CN213543979U - Test experiment device for simulating leakage fault of aviation hydraulic pipeline - Google Patents
Test experiment device for simulating leakage fault of aviation hydraulic pipeline Download PDFInfo
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- CN213543979U CN213543979U CN202022687688.9U CN202022687688U CN213543979U CN 213543979 U CN213543979 U CN 213543979U CN 202022687688 U CN202022687688 U CN 202022687688U CN 213543979 U CN213543979 U CN 213543979U
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- 238000012360 testing method Methods 0.000 title claims abstract description 49
- 238000002474 experimental method Methods 0.000 title claims abstract description 12
- 238000006243 chemical reaction Methods 0.000 claims abstract description 20
- 230000001133 acceleration Effects 0.000 claims abstract description 13
- 238000004088 simulation Methods 0.000 claims description 7
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 239000003921 oil Substances 0.000 abstract description 65
- 239000010720 hydraulic oil Substances 0.000 abstract description 4
- 230000008901 benefit Effects 0.000 abstract description 2
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- 230000008878 coupling Effects 0.000 description 1
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- 238000005859 coupling reaction Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
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Abstract
A test experimental device for simulating a leakage fault of an aviation hydraulic pipeline. The oil leakage test device comprises an oil inlet pipe diameter conversion head, an oil inlet main pipeline, a three-way pipe, a spherical valve, a connecting hose, a variable test pipeline, a leakage degree control joint, an acceleration sensor, an oil outlet main pipeline, an oil outlet pipe diameter conversion head, a main body frame, an oil leakage base and a pipe clamp. The utility model discloses the advantage: the mode that the variable test pipeline of usable change satisfies different pipe diameters, different pipe lengths, the pipeline test requirement of different shapes. The hydraulic pipelines with different leakage degrees can be simply and conveniently tested by replacing the leakage degree control joint. The acceleration sensor can simply and conveniently detect the acceleration of the measured pipeline and other data related to the experiment. The oil leakage base can be used for preventing oil sprayed from the test pipeline from splashing all around, and hydraulic oil can be uniformly treated.
Description
Technical Field
The utility model belongs to the technical field of aviation hydraulic line fault diagnosis experiments, especially, relate to a test experiment device of simulation aviation hydraulic line leakage fault.
Background
After the aviation hydraulic pipeline is worn and aged at different degrees, some pipelines can have faults such as cracks at different degrees, and the hydraulic pipeline extends to each corner of the aircraft, so that the leakage of the hydraulic pipeline can influence the operation condition of the aircraft undoubtedly. However, corresponding test equipment is still lacking.
Disclosure of Invention
In order to solve the problem, the utility model aims to provide a test device of simulation aviation hydraulic pressure pipeline leakage fault degree.
In order to achieve the purpose, the test experiment device for simulating the leakage fault of the aviation hydraulic pipeline provided by the utility model comprises an oil inlet pipe diameter conversion head, an oil inlet main pipeline, a three-way pipe, a spherical valve, a connecting hose, a variable test pipeline, a leakage degree control joint, an acceleration sensor, an oil outlet main pipeline, an oil outlet pipe diameter conversion head, a main body frame, an oil leakage base and a pipe clamp; the oil leakage base is of a rectangular disc-shaped structure; the main body frame is of a cuboid frame structure, a plurality of cross beams are arranged at intervals on the top of the main body frame, and the lower end of the main body frame is arranged in the oil leakage base; the main oil inlet pipeline is fixed on a cross beam on one side of the main body frame by using a pipe clamp, one end of the main oil inlet pipeline is used as an inlet end and connected with the oil inlet pipe diameter conversion head, a plurality of three-way pipes are arranged in the middle of the main oil inlet pipeline at intervals, and branch pipes which are not connected with the main oil inlet pipeline on the three-way pipes are used as outlet ends; the main oil outlet pipe is fixed on a cross beam on the other side of the main body frame by using a pipe clamp, one end of the main oil outlet pipe is used as an outlet end and is connected with an oil outlet pipe diameter conversion head, a plurality of three-way pipes are arranged in the middle of the main oil outlet pipe at intervals, and branch pipes which are not connected with the main oil outlet pipe are used as inlet ends on the three-way pipes; the outlet end or the inlet end of each three-way pipe is respectively connected with one end of a connecting hose; a variable test pipeline is connected between the outer ends of two connecting hoses which are connected to corresponding positions on the oil inlet main pipeline and the oil outlet main pipeline; each leakage degree control joint is in threaded connection with one variable test pipeline; at least one acceleration sensor is glued on the outside of a variable test pipeline; and a ball valve is arranged at the outlet end of each three-way pipe arranged on the oil inlet main pipeline.
The two side parts of the variable test pipeline are fixed on a cross beam in the middle of the main body frame by using pipe clamps.
The leakage degree control joint and the oil inlet pipe diameter conversion joint have different specifications.
The variable test pipeline has different pipe diameters, lengths and shapes.
The oil leakage base and the main body frame are made of aluminum alloy materials.
Compared with the prior art, the utility model provides a test experiment device of simulation aviation hydraulic pressure pipeline leakage fault has following advantage:
(1) the mode that the variable test pipeline of usable change satisfies different pipe diameters, different pipe lengths, the pipeline test requirement of different shapes.
(2) The hydraulic pipelines with different leakage degrees can be simply and conveniently tested by replacing the leakage degree control joint.
(3) The acceleration sensor can simply and conveniently detect the acceleration of the measured pipeline and other data related to the experiment.
(4) The oil leakage base can be used for preventing oil sprayed from the test pipeline from splashing all around, and hydraulic oil can be uniformly treated.
Drawings
Fig. 1 is the utility model provides a simulation aviation hydraulic pressure pipeline leaks test experiment device overall structure stereogram of trouble.
Detailed Description
It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1, the utility model provides a simulation aviation hydraulic pressure pipeline leakage fault's test experiment device includes oil feed pipe diameter crossover sub 1, oil feed trunk line 2, three-way pipe 3, globe valve 4, coupling hose 5, variable test pipeline 6, leakage degree control joint 7, acceleration sensor 8, the trunk line 9 that produces oil, the pipe diameter crossover sub 10 that produces oil, main body frame 11, oil leak base 12 and pipe clamp 13: wherein, the oil leakage base 12 is a rectangular disc structure; the main body frame 11 is a cuboid frame structure, a plurality of cross beams 14 are arranged at intervals on the top, and the lower end of the main body frame is arranged in the oil leakage base 12; the main oil inlet pipeline 2 is fixed on a cross beam 14 on one side of the main body frame 11 by a pipe clamp 13, one end of the main oil inlet pipeline is used as an inlet end and connected with the oil inlet pipe diameter conversion head 1, a plurality of three-way pipes 3 are arranged in the middle of the main oil inlet pipeline at intervals, and branch pipes which are not connected with the main oil inlet pipeline 2 on the three-way pipes 3 are used as outlet ends; the main oil outlet pipe 9 is fixed on a cross beam 14 on the other side of the main body frame 11 by a pipe clamp 13, one end of the main oil outlet pipe is used as an outlet end and is connected with the oil outlet pipe diameter conversion head 10, a plurality of three-way pipes 3 are arranged in the middle of the main oil outlet pipe at intervals, and branch pipes which are not connected with the main oil outlet pipe 9 on the three-way pipes 3 are used as inlet ends; the outlet end or the inlet end of each three-way pipe 3 is respectively connected with one end of a connecting hose 5; a variable test pipeline 6 is connected between the outer ends of two connecting hoses 5 which are connected to corresponding positions on the oil inlet main pipeline 2 and the oil outlet main pipeline 9; each leakage degree control joint 7 is in threaded connection with one variable test pipeline 6; at least one acceleration sensor 8 is glued to the outside of one variable test duct 6; and a ball valve 4 is arranged at the outlet end of each three-way pipe 3 arranged on the oil inlet main pipeline 2.
The two side parts of the variable test pipeline 6 are fixed on a cross beam 14 which is positioned in the middle of the main body frame 11 by using pipe clamps 13.
The leakage degree control joint 7 and the oil inlet pipe diameter conversion head 1 have different specifications.
The variable test tubes 6 have different tube diameters, lengths and shapes.
The oil leakage base 12 and the main body frame 11 are made of aluminum alloy materials.
Will now the utility model provides a test experiment device of simulation aviation hydraulic pressure pipeline leakage fault's application method explains as follows:
the testing experimental device is firstly arranged in an appointed area, a variable testing pipeline 6 with proper pipe diameter and length and leakage degree control joints 7 with different specifications are selected according to experimental requirements, an oil inlet pipe diameter conversion head 1 is connected with a pressure outlet of a hydraulic station, an oil outlet pipe diameter conversion head 10 is connected with an oil tank loop, a ball valve 4 of a required testing branch is opened, the hydraulic station is started to generate different oil pressure, at the moment, hydraulic oil from the hydraulic station enters an oil inlet main pipeline 2 through the oil inlet pipe diameter conversion head 1, then flows into a connecting hose 5 connected with the oil inlet main pipeline 2 through a corresponding three-way pipe 3, then flows into the variable testing pipeline 6, then flows into an oil outlet main pipeline 9 through another connecting hose 5 and the three-way pipe 3, and finally flows into the oil tank loop through the oil outlet pipe diameter conversion head 10. In the process, leakage faults of different degrees can be simulated by using the leakage degree control joints 7 of different specifications and the variable test pipelines 6 of different pipe diameters and lengths, inlet pressures of different conditions are provided by using the oil inlet pipe diameter conversion heads 1 of different specifications, acceleration time domain signals of hydraulic oil in the variable test pipelines 6 are acquired by using the acceleration sensor 8, and finally the rules are summarized by analyzing the signals.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The utility model provides a test experiment device of simulation aviation hydraulic line leakage fault which characterized in that: the test experimental device comprises an oil inlet pipe diameter conversion head (1), an oil inlet main pipeline (2), a three-way pipe (3), a ball valve (4), a connecting hose (5), a variable test pipeline (6), a leakage degree control joint (7), an acceleration sensor (8), an oil outlet main pipeline (9), an oil outlet pipe diameter conversion head (10), a main body frame (11), an oil leakage base (12) and a pipe clamp (13): wherein, the oil leakage base (12) is of a rectangular disc-shaped structure; the main body frame (11) is of a cuboid frame structure, a plurality of cross beams (14) are arranged at intervals on the top of the main body frame, and the lower end of the main body frame is arranged in the oil leakage base (12); the main oil inlet pipeline (2) is fixed on a cross beam (14) on one side of the main body frame (11) by a pipe clamp (13), one end of the main oil inlet pipeline is used as an inlet end and connected with the oil inlet pipe diameter conversion head (1), a plurality of three-way pipes (3) are arranged in the middle of the main oil inlet pipeline at intervals, and branch pipes which are not connected with the main oil inlet pipeline (2) on the three-way pipes (3) are used as outlet ends; the main oil outlet pipe (9) is fixed on a cross beam (14) on the other side of the main body frame (11) by a pipe clamp (13), one end of the main oil outlet pipe is used as an outlet end and connected with an oil outlet pipe diameter conversion head (10), a plurality of three-way pipes (3) are arranged in the middle of the main oil outlet pipe at intervals, and branch pipes which are not connected with the main oil outlet pipe (9) on the three-way pipes (3) are used as inlet ends; the outlet end or the inlet end of each three-way pipe (3) is respectively connected with one end of a connecting hose (5); a variable test pipeline (6) is connected between the outer ends of two connecting hoses (5) which are connected to corresponding positions on the oil inlet main pipeline (2) and the oil outlet main pipeline (9); each leakage degree control joint (7) is in threaded connection with a variable test pipeline (6); at least one acceleration sensor (8) is glued to the outside of a variable test duct (6); each three-way pipe (3) arranged on the oil inlet main pipeline (2) is provided with a ball valve (4) at the outlet end.
2. The test experimental device for simulating the leakage fault of the aviation hydraulic pipeline according to claim 1, characterized in that: two side parts of the variable test pipeline (6) are fixed on a cross beam (14) which is positioned in the middle of the main body frame (11) by using pipe clamps (13).
3. The test experimental device for simulating the leakage fault of the aviation hydraulic pipeline according to claim 1, characterized in that: the leakage degree control joint (7) and the oil inlet pipe diameter conversion joint (1) have different specifications.
4. The test experimental device for simulating the leakage fault of the aviation hydraulic pipeline according to claim 1, characterized in that: the variable test pipelines (6) have different pipe diameters, lengths and shapes.
5. The test experimental device for simulating the leakage fault of the aviation hydraulic pipeline according to claim 1, characterized in that: the oil leakage base (12) and the main body frame (11) are made of aluminum alloy materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022687688.9U CN213543979U (en) | 2020-11-19 | 2020-11-19 | Test experiment device for simulating leakage fault of aviation hydraulic pipeline |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022687688.9U CN213543979U (en) | 2020-11-19 | 2020-11-19 | Test experiment device for simulating leakage fault of aviation hydraulic pipeline |
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| CN213543979U true CN213543979U (en) | 2021-06-25 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115389137A (en) * | 2022-10-27 | 2022-11-25 | 烟台中宇航空液压有限公司 | Test experiment device for simulating leakage fault of aviation hydraulic pipeline |
| CN115898855A (en) * | 2023-02-10 | 2023-04-04 | 南京航空航天大学金城学院 | Single-double pump test control device and test method |
-
2020
- 2020-11-19 CN CN202022687688.9U patent/CN213543979U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115389137A (en) * | 2022-10-27 | 2022-11-25 | 烟台中宇航空液压有限公司 | Test experiment device for simulating leakage fault of aviation hydraulic pipeline |
| CN115898855A (en) * | 2023-02-10 | 2023-04-04 | 南京航空航天大学金城学院 | Single-double pump test control device and test method |
| CN115898855B (en) * | 2023-02-10 | 2023-12-29 | 南京航空航天大学金城学院 | Single-double pump test control device and test method |
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Assignee: Xiaotang (Tianjin) Technology Co.,Ltd. Assignor: CIVIL AVIATION University OF CHINA Contract record no.: X2024980002340 Denomination of utility model: A testing experimental device for simulating leakage faults in aviation hydraulic pipelines Granted publication date: 20210625 License type: Common License Record date: 20240228 |