft porthole assembly test device (3) that is connected with programmable logic controller (PLC) (2), and receive the current signal through programmable logic controller (PLC) (2) aircraft porthole after treatment assembly test device (3);
Comprise programmable logic controller (PLC) (2), control the impulse singla of aircraft porthole assembly test device (3) for receiving industrial computer (1), and the current signal of reception & disposal aircraft porthole assembly test device (3);
Comprise aircraft porthole assembly test device (3) and be used to aircraft porthole assembly test device (3) that the source of the gas (4) of air is provided.
2. the test macro of a kind of aircraft porthole assembly property according to claim 1, is characterized in that: the current signal of described aircraft porthole assembly test device (3) comprises the deformation current signal of temperature current signal, air pressure current signal and aircraft side of a ship window assembly.
3. the test macro of a kind of aircraft porthole assembly property according to claim 1, is characterized in that: described aircraft porthole assembly test device (3) comprises proofing box (5), aircraft side of a ship window assembly (36), two temperature sensors for detection of proofing box temperature (31), two pressure sensors for detection of proofing box air pressure (32), displacement pickup (33), air inlet switch electromagnetic valve (34), air discharge cook electromagnetic valve (6), electric Proportion valve (35) and high-low temperature controller (39) for detection of the deformation of aircraft side of a ship window assembly, proofing box is divided into upper chambers and lower chamber in (5), aircraft side of a ship window assembly (36) is contained between the upper chambers and lower chamber of proofing box (5), aircraft side of a ship window assembly (36) is by upper chambers and lower chamber isolation, source of the gas (4) is successively through electric Proportion valve (35), after air inlet switch electromagnetic valve (34), be connected with the upper chambers of proofing box (5), the upper chambers of proofing box (5) is connected with air discharge cook electromagnetic valve (6), the upper chambers of proofing box (5) is respectively connected with temperature sensor (31) and pressure sensor (32) with lower chamber, high-low temperature controller (39) is housed in the lower chamber of proofing box (5), displacement pickup (33) is contained in the lower chamber under aircraft side of a ship window assembly (36), the thimble of displacement pickup (33) contacts with the center of aircraft side of a ship window assembly (36), two temperature sensors (31), two pressure sensors (32), displacement pickup (33), air inlet switch electromagnetic valve (34), air discharge cook electromagnetic valve (6) and electric Proportion valve (35) are connected with industrial computer (1) through described programmable logic controller (PLC) (2).
4. the test macro of a kind of aircraft porthole assembly property according to claim 3, it is characterized in that: described programmable logic controller (PLC) (2) comprises digital I/O mouth (20), analog output module (22) and analog input module (21), described air inlet switch electromagnetic valve (34), air discharge cook electromagnetic valve (6) is all connected with digital I/O mouth (20), described electric Proportion valve (35) is connected with analog output module (22), described two temperature sensors (31), two pressure sensors (32), displacement pickup (33) is all connected with analog input module (21).
5. the test macro of a kind of aircraft porthole assembly property according to claim 3, is characterized in that: between described source of the gas (4) and electric Proportion valve (35), be connected with manual ball valve (37).
6. the test macro of a kind of aircraft porthole assembly property according to claim 3, is characterized in that: between described air inlet switch electromagnetic valve (34) and the upper chambers of proofing box (5), be connected with check valve (38).
7. the test macro of a kind of aircraft porthole assembly property according to claim 3, it is characterized in that: the described upper chambers of proofing box (5) and the air pressure positive differential pressure of lower chamber are 0～6bar, upper chambers temperature is normal temperature, and lower chamber temperature is-55 ~ 80 degrees Celsius.
8. the test macro of a kind of aircraft porthole assembly property according to claim 3, is characterized in that: described aircraft side of a ship window assembly (36) comprises the load module of air port glass and air port glass periphery.
9. the test macro of a kind of aircraft porthole assembly property according to claim 4, is characterized in that: between described industrial computer (1) and programmable logic controller (PLC) (2), connect by serial transmission mouth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320771559.5U CN203601583U (en) | 2013-11-29 | 2013-11-29 | System for testing performance of airplane porthole assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320771559.5U CN203601583U (en) | 2013-11-29 | 2013-11-29 | System for testing performance of airplane porthole assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203601583U true CN203601583U (en) | 2014-05-21 |
Family
ID=50714271
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320771559.5U Expired - Fee Related CN203601583U (en) | 2013-11-29 | 2013-11-29 | System for testing performance of airplane porthole assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203601583U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662086A (en) * | 2013-11-29 | 2014-03-26 | 浙江省计量科学研究院 | Airplane porthole component performance test system |
| CN106556548A (en) * | 2017-01-16 | 2017-04-05 | 江苏铁锚玻璃股份有限公司 | A kind of cold-resistant thermal impact of aircraft glass and compression resistance fatigue resistance test device |
| CN108622438A (en) * | 2018-07-30 | 2018-10-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The Physical Simulation Platform of component performance degradation and failure in a kind of simulation fuel system |
| CN110963074A (en) * | 2019-12-25 | 2020-04-07 | 中航贵州飞机有限责任公司 | Unmanned aerial vehicle undercarriage signal simulation system |
-
2013
- 2013-11-29 CN CN201320771559.5U patent/CN203601583U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662086A (en) * | 2013-11-29 | 2014-03-26 | 浙江省计量科学研究院 | Airplane porthole component performance test system |
| CN106556548A (en) * | 2017-01-16 | 2017-04-05 | 江苏铁锚玻璃股份有限公司 | A kind of cold-resistant thermal impact of aircraft glass and compression resistance fatigue resistance test device |
| CN108622438A (en) * | 2018-07-30 | 2018-10-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The Physical Simulation Platform of component performance degradation and failure in a kind of simulation fuel system |
| CN108622438B (en) * | 2018-07-30 | 2023-08-25 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Physical simulation platform for simulating performance degradation and faults of components in fuel system |
| CN110963074A (en) * | 2019-12-25 | 2020-04-07 | 中航贵州飞机有限责任公司 | Unmanned aerial vehicle undercarriage signal simulation system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103662086B (en) | The test macro of aircraft windows assembly property | |
| CN203601583U (en) | System for testing performance of airplane porthole assembly | |
| CN102866007B (en) | A kind of cylinder head fatigue test device and test method | |
| CN105302003B (en) | A kind of servo-control system for the simulation of aircraft air pressure | |
| CN101887479B (en) | Rapid diagnosis method for rotating stall of axial flow compressor based on determined learning theory | |
| CN202628482U (en) | Automatic blower fan performance testing system | |
| CN106066606B (en) | Hydrogen internal combustion engine ignition timing calibration optimization system and its optimization method based on L-M neural network | |
| CN105201639B (en) | The control device and control method of internal combustion engine | |
| CN101629879A (en) | Cabin type gas sampler | |
| CN202221468U (en) | Gas density relay calibrator | |
| CN103487251A (en) | Electric-heating-based turbo-supercharger checking test bench and turbo-supercharger property testing method | |
| CN105352735A (en) | Engine plateau air inlet simulation device | |
| CN1834609B (en) | Fast point sampling system of internal cylinder of I.C. engine | |
| CN104153931B (en) | Method for detecting deflagration phenomenon in explosive motor | |
| CN102670322A (en) | Shock wave generating device | |
| CN103728143B (en) | High-speed train load fatigue and comfort testing system and testing method | |
| CN103674718B (en) | Based on cell pressure method of testing and the test macro of explosion-proof mathematical model | |
| CN201732032U (en) | Vehicle seat fatigue durability testing system | |
| CN205247229U (en) | Device of gaseous decompression of pulsewidth modulation | |
| CN102393288B (en) | Spatial inflatable structure ground expansion performance test system | |
| CN106249070A (en) | A kind of test system and method for electric automobile heat management pipeline | |
| CN202537697U (en) | Shock wave generating device | |
| CN204439278U (en) | TPMS pressure test platform | |
| CN103323182A (en) | Automatic transmitter leak hunting system based on PLC control | |
| CN106969879A (en) | A kind of dynamic and static pressure exerciser |
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: 20140521 Termination date: 20151129 |