CN208778557U - A kind of piston-engined damping device of unmanned plane - Google Patents
A kind of piston-engined damping device of unmanned plane Download PDFInfo
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- CN208778557U CN208778557U CN201821584815.9U CN201821584815U CN208778557U CN 208778557 U CN208778557 U CN 208778557U CN 201821584815 U CN201821584815 U CN 201821584815U CN 208778557 U CN208778557 U CN 208778557U
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- mounting plate
- engine mounting
- connecting column
- engine
- fuselage
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Abstract
The utility model discloses a kind of piston-engined damping devices of unmanned plane, its main structure includes: fuselage ring, engine mounting plate, connecting column and dampening assembly, the fuselage ring and engine mounting plate are respectively fixedly disposed at the both ends of the connecting column, and the junction and the engine mounting plate of the fuselage ring and connecting column and the junction of connecting column are respectively provided with a dampening assembly.The utility model substantially alleviates engine vibration influence caused by fuselage, improves the bulk life time of fuselage by the dual shock absorption to fuselage ring and engine mounting plate；The damping device is axial damping structure, not only realizes the axial damping of engine, while also achieving the damping for engine around axis oscillating, is beneficial to prevent the fatigue failure of body, the noise of engine is reduced while improving engine efficiency.
Description
Technical field
The utility model relates to air vehicle technique field, in particular to a kind of piston-engined damping device of unmanned plane.
Background technique
The piston screw paddle motor used in small and medium size unmanned aerial vehicles, especially single cylinder or twin-tub opposed-piston engine,
In the presence of vibration and the biggish disadvantage of noise.Currently, damping of the main damping modes using single layer, two-dimensions, thus subtract
Shake ineffective, noise-reducing effect is also undesirable.In the case where good damping cannot be obtained, engine effect not only will affect
Rate, and it is also detracted from organism life-span.
Utility model content
In order to solve the above technical problems, the utility model discloses a kind of piston-engined damping device of unmanned plane,
Main structure includes: fuselage ring, engine mounting plate, connecting column and dampening assembly, and the fuselage ring and engine are pacified
Loading board is respectively fixedly disposed at the both ends of the connecting column, the junction and the engine of the fuselage ring and connecting column
The junction of mounting plate and connecting column is respectively provided with a dampening assembly.
As a further improvement of the above technical scheme, the dampening assembly include the first resilient cushion, the second resilient cushion with
And gland, first resilient cushion setting is in the fuselage ring/between engine mounting plate and connecting column, second damping
In the fuselage ring/between engine mounting plate and gland, the gland is bolted to connection with connecting column for pad setting.
As a further improvement of the above technical scheme, first resilient cushion includes circular ring shape base and is arranged in institute
The round ring boss in circular ring shape base is stated, second resilient cushion is circular ring structure.
As a further improvement of the above technical scheme, the connecting column both ends are respectively provided with a circular groove, the annulus
Shape pedestal is arranged in the circular groove, and it is outer that the fuselage ring/engine mounting plate is arranged in second resilient cushion
Side, the circular hole that the round ring boss passes through on the fuselage ring/engine mounting plate are connect with second resilient cushion.
As a further improvement of the above technical scheme, the fuselage ring and engine mounting plate are circular ring shape knot
Structure.
As a further improvement of the above technical scheme, axial symmetry is equipped between the fuselage ring and engine mounting plate
Four groups of connecting columns and dampening assembly.
As a further improvement of the above technical scheme, gasket is equipped between the bolt end and gland.
Compared with prior art, the utility model has the beneficial effects that
1, it by the dual shock absorption to fuselage ring and engine mounting plate, substantially alleviates engine vibration and fuselage is made
At influence, improve the bulk life time of fuselage；
2, the damping device is axial damping structure, not only realizes the axial damping of engine, while also achieving needle
To engine around the damping of axis oscillating, it is beneficial to prevent the fatigue failure of body, reduction while improving engine efficiency
The noise of engine.
Detailed description of the invention
In order to illustrate more clearly of the technical scheme in the embodiment of the utility model, will make below to required in embodiment
Attached drawing is briefly described, it should be apparent that, the drawings in the following description are merely some embodiments of the present invention,
For those of ordinary skill in the art, without any creative labor, it can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the structural schematic diagram of the utility model；
Fig. 2 is the structure sectional view in Fig. 1 along the face A-A.
Appended drawing reference:
1- fuselage ring；2- engine mounting plate；3- connecting column；31- circular groove；The first resilient cushion of 4-；41- circular ring shape
Pedestal；42- round ring boss；The second resilient cushion of 5-；6- gland；7- bolt；8- gasket.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.
It is to be appreciated that the directional instruction (such as up, down, left, right, before and after ...) of institute in the utility model embodiment
It is only used for explaining in relative positional relationship, the motion conditions etc. under a certain particular pose (as shown in the picture) between each component, such as
When the fruit particular pose changes, then directionality instruction also correspondingly changes correspondingly.
In addition, the description for being related to " first ", " second " etc. in the present invention is used for description purposes only, and cannot understand
For its relative importance of indication or suggestion or implicitly indicate the quantity of indicated technical characteristic.Define as a result, " first ",
The feature of " second " can explicitly or implicitly include at least one of the features.
As shown in Figs. 1-2, the piston-engined damping device of the unmanned plane of the present embodiment, main structure include: fuselage
Frame 1, engine mounting plate 2, connecting column 3 and dampening assembly.Fuselage ring 1 and engine mounting plate 2 are fixedly installed respectively
At the both ends of connecting column 3, fuselage ring 1 and the junction of connecting column 3 and the junction of engine mounting plate 2 and connecting column 3
It is respectively provided with a dampening assembly.
Fuselage ring 1 and engine mounting plate 2 are cirque structure, and fuselage ring 1 and engine mounting plate 2 it
Between in a manner of axisymmetric be equipped with four groups of connecting columns 3 and dampening assembly.
Dampening assembly includes the first resilient cushion 4, the second resilient cushion 5 and gland 6, and the first resilient cushion 4 is arranged in fuselage frame
Between 1/ engine mounting plate 2 of frame and connecting column 3, the second resilient cushion 5 is arranged in 1/ engine mounting plate 2 of fuselage ring and gland
Between 6, gland 6 is fixedly connected with connecting column 3 by bolt 7, is additionally provided with gasket 8 between the end and gland 6 of bolt 7.
First resilient cushion 4 includes circular ring shape base 41 and the round ring boss 42 being arranged in circular ring shape base 41, the
Two resilient cushions 5 are circular ring structure；3 both ends of connecting column are respectively provided with a circular groove 31, and circular ring shape base 41 is arranged in circular groove
In 31.
The outside of 1/ engine mounting plate 2 of fuselage ring is arranged in second resilient cushion 5, and round ring boss 42 passes through fuselage frame
Circular hole on 1/ engine mounting plate 2 of frame is connect with the second resilient cushion 5.
The utility model substantially alleviates engine shake by the dual shock absorption to fuselage ring 1 and engine mounting plate 2
It is dynamic to be influenced caused by fuselage, improve the bulk life time of fuselage；And the damping device is axial damping structure, is not only realized
The axial damping of engine, while the damping for engine around axis oscillating is also achieved, it is beneficial to prevent the tired of body
Labor failure, reduces the noise of engine while improving engine efficiency.
The above is only the preferred embodiment of the utility model only, is not intended to limit the utility model, all at this
Within the spirit and principle of utility model, any modification, equivalent replacement, improvement and so on should be included in the utility model
Protection scope within.It in addition, the technical solution between each embodiment can be combined with each other, but must be general with this field
Based on logical technical staff can be realized；It will be understood that when the combination of technical solution appearance is conflicting or cannot achieve this
The combination of technical solution is not present, also not within the protection scope of the requires of the utility model.
Claims (7)
1. a kind of piston-engined damping device of unmanned plane, it is characterised in that: including fuselage ring, engine mounting plate, connect
Column and dampening assembly are connect, the fuselage ring and engine mounting plate are respectively fixedly disposed at the both ends of the connecting column, institute
The junction of the junction and the engine mounting plate and connecting column of stating fuselage ring and connecting column is respectively provided with a damping group
Part.
2. the piston-engined damping device of unmanned plane according to claim 1, it is characterised in that: the dampening assembly packet
The first resilient cushion, the second resilient cushion and gland are included, first resilient cushion is arranged in the fuselage ring/engine mounting plate
Between connecting column, second resilient cushion setting is in the fuselage ring/between engine mounting plate and gland, the gland
It is bolted to connection with connecting column.
3. the piston-engined damping device of unmanned plane according to claim 2, it is characterised in that: first resilient cushion
Including circular ring shape base and the round ring boss being arranged in the circular ring shape base, second resilient cushion is annulus knot
Structure.
4. the piston-engined damping device of unmanned plane according to claim 3, it is characterised in that: the connecting column both ends
It is respectively provided with a circular groove, the circular ring shape base is arranged in the circular groove, and second resilient cushion is arranged described
Fuselage ring/engine mounting plate outside, the round ring boss pass through the circle on the fuselage ring/engine mounting plate
Hole is connect with second resilient cushion.
5. the piston-engined damping device of unmanned plane according to claim 1, it is characterised in that: the fuselage ring and
Engine mounting plate is cirque structure.
6. the piston-engined damping device of unmanned plane according to claim 1, it is characterised in that: the fuselage ring with
Axial symmetry is equipped with four groups of connecting columns and dampening assembly between engine mounting plate.
7. the piston-engined damping device of unmanned plane according to claim 2, it is characterised in that: the bolt end with
Gasket is equipped between gland.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821584815.9U CN208778557U (en) | 2018-09-27 | 2018-09-27 | A kind of piston-engined damping device of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821584815.9U CN208778557U (en) | 2018-09-27 | 2018-09-27 | A kind of piston-engined damping device of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208778557U true CN208778557U (en) | 2019-04-23 |
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ID=66161058
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821584815.9U Active CN208778557U (en) | 2018-09-27 | 2018-09-27 | A kind of piston-engined damping device of unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208778557U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
-
2018
- 2018-09-27 CN CN201821584815.9U patent/CN208778557U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
| CN110844090B (en) * | 2019-10-11 | 2022-11-22 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
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