CN105015766A - Vibration reduction device for skid landing gear - Google Patents
Vibration reduction device for skid landing gear Download PDFInfo
- Publication number
- CN105015766A CN105015766A CN201410177478.1A CN201410177478A CN105015766A CN 105015766 A CN105015766 A CN 105015766A CN 201410177478 A CN201410177478 A CN 201410177478A CN 105015766 A CN105015766 A CN 105015766A
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- vibration reduction
- damping block
- blocks
- vibration
- damping
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Abstract
The invention relates to a vibration reduction device for a skid landing gear. The vibration reduction device comprises two vibration reduction blocks (1), a vibration reduction plate (2), connecting bolts (3), gaskets (4), nuts (5) and four connecting rods (6), wherein the vibration reduction plate (2) is connected to a front beam (9) of a skid (7) through the four connecting rods (6), the gasket (4), the nut (5) and a machine body connecting half clamping ring (8). The vibration reduction blocks (1) are made of steel material, and the two vibration reduction blocks (1) are installed on the vibration reduction plate (2) through the two connecting bolts (3), the gaskets (4) and the nuts (5). The vibration reduction blocks (1) can swing at the end of the vibration reduction plate (2) in the vertical direction and absorb vibration energy of a helicopter in the vertical direction, the vibration reduction plate (2) is provided with multiple holes, so as to guarantee that the vibration reduction blocks (1) can undergo position adjustment on the vibration reduction plate (2), the distance between the vibration reduction blocks (1) and the front beam (9) is adjusted, and different vibration reduction effects are achieved.
Description
Technical field
The invention belongs to aeronautical engineering field, relate to a kind of shock attenuation unit of skid landing gear.
Background technology
At present, especially easily there is ground resonance in the helicopter installing skid landing gear, the method of vibration damping strengthens airframe structure rigidity, Anti-vibration Design is carried out to the propeller hub position of helicopter, or prevent resonance from occurring by using other device, not only version is complicated, and anti-resonance limited efficiency.
Summary of the invention
The technical problem to be solved in the present invention: for the ground resonance problem of helicopter.
Technical scheme of the present invention: a kind of shock attenuation unit of skid landing gear, comprise 2 damping blocks (1), damping block (2), tie bolt (3), packing ring (4), nut (5) and 4 pipe links (6), wherein, damping block (2) is by 4 pipe links (6), packing ring (4), nut (5) connects half snap ring (8) by fuselage and is connected on the front cross rail (9) of sled (7), damping block (1) is made up of Steel material, 2 damping blocks (1) are by 2 tie bolts (3), packing ring (4), nut (5) is installed on damping block (2), damping block (1) can swing in vertical direction in damping block (2) end, absorb helicopter vibrational energy in vertical direction, (2) offer multiple hole to damping block, ensure that damping block (1) can regulate at the enterprising line position of damping block (2), thus the distance between adjustment damping block (1) and front cross rail (9), reach different effectiveness in vibration suppression.
Beneficial effect of the present invention: version is simple, the level of vibration of any direction can be provided to control, can provide the vibrational energy of certain limit, assembling mode is simple, and cost is low, be easy to realization.
Accompanying drawing explanation
Fig. 1 is constructional drawing of the present invention, and wherein, 7 is sled, and 8 connect half snap ring for fuselage, and 9 is front cross rail, 10 shock attenuation units for installing.
Fig. 2 is assembling schematic diagram of the present invention, and wherein, 1 is damping block, and 2 is damping block, and 3 is tie bolt, and 4 is packing ring, and 5 is nut, and 6 is 4 pipe links, and 8 connect half snap ring for fuselage, and 9 is front cross rail.
Detailed description of the invention
Below in conjunction with Figure of description, installation of the present invention and mode of operation are described.
The technical conceive of shock attenuation unit of the present invention is: on skid landing gear or fuselage, install a kind of damping block that can produce certain oscillation frequency and amplitude, on damping block, configure the damping block of respective quality simultaneously, damping block by the vibrational energy of vibration cancellation rotor on damping block and fuselage, thus makes helicopter be in suitable level of vibration.The feature of this structure is, version is simple, is easy to realize, and without the restriction of strict installation site, can reduce the level of vibration in helicopter X, Y, Z-direction, can mate corresponding vibrational energy simultaneously according to helicopter actual vibration level.
First, the first step carries out damping block assembling: damping block 2 is connected to fuselage is connected on half snap ring 8 by pipe link 6, packing ring 4, nut 5.Damping block assembles by second step: damping block 1 is connected on damping block 2 by bolt 3, packing ring 4, nut 5.
After assembling, when driving in helicopter ground, the vibration that shock attenuation unit produces is contrary with the direction of vibration that rotor and fuselage produce, energy is close, make helicopter be on suitable level of vibration, improve the use safety of helicopter, improve the ride quality of helicopter.
Vibration attenuation mechanism of the present invention is: when lifting airscrew rotates, and fuselage can be made to produce the vibrational energy with certain frequency and amplitude; And shock attenuation unit is under the effect of rotor, damping block also can produce contrary with fuselage shaking direction, that energy is close vibration in the end of damping block, thus offsets the vibration of helicopter, and helicopter is on suitable level of vibration.When the vibrational energy that shock attenuation unit provides cannot offset the vibrational energy of fuselage, the installation site of adjustable damping block on damping block.
Claims (1)
1. the shock attenuation unit of a skid landing gear, comprise 2 damping blocks (1), damping block (2), tie bolt (3), packing ring (4), nut (5) and 4 pipe links (6), wherein, damping block (2) is by 4 pipe links (6), packing ring (4), nut (5) connects half snap ring (8) by fuselage and is connected on the front cross rail (9) of sled (7), damping block (1) is made up of Steel material, 2 damping blocks (1) are by 2 tie bolts (3), packing ring (4), nut (5) is installed on damping block (2), damping block (1) can swing in vertical direction in damping block (2) end, absorb helicopter vibrational energy in vertical direction, (2) offer multiple hole to damping block, ensure that damping block (1) can regulate at the enterprising line position of damping block (2), thus the distance between adjustment damping block (1) and front cross rail (9), reach different effectiveness in vibration suppression.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410177478.1A CN105015766A (en) | 2014-04-29 | 2014-04-29 | Vibration reduction device for skid landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410177478.1A CN105015766A (en) | 2014-04-29 | 2014-04-29 | Vibration reduction device for skid landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105015766A true CN105015766A (en) | 2015-11-04 |
Family
ID=54406162
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410177478.1A Pending CN105015766A (en) | 2014-04-29 | 2014-04-29 | Vibration reduction device for skid landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105015766A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106240805A (en) * | 2016-08-18 | 2016-12-21 | 李雪锋 | A kind of depopulated helicopter carbon fiber landing gear |
| CN106347638A (en) * | 2016-10-26 | 2017-01-25 | 山东鹰翼航空科技有限公司 | Unmanned helicopter landing gear |
| WO2018027685A1 (en) * | 2016-08-10 | 2018-02-15 | 张琬彬 | Cushioning leg support for small unmanned aerial vehicle |
| WO2023214943A1 (en) * | 2022-05-05 | 2023-11-09 | İstanbul Geli̇şi̇m Üni̇versi̇tesi̇ | Landing gear bracket |
-
2014
- 2014-04-29 CN CN201410177478.1A patent/CN105015766A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018027685A1 (en) * | 2016-08-10 | 2018-02-15 | 张琬彬 | Cushioning leg support for small unmanned aerial vehicle |
| CN106240805A (en) * | 2016-08-18 | 2016-12-21 | 李雪锋 | A kind of depopulated helicopter carbon fiber landing gear |
| CN106347638A (en) * | 2016-10-26 | 2017-01-25 | 山东鹰翼航空科技有限公司 | Unmanned helicopter landing gear |
| WO2023214943A1 (en) * | 2022-05-05 | 2023-11-09 | İstanbul Geli̇şi̇m Üni̇versi̇tesi̇ | Landing gear bracket |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20151104 |
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| WD01 | Invention patent application deemed withdrawn after publication |