CN114508558B - Wire sealing structure for aircraft landing gear damper - Google Patents
Wire sealing structure for aircraft landing gear damper Download PDFInfo
- Publication number
- CN114508558B CN114508558B CN202210064179.1A CN202210064179A CN114508558B CN 114508558 B CN114508558 B CN 114508558B CN 202210064179 A CN202210064179 A CN 202210064179A CN 114508558 B CN114508558 B CN 114508558B
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- sealing
- sealing ring
- damper
- damper shell
- block
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- 238000007789 sealing Methods 0.000 title claims abstract description 163
- 238000013016 damping Methods 0.000 claims abstract description 34
- 230000007246 mechanism Effects 0.000 claims abstract description 23
- 239000000758 substrate Substances 0.000 claims abstract description 11
- 230000001681 protective effect Effects 0.000 claims abstract description 10
- 210000001503 joint Anatomy 0.000 claims description 28
- 238000009434 installation Methods 0.000 claims description 9
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 239000007788 liquid Substances 0.000 claims description 4
- 238000003032 molecular docking Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 12
- 239000012530 fluid Substances 0.000 abstract description 2
- 238000001125 extrusion Methods 0.000 description 2
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000001603 reducing effect Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002940 repellent Effects 0.000 description 1
- 239000005871 repellent Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/3207—Constructional features
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/36—Special sealings, including sealings or guides for piston-rods
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Fluid-Damping Devices (AREA)
- Gasket Seals (AREA)
Abstract
The invention discloses a wire sealing structure for an aircraft landing gear damper, which comprises a damper shell, wherein a piston block moving along the inner cavity of the damper shell is arranged in the damper shell, a permanent magnet is arranged at the bottom of the piston block, a protective substrate is arranged at the bottom of the permanent magnet, an electromagnet which is magnetically repelled with the permanent magnet is arranged at the bottom of the inner cavity of the damper shell, a protective plate is arranged on the surface of the electromagnet, a sealing strip is arranged between the protective plate and the inner wall of the permanent magnet, a lead hole for a wire on a power supply magnet to penetrate is formed in the damper shell, and a positive pressure sealing mechanism is arranged at the lead hole of the damper shell. According to the invention, the hydraulic damping structure, the spring damping and the electromagnetic damping are combined together in the damper shell, so that the damping effect is effectively improved, and the positive pressure sealing mechanism for sealing the lead on the electromagnet is arranged in the damper shell, so that damping fluid of the damper shell cannot overflow.
Description
Technical Field
The invention relates to the technical field of dampers, in particular to a wire sealing structure for an aircraft landing gear damper.
Background
The low-frequency brake induced vibration of the main landing gear of the aircraft is also called buffeting phenomenon, and the buffeting vibration frequency is generally below 30 Hz. In the whole running braking process of an airplane main landing gear after the grounding of the airplane wheel, under the action of a braking system, due to factors such as ground binding force change caused by braking force excitation, flexibility of a main landing gear strut, non-rigid connection of a main landing gear and a machine body connection part, elasticity of a tire and the like, the landing gear can generate buffeting phenomenon when subjected to the changed ground tire force, so that a damper is required to absorb vibration and absorb shock, and the existing damper also has the phenomenon that electromagnetic damping and hydraulic damping are combined together, but the sealing performance of a lead-out end of a wire is poor, and damping liquid is leaked. We have therefore improved on this by proposing a wire seal for an aircraft landing gear damper.
Disclosure of Invention
In order to solve the technical problems, the invention provides the following technical scheme:
the invention discloses a wire sealing structure for an aircraft landing gear damper, which comprises a damper shell, wherein a piston block moving along the inner cavity of the damper shell is arranged in the damper shell, a permanent magnet is arranged at the bottom of the piston block, a protective substrate is arranged at the bottom of the permanent magnet, damping holes are formed in the piston block, the permanent magnet and the protective substrate, damping liquid is filled in the inner cavity of the damper shell, an electromagnet which is magnetically repulsed with the permanent magnet is arranged at the bottom of the inner cavity of the damper shell, a protection plate is arranged on the surface of the electromagnet, a sealing strip is arranged between the protection plate and the inner wall of the permanent magnet, a lead hole through which a wire on a power supply magnet passes is formed in the damper shell, a positive pressure sealing mechanism is arranged at the lead hole of the damper shell, a damping spring is arranged between the protection plate and the protective substrate, and a piston rod penetrating out of the damper shell is arranged on the piston block.
As a preferable technical scheme of the invention, the positive pressure sealing mechanism comprises a butt joint pipe which is arranged on the damper shell and positioned at the periphery of the lead hole, an installation cavity is formed between the butt joint pipe and the outer wall of the damper shell, a first sealing ring block positioned at the periphery of the lead hole is arranged on the outer wall of the damper shell, a sealing block embedded into the installation cavity is arranged on a lead wire, a first sealing ring groove for embedding the first sealing ring block is arranged on the sealing block, a sealing cover is arranged on the butt joint pipe, and a positive pressure sealing ring which is in extrusion contact with the first sealing ring block is arranged in the sealing cover.
As a preferable technical scheme of the invention, the first sealing ring block and the lead are integrally formed.
As an optimized technical scheme of the invention, the positive pressure sealing ring comprises a sealing ring main body, a through hole for a lead to pass through is formed in the sealing ring main body, an annular air cavity arranged around the through hole is formed in the sealing ring main body, an air inlet pipe communicated with the annular air cavity is arranged on the sealing ring main body, a one-way valve is arranged on the air inlet pipe, and a through hole for the air inlet pipe to pass through is formed in the sealing cover.
As a preferable technical scheme of the invention, a second sealing ring groove is arranged on one side of the sealing block, which is contacted with the positive pressure sealing ring, and a second sealing ring block embedded into the second sealing ring groove is arranged on the sealing ring main body.
As a preferable technical scheme of the invention, a locking mechanism is arranged between the sealing cover and the butt joint pipe.
As a preferable technical scheme of the invention, the anti-loosening mechanism comprises a first positioning flange arranged at a port of the sealing cover, a second positioning flange matched with the first positioning flange is arranged on the butt joint pipe, a first arc-shaped through hole is arranged on the first positioning flange, a second arc-shaped through hole matched with the first arc-shaped through hole is arranged on the second positioning flange, a positioning bolt is arranged between the first arc-shaped through hole and the second arc-shaped through hole in a penetrating way, a locking nut group is arranged at the end part of the positioning bolt, and a locking nut at the outermost end in the locking nut group is welded with the positioning bolt.
As a preferable technical scheme of the invention, the first positioning flange and the sealing cover are integrally formed, and the butt joint pipe and the second positioning flange are integrally formed.
1. This kind of be arranged in aircraft landing gear attenuator wire seal structure is in the same place through combining hydraulic damping structure, spring damping and electromagnetic damping three in the attenuator casing to thereby effectively improved damping shock attenuation's effect, and be equipped with the positive pressure seal mechanism that seals the wire on the electro-magnet at the attenuator casing, mainly be equipped with the sealing block of embedding to the installation intracavity through the line, be equipped with the first sealing ring groove that supplies first sealing ring piece embedding on the sealing block, be equipped with sealed lid on the butt joint pipe, the internally mounted of sealed lid has the positive pressure seal circle that first sealing ring piece crowded touched mutually, after installing the positive pressure seal circle, injects air in to the annular air cavity through the intake pipe, thereby makes the positive pressure seal expand and makes positive pressure seal circle and sealing block inseparable laminating, thereby played fine sealing effect, and be equipped with the second sealing ring groove in the side that sealing block contacted with the positive pressure seal circle, be equipped with the second sealing ring piece that imbeds in the second sealing ring groove on the sealing ring body, make sealing block and positive pressure seal circle have better sealing effect, thereby make the damping fluid of attenuator casing can not overflow.
2. This kind of be equipped with locking mechanism between sealed lid and the butt joint pipe for among aircraft undercarriage attenuator wire seal structure has played the effect of location, avoids taking place to loosen between sealed lid and the butt joint pipe and drops, mainly through wear to be equipped with positioning bolt between first arc through-hole and the second arc through-hole, positioning bolt's tip is equipped with lock nut group, lock nut and positioning bolt welding of the outer end in the lock nut group to play the effect of location to sealed lid and butt joint pipe, and then guarantee to have better sealed effect to the wire.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate the invention and together with the embodiments of the invention, serve to explain the invention. In the drawings:
FIG. 1 is a schematic illustration of a wire seal configuration for an aircraft landing gear damper according to the present invention;
FIG. 2 is a schematic illustration of a positive pressure seal mechanism for an aircraft landing gear damper wire seal structure of the present invention;
FIG. 3 is a schematic view of a first seal ring block for an aircraft landing gear damper wire seal configuration of the present invention;
FIG. 4 is a schematic illustration of a positive pressure seal for an aircraft landing gear damper wire seal in accordance with the present invention;
fig. 5 is a schematic structural view of a locking mechanism for an aircraft landing gear damper wire seal structure according to the present invention.
In the figure: 1. a damper housing; 2. a piston block; 3. a permanent magnet; 4. a protective substrate; 5. a damping hole; 6. an electromagnet; 7. a protection plate; 8. a sealing strip; 9. a lead hole; 10. a positive pressure sealing mechanism; 11. a butt joint pipe; 12. a mounting cavity; 13. a first sealing ring block; 14. a sealing block; 15. a first seal ring groove; 16. sealing cover; 17. a positive pressure seal ring; 18. a seal ring main body; 19. a through hole; 20. an annular air cavity; 21. an air inlet pipe; 22. a one-way valve; 23. perforating; 24. a second seal ring groove; 25. a second sealing ring block; 26. a locking mechanism; 27. a first positioning flange; 28. a second positioning flange; 29. a first arc-shaped through hole; 30. a second arcuate through hole; 31. positioning bolts; 32. a lock nut group; 33. a piston rod; 34. damping spring.
Detailed Description
The preferred embodiments of the present invention will be described below with reference to the accompanying drawings, it being understood that the preferred embodiments described herein are for illustration and explanation of the present invention only, and are not intended to limit the present invention.
Examples: as shown in fig. 1-5, the wire sealing structure for the aircraft landing gear damper comprises a damper shell 1, wherein a piston block 2 moving along the inner cavity of the damper shell 1 is arranged in the damper shell 1, a permanent magnet 3 is arranged at the bottom of the piston block 2, a protection substrate 4 is arranged at the bottom of the permanent magnet 3, damping holes 5 are formed in the piston block 2, the permanent magnet 3 and the protection substrate 4, damping liquid is filled in the inner cavity of the damper shell 1, an electromagnet 6 magnetically repellent to the permanent magnet 3 is arranged at the bottom of the inner cavity of the damper shell 1, a protection plate 7 is arranged on the surface of the electromagnet 6, a sealing strip 8 is arranged between the protection plate 7 and the inner wall of the permanent magnet 3, a lead hole 9 through which a wire on the power supply magnet 6 passes is formed in the damper shell 1, a positive pressure sealing mechanism 10 is arranged at the lead hole, a damping spring 34 is arranged between the protection plate and the protection substrate 4, and a piston rod 33 penetrating out of the damper shell 1 is arranged on the piston block 2.
The positive pressure sealing mechanism 10 comprises a butt joint pipe 11 which is arranged on the damper shell 1 and positioned at the periphery of the lead hole 9, an installation cavity 12 is formed between the butt joint pipe 11 and the outer wall of the damper shell 1, a first sealing ring block 13 positioned at the periphery of the lead hole 9 is arranged on the outer wall of the damper shell 1, a sealing block 14 embedded into the installation cavity 12 is arranged on a lead wire, a first sealing ring groove 15 for embedding the first sealing ring block 13 is arranged on the sealing block 14, a sealing cover 16 is arranged on the butt joint pipe 11, and a positive pressure sealing ring 17 which is in extrusion contact with the first sealing ring block 13 is arranged in the sealing cover 16. The first sealing ring block 13 and the lead are integrally formed.
The positive pressure sealing ring 17 comprises a sealing ring main body 18, a through hole 19 for a lead to pass through is formed in the sealing ring main body 18, an annular air cavity 20 arranged around the through hole 19 is formed in the sealing ring main body 18, an air inlet pipe 21 communicated with the annular air cavity 20 is formed in the sealing ring main body 18, a one-way valve 22 is arranged on the air inlet pipe 21, and a through hole 23 for the air inlet pipe 21 to pass through is formed in the sealing cover 16.
The hydraulic damping structure, the spring damping and the electromagnetic damping are combined together in the damper shell 1, so that the damping and vibration reducing effects are effectively improved, the positive pressure sealing mechanism 10 for sealing the lead on the electromagnet is arranged in the damper shell 1, the sealing block 14 embedded in the installation cavity 12 is mainly arranged on the lead, the first sealing ring groove 15 for embedding the first sealing ring block 13 is arranged on the sealing block 14, the sealing cover 16 is arranged on the butt joint pipe 11, the positive pressure sealing ring 17 pressed by the first sealing ring block 13 is arranged in the butt joint pipe 11, after the positive pressure sealing ring 17 is installed, air is injected into the annular air cavity 20 through the air inlet pipe 21, so that the positive pressure sealing ring 17 is expanded, the positive pressure sealing ring 17 is tightly attached to the sealing block 14, a good sealing effect is achieved, the second sealing ring groove 24 is arranged on one side, contacted with the positive pressure sealing ring 17, of the sealing block 14 is provided with the second sealing ring groove 25 embedded in the second sealing ring groove 24, and the positive pressure sealing ring 14 and the positive pressure sealing ring 17 are provided with good damping overflow effects of the damper shell 1.
A second sealing ring groove 24 is arranged on the side, which is contacted with the positive pressure sealing ring 17, of the sealing block 14, and a second sealing ring block 25 embedded into the second sealing ring groove 24 is arranged on the sealing ring main body 18.
The sealing cover 16 is in threaded connection with the docking tube 11.
An anti-loosening mechanism 26 is arranged between the sealing cover 16 and the butt joint pipe 11, and an anti-loosening mechanism 26 is arranged between the sealing cover 16 and the butt joint pipe 11, so that the positioning function is achieved, and the loosening and falling-off of the sealing cover and the butt joint pipe are avoided. The locking mechanism 26 comprises a first positioning flange 27 arranged at the port of the sealing cover 16, a second positioning flange 28 matched with the first positioning flange 27 is arranged on the butt joint pipe 11, a first arc-shaped through hole 29 is arranged on the first positioning flange 27, a second arc-shaped through hole 30 matched with the first arc-shaped through hole 29 is arranged on the second positioning flange 28, a positioning bolt 31 is arranged between the first arc-shaped through hole 29 and the second arc-shaped through hole 30 in a penetrating mode, a locking nut group 32 is arranged at the end portion of the positioning bolt 31, and a locking nut at the outermost end in the locking nut group 32 is welded with the positioning bolt 31. The first positioning flange 27 and the sealing cover 16 are integrally formed, and the butt joint pipe 11 and the second positioning flange 28 are integrally formed, so that the sealing cover and the butt joint pipe are positioned, and a good sealing effect on the lead is ensured.
Working principle: the hydraulic damping structure, the spring damping and the electromagnetic damping are combined together in the damper shell 1, so that the damping and vibration reducing effects are effectively improved, the positive pressure sealing mechanism 10 for sealing the lead on the electromagnet is arranged in the damper shell 1, the sealing block 14 embedded in the installation cavity 12 is mainly arranged on the lead, the first sealing ring groove 15 for embedding the first sealing ring block 13 is arranged on the sealing block 14, the sealing cover 16 is arranged on the butt joint pipe 11, the positive pressure sealing ring 17 pressed by the first sealing ring block 13 is arranged in the butt joint pipe 11, after the positive pressure sealing ring 17 is installed, air is injected into the annular air cavity 20 through the air inlet pipe 21, so that the positive pressure sealing ring 17 is expanded, the positive pressure sealing ring 17 is tightly attached to the sealing block 14, a good sealing effect is achieved, the second sealing ring groove 24 is arranged on one side, contacted with the positive pressure sealing ring 17, of the sealing block 14 is provided with the second sealing ring groove 25 embedded in the second sealing ring groove 24, and the positive pressure sealing ring 14 and the positive pressure sealing ring 17 are provided with good damping overflow effects of the damper shell 1.
Finally, it should be noted that: the above is only a preferred embodiment of the present invention, and the present invention is not limited thereto, but it is to be understood that the present invention is described in detail with reference to the foregoing embodiments, and modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A wire seal structure for an aircraft landing gear damper, characterized by: the damper comprises a damper shell (1), a piston block (2) moving along an inner cavity of the damper shell (1) is arranged in the damper shell (1), a permanent magnet (3) is arranged at the bottom of the piston block (2), a protective substrate (4) is arranged at the bottom of the permanent magnet (3), damping holes (5) are formed in the piston block (2), the permanent magnet (3) and the protective substrate (4), damping liquid is filled in the inner cavity of the damper shell (1), an electromagnet (6) which is magnetically repulsed with the permanent magnet (3) is arranged at the bottom of the inner cavity of the damper shell (1), a protection plate (7) is arranged on the surface of the electromagnet (6), a sealing strip (8) is arranged between the protection plate (7) and the inner wall of the damper shell (1), a lead hole (9) through which a wire on the power supply magnet (6) penetrates out is formed in the damper shell (1), a positive pressure sealing mechanism (10) is arranged at the lead hole, and a damping spring (34) is arranged between the protection plate and the protective substrate (4); a piston rod (33) penetrating out of the damper shell (1) is arranged on the piston block (2);
the positive pressure sealing mechanism (10) comprises a butt joint pipe (11) which is arranged on the damper shell (1) and positioned at the periphery of the lead hole (9), an installation cavity (12) is formed between the butt joint pipe (11) and the outer wall of the damper shell (1), a first sealing ring block (13) positioned at the periphery of the lead hole (9) is arranged on the outer wall of the damper shell (1), a sealing block (14) embedded into the installation cavity (12) is arranged on a wire, a first sealing ring groove (15) for embedding the first sealing ring block (13) is arranged on the sealing block (14), a sealing cover (16) is arranged on the butt joint pipe (11), and a positive pressure sealing ring (17) extruded with the first sealing ring block (13) is arranged in the sealing cover (16);
the positive pressure sealing ring (17) comprises a sealing ring main body (18), a through hole (19) for a conducting wire to pass through is formed in the sealing ring main body (18), an annular air cavity (20) arranged around the through hole (19) is formed in the sealing ring main body (18), an air inlet pipe (21) communicated with the annular air cavity (20) is formed in the sealing ring main body (18), a one-way valve (22) is arranged on the air inlet pipe (21), and a through hole (23) for the air inlet pipe (21) to pass through is formed in the sealing cover (16);
a second sealing ring groove (24) is formed in one side, in contact with the positive pressure sealing ring (17), of the sealing block (14), and a second sealing ring block (25) embedded into the second sealing ring groove (24) is arranged on the sealing ring main body (18).
2. A wire seal for an aircraft landing gear damper according to claim 1, wherein the seal block (14) is integrally formed with the wire.
3. A wire seal for an aircraft landing gear damper according to claim 2, wherein the seal cap (16) is threadably connected to the docking tube (11).
4. A wire sealing structure for an aircraft landing gear damper according to claim 1, characterized in that a locking mechanism (26) is provided between the sealing cap (16) and the docking tube (11).
5. The wire sealing structure for the landing gear damper of the aircraft according to claim 4, wherein the anti-loosening mechanism (26) comprises a first positioning flange (27) arranged at a port of the sealing cover (16), a second positioning flange (28) matched with the first positioning flange (27) is arranged on the butt joint pipe (11), a first arc-shaped through hole (29) is formed in the first positioning flange (27), a second arc-shaped through hole (30) matched with the first arc-shaped through hole (29) is formed in the second positioning flange (28), a positioning bolt (31) is arranged between the first arc-shaped through hole (29) and the second arc-shaped through hole (30) in a penetrating mode, a locking nut group (32) is arranged at the end portion of the positioning bolt (31), and a locking nut at the outermost end of the locking nut group (32) is welded with the positioning bolt (31).
6. A wire seal for an aircraft landing gear damper according to claim 5, wherein the first locating flange (27) is integrally formed with the sealing cap (16) and the docking tube (11) is integrally formed with the second locating flange (28).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210064179.1A CN114508558B (en) | 2022-01-20 | 2022-01-20 | Wire sealing structure for aircraft landing gear damper |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210064179.1A CN114508558B (en) | 2022-01-20 | 2022-01-20 | Wire sealing structure for aircraft landing gear damper |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114508558A CN114508558A (en) | 2022-05-17 |
| CN114508558B true CN114508558B (en) | 2024-03-12 |
Family
ID=81550545
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210064179.1A Active CN114508558B (en) | 2022-01-20 | 2022-01-20 | Wire sealing structure for aircraft landing gear damper |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114508558B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4002188A1 (en) * | 1989-10-04 | 1991-04-11 | Sasse Eugen Gmbh Co Kg Dr | Screened cable entry into electrical or electronic equipment - passes cable core through two tapered inserts which grip braid and compress seal against outward traction |
| CN103016599A (en) * | 2012-12-13 | 2013-04-03 | 浙江师范大学 | Integrated type self-powered hydraulic damper |
| CN108167371A (en) * | 2018-02-02 | 2018-06-15 | 山东科技大学 | A kind of new permanent-magnet formula MR damper |
| KR101973696B1 (en) * | 2017-11-03 | 2019-04-30 | 인하대학교 산학협력단 | Mr fluid damper using permanent magnet |
| CN209213609U (en) * | 2018-12-27 | 2019-08-06 | 荣朗防爆科技有限公司 | A kind of explosion suppression type explosion-preventing lamp |
| CN110513431A (en) * | 2019-09-05 | 2019-11-29 | 安徽理工大学 | A kind of magnetoelectricity mix suspending formula hydraulic damper |
| CN211629101U (en) * | 2020-05-25 | 2020-10-02 | 上海润璋智能科技股份有限公司 | Power transistor with protective housing structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7900755B2 (en) * | 2007-09-28 | 2011-03-08 | GM Global Technology Operations LLC | Bi-fold valve-type magnetorheological fluid energy absorbing device |
-
2022
- 2022-01-20 CN CN202210064179.1A patent/CN114508558B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4002188A1 (en) * | 1989-10-04 | 1991-04-11 | Sasse Eugen Gmbh Co Kg Dr | Screened cable entry into electrical or electronic equipment - passes cable core through two tapered inserts which grip braid and compress seal against outward traction |
| CN103016599A (en) * | 2012-12-13 | 2013-04-03 | 浙江师范大学 | Integrated type self-powered hydraulic damper |
| KR101973696B1 (en) * | 2017-11-03 | 2019-04-30 | 인하대학교 산학협력단 | Mr fluid damper using permanent magnet |
| CN108167371A (en) * | 2018-02-02 | 2018-06-15 | 山东科技大学 | A kind of new permanent-magnet formula MR damper |
| CN209213609U (en) * | 2018-12-27 | 2019-08-06 | 荣朗防爆科技有限公司 | A kind of explosion suppression type explosion-preventing lamp |
| CN110513431A (en) * | 2019-09-05 | 2019-11-29 | 安徽理工大学 | A kind of magnetoelectricity mix suspending formula hydraulic damper |
| CN211629101U (en) * | 2020-05-25 | 2020-10-02 | 上海润璋智能科技股份有限公司 | Power transistor with protective housing structure |
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| CN114508558A (en) | 2022-05-17 |
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