CN114088368A - Performance test device and method for aerospace damper - Google Patents
Performance test device and method for aerospace damper Download PDFInfo
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- CN114088368A CN114088368A CN202111297342.0A CN202111297342A CN114088368A CN 114088368 A CN114088368 A CN 114088368A CN 202111297342 A CN202111297342 A CN 202111297342A CN 114088368 A CN114088368 A CN 114088368A
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- 238000011056 performance test Methods 0.000 title claims abstract description 11
- 238000000034 method Methods 0.000 title claims description 18
- 238000012360 testing method Methods 0.000 claims abstract description 34
- 238000005259 measurement Methods 0.000 claims abstract description 25
- 238000006073 displacement reaction Methods 0.000 claims abstract description 23
- 238000013016 damping Methods 0.000 claims description 18
- 239000007788 liquid Substances 0.000 claims description 13
- 238000010998 test method Methods 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 3
- 238000012795 verification Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- 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 provides a performance test device and a test method for a space damper, wherein the device comprises: the device comprises a test bench (1), a bottom fixed seat (2), a force sensor (4), a servo hydraulic actuator (6), a displacement sensor (7) and a measurement and control system; the test bench (1) is of a door-shaped frame structure, and the bottom fixing seat (2), the aerospace damper (8), the force sensor (4), the servo hydraulic actuator (6) and the displacement sensor (7) are vertically arranged on the test bench (1) from bottom to top in sequence; the measurement and control system is respectively connected with the force sensor (4), the servo hydraulic actuator (6) and the displacement sensor (7) and used for sending an action instruction to the servo hydraulic actuator (6) and receiving feedback data of the force sensor (4) and the displacement sensor (7) and determining the performance of the aviation damper (8) according to the feedback information. The connection mode is simple and effective.
Description
Technical Field
The invention belongs to the technical field of damping verification tests, and particularly relates to a device and a method for testing the performance of a space damper.
Background
Various dampers are applied to the industries of aerospace, aviation, war industry, firearms, automobiles and the like for damping vibration and dissipating energy, and the performance of the dampers has important significance for the safe use of the dampers.
The performance of the existing damper, such as damping characteristic curve, is usually obtained by simulation calculation according to design data.
However, for dampers used on precision aerospace equipment such as rocket escape capsules, and particularly when a plurality of dampers are linked and the working states of the dampers need to be ensured to be consistent, the performance characteristics of the existing dampers are not accurate enough, and the test requirements of the aerospace equipment cannot be met.
Disclosure of Invention
The invention provides a performance test device and a test method for a space damper, which can verify the damping characteristic performance, detect and draw a relation curve between the damping force of a damper and the movement speed of the damper; measuring an actual value of the liquid level inside the damper; measuring a locking force value on the damper; and verifying the locking bearing capacity of the damper.
The invention provides a spacecraft damper performance test device in a first aspect, which comprises: the test bed comprises a test bed 1, a bottom fixed seat 2, a force sensor 4, a servo hydraulic actuator 6, a displacement sensor 7 and a measurement and control system;
the test bench 1 is of a door-shaped frame structure, the bottom fixing seat 2 is fixedly arranged at the bottom of the test bench 1, the space damper 8 is vertically installed, and the end of a test piece piston rod of the space damper 8 is connected with the bottom fixing seat 2;
the fixed part of the servo hydraulic actuator 6 is vertically and fixedly arranged on the top beam of the test bed 1, and the displacement sensor 7 is fixed at the top of the servo hydraulic actuator 6 and connected with the upper piston rod of the servo hydraulic actuator 6; the force sensor 4 is arranged between the bottom of the servo hydraulic actuator 6 and the outer cylinder end of the aerospace damper 8;
the measurement and control system is respectively connected with the force sensor 4, the servo hydraulic actuator 6 and the displacement sensor 7 and is used for sending an action instruction to the servo hydraulic actuator 6, receiving feedback data of the force sensor 4 and the displacement sensor 7 and determining a relation curve between the damping force of the damper and the movement speed of the damper according to the feedback information; measuring an actual value of the liquid level inside the damper; measuring a locking force value on the damper; and verifying the locking bearing capacity of the damper.
Optionally, the method further includes: a length adjusting screw sleeve 5;
the length adjusting thread sleeve 5 is arranged between the aerospace damper 8 and the servo hydraulic actuator 6 and used for eliminating a gap between the aerospace damper 8 and the servo hydraulic actuator 6.
Optionally, the method further includes: a loading joint 3;
the force sensor 4 is connected between the length adjusting threaded sleeve 5 and the outer cylinder end of the aerospace damper 8 through the loading joint 3.
Optionally, the loading joint 3 and the aerospace damper 8 are hinged by using a joint bearing.
Optionally, the bottom fixing seat 2, the servo hydraulic actuator 6, the displacement sensor 7 and the aerospace damper 8 are connected and then located on the same vertical axis.
The invention also provides a performance test method of an aerospace damper, which adopts the device in any one of the first aspect, and comprises the following steps:
the measurement and control system sends a first instruction to the servo hydraulic actuator, and the first instruction is used for controlling the servo hydraulic actuator to move according to a first preset speed; the first preset speed is 0.5-1 m/s;
the servo hydraulic actuator moves according to the first instruction to drive the piston of the aerospace damper to impact a damping liquid level in the aerospace damper;
the measurement and control system receives the collected data of the force sensor and acquires a force-time curve of the aerospace damper according to the collected data and the first instruction; and determining the actual value of the liquid level height in the aerospace damper according to the force-time curve.
Optionally, the method further includes:
the measurement and control system sends a plurality of second instructions to the servo hydraulic actuator, and each second instruction is used for controlling the servo hydraulic actuator to move according to different preset speeds;
the servo hydraulic actuator moves according to different preset speeds according to the second instructions;
the measurement and control system receives the data collected by the displacement sensor and the force sensor at different preset speeds, and determines a damping characteristic curve of the damping force of the aerospace damper and the movement speed of the damper piston.
Optionally, the method further includes:
the measurement and control system sends a third instruction to the servo hydraulic actuator, and the third instruction is used for indicating the servo hydraulic actuator to stretch the aerospace damper;
the servo hydraulic actuator pulls the aerospace damper according to the third instruction to enable a piston rod of the aerospace damper to uniformly and slowly extend out until the aerospace damper is locked after being stretched to the maximum extent;
the measurement and control system collects the axial force fed back by the force sensor to obtain a force and time curve of the aerospace damper; after the collection is finished, reading the maximum value of the wave crest of the force and time curve according to the force and time curve, namely the locking force on the damper;
after the space damper is locked, the measurement and control system applies rated axial pressure to the space damper through the servo hydraulic actuator to verify whether the damper is in a locking state or not.
The performance test device and the performance test method for the aerospace damper provided by the invention adopt the overall structural design of the test bed, and the rigidity is stable. The sensor and the loading structure are arranged according to the structural principle of the aerospace damper, the connection mode is simple and effective, a redundant structure is avoided, and the measurement precision and the test efficiency are effectively guaranteed. The invention can quickly and efficiently carry out batch test on the damper, has higher practical value and is developed and applied at present.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a spacecraft damper performance test device provided by the invention;
FIG. 2 is a schematic diagram of a verification and testing method for performance indexes of an aerospace damper provided by the invention;
description of reference numerals:
1-test stand; 2-bottom fixing seat;
3-a loading joint; 4-a force sensor;
5, adjusting the length of the screw sleeve; 6-servo hydraulic actuator;
7-a displacement sensor; 8-space damper.
Detailed Description
The invention provides a device and a method for testing the performance of an aerospace damper, which are explained in the following by combining with the accompanying drawings.
Referring to the accompanying drawings 1-2, the invention provides a performance test device for a space damper, which comprises: the test bed comprises a test bed 1, a bottom fixing seat 2, a loading joint 3, a force sensor 4, a length adjusting threaded sleeve 5, a servo hydraulic actuator 6 and a displacement sensor 7.
Furthermore, a servo hydraulic actuator 6 is fixed at the top of the test bed 1, and a displacement sensor 7 is fixed at the top of the servo hydraulic actuator 6 and is connected with a piston rod at the upper part of the servo hydraulic actuator 6. The loading joint 3 is connected with the force sensor 4 and the length adjusting threaded sleeve 5 and is connected with the servo hydraulic actuator 6.
Furthermore, the aerospace damper 8 is vertically installed during testing, so that the damping liquid in the aerospace damper is completely concentrated on the lower part under the action of gravity. The bottom fixing seat 2 is connected with a piston rod end of a test piece of the space damper 8, the loading joint 3 is connected with the outer cylinder end of the other side of the test piece of the space damper 8, and a connecting point is hinged by adopting a joint bearing. The bottom fixing seat 2, the loading joints 3 and 4, the length adjusting threaded sleeve 5, the servo hydraulic actuator 6, the displacement sensor 7 and the test piece of the aerospace damper 8 are connected and then located on the same vertical axis.
In addition, the force sensor 4, the servo hydraulic actuator 6 and the displacement sensor 7 are electrically connected with a test measurement and control system.
Referring to fig. 2, the method for testing the performance verification of the aerospace damper of the invention includes the following steps:
A. the aerospace damper 8 is installed on the test bed 1, the outer cylinder end is connected with the loading connector 3, and the piston rod end is connected with the bottom fixing seat 2.
B. The connector play is eliminated by the length adjustment thread insert 5.
C. The servo hydraulic actuator 6 is driven to move at a high speed by giving an instruction through a measurement and control system and controlling a valve in the servo hydraulic actuator 6, a piston of the aerospace damper 8 is driven to impact the internal damping liquid level, and a force-time curve is obtained by feeding back data through the force sensor 4. The actual value of the liquid level in the aerospace damper 8 and the deviation from the designed value are obtained by comparing the stroke of the displacement sensor 7 corresponding to the sudden change of the feedback force-time curve (the force-time curve has a relatively gentle waveform and is basically kept horizontal when the piston of the aerospace damper 8 is not in contact with the liquid level, the force-time curve has a relatively large upward slope sudden change when the piston of the aerospace damper 8 is in contact with the liquid level, and the slope sudden change point is the actual liquid level height point).
D. Different commands are given by the measurement and control system to obtain different operating speeds of the servo hydraulic actuator 6. The motion speed of the piston of the aerospace damper 8 in unit time is obtained by monitoring the stroke of the displacement sensor 7. And the damping force corresponding to the running speeds of the different space dampers 8 is obtained through the feedback of the force sensor 4. And then carrying out quadratic curve fitting on each group of data to obtain a damping characteristic curve of the damping force of the aerospace damper 8 and the movement speed of the damper piston.
E. The servo hydraulic actuator 6 is controlled to pull the piston rod of the aerospace damper 8 to uniformly and slowly extend out by giving an instruction through the measurement and control system until the aerospace damper 8 is locked mechanically after being stretched to the maximum extent, and meanwhile, the axial force fed back by the force sensor 4 is collected in real time, so that a force and time curve is obtained. When the lock is unlocked, the waveform of a force and time curve is relatively gentle and basically kept horizontal, the force and time curve has a large upward slope sudden change at the time point of locking, a peak appears, the damper is locked after the sudden change, and the peak keeps a certain slope rising after the first wave trough in the follow-up process. And reading the maximum value of the peak of the curve, namely the locking force on the aerospace damper 8.
F. After the space damper 8 is locked, the servo hydraulic actuator 6 is controlled to apply rated axial pressure, and whether the space damper 8 is locked or not is verified to be safe and reliable.
The aerospace damper has an automatic locking function when being stretched to the maximum length, and after being locked, the piston rod can be locked to move and can not be retracted. The piston rod can recover the motion capability only after being unlocked by a special unlocking device. The rated axial pressure value is given by the design specification of the aerospace damper product, and the limit load value which can be borne by the aerospace damper product is not allowed to be exceeded.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111297342.0A CN114088368A (en) | 2021-11-03 | 2021-11-03 | Performance test device and method for aerospace damper |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111297342.0A CN114088368A (en) | 2021-11-03 | 2021-11-03 | Performance test device and method for aerospace damper |
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| CN114088368A true CN114088368A (en) | 2022-02-25 |
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| CN202111297342.0A Pending CN114088368A (en) | 2021-11-03 | 2021-11-03 | Performance test device and method for aerospace damper |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118329429A (en) * | 2024-06-13 | 2024-07-12 | 烟台航空液压控制有限责任公司 | Dynamic test device for hydraulic damper |
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| CN202661255U (en) * | 2012-05-29 | 2013-01-09 | 常州格林电力机械制造有限公司 | Dynamic test device of hydraulic damper |
| CN203385548U (en) * | 2013-08-14 | 2014-01-08 | 北京市佛力系统公司 | Damping device performance testing system |
| CN207610564U (en) * | 2017-11-06 | 2018-07-13 | 江苏核电有限公司 | A kind of double back pressure double-flow condensers bottom supporting rod |
| CN108645606A (en) * | 2018-05-11 | 2018-10-12 | 常州格林电力机械制造有限公司 | A kind of test method and equipment of large hydraulic damper |
| CN108692956A (en) * | 2018-04-09 | 2018-10-23 | 杭州亿恒科技有限公司 | Double crossbeam Vehicle Suspension Vibration experimental rigs and method |
| CN109269792A (en) * | 2018-11-08 | 2019-01-25 | 航天科工哈尔滨风华有限公司电站设备分公司 | A kind of safety equipment hydraulic damper measure and control device and its application method |
| CN209432394U (en) * | 2019-03-07 | 2019-09-24 | 绵阳睿控电子有限公司 | A kind of vibration test equipment |
| CN111929082A (en) * | 2020-08-11 | 2020-11-13 | 一汽解放青岛汽车有限公司 | Method for testing damping force of shock absorber |
| CN112268690A (en) * | 2020-09-30 | 2021-01-26 | 武汉海润工程设备有限公司 | High-speed large-displacement damper testing machine |
-
2021
- 2021-11-03 CN CN202111297342.0A patent/CN114088368A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202661279U (en) * | 2012-05-29 | 2013-01-09 | 常州格林电力机械制造有限公司 | Static test device of hydraulic damper |
| CN202661255U (en) * | 2012-05-29 | 2013-01-09 | 常州格林电力机械制造有限公司 | Dynamic test device of hydraulic damper |
| CN203385548U (en) * | 2013-08-14 | 2014-01-08 | 北京市佛力系统公司 | Damping device performance testing system |
| CN207610564U (en) * | 2017-11-06 | 2018-07-13 | 江苏核电有限公司 | A kind of double back pressure double-flow condensers bottom supporting rod |
| CN108692956A (en) * | 2018-04-09 | 2018-10-23 | 杭州亿恒科技有限公司 | Double crossbeam Vehicle Suspension Vibration experimental rigs and method |
| CN108645606A (en) * | 2018-05-11 | 2018-10-12 | 常州格林电力机械制造有限公司 | A kind of test method and equipment of large hydraulic damper |
| CN109269792A (en) * | 2018-11-08 | 2019-01-25 | 航天科工哈尔滨风华有限公司电站设备分公司 | A kind of safety equipment hydraulic damper measure and control device and its application method |
| CN209432394U (en) * | 2019-03-07 | 2019-09-24 | 绵阳睿控电子有限公司 | A kind of vibration test equipment |
| CN111929082A (en) * | 2020-08-11 | 2020-11-13 | 一汽解放青岛汽车有限公司 | Method for testing damping force of shock absorber |
| CN112268690A (en) * | 2020-09-30 | 2021-01-26 | 武汉海润工程设备有限公司 | High-speed large-displacement damper testing machine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118329429A (en) * | 2024-06-13 | 2024-07-12 | 烟台航空液压控制有限责任公司 | Dynamic test device for hydraulic damper |
| CN118329429B (en) * | 2024-06-13 | 2024-08-16 | 烟台航空液压控制有限责任公司 | Dynamic test device for hydraulic damper |
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Application publication date: 20220225 |