CN113108004A - Bidirectional full-circle rotating airplane damper - Google Patents
Bidirectional full-circle rotating airplane damper Download PDFInfo
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- CN113108004A CN113108004A CN202110498720.5A CN202110498720A CN113108004A CN 113108004 A CN113108004 A CN 113108004A CN 202110498720 A CN202110498720 A CN 202110498720A CN 113108004 A CN113108004 A CN 113108004A
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- cavity
- shaft
- seat body
- shaft core
- sealing
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- 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
- F16F9/10—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using liquid only; using a fluid of which the nature is immaterial
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- 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
- F16F2232/00—Nature of movement
- F16F2232/02—Rotary
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
本发明公开一种双向全周旋转飞机阻尼器，其包括：座体，其设有内壁光滑的型腔，座体上端开设有贯通型腔的轴孔；轴芯，其开设有油腔，轴芯外侧设有若干贯通油腔的油孔，轴芯上端通过上轴承安装于座体上部，轴芯上端穿过轴孔伸出于该座体上端面外；封装盖，其固定于座体中型腔的下端，并密封接触；封装盖上部安装有下轴承，轴芯下端穿设固定于下轴承中；封装盖具有贯通上下端面并与轴芯中油腔的下端开口对应的螺孔；密封螺丝螺旋固定于螺孔中，并将螺孔封堵；座体中型腔的内壁与轴芯外壁及封装盖上端面之间形成的第一腔室及油腔均灌注有阻尼油。本发明可实现更小的扭矩，还能够双向全周旋转阻尼，可适用于飞机或者需要更小阻尼力的阻尼器。
The invention discloses a bidirectional full-circumferential rotating aircraft damper, which comprises: a seat body, which is provided with a cavity with a smooth inner wall, and a shaft hole penetrating the cavity is formed at the upper end of the seat body; a shaft core is provided with an oil cavity, and a shaft The outer side of the core is provided with a number of oil holes penetrating the oil cavity, the upper end of the shaft core is installed on the upper part of the seat body through the upper bearing, and the upper end of the shaft core protrudes out of the upper end face of the seat body through the shaft hole; the encapsulation cover is fixed on the middle type of the seat body The lower end of the cavity is in sealing contact; a lower bearing is installed on the upper part of the packaging cover, and the lower end of the shaft core is penetrated and fixed in the lower bearing; the packaging cover has a screw hole that penetrates the upper and lower end faces and corresponds to the lower end opening of the oil cavity in the shaft core; the sealing screw is screwed The first cavity and the oil cavity formed between the inner wall of the cavity in the seat body, the outer wall of the shaft core and the upper end face of the packaging cover are filled with damping oil. The present invention can realize smaller torque, and can also perform bidirectional full-circle rotational damping, and can be applied to aircraft or dampers that require smaller damping force.
Description
The technical field is as follows:
the invention relates to the technical field of damper products, in particular to a bidirectional full-circle rotating airplane damper.
Background art:
the damper is a device for providing resistance to movement and reducing movement energy. Wherein, rotary damper makes the product obtain gentle mechanical motion, promotes the quality and the life-span of product, and the wide application in each field, the noise that produces when it can effectively reduce the product use more can improve the life of product.
The rotary damper in the prior art can not rotate in a bidirectional and full circle mode generally, is assembled by adopting a single bearing, has large friction torque and unsatisfactory operation precision, and can not meet the use requirements of certain special fields, such as the damper used by an airplane.
In view of the above, the present inventors propose the following.
The invention content is as follows:
the invention aims to overcome the defects of the prior art and provides a bidirectional full-circle rotating airplane damper.
In order to solve the technical problems, the invention adopts the following technical scheme: the bi-directional full-circle rotary aircraft damper comprises: the lower end surface of the seat body is upwards provided with a cavity with a smooth inner wall, and the upper end of the seat body is provided with a shaft hole penetrating through the cavity; the upper end of the shaft core is arranged at the upper part of the seat body through an upper bearing, and the upper end of the shaft core penetrates through the shaft hole and extends out of the upper end surface of the seat body; the packaging cover is fixedly arranged at the lower end of the cavity in the seat body and is in sealing contact with the cavity; the upper part of the packaging cover is provided with a lower bearing, and the lower end of the shaft core is fixedly arranged in the lower bearing in a penetrating way; the packaging cover is provided with a screw hole which penetrates through the upper end surface and the lower end surface and corresponds to the lower end opening of the oil cavity in the shaft core; the sealing screw is fixed in the screw hole in a spiral way and seals the screw hole; damping oil is filled in a first cavity and an oil cavity formed between the inner wall of the cavity in the seat body, the outer wall of the shaft core and the upper end face of the packaging cover.
Furthermore, in the above technical solution, a step portion and an upper shaft body located at an upper end of the step portion are formed at an upper end of the shaft core, the upper bearing is fixedly sleeved on the step portion, and the upper shaft body passes through the shaft hole and extends out of an upper end surface of the seat body; the lower end of the shaft core is formed with a narrowed lower shaft body, and the lower shaft body is inserted and fixed in the lower bearing.
Further, in the above technical solution, the upper end surface of the upper bearing is provided with a first gasket, a first seal ring is further provided between the first gasket and the upper inner wall of the cavity, and the first gasket is further sleeved on the periphery of the upper shaft body; the first sealing ring is sleeved on the periphery of the upper shaft body and is in sealing contact with the upper shaft body.
Furthermore, in the above technical solution, the periphery of the upper end of the package cover is provided with a plurality of sealing grooves distributed in upper and lower layers, and second sealing rings are installed in the sealing grooves, and the second sealing rings contact with the inner wall of the cavity of the seat body, so that the package cover and the seat body form a sealed assembly.
Further, in the above technical solution, a clamp spring for limiting the package cover in the seat body is disposed on a lower inner wall of the cavity in the seat body, and a second gasket is disposed between an upper end surface of the clamp spring and a lower end surface of the package cover.
Furthermore, in the above technical scheme, a ring groove is formed in the lower inner wall of the cavity in the seat body, and the snap spring is embedded in the ring groove.
Further, in the above technical solution, the package cover is integrally accommodated in the cavity of the base, and the lower end of the base is provided with a plurality of notches for fixing the test torque.
Furthermore, in the above technical scheme, a positioning groove is formed in the upper end surface of the shaft core downward.
Further, in the above technical solution, a limit groove is provided at the periphery of the upper shaft body in the shaft core.
Furthermore, in the above technical solution, a third sealing ring is further sleeved on the periphery of the sealing screw, and the third sealing ring contacts with the lower end surface of the encapsulation cover to form a sealing structure.
After adopting the technical scheme, compared with the prior art, the invention has the following beneficial effects: the upper bearing and the lower bearing are adopted to respectively support the upper end and the lower end of the shaft core, so that the friction torque between the shaft core and the seat body is reduced, smaller torque is realized, the operation precision can be improved, and the damper is suitable for airplanes or dampers needing smaller damping force; the die cavity in the base body is communicated with the oil cavity in the shaft core through the oil hole, so that after the damping oil is filled, the shaft core can rotate clockwise or anticlockwise all around relative to the base body, and in the rotating process, the oil cavity of the shaft core and the damping oil in the smooth die cavity of the base body can be extruded to generate damping force, and the purpose of bidirectional all-around rotation damping is achieved.
Description of the drawings:
FIG. 1 is a perspective view of the present invention;
FIG. 2 is a perspective view of another aspect of the present invention;
FIG. 3 is an exploded perspective view of the present invention;
FIG. 4 is a cross-sectional view of the present invention;
FIG. 5 is a perspective view of the shaft core of the present invention;
fig. 6 is a perspective view of the present invention with the seat body removed.
The specific implementation mode is as follows:
the invention is further illustrated below with reference to specific embodiments and the accompanying drawings.
Referring to fig. 1-6, a bi-directional full-circle rotary aircraft damper is shown, comprising: the lower end surface of the seat body 1 is upwards provided with a cavity 11 with a smooth inner wall, and the upper end of the seat body 1 is provided with a shaft hole 12 penetrating through the cavity 11; the lower end surface of the shaft core 2 is upwards provided with an oil cavity 21, the outer side of the shaft core 2 is provided with a plurality of oil holes 22 penetrating through the oil cavity 21, the upper end of the shaft core 2 is arranged at the upper part of the seat body 1 through an upper bearing 3, and the upper end of the shaft core 2 passes through the shaft hole 12 and extends out of the upper end surface of the seat body 1; the packaging cover 4 is fixedly arranged at the lower end of the cavity 11 in the base body 1 and is in sealing contact with the cavity; the upper part of the packaging cover 4 is provided with a lower bearing 5, and the lower end of the shaft core 2 is fixedly arranged in the lower bearing 5 in a penetrating way; the packaging cover 4 is provided with a screw hole 41 which penetrates through the upper end surface and the lower end surface and corresponds to the lower end opening of the oil cavity 21 in the shaft core 2; the sealing screw 6 is screwed in the screw hole 41 and seals the screw hole 41; damping oil is filled in a first cavity and an oil cavity 21 formed between the inner wall of the cavity 11 in the seat body 1, the outer wall of the shaft core 2 and the upper end face of the packaging cover 4. The invention adopts the upper bearing 3 and the lower bearing 4 to respectively support the upper end and the lower end of the shaft core 2, so as to reduce the friction torque between the shaft core 2 and the seat body 1, thereby realizing smaller torque, improving the operation precision and being applicable to airplanes; the cavity 11 in the seat body 1 is communicated with the oil cavity 21 in the shaft core 2 through the oil hole 22, so that after the damping oil is filled, the shaft core 2 can rotate clockwise or anticlockwise all around relative to the seat body 1, and during rotation, the oil cavity 21 of the shaft core and the damping oil in the smooth cavity of the seat body 1 can be extruded to generate damping force, so that the purpose of bidirectional all-around rotation damping is achieved.
The inner wall of the oil chamber 21 is smooth, and the outer part of the shaft core 2 is also smooth.
A stepped portion 23 and an upper shaft body 24 located at the upper end of the stepped portion 23 are formed at the upper end of the shaft core 2, the upper bearing 3 is fixedly sleeved on the stepped portion 23, and the upper shaft body 24 passes through the shaft hole 12 and extends out of the upper end surface of the seat body 1, so that the stability of the assembling structure is ensured. A first gasket 31 is arranged on the upper end surface of the upper bearing 3, a first seal ring 32 is further arranged between the first gasket 31 and the upper inner wall of the cavity 11, and the first gasket 31 is further sleeved on the periphery of the upper shaft body 24; the first seal ring 32 is sleeved on the periphery of the upper shaft 24 and is in sealing contact with the upper shaft, so that the sealing performance of the assembly structure is ensured to be in a high state.
A narrowed lower shaft body 20 is formed at the lower end of the shaft core 2, and the lower shaft body 20 is inserted and fixed in the lower bearing 5.
The periphery of the upper end of the packaging cover 4 is provided with a plurality of sealing grooves 42 which are distributed in an upper layer and a lower layer, the sealing grooves 42 are internally provided with second sealing rings 43, and the second sealing rings 43 are contacted with the inner wall of the cavity 11 of the seat body 1, so that the packaging cover 4 and the seat body 1 form sealing assembly, and oil can not be exposed during assembly.
A clamp spring 13 for limiting the package cover 4 in the seat body 1 is arranged on the lower inner wall of the cavity 11 in the seat body 1, and a second gasket 14 is arranged between the upper end surface of the clamp spring 13 and the lower end surface of the package cover 4, that is, the clamp spring 13 cooperates with the second gasket 14 to stably limit the package cover 4 in the seat body 1. Wherein, the lower inner wall shaping of die cavity 11 has annular 15 in the pedestal 1, jump ring 13 inlay card is in this annular 15.
The whole packaging cover 4 is accommodated in the cavity 11 of the base body 1, and the lower end of the base body 1 is provided with a plurality of notches 16 for fixing the test torque, so that the mounting of the invention is facilitated, and the stability of the assembly structure can be improved.
The locating slot 25 has been seted up downwards to 2 upper end faces of axle core, the periphery of the upper shaft body 24 in the axle core 2 is provided with spacing groove 26, and this locating slot 25 and spacing groove 26 all are used for assembling with outside structure, can improve assembly structure's stability.
And a third sealing ring 61 is further sleeved on the periphery of the sealing screw 6, and the third sealing ring 61 is in contact with the lower end face of the packaging cover 4 to form a sealing structure. In addition, the volume of the oil chamber 21 of the shaft core 2 can be adjusted by screwing in or screwing out the sealing screw 6, so that the magnitude of the damping force can be adjusted.
The precision of the product of the invention can reach-0.002 to-0.006 mm.
All the sealing rings can be replaced, and the sealing screw 6 can be screwed out to discharge damping oil and replace new damping oil, so that the aim of repeated use is fulfilled, namely, when the sealing rings and the damping oil are damaged due to long-time use, the sealing rings and the damping oil are replaced, so that the purposes of repairing and repeated use are fulfilled.
In conclusion, the upper bearing 3 and the lower bearing 4 are adopted to respectively support the upper end and the lower end of the shaft core 2, so that the friction torque between the shaft core 2 and the seat body 1 is reduced, smaller torque is realized, the operation precision can be improved, and the damper is suitable for airplanes or dampers needing smaller damping force; the cavity 11 in the seat body 1 is communicated with the oil cavity 21 in the shaft core 2 through the oil hole 22, so that after the damping oil is filled, the shaft core 2 can rotate clockwise or anticlockwise all around relative to the seat body 1, and during rotation, the oil cavity 21 of the shaft core and the damping oil in the smooth cavity of the seat body 1 can be extruded to generate damping force, so that the purpose of bidirectional all-around rotation damping is achieved.
It should be understood that the above description is only exemplary of the present invention, and is not intended to limit the scope of the present invention, which is defined by the appended claims.
Claims (10)
1. A two-way full-circle rotary aircraft damper is characterized in that: it includes:
the lower end face of the seat body (1) is upwards provided with a cavity (11) with a smooth inner wall, and the upper end of the seat body (1) is provided with a shaft hole (12) penetrating through the cavity (11);
the lower end face of the shaft core (2) is upwards provided with an oil cavity (21), a plurality of oil holes (22) penetrating through the oil cavity (21) are formed in the outer side of the shaft core (2), the upper end of the shaft core (2) is installed on the upper portion of the seat body (1) through an upper bearing (3), and the upper end of the shaft core (2) penetrates through the shaft hole (12) and extends out of the upper end face of the seat body (1);
the packaging cover (4) is fixedly arranged at the lower end of the cavity (11) in the base body (1) and is in sealing contact with the cavity; the upper part of the packaging cover (4) is provided with a lower bearing (5), and the lower end of the shaft core (2) is fixedly arranged in the lower bearing (5) in a penetrating way; the packaging cover (4) is provided with a screw hole (41) which penetrates through the upper end surface and the lower end surface and corresponds to the lower end opening of the oil cavity (21) in the shaft core (2); the sealing screw (6) is fixed in the screw hole (41) in a spiral way and seals the screw hole (41);
damping oil is filled in a first cavity and an oil cavity (21) formed among the inner wall of a cavity (11) in the seat body (1), the outer wall of the shaft core (2) and the upper end face of the packaging cover (4).
2. A bi-directional full-rotation aircraft damper as claimed in claim 1, wherein: a step part (23) and an upper shaft body (24) positioned at the upper end of the step part (23) are formed at the upper end of the shaft core (2), the upper bearing (3) is fixedly sleeved on the step part (23), and the upper shaft body (24) penetrates through the shaft hole (12) and extends out of the upper end surface of the seat body (1); a narrowed lower shaft body (20) is formed at the lower end of the shaft core (2), and the lower shaft body (20) is inserted and fixed in the lower bearing (5).
3. A bi-directional full-rotation aircraft damper as claimed in claim 2, wherein: a first gasket (31) is arranged on the upper end surface of the upper bearing (3), a first sealing ring (32) is further arranged between the first gasket (31) and the upper inner wall of the cavity (11), and the first gasket (31) is further sleeved on the periphery of the upper shaft body (24); the first sealing ring (32) is sleeved on the periphery of the upper shaft body (24) and is in sealing contact with the upper shaft body.
4. A bi-directional full-rotation aircraft damper as claimed in any one of claims 1 to 3, wherein: the periphery of the upper end of the packaging cover (4) is provided with a plurality of sealing grooves (42) which are distributed in an upper layer and a lower layer, second sealing rings (43) are installed in the sealing grooves (42), and the second sealing rings (43) are in contact with the inner wall of a cavity (11) of the seat body (1), so that the packaging cover (4) and the seat body (1) form sealing assembly.
5. A bi-directional full-rotation aircraft damper as claimed in claim 4, wherein: the lower inner wall of the cavity (11) in the seat body (1) is provided with a clamp spring (13) used for limiting the packaging cover (4) in the seat body (1), and a second gasket (14) is arranged between the upper end face of the clamp spring (13) and the lower end face of the packaging cover (4).
6. A bi-directional full-rotation aircraft damper as claimed in claim 5, wherein: the lower inner wall shaping of die cavity (11) has annular (15) in pedestal (1), jump ring (13) inlay card is in this annular (15).
7. A bi-directional full-rotation aircraft damper as claimed in claim 4, wherein: the packaging cover (4) is integrally accommodated in a cavity (11) of the base body (1), and a plurality of notches (16) for fixing the test torque are formed in the lower end of the base body (1).
8. A bi-directional full-rotation aircraft damper as claimed in claim 4, wherein: the upper end surface of the shaft core (2) is downwards provided with a positioning groove (25).
9. A bi-directional full-rotation aircraft damper as claimed in claim 4, wherein: the periphery of the upper shaft body (24) in the shaft core (2) is provided with a limit groove (26).
10. A bi-directional full-rotation aircraft damper as claimed in any one of claims 1 to 3, wherein: and a third sealing ring (61) is further sleeved on the periphery of the sealing screw (6), and the third sealing ring (61) is in contact with the lower end face of the packaging cover (4) to form a sealing structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110498720.5A CN113108004B (en) | 2021-05-08 | 2021-05-08 | A bidirectional full-circle rotating aircraft damper |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110498720.5A CN113108004B (en) | 2021-05-08 | 2021-05-08 | A bidirectional full-circle rotating aircraft damper |
Publications (2)
| Publication Number | Publication Date |
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| CN113108004A true CN113108004A (en) | 2021-07-13 |
| CN113108004B CN113108004B (en) | 2025-06-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110498720.5A Active CN113108004B (en) | 2021-05-08 | 2021-05-08 | A bidirectional full-circle rotating aircraft damper |
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| Country | Link |
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| CN (1) | CN113108004B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9492041B1 (en) * | 2015-08-04 | 2016-11-15 | Regent (Hong-Kong) Limited Speedy | Adjustable rotary damper for toilet seats |
| DE202017106210U1 (en) * | 2017-10-12 | 2017-10-19 | Hoti (Xiamen) Plumbing Inc. | Rotating buffer for adjusting the damping |
| CN108869609A (en) * | 2018-08-25 | 2018-11-23 | 河南天减振器科技有限公司 | The vibration-damper valve system of its damping force is still adjustable after a kind of sealing of damper |
| WO2019134626A1 (en) * | 2018-01-03 | 2019-07-11 | 厦门倍杰特科技股份公司 | Damper having adjustable damping |
| CN110141149A (en) * | 2019-06-27 | 2019-08-20 | 泉州科发卫浴有限公司 | An adjustable damper with overload protection function |
| CN110822001A (en) * | 2019-11-25 | 2020-02-21 | 宁波市正一砼泵配件有限公司 | Spiral damper applied to low-speed rotating device |
| CN112945278A (en) * | 2021-02-03 | 2021-06-11 | 四川凌峰航空液压机械有限公司 | Newton's law of internal friction rotary damper |
| CN214661685U (en) * | 2021-05-08 | 2021-11-09 | 东莞市培尔电子有限公司 | Bidirectional full-circle rotating airplane damper |
-
2021
- 2021-05-08 CN CN202110498720.5A patent/CN113108004B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9492041B1 (en) * | 2015-08-04 | 2016-11-15 | Regent (Hong-Kong) Limited Speedy | Adjustable rotary damper for toilet seats |
| DE202017106210U1 (en) * | 2017-10-12 | 2017-10-19 | Hoti (Xiamen) Plumbing Inc. | Rotating buffer for adjusting the damping |
| WO2019134626A1 (en) * | 2018-01-03 | 2019-07-11 | 厦门倍杰特科技股份公司 | Damper having adjustable damping |
| CN108869609A (en) * | 2018-08-25 | 2018-11-23 | 河南天减振器科技有限公司 | The vibration-damper valve system of its damping force is still adjustable after a kind of sealing of damper |
| CN110141149A (en) * | 2019-06-27 | 2019-08-20 | 泉州科发卫浴有限公司 | An adjustable damper with overload protection function |
| CN110822001A (en) * | 2019-11-25 | 2020-02-21 | 宁波市正一砼泵配件有限公司 | Spiral damper applied to low-speed rotating device |
| CN112945278A (en) * | 2021-02-03 | 2021-06-11 | 四川凌峰航空液压机械有限公司 | Newton's law of internal friction rotary damper |
| CN214661685U (en) * | 2021-05-08 | 2021-11-09 | 东莞市培尔电子有限公司 | Bidirectional full-circle rotating airplane damper |
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| CN113108004B (en) | 2025-06-13 |
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