CN112611674A - Aircraft landing gear buffer gas oil dissolution dynamic balance test device and test method thereof - Google Patents
Aircraft landing gear buffer gas oil dissolution dynamic balance test device and test method thereof Download PDFInfo
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- CN112611674A CN112611674A CN202011169798.4A CN202011169798A CN112611674A CN 112611674 A CN112611674 A CN 112611674A CN 202011169798 A CN202011169798 A CN 202011169798A CN 112611674 A CN112611674 A CN 112611674A
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Abstract
The invention discloses a dynamic balance test device and a test method for gas oil dissolution of an aircraft landing gear buffer, and belongs to the technical field of aircraft landing gear tests. The dynamic balance test device and the test method for the gas oil solution dissolution of the aircraft landing gear buffer can effectively simulate the compression and extension action processes of the aircraft landing gear buffer during vibration work, so that the dynamic solubility test of nitrogen in the buffer in hydraulic oil can be carried out. Comprises a base, an actuating cylinder 12, a test bed, an environment box 8, a hydraulic cylinder 1 and a pressure transmitter 5; one side of the test bed is hinged to the top surface of the base, the other side of the test bed is connected with the base through the actuating cylinder 12, and the test bed is driven to vibrate through the actuating cylinder 12. The testing device is simple in structure, reduces the testing scale and saves the testing cost. The dynamic process of oil-liquid-gas dissolution in the buffer under vibration can be researched, and the balance point in the dynamic dissolution process can be found.
Description
Technical Field
The invention relates to a dynamic balance test device and a test method for gas oil dissolution of an aircraft landing gear buffer, and belongs to the technical field of aircraft landing gear tests.
Background
The hydraulic buffer buffers and decelerates the object acting on the hydraulic buffer to stop by means of hydraulic damping, and plays a certain protection role. The safety buffer device is used for preventing the mechanism from being damaged due to hard collision in the working process. The solubility of nitrogen in hydraulic oil is an important factor influencing the performance of the buffer, and because the motion of the buffer cannot be completely kept static when an airplane takes off and lands, the research on the gas-oil dissolution dynamic balance of the buffer is necessary.
At present, the solubility test device and the test method of nitrogen in hydraulic oil in an aircraft landing gear buffer have less domestic disclosures, and the research and the starting are earlier in the aspect abroad, but the disclosures of the test device and the test method of nitrogen in the aircraft landing gear buffer and the Chinese invention patent with the application number of 202010130738.5 which are disclosed by the intellectual property office of China in 6, 9.2020 have been disclosed, but the buffer is still in a static state in the simulation process, and the actual working state of the buffer cannot be really simulated. Therefore, further experimental simulation studies on this problem are needed.
Disclosure of Invention
Aiming at the problems, the invention provides a test device and a test method for the gas oil dissolution dynamic balance of the undercarriage buffer, which can effectively simulate the compression and extension action processes of the undercarriage buffer when the undercarriage buffer works in a vibration mode, so as to perform a dynamic solubility test on nitrogen in the buffer in hydraulic oil.
The technical scheme of the invention is as follows: comprises a base, an actuating cylinder 12, a test bed, an environment box 8, a hydraulic cylinder 1 and a pressure transmitter 5;
one side of the test bed is hinged to the top surface of the base, the other side of the test bed is connected with the base through an actuating cylinder 12, and the test bed is driven to vibrate through the actuating cylinder 12;
the environment box 8 and the hydraulic cylinder 1 are both fixedly connected to the test bed, the test piece is arranged in the environment box 8, the environment box 8 provides environment temperature for the test piece, the hydraulic cylinder 1 is fixedly connected to one side of the environment box, the output end of the hydraulic cylinder 1 is connected with the test piece, and pressure is applied to the test piece through the hydraulic cylinder 1; and the pressure transmitter 5 is connected to the test piece and is used for acquiring the pressure inside the test piece.
The bottom end of the actuating cylinder 12 is hinged to the top surface of the base, and the top end of the actuating cylinder 12 is hinged to the bottom surface of the test bed.
The environment box is also provided with a load sensor 2 for acquiring axial load, a displacement sensor 6 for acquiring displacement and a temperature sensor 11 for acquiring temperature value;
one end of the test piece is connected with the output end of the hydraulic cylinder 1 through the load transfer joint 3 and the load sensor 2, and the axial load applied to the test piece is obtained through the load sensor 2;
the displacement sensor 6 is connected to one side of the test piece, and the displacement of the test piece during stretching is obtained through the displacement sensor 6;
the temperature sensor 11 is arranged in the environment box 8, and the real-time temperature value in the environment box 8 is obtained through the temperature sensor 11.
The whole test piece is positioned in an environment box 8, and the side surface of the environment box is connected with an air inlet pipeline 9 and an air outlet pipeline 10.
The test was carried out as follows:
the method comprises the following steps: assembling a test piece according to the test technical requirements and installing the test piece on a test bed;
step two: the buffer temperature is observed by a temperature sensor 11, and the inside of the environmental chamber 8 is kept at a constant temperature; starting the hydraulic cylinder 1, recording the instantaneous axial load through the load sensor 2, and recording the compression stroke of the buffer piston rod through the displacement sensor 6; after the piston rod is compressed to different strokes, the actuating cylinder 12 continuously stretches to enable the test bed to vibrate, the pressure transmitter 5 is used for recording the pressure corresponding to the different compression strokes, the data collector is used for collecting pressure data, the time when the pressure is stable in the vibration process is concerned, and corresponding data are recorded; then adjusting the compression stroke of the buffer, and performing the steps again until the data of the compression stroke of the whole buffer is recorded;
step three: the temperature in the environment box is controlled by the hot gas entering and exiting through the air inlet pipeline 9 and the air outlet pipeline 10 in the environment box 8, the temperature is raised, and the operation in the second step is repeated until the data of the whole limit temperature range are recorded;
step four: and (5) after one group of tests are finished, repeating the tests, collecting multiple groups of data, and processing the data.
The data processing mentioned in the fourth step specifically includes: the pressure under different temperatures and compression strokes is obtained through the reading of the pressure transmitter 5, the amount of dissolved substances of the oil is calculated through an ideal gas state equation, and then the gas solubility of the buffer can be obtained, and in the vibration process, the pressure tends to be stable, and the solubility also tends to be stable.
The invention has the following beneficial effects: the vibration of the buffer in the action process is simulated, and the dynamic balance of the dissolution process is favorably researched; the hydraulic actuating cylinder is adopted for loading, so that the load is stable and the continuity is good; the testing device is simple in structure, reduces the testing scale and saves the testing cost. The vibration factor has been added to this test bench, can be faster reach dissolving balance, has shortened test cycle greatly, can study the dynamic process that the interior oil liquid gas of buffer dissolved under the vibration, find out the equilibrium point in the middle of the dynamic dissolving process to calculate under corresponding temperature and the compression stroke nitrogen gas solubility size in the middle of the fluid.
Drawings
FIG. 1 is a schematic structural diagram of the present application,
FIG. 2 is a perspective view of the present disclosure;
in the figure, 1 is a hydraulic cylinder, 2 is a load sensor, 3 is a load transmission joint, 4 is a buffer piston rod, 5 is a pressure transmitter, 6 is a displacement sensor, 7 is a buffer outer cylinder, 8 is an environment box, 9 is an air inlet pipeline, 10 is an air outlet pipeline, 11 is a temperature sensor, 12 is an actuating cylinder, and 13 is a fixed hinged support.
Detailed Description
In order to clearly explain the technical features of the present patent, the following detailed description of the present patent is provided in conjunction with the accompanying drawings.
The invention is shown in figure 1-2, comprising a base, an actuating cylinder 12, a test bed, an environment box 8, a hydraulic cylinder 1 and a pressure transmitter 5;
one side of the test bed is hinged on the top surface of the base through a fixed hinge support 13, the other side of the test bed is connected with the base through an actuating cylinder 12, and the test bed is driven to vibrate through the actuating cylinder 12;
the environment box 8 and the hydraulic cylinder 1 are both fixedly connected to the test bed, the test piece is arranged in the environment box 8, the environment box 8 provides environment temperature for the test piece, the hydraulic cylinder 1 is fixedly connected to one side of the environment box, the output end of the hydraulic cylinder 1 is connected with the test piece, and pressure is applied to the test piece through the hydraulic cylinder 1; the pressure transmitter 5 is connected to the test piece and is used for collecting the pressure inside the test piece (namely, the oil pressure value of the inner cavity of the instantaneous buffer can be read). Therefore, the pressure in the buffer test piece at different temperatures is obtained through the sensor connected to the buffer test piece, and the solubility of the gas in the buffer test piece is calculated.
The test piece includes buffer piston rod 4 and buffer urceolus 7, the one end of test piece articulates within environment case 8, and the other end is articulated with the output that pneumatic cylinder 1 stretched into environment case 8, the test piece is with the axle center with pneumatic cylinder 1. Because the hydraulic cylinder 1 pushes the test piece damper to move along the axial direction, stable loading of the load can be ensured in the process of compressing the damper piston rod 4.
The bottom end of the actuating cylinder 12 is hinged to the top surface of the base, and the top end of the actuating cylinder 12 is hinged to the bottom surface of the test bed. Therefore, the whole test bed can vibrate up and down by controlling the extension and retraction of the actuating cylinder, so that the gas oil and the liquid of the buffer in the environment box 8 can be fully mixed, and the dissolution balance point in the vibration process can be researched.
Meanwhile, the action processes of compression and extension of the aircraft landing gear buffer during vibration work can be effectively simulated by means of the actuating cylinder 12, the dynamic balance of the dissolving process can be researched, and the dynamic solubility test of nitrogen in the buffer in hydraulic oil can be carried out in the real sense.
The environment box is also provided with a load sensor 2 for acquiring axial load, a displacement sensor 6 for acquiring displacement and a temperature sensor 11 for acquiring temperature value;
one end of the test piece is connected with the output end of the hydraulic cylinder 1 through the load transfer joint 3 and the load sensor 2, and the axial load applied to the test piece is obtained through the load sensor 2;
the displacement sensor 6 is connected to one side of the test piece, and the displacement of the test piece during stretching is obtained through the displacement sensor 6;
the temperature sensor 11 is arranged in the environment box 8, and the real-time temperature value in the environment box 8 is obtained through the temperature sensor 11.
The whole test piece is positioned in an environment box 8, and the side surface of the environment box is provided with an air inlet pipeline 9 and an air outlet pipeline 10. Therefore, the temperature in the environment box can be effectively controlled in a mode of introducing hot air or cold air into the air inlet pipeline.
The test was carried out as follows:
the method comprises the following steps: assembling a test piece according to the test technical requirements and installing the test piece on a test bed;
step two: the buffer temperature is observed by a temperature sensor 11, and the inside of the environmental chamber 8 is kept at a constant temperature; starting the hydraulic cylinder 1, recording the instantaneous axial load through the load sensor 2, and recording the compression stroke of the buffer piston rod through the displacement sensor 6; after the piston rod is compressed to different strokes, the actuating cylinder 12 continuously stretches to enable the test bed to vibrate, the pressure transmitter 5 is used for recording the pressure corresponding to the different compression strokes, the data collector is used for collecting pressure data, the time when the pressure is stable in the vibration process is concerned, and corresponding data are recorded; then adjusting the compression stroke of the buffer, and performing the steps again until the data of the compression stroke of the whole buffer is recorded;
step three: the temperature in the environment box is controlled by the hot gas entering and exiting through the air inlet pipeline 9 and the air outlet pipeline 10 in the environment box 8, the temperature is raised, and the operation in the second step is repeated until the data of the whole limit temperature range are recorded;
step four: and (5) after one group of tests are finished, repeating the tests, collecting multiple groups of data, and processing the data.
The data processing mentioned in the fourth step specifically includes: the pressure under different temperatures and compression strokes is obtained through the reading of the pressure transmitter (5), the amount of dissolved substances of the oil is calculated through an ideal gas state equation, and then the gas solubility of the buffer can be obtained, and in the vibration process, the pressure tends to be stable, and the solubility also tends to be stable.
While the invention has been described in terms of its preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.
Claims (6)
1. A gas oil dissolution dynamic balance test device for an aircraft landing gear buffer is characterized by comprising a base, an actuating cylinder (12), a test bed, an environment box (8), a hydraulic cylinder (1) and a pressure transmitter (5);
one side of the test bed is hinged to the top surface of the base, the other side of the test bed is connected with the base through an actuating cylinder (12), and the test bed is driven to vibrate through the actuating cylinder (12);
the environment box (8) and the hydraulic cylinder (1) are both fixedly connected to the test bed, the test piece is arranged in the environment box (8), the environment box (8) is used for providing environment temperature for the test piece, the hydraulic cylinder (1) is fixedly connected to one side of the environment box, the output end of the hydraulic cylinder (1) is connected with the test piece, and pressure is applied to the test piece through the hydraulic cylinder (1); and the pressure transmitter (5) is connected to the test piece and is used for acquiring the pressure inside the test piece.
2. An aircraft landing gear bumper gas oil dissolution dynamic balance test device according to claim 1, wherein the bottom end of the actuator cylinder (12) is hinged to the top surface of the base and the top end of the actuator cylinder (12) is hinged to the bottom surface of the test bed.
3. The aircraft landing gear bumper gas oil dissolution dynamic balance test device according to claim 1, wherein a load sensor (2) for acquiring an axial load, a displacement sensor (6) for acquiring a displacement amount and a temperature sensor (11) for acquiring a temperature value are further arranged in the environment box;
one end of the test piece is connected with the output end of the hydraulic cylinder (1) through the load transfer joint (3) and the load sensor (2), and the axial load applied to the test piece is obtained through the load sensor (2);
the displacement sensor (6) is connected to one side of the test piece, and the displacement of the test piece during expansion and contraction is obtained through the displacement sensor (6);
the temperature sensor (11) is arranged in the environment box (8), and the real-time temperature value in the environment box (8) is obtained through the temperature sensor (11).
4. An aircraft landing gear bumper gas oil dissolution dynamic balance test device according to claim 1, wherein the whole test piece is positioned in an environment box (8), and the side surface of the environment box is connected with an air inlet pipeline (9) and an air outlet pipeline (10).
5. A dynamic balance test method for gas oil dissolution of an aircraft landing gear buffer is characterized by comprising the following steps of:
the method comprises the following steps: assembling a test piece according to the test technical requirements and installing the test piece on a test bed;
step two: observing the buffer temperature through a temperature sensor (11), and keeping the inside of the environment box (8) at a constant temperature; starting the hydraulic cylinder (1), recording instantaneous axial load through the load sensor (2), and recording the compression stroke of the piston rod of the buffer through the displacement sensor (6); after the piston rod is compressed to different strokes, the actuating cylinder (12) continuously stretches to enable the test bed to vibrate, the pressure transmitter (5) is used for recording the pressure corresponding to the different compression strokes, the data collector is used for collecting pressure data, and the corresponding data are recorded when the pressure is stable in the vibration process; then adjusting the compression stroke of the buffer, and performing the steps again until the data of the compression stroke of the whole buffer is recorded;
step three: controlling the temperature in the environment box by hot gas entering and exiting through an air inlet pipeline (9) and an air outlet pipeline (10) in the environment box (8), increasing the temperature, and repeating the operation of the second step until the data of the whole limit temperature range are recorded;
step four: and (5) after one group of tests are finished, repeating the tests, collecting multiple groups of data, and processing the data.
6. The aircraft landing gear bumper gas oil liquid dissolution dynamic balance test method according to claim 5, wherein the data processing in the fourth step specifically refers to: the pressure under different temperatures and compression strokes is obtained through the reading of the pressure transmitter (5), the amount of dissolved substances of the oil is calculated through an ideal gas state equation, and then the gas solubility of the buffer can be obtained, and in the vibration process, the pressure tends to be stable, and the solubility also tends to be stable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011169798.4A CN112611674A (en) | 2020-10-28 | 2020-10-28 | Aircraft landing gear buffer gas oil dissolution dynamic balance test device and test method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011169798.4A CN112611674A (en) | 2020-10-28 | 2020-10-28 | Aircraft landing gear buffer gas oil dissolution dynamic balance test device and test method thereof |
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Citations (8)
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| EP0588563B1 (en) * | 1992-09-17 | 1999-03-10 | Sanyo Chemical Industries, Ltd. | Vibration-absorbing elastomeric composite, process for making the same, and vibration damper comprising the same |
| CN204025512U (en) * | 2014-07-25 | 2014-12-17 | 王军 | A kind of automobile absorber |
| CN204479256U (en) * | 2015-01-14 | 2015-07-15 | 中国矿业大学 | A kind of single table surface horizontal vertical vibration table |
| CN206095775U (en) * | 2016-10-17 | 2017-04-12 | 三峡大学 | A shaking table for GDS pressure controller bubble is eliminated |
| CN106895948A (en) * | 2017-01-17 | 2017-06-27 | 同济大学 | It is a kind of that the shaking table model device that oscillatory load is toppled in earthquake is provided |
| CN109443679A (en) * | 2018-11-30 | 2019-03-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of vibration experiment |
| CN110619156A (en) * | 2019-08-30 | 2019-12-27 | 长沙理工大学 | High-precision mathematical model modeling method for dynamic characteristics of oil-gas suspension |
| CN111257163A (en) * | 2020-02-28 | 2020-06-09 | 南京航空航天大学 | Aircraft landing gear buffer oil liquid gas solubility test device and test method thereof |
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2020
- 2020-10-28 CN CN202011169798.4A patent/CN112611674A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0588563B1 (en) * | 1992-09-17 | 1999-03-10 | Sanyo Chemical Industries, Ltd. | Vibration-absorbing elastomeric composite, process for making the same, and vibration damper comprising the same |
| CN204025512U (en) * | 2014-07-25 | 2014-12-17 | 王军 | A kind of automobile absorber |
| CN204479256U (en) * | 2015-01-14 | 2015-07-15 | 中国矿业大学 | A kind of single table surface horizontal vertical vibration table |
| CN206095775U (en) * | 2016-10-17 | 2017-04-12 | 三峡大学 | A shaking table for GDS pressure controller bubble is eliminated |
| CN106895948A (en) * | 2017-01-17 | 2017-06-27 | 同济大学 | It is a kind of that the shaking table model device that oscillatory load is toppled in earthquake is provided |
| CN109443679A (en) * | 2018-11-30 | 2019-03-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of vibration experiment |
| CN110619156A (en) * | 2019-08-30 | 2019-12-27 | 长沙理工大学 | High-precision mathematical model modeling method for dynamic characteristics of oil-gas suspension |
| CN111257163A (en) * | 2020-02-28 | 2020-06-09 | 南京航空航天大学 | Aircraft landing gear buffer oil liquid gas solubility test device and test method thereof |
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