CN208364665U - A kind of Combined-type shock-absorption device for aircraft - Google Patents
A kind of Combined-type shock-absorption device for aircraft Download PDFInfo
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- CN208364665U CN208364665U CN201821018220.7U CN201821018220U CN208364665U CN 208364665 U CN208364665 U CN 208364665U CN 201821018220 U CN201821018220 U CN 201821018220U CN 208364665 U CN208364665 U CN 208364665U
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- aircraft
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- combined
- absorption device
- type shock
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- 238000010521 absorption reaction Methods 0.000 title claims abstract description 27
- 239000003292 glue Substances 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 238000001727 in vivo Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 11
- 238000013016 damping Methods 0.000 abstract description 10
- 238000002955 isolation Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000003116 impacting effect Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000006096 absorbing agent Substances 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000575 pesticide Substances 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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- Springs (AREA)
Abstract
The utility model discloses a kind of Combined-type shock-absorption devices for aircraft, are installed between aircraft body and pulley, including elastic rubber component, spring assembly and connection component；It the elastic rubber component and spring assembly coaxial line and is sequentially connected by connection component.The Combined-type shock-absorption device for aircraft of the utility model has many advantages, such as structure simple, good damping effect, small in size and light-weight.
Description
Technical field
The utility model relates generally to vehicle technology field, refers in particular to a kind of Combined-type shock-absorption device for aircraft.
Background technique
Currently, small aircraft is widely used in various industries.Agricultural can be used to carry out pesticide spraying, the condition of a disaster detection；
Petroleum industry can be used to carry out oil-gas pipeline tour；The delivery etc. that delivery industry can be used for wrapping up.Furthermore it can also be used in gas
As, photography etc. industries.
Existing aircraft is divided into Fixed Wing AirVehicle and two kinds of rotor craft.Either Fixed Wing AirVehicle is still more
Rotor craft is taking off and, due to artificial or control system factor, is inevitably being formed and rushed to ground in descent
It hits, while impacting and can have to the structure safety of aircraft, the comfort of passenger and the reliability of flight control system
Large effect, thus aircraft bottom mounting shock absorber come mitigate take off, land caused by impact it is very necessary.
Damper used at present mostly uses greatly hydraulic damper, air bump and spring damper etc..
Wherein structure is complicated for hydraulic damper, has fluid chamber, volume is big, than cumbersome, also deposits in use
The hydraulic fluid leak the problems such as, be not suitable for being applied in aircraft.
Air bump maintains difficulty due to the problem of with air bag, volume is bigger, while there is also helium leaks
Greatly.
Traditional spring damper is poor for the shock absorption from ground, and amplitude of vibration decaying is slow, causes to take and feel
Discomfort, and in the case where impacting biggish situation or even the case where will appear damper on earth, spring and shell rigid contact occurs
The case where, to cause the damage of damper.
Utility model content
The technical problems to be solved in the utility model is that for technical problem of the existing technology, this is practical new
Type provides that a kind of structure is simple, the Combined-type shock-absorption device for aircraft of good damping effect.
In order to solve the above technical problems, the utility model proposes technical solution are as follows:
A kind of Combined-type shock-absorption device for aircraft, is installed between aircraft body and pulley, including elastic rubber
Component, spring assembly and connection component；The elastic rubber component successively connects with spring assembly coaxial line and by connection component
It connects.
As a further improvement of the above technical scheme:
The elastic rubber component includes cylinder, rubber parts, cover board and connector；The cylinder is hollow cylinder and one end
Opening, the rubber parts are installed in the hollow cavity of the cylinder and are blocked by cover board, the rubber parts and cover board
It is fastened on by connector in the hollow cavity of the cylinder.
One group or more of corresponding through-hole is offered on the axial direction of the cylinder, rubber parts and cover board；It is described
Connector includes screw bolt and nut, one end of the bolt sequentially pass through after the through-hole on cylinder, rubber parts and cover board with it is described
Nut thread connection.
The closed end of the cylinder is connected with the shell being connected with the aircraft body, the shell and the cylinder it
Between connected by screw thread or welding manner.
The spring assembly includes compressed spring.
The connection component includes guide rod and pressing plate, offers and passes through on the axis of the cylinder, rubber parts and cover board
The pilot hole worn, one end of the guide rod successively through cylinder, rubber parts, cover board pilot hole after, be then passed through compressed spring with
The pressing plate connection.
It is provided with ring-shaped step on the cover board and the end face contacted on pressing plate with compressed spring, for compressed spring
Carry out radial limit.
One end of the pressing plate is provided with the mounting portion for being connected with aircraft pulley.
The mounting portion is ear mount.
The quantity of the through-hole is two groups, is evenly distributed on axial end face.
Compared with the prior art, the advantages of the utility model are:
The Combined-type shock-absorption device for aircraft of the utility model, by by elastic rubber component and traditional groups of springs
Part is combined, and forms Combined-type shock-absorption device, since the elastic modulus difference between elastic rubber and spring is larger, the two combination
After can absorb vibration energy to the greatest extent, to improve damping effect, improve aircraft body safety of structure and fly
The reliability of row device control system；Due to being equipped with elastic rubber component on vibration transmission path, additionally it is possible to play vibration isolation and drop
The effect made an uproar, to improve the comfort of aircraft；In addition, Combined-type shock-absorption device structure is simple, small in size and light-weight.
The Combined-type shock-absorption device for aircraft of the utility model, using the shock-damping structure of spring and building rubber compound formula,
Exclusive use spring is overcome as damping component and damps disadvantage small, that vibration isolating effect is poor；The internally-damped big, vibration of bound rubber
Dynamic isolation performance is good, it is easily molded, with metal can also be bonded securely and density it is small the advantages that, the two is in turn connected to form combination
Formula damper, the advantages of combining two kinds of materials, the shortcomings that having evaded the two.Rubber is utilized in damper compression and elongation process
The heavy damping of glue acts on, and absorbs most vibration energy, improves comfort, and reducing vibration bring influences.
Detailed description of the invention
Fig. 1 is the schematic perspective view of the utility model.
Fig. 2 is the configuration schematic diagram of the utility model.
Fig. 3 is the schematic perspective view of rubber parts in the utility model.
Fig. 4 is the cross-sectional view of rubber parts in the utility model.
Fig. 5 is the schematic perspective view of the utility model middle cylinder body.
Fig. 6 is the schematic cross-sectional view of the utility model middle cylinder body.
Fig. 7 is the schematic perspective view of the utility model cover plate.
Fig. 8 is the cross-sectional view of the utility model cover plate.
Figure label indicates: 1, elastic rubber component；101, cylinder；102, rubber parts；103, cover board；104, connector；
1041, bolt；1042, nut；105, through-hole；106, pilot hole；107, shell；2, spring assembly；201, compressed spring；3, even
Connected components；301, guide rod；302, pressing plate.
Specific embodiment
The utility model is further described below in conjunction with Figure of description and specific embodiment.
As shown in Figures 1 to 7, the Combined-type shock-absorption device for aircraft of the present embodiment, wherein aircraft is that flight rubs
Support or other aircraft, damper are installed between aircraft body and pulley, and specific structure includes elastic rubber component 1, bullet
Spring component 2 and connection component 3；Elastic rubber component 1 is sequentially connected with spring assembly 2 by connection component 3 and coaxial line.Specifically
The one end on ground, elastic rubber component 1 is connect with aircraft body, and one end of the other end and spring assembly 2 passes through 3 phase of connection component
Even, the other end of spring assembly 2 is then connected with the sliding part of aircraft (such as pulley).Certainly, in other embodiments, may be used
To exchange elastic rubber component 1 and the position of spring assembly 2, i.e., elastic rubber component 1 is connected with pulley, spring assembly
2 are connected with aircraft body.The Combined-type shock-absorption device for aircraft of the utility model, by by elastic rubber component 1 with
Traditional spring assembly 2 is combined, and Combined-type shock-absorption device is formed, due to the elastic modulus difference between elastic rubber and spring
It is larger, vibration energy can be absorbed to the greatest extent after the two combination, to improve damping effect, improve aircraft body knot
The reliability of structure safety and flight control system；Due to being equipped with elastic rubber component 1 on vibration transmission path, additionally it is possible to
Play the role of vibration isolation and noise reduction, to improve the comfort of aircraft；In addition, Combined-type shock-absorption device structure is simple, small in size
And it is light-weight.
In the present embodiment, spring assembly 2 includes compressed spring 201；Elastic rubber component 1 then includes cylinder 101, rubber parts
102, cover board 103 and connector 104；Cylinder 101 be hollow cylindric cylinder 101, it is closed at one end open at one end, it is cylindric or
The rubber parts 102 of drum type is installed in the hollow cavity of cylinder 101 and is blocked by cover board 103, rubber parts 102 and cover board
103 are fastened in the hollow cavity of cylinder 101 by connector 104.Specifically, as shown in Fig. 3~8, cylinder 101, rubber parts
102 and the axial end face of cover board 103 be uniformly provided with one group or more of through-hole 105 in a circumferential direction；Lead to it is preferred that opening up two groups
Hole 105, connector 104 then correspond to two groups, specifically include bolt 1041 and nut 1042, and one end of bolt 1041 sequentially passes through
It is threadedly coupled after through-hole 105 on cylinder 101, rubber parts 102 and cover board 103 with nut 1042, thus by cylinder 101, rubber
Part 102 connects to form entirety with 103 three of cover board, and structure is simple, convenient for disassembly and assembly；The wherein aperture of through-hole 105 and bolt 1041
Diameter matches.In addition, the closed end of cylinder 101 is connected with shell 107, shell 107 then passes through ear mount and aircraft body phase
Even, the circumferencial direction of the closed end of middle cylinder body 101 is equipped with external screw thread, is threadedly coupled with the internal screw thread of shell 107；Certainly,
Cylinder 101 and shell 107 can also be attached fastening by other ways such as welding.
As depicted in figs. 1 and 2, in the present embodiment, connection component 3 includes the same bolt of guide rod 301(structure) and pressing plate
302, perforative pilot hole 106, the diameter of guide rod 301 are offered on the axis of cylinder 101, rubber parts 102 and cover board 103
It is identical as the aperture of pilot hole 106, one end of guide rod 301 successively through cylinder 101, rubber parts 102, cover board 103 pilot hole
It after 106, is then passed through compressed spring 201 and is connect with pressing plate 302, so that cover board 103 and pressing plate 302 be made to carry out compressed spring 201
Axial limiting；Both elastic rubber component 1 and spring assembly 2 combination structure is simple, it is convenient for disassembly and assembly, be easily achieved.In addition,
Cover board 103 is provided with ring-shaped step with what compressed spring 201 contacted on pressing plate 302 on one side, for compressed spring 201 into
Conduct guarantees the reliability that compressed spring 201 works to limit.Wherein one end of pressing plate 302 is provided with for sliding with aircraft
Take turns the mounting portion (such as ear mount) being connected.
Working principle: when damper is impacted and compressed, compressed spring 201 is compressed and then rubber parts 102 is pushed to press
Contracting, since the elasticity modulus of rubber and the elastic modulus difference of spring are larger, rubber parts 102 is first compressed to maximum, then presses
Contracting spring 201 is compressed to maximum, both farthest absorbs vibration energy, and in the process, rubber parts 102 also rises
Vibration isolation and the effect of noise reduction are arrived.The stage is sprung back in damper, compressed spring 201 is first restored, and rubber parts 102 restores again, due to
Spring is different from rubber property, and at a time, rubber parts 102 will receive pulling force effect, further absorbs vibration, consumes energy
Amount, to make to shake quick stopping, playing cushioning effect.Vibration energy is being absorbed in compressed spring 201 and rubber parts 102
Afterwards, the temperature of material itself can be made to increase, passed to the heat of generation in air by cylinder 101 and shell 107.
The Combined-type shock-absorption device for aircraft of the utility model, using the shock-damping structure of spring and building rubber compound formula,
Exclusive use spring is overcome as damping component and damps disadvantage small, that vibration isolating effect is poor；The internally-damped big, vibration of bound rubber
Dynamic isolation performance is good, it is easily molded, with metal can also be bonded securely and density it is small the advantages that, the two is in turn connected to form combination
Formula damper, the advantages of combining two kinds of materials, the shortcomings that having evaded the two.Rubber is utilized in damper compression and elongation process
The heavy damping of glue acts on, and absorbs most vibration energy, improves comfort, and reducing vibration bring influences.
Although the utility model has been disclosed with preferred embodiment as above, it is not intended to limit the utility model.It is any
Those skilled in the art, in the case where not departing from technical solutions of the utility model range, all using the disclosure above
Technology contents many possible changes and modifications are made to technical solutions of the utility model, or be revised as the equivalent of equivalent variations
Embodiment.Therefore, all contents without departing from technical solutions of the utility model, according to the utility model technical spirit to the above reality
Any simple modifications, equivalents, and modifications that example is done are applied, should all be fallen in the range of technical solutions of the utility model protection.
Claims (10)
1. a kind of Combined-type shock-absorption device for aircraft, is installed between aircraft body and pulley, which is characterized in that including
Elastic rubber component (1), spring assembly (2) and connection component (3)；The elastic rubber component (1) and spring assembly (2) are coaxial
It line and is sequentially connected by connection component (3).
2. the Combined-type shock-absorption device according to claim 1 for aircraft, which is characterized in that the elastic rubber component
It (1) include cylinder (101), rubber parts (102), cover board (103) and connector (104)；The cylinder (101) is hollow cylinder
(101) and open at one end, the rubber parts (102) is installed in the hollow cavity of the cylinder (101) and by cover board (103)
It is blocked, the rubber parts (102) and cover board (103) pass through the hollow cavity that connector (104) are fastened on the cylinder (101)
In vivo.
3. the Combined-type shock-absorption device according to claim 2 for aircraft, which is characterized in that the cylinder (101), rubber
One group or more of corresponding through-hole (105) is offered on the axial direction of glue part (102) and cover board (103)；The connection
Part (104) includes bolt (1041) and nut (1042), and one end of the bolt (1041) sequentially passes through cylinder (101), rubber
Through-hole (105) on part (102) and cover board (103) is threadedly coupled with the nut (1042) afterwards.
4. the Combined-type shock-absorption device according to claim 2 or 3 for aircraft, which is characterized in that the cylinder (101)
Closed end be connected with the shell (107) being connected with the aircraft body, the shell (107) and the cylinder (101) it
Between connected by screw thread or welding manner.
5. the Combined-type shock-absorption device according to claim 2 or 3 for aircraft, which is characterized in that the spring assembly
It (2) include compressed spring (201).
6. the Combined-type shock-absorption device according to claim 5 for aircraft, which is characterized in that the connection component (3)
Including guide rod (301) and pressing plate (302), opened up on the axis of the cylinder (101), rubber parts (102) and cover board (103)
Have perforative pilot hole (106), one end of the guide rod (301) is successively through cylinder (101), rubber parts (102), cover board
(103) it after pilot hole (106), is then passed through compressed spring (201) and is connect with the pressing plate (302).
7. the Combined-type shock-absorption device according to claim 6 for aircraft, which is characterized in that the cover board (103) with
Be provided with ring-shaped step on the end face contacted on pressing plate (302) with compressed spring (201), for compressed spring (201) into
Conduct is to limit.
8. the Combined-type shock-absorption device according to claim 6 for aircraft, which is characterized in that the pressing plate (302)
One end is provided with the mounting portion for being connected with aircraft pulley.
9. the Combined-type shock-absorption device according to claim 8 for aircraft, which is characterized in that the mounting portion is ear
Seat.
10. the Combined-type shock-absorption device according to claim 3 for aircraft, which is characterized in that the through-hole (105)
Quantity is two groups, is evenly distributed on axial end face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821018220.7U CN208364665U (en) | 2018-06-29 | 2018-06-29 | A kind of Combined-type shock-absorption device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821018220.7U CN208364665U (en) | 2018-06-29 | 2018-06-29 | A kind of Combined-type shock-absorption device for aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN208364665U true CN208364665U (en) | 2019-01-11 |
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ID=64927554
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821018220.7U Expired - Fee Related CN208364665U (en) | 2018-06-29 | 2018-06-29 | A kind of Combined-type shock-absorption device for aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108561494A (en) * | 2018-06-29 | 2018-09-21 | 长沙市云智航科技有限公司 | A kind of Combined-type shock-absorption device for aircraft |
| CN110374010A (en) * | 2019-07-22 | 2019-10-25 | 中铁大桥局集团有限公司 | A kind of constructing device and its application method of the interim vibration damping of suspension cable |
-
2018
- 2018-06-29 CN CN201821018220.7U patent/CN208364665U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108561494A (en) * | 2018-06-29 | 2018-09-21 | 长沙市云智航科技有限公司 | A kind of Combined-type shock-absorption device for aircraft |
| CN108561494B (en) * | 2018-06-29 | 2024-04-19 | 长沙市云智航科技有限公司 | Combined shock absorber for aircraft |
| CN110374010A (en) * | 2019-07-22 | 2019-10-25 | 中铁大桥局集团有限公司 | A kind of constructing device and its application method of the interim vibration damping of suspension cable |
| CN110374010B (en) * | 2019-07-22 | 2021-09-03 | 中铁大桥局集团有限公司 | Construction device for temporary vibration reduction of stay cable and use method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190111 |