CN109115486B - Unmanned aerial vehicle engine oil gas shock absorber static pressure testing arrangement - Google Patents
Unmanned aerial vehicle engine oil gas shock absorber static pressure testing arrangement Download PDFInfo
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- CN109115486B CN109115486B CN201811243634.4A CN201811243634A CN109115486B CN 109115486 B CN109115486 B CN 109115486B CN 201811243634 A CN201811243634 A CN 201811243634A CN 109115486 B CN109115486 B CN 109115486B
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
The invention discloses a static pressure testing device of an unmanned engine oil-gas shock absorber, which consists of mounting seats, a screw transmission table, a servo motor, a tension-compression sensor, a displacement sensor and a control computer, wherein the shock absorber is arranged between the two mounting seats through a connecting piece. The control computer judges the working state of the shock absorber according to the numerical value of the tension-compression sensor, sends a stroke compression instruction and controls the servo motor to compress the shock absorber on the screw transmission table, the pressure sensor measures and feeds back the compression force transmitted by the shock absorber, the control computer judges and adjusts after collecting the compression force, the static pressure of the shock absorber can be effectively and rapidly tested, the situation that the static pressure of the shock absorber is reduced after the unmanned aerial vehicle is recovered and falls for many times is avoided, and the compression stroke of the shock absorber exceeds the allowable range due to the reduction of the static pressure of the oil gas leakage of the shock absorber. The testing device has the advantages of simple structure, convenient maintenance, contribution to field implementation operation, high testing precision, easy reading of testing results, strong environmental applicability and low use cost.
Description
Technical Field
The invention relates to the technical field of static pressure testing, in particular to a static pressure testing device of an unmanned engine oil-gas shock absorber.
Background
The recovery mode of the unmanned aerial vehicle is mainly divided into two modes of running landing and parachute landing. The landing of running is higher to the place requirement, and to middle-size small-size unmanned aerial vehicle, in order to retrieve simple convenient, adopts the parachuting to retrieve more to absorb the energy when landing through the bumper shock absorber. The interior of the shock absorber is filled with aviation hydraulic oil and compressed nitrogen, and energy is absorbed through damping force of the hydraulic oil flowing through the flow limiting hole and spring force of air compression. The magnitude of static pressure in the air cavity is in direct proportion to the air spring force, and is an important parameter for determining the buffer performance of the unmanned aerial vehicle shock absorber. Therefore, after recycling, a user needs to periodically carry out static pressure test on the shock absorber to judge whether the shock absorber is in a safe use range.
At present, a user mainly relies on manual experience to judge whether the pressure value meets the design requirement or not through the difficulty degree of manual compression of the shock absorber. The method has higher requirement on experience of a user, lacks quantization standard, is easy to generate artificial misjudgment, and has larger potential safety hazard; meanwhile, due to the lack of test data, the method is also unfavorable for guiding subsequent maintenance work. The testing method adopted by the manufacturer depends on a large professional testing experiment table and a high-precision testing instrument, and is unfavorable for delivering users from the aspects of use cost and convenience. In the technical field, the static pressure testing device and method for the oil-gas shock absorber of the parachute unmanned aerial vehicle are not disclosed in various documents.
Therefore, development of a static pressure testing device for the shock absorber of the unmanned aerial vehicle, which is simple in structure and convenient to use, and provides a set of quick and simple testing method and a standardized testing flow, can quickly and quantitatively test the shock absorber, and guide subsequent maintenance and repair work, is urgently needed.
Disclosure of Invention
In order to avoid the defects in the prior art, the invention provides the static pressure testing device for the unmanned aerial vehicle oil-gas shock absorber, which can test the static pressure of the shock absorber efficiently and quickly, and avoid that the compression stroke of the shock absorber exceeds the allowable range due to the leakage and the static pressure reduction of the oil-gas of the shock absorber after the unmanned aerial vehicle is recovered and fallen for a plurality of times; the testing device has a simple structure and is convenient to maintain and use; the testing method is beneficial to field implementation operation.
The technical scheme includes that the hydraulic vibration damping device comprises a platform support, a guide rail, a bolt, a digital display instrument, a control computer, a first connecting piece, a pressure sensor, a first mounting seat, a connector, a connecting pin, a shock absorber, a second connecting piece, a tension and compression sensor, a second mounting seat, a digital display displacement sensor, a hand wheel and a screw transmission platform, wherein the screw transmission platform comprises a motor mounting plate, a mounting vertical plate, a screw mounting seat, a servo motor and a screw, the screw transmission platform is fixedly connected to the side end of the upper part of the platform support through the bolt, the first mounting seat is positioned at the inner side of the screw transmission platform, the first mounting seat is mounted on the platform support through the guide rail, the screw transmission platform is connected with the first mounting seat through the screw in a matched manner, one end of the screw is connected with the screw mounting seat and the vertical plate through the connecting pin, the other end of the screw is connected with the first mounting seat through the first connecting piece, the pressure sensor is positioned on the first mounting seat, the second mounting seat is fixed on the platform support at one end opposite to the first mounting seat, the shock absorber is positioned between the first mounting seat and the second mounting seat, one end of the shock absorber is connected with the first mounting seat through the connecting pin and the first mounting seat through the connecting pin, the second mounting seat is connected with the second mounting seat through the second connecting piece through the connecting piece, and the tension and the vibration absorber is coaxially arranged in the compression sensor; the control computer and the digital display instrument are positioned at the end side of the platform bracket and are connected with the servo motor, and the digital display instrument is used for displaying a test result; the static pressure test method comprises the following steps:
step 1, clamping; the static pressure testing device is checked, and after the testing device is checked, two ends of the shock absorber of the unmanned aerial vehicle to be tested are connected with the platform connecting piece and are connected with the pressure sensor;
step 2, pressurizing; the control computer judges the working state of the shock absorber according to the numerical value of the pulling and pressing sensor, sends out a stroke compression instruction, and compresses the piston rod of the shock absorber inwards to enable the hydraulic oil surface to be flush with the end surface, and the uncompressed part of the piston rod is an extension; or the hand wheel is rocked to rotate the lead screw, so that the shock absorber is compressed, and the piston rod of the shock absorber is compressed inwards until the oil surface is flush with the end surface;
step 3, measuring; according to the static end pressure value when the pressure sensor measures the maximum compression amount, the control computer is used for judging whether the static pressure value of the shock absorber accords with the design allowable value after collecting the static end pressure value;
step 4, resetting; after the control computer collects the static pressure value, connecting pieces at two ends of the shock absorber are disassembled, and the servo motor is driven to reset;
step 5, adjusting; if the static end pressure does not meet the requirement, the test piece is regulated by selecting a reasonable oil-gas proportion, if the static end pressure is too low, the overhang amount is increased, the oil gas quantity is regulated, and if the static end pressure is too high, the overhang amount is reduced, and the oil gas quantity is regulated;
step 6, recording; and after the test is completed, recording a test result, and analyzing and processing data to form a test report.
Advantageous effects
The invention provides a static pressure testing device of an unmanned engine oil-gas shock absorber, which consists of mounting seats, a screw transmission table, a servo motor, a tension-compression sensor, a displacement sensor and a control computer, wherein the shock absorber is arranged between the two mounting seats through a connecting piece. The control computer judges the working state of the shock absorber according to the numerical value of the tension-compression sensor, sends a stroke compression instruction, controls the servo motor to compress the shock absorber on the screw transmission table, and the pressure sensor measures and feeds back the compression force transmitted by the shock absorber. The static pressure testing device has a simple structure and is beneficial to maintenance and use; the testing method is simple and convenient, and is beneficial to field implementation operation; the test precision is high, the test result is easy to read, and the environment applicability and the use cost are extremely high.
The static pressure testing device for the unmanned engine oil-gas shock absorber can test the static pressure of the shock absorber efficiently and rapidly, the testing method has visual results, and the situation that the static pressure is difficult to accurately judge when being reduced and human errors are caused by depending on experience is avoided. The static pressure testing device can be applied to various stages of manufacturing, testing, maintaining and repairing of the unmanned aerial vehicle shock absorber. Through the accurate test to the shock absorber static pressure value after unmanned aerial vehicle multiple parachute recovery or unconventional recovery, provide the basis for accurate judgement shock absorber whether available, improved unmanned aerial vehicle and equipped availability factor. Meanwhile, accurate information support is provided for the maintenance of the subsequent shock absorber by providing clear information feedback, so that the maintenance cost is reduced.
Drawings
The invention relates to an unmanned engine oil-gas shock absorber static pressure testing device, which is further described in detail below with reference to the accompanying drawings and the embodiments.
FIG. 1 is a schematic diagram of a static pressure testing device of an oil-gas shock absorber of an unmanned aerial vehicle.
Fig. 2 is a schematic structural diagram of a simple unmanned engine oil-gas shock absorber static pressure testing device.
Fig. 3 is a flow chart of a method for testing the static pressure of the shock absorber of the unmanned aerial vehicle.
In the figure:
1. platform bracket 2, guide rail 3, bolt 4, motor mounting plate 5, digital display 6, control computer 7, mounting plate 8, lead screw mounting seat 9, servo motor 10, lead screw 11, first connector 12, pressure sensor 13, first mounting seat 14, joint 15, connecting pin 16, damper 17, second connector 18, tension and compression sensor 19, second mounting seat 20, digital displacement sensor 21, hand wheel
Detailed Description
The embodiment is an unmanned aerial vehicle oil-gas shock absorber static pressure testing device.
Referring to fig. 1 to 3, the static pressure testing device for the unmanned aerial vehicle oil-gas shock absorber of the embodiment comprises a platform bracket 1, a guide rail 2, a bolt 3, a digital display 5, a control computer 6, a first connecting piece 11, a pressure sensor 12, a first mounting seat 13, a joint 14, a connecting pin 15, a shock absorber 16, a second connecting piece 17, a tension-compression sensor 18, a second mounting seat 19, a digital display displacement sensor 20, a hand wheel 21 and a screw transmission platform; the screw transmission platform comprises a motor mounting plate 4, a mounting vertical plate 7, a screw mounting seat 8, a servo motor 9 and a screw 10, the screw transmission platform is fixedly connected to the upper side end of the platform support 1 through bolts 3, a first mounting seat 13 is located on the inner side of the screw transmission platform, the first mounting seat 13 is mounted on the platform support 1 through a guide rail 2, and the screw transmission platform is connected with the first mounting seat 13 through the screw 10 in a matched mode. One end of a screw rod 10 is connected with the screw rod mounting seat 8 and the mounting vertical plate 7, the other end of the screw rod 10 is connected with the first mounting seat 13 through a first connecting piece 11, and the pressure sensor 12 is positioned on the first mounting seat 13. The second mount 19 is fixed to the platform bracket 1 at an end opposite the first mount 13. The shock absorber 16 is located between first mount pad 13 and the second mount pad 19, and shock absorber 16 one end is connected with first mount pad 13 through joint 14, connecting pin 15, and the other end of shock absorber 16 is connected with second mount pad 19 through second connecting piece 17, and second mount pad 19 front end has and draws pressure sensor 18 and digital display displacement sensor 20. The servo motor 9 is arranged on the motor mounting plate 4 and is coaxially connected with a turbine in the screw rod mounting seat 8, the servo motor 9 drives the screw rod 10 to rotate, and meanwhile, the first mounting seat 13 is pushed to move along the guide rail 2 to compress the shock absorber 16.
In this embodiment, the control computer 6 and the digital display 5 are installed on one side of the end of the platform bracket 1, and are connected to the servo motor 9. The digital display 5 is used for displaying the test results.
In this embodiment, the static pressure test method includes the following steps:
1. clamping; and (3) performing test operation inspection on the static pressure testing device, wherein each connecting piece is free of looseness, the lead screw is flexible to operate, and after the inspection of the testing device, two ends of the shock absorber of the unmanned aerial vehicle to be tested are connected with the platform connecting pieces and are connected with the pressure sensor.
2. Pressurizing; the control computer judges the working state of the shock absorber according to the numerical value of the distance sensor, sends out a stroke compression instruction, and compresses the piston rod of the shock absorber inwards to enable the hydraulic oil surface to be flush with the end surface, and at the moment, the uncompressed part of the piston rod is the extension; or the hand wheel is rotated to rotate the screw rod, so that the shock absorber is compressed, and the piston rod of the shock absorber is compressed inwards until the oil surface is flush with the end surface.
3. Measuring; and according to the static end pressure value when the pressure sensor measures the maximum compression amount, the control computer is used for judging whether the static pressure value of the shock absorber accords with the design allowable value after collecting the static end pressure value.
4. Resetting; after the control computer collects the static pressure value, connecting pieces at two ends of the shock absorber are disassembled, and the servo motor is driven to reset.
5. Adjusting; if the static end pressure does not meet the requirement, the test piece is adjusted by selecting a reasonable oil-gas proportion, the overhang amount is increased and the oil gas amount is adjusted when the static end pressure is too low, and the overhang amount is reduced and the oil gas amount is adjusted when the static end pressure is too high.
6. Recording; and (3) after the test is completed, recording a test result, and analyzing and processing data.
7. A test report is formed.
Claims (1)
1. The static pressure testing device for the unmanned engine oil-gas shock absorber is characterized by comprising a platform bracket, a guide rail, a bolt, a digital display instrument, a control computer, a first connecting piece, a pressure sensor, a first mounting seat, a connector, a connecting pin, a shock absorber, a second connecting piece, a tension-compression sensor, a second mounting seat, a digital display displacement sensor, a hand wheel and a screw transmission platform, wherein the screw transmission platform comprises a motor mounting plate, a mounting vertical plate, a screw mounting seat, a servo motor and a screw, the screw transmission platform is fixedly connected to the side end of the upper part of the platform bracket through the bolt, the first mounting seat is positioned on the inner side of the screw transmission platform, the first mounting seat is mounted on the platform bracket through the guide rail, the screw transmission platform is connected with the first mounting seat through the screw in a matched manner, one end of the screw is connected with the screw mounting seat and the mounting vertical plate through the first connecting piece, the other end of the screw is connected with the first mounting seat through the first connecting piece, the pressure sensor is positioned on the first mounting seat, the second mounting seat is fixed on the platform bracket at one end opposite to the first mounting seat, the shock absorber is positioned between the first mounting seat and the second mounting seat, one end of the shock absorber is positioned on the first mounting seat through the connector and the second mounting seat through the connector, the connecting pin is connected with the first servo motor through the second mounting seat, and the other end of the shock absorber is coaxially connected with the second mounting seat through the servo motor, and the first mounting seat through the servo motor, and the shock absorber is mounted in front and the vibration absorber; the control computer and the digital display instrument are positioned at the end side of the platform bracket and are connected with the servo motor, and the digital display instrument is used for displaying a test result; the static pressure test method comprises the following steps:
step 1, clamping; the static pressure testing device is checked, and after the testing device is checked, two ends of the shock absorber of the unmanned aerial vehicle to be tested are connected with the platform connecting piece and are connected with the pressure sensor;
step 2, pressurizing; the control computer judges the working state of the shock absorber according to the numerical value of the pulling and pressing sensor, sends out a stroke compression instruction, and compresses the piston rod of the shock absorber inwards to enable the hydraulic oil surface to be flush with the end surface, and the uncompressed part of the piston rod is an extension; or the hand wheel is rocked to rotate the lead screw, so that the shock absorber is compressed, and the piston rod of the shock absorber is compressed inwards until the oil surface is flush with the end surface;
step 3, measuring; according to the static end pressure value when the pressure sensor measures the maximum compression amount, the control computer is used for judging whether the static pressure value of the shock absorber accords with the design allowable value after collecting the static end pressure value;
step 4, resetting; after the control computer collects the static pressure value, connecting pieces at two ends of the shock absorber are disassembled, and the servo motor is driven to reset;
step 5, adjusting; if the static end pressure does not meet the requirement, the test piece is regulated by selecting a reasonable oil-gas proportion, if the static end pressure is too low, the overhang amount is increased, the oil gas quantity is regulated, and if the static end pressure is too high, the overhang amount is reduced, and the oil gas quantity is regulated;
step 6, recording; and after the test is completed, recording a test result, and analyzing and processing data to form a test report.
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| CN201811243634.4A CN109115486B (en) | 2018-10-24 | 2018-10-24 | Unmanned aerial vehicle engine oil gas shock absorber static pressure testing arrangement |
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| CN201811243634.4A CN109115486B (en) | 2018-10-24 | 2018-10-24 | Unmanned aerial vehicle engine oil gas shock absorber static pressure testing arrangement |
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| CN109115486B true CN109115486B (en) | 2023-10-17 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113803315B (en) * | 2021-07-29 | 2023-08-18 | 武汉船用机械有限责任公司 | Hydro-cylinder test device and test method |
| CN118032326A (en) * | 2024-04-15 | 2024-05-14 | 山东星辉液压设备有限公司 | Static pressure testing device for oil-gas shock absorber |
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| GB2104185A (en) * | 1981-07-02 | 1983-03-02 | Twyford Moors | Apparatus for testing shock absorbers |
| CN103217244A (en) * | 2013-03-26 | 2013-07-24 | 山东科技大学 | Shock absorber tension and pressure measuring instrument and detection method thereof |
| CN103630377A (en) * | 2013-12-16 | 2014-03-12 | 江苏科技大学 | Testing device for static load characteristics of shock absorber at rear part of motorcycle |
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| CN206832445U (en) * | 2017-06-01 | 2018-01-02 | 西安工程大学 | A kind of monitoring platform of unmanned plane Sledge type damper |
| CN207964237U (en) * | 2018-03-22 | 2018-10-12 | 西安爱生技术集团公司 | A kind of parachuting unmanned plane damper apparatus for impact testing |
| CN108692928A (en) * | 2018-04-09 | 2018-10-23 | 张家港市欧微自动化研发有限公司 | A kind of damper detection method |
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2018
- 2018-10-24 CN CN201811243634.4A patent/CN109115486B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2104185A (en) * | 1981-07-02 | 1983-03-02 | Twyford Moors | Apparatus for testing shock absorbers |
| CN103217244A (en) * | 2013-03-26 | 2013-07-24 | 山东科技大学 | Shock absorber tension and pressure measuring instrument and detection method thereof |
| CN103630377A (en) * | 2013-12-16 | 2014-03-12 | 江苏科技大学 | Testing device for static load characteristics of shock absorber at rear part of motorcycle |
| CN204389150U (en) * | 2014-12-30 | 2015-06-10 | 广东西电动力科技股份有限公司 | A kind of vibroshock static properties testing table |
| CN206832445U (en) * | 2017-06-01 | 2018-01-02 | 西安工程大学 | A kind of monitoring platform of unmanned plane Sledge type damper |
| CN207964237U (en) * | 2018-03-22 | 2018-10-12 | 西安爱生技术集团公司 | A kind of parachuting unmanned plane damper apparatus for impact testing |
| CN108692928A (en) * | 2018-04-09 | 2018-10-23 | 张家港市欧微自动化研发有限公司 | A kind of damper detection method |
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Effective date of registration: 20221020 Address after: No.34, Fenghui South Road, Xi'an, Shaanxi 710065 Applicant after: Xi'an Aisheng Technology Group Co.,Ltd. Address before: No.34, Fenghui South Road, Xi'an, Shaanxi 710065 Applicant before: XI'AN AISHENG TECHNOLOGY GROUP Co.,Ltd. Applicant before: Northwestern Polytechnical University |
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