CN205554613U - Shock attenuation coupling mechanism of engine and fuselage - Google Patents
Shock attenuation coupling mechanism of engine and fuselage Download PDFInfo
- Publication number
- CN205554613U CN205554613U CN201620388443.7U CN201620388443U CN205554613U CN 205554613 U CN205554613 U CN 205554613U CN 201620388443 U CN201620388443 U CN 201620388443U CN 205554613 U CN205554613 U CN 205554613U
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- fuselage
- electromotor
- post
- fastening structure
- flange
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Abstract
The utility model belongs to the technical field of unmanned aerial vehicle, especially, relate to a shock attenuation coupling mechanism of engine and fuselage, including setting up a plurality of spliced poles between the mounting panel of fuselage and engine, be equipped with the flange near mounting hole department on the spliced pole, between flange and the fuselage, be equipped with the shock pad that is the echelonment between flange and the mounting panel respectively, be equipped with the fastening structure of being connected with the spliced pole respectively in one side that the spliced pole was kept away from to fuselage, mounting panel, between fastening structure and the fuselage, be equipped with the shock pad that is the echelonment between fastening structure and the mounting panel respectively, the shock pad includes the advance capital for body, with advance capital for body fixed connection and the downthehole installation department of insert the installation, the diameter of the advance capital for body is greater than the diameter of installation department, the fastening structure includes the backing plate, passes backing plate and spliced pole end connection's bolt, the problem of the shock pad easily deviate from and the bolt easily splits is solved, can improve shock attenuation effect increase of service life.
Description
Technical field
This utility model belongs to unmanned air vehicle technique field, particularly relates to a kind of electromotor and is connected with the damping of fuselage
Mechanism.
Background technology
At present, unmanned plane is many uses bolt to be connected as power, electromotor with fuselage using fuel engines,
Using O type cushion as bumper and absorbing shock parts.Under alternate load, O type cushion is the most tired, causes becoming
Shape is deviate from, and once O type cushion lost efficacy, and bolt the most easily ruptures, and causes falling accident to occur.
Utility model content
The purpose of this utility model is the damping connection mechanism providing a kind of electromotor with fuselage, it is intended to solve
Cushion is easily deviate from and the problem of bolt easy fracture, it is possible to increase damping effect increases the service life.
This utility model is achieved in that the damping connection mechanism of a kind of electromotor and fuselage, described in start
If the damping connection mechanism of machine and fuselage includes being arranged between the installing plate of described fuselage and described electromotor
Dry root connects post, is provided with flange, at described flange with described on described connection post at described installing hole
Between fuselage, between described flange and described installing plate, it is respectively equipped with stepped cushion；At described machine
Body, described installing plate are respectively equipped with and the described fastening structure being connected post connection away from the side of described connection post,
Be respectively equipped with between described fastening structure and described fuselage, between described fastening structure and described installing plate in
Stair-stepping cushion；Described cushion includes that pad body and described pad body are fixing and is connected and inserts institute
Stating the installation portion in installing hole, the diameter of described pad body is more than the diameter of described installation portion；Described fastening knot
Structure includes backing plate, is connected, with described, the bolt that column end connects through described backing plate.
Improving as one, the both ends of described connection post are inserted on described installing plate, described fuselage respectively
In installing hole.
Improving as one, described connection post inserts the diameter of the interior part of described installing hole less than described connection post
It is not inserted into the diameter of the interior part of installing hole.
Improving as one, described pad body and described installation portion are integral type structure.
Improving as one, described connection post is set to four, circumferentially divides equally layout.
Owing to have employed technique scheme, the electromotor that this utility model provides is connected machine with the damping of fuselage
Structure includes the some connection posts being arranged between the installing plate of total time, airframe, and engine, is connecting on post near peace
Dress hole at be provided with flange, between flange and fuselage, be respectively equipped with between flange and installing plate stepped
Cushion；It is respectively equipped with and is connected, away from the side of connection post, the fastening structure that post connects at fuselage, installing plate,
Stepped cushion it is respectively equipped with between fastening structure and fuselage, between fastening structure and installing plate；
Cushion includes that pad body fixes the installation portion being connected and inserting in installing hole with pad body, pad body
Diameter is more than the diameter of installation portion；Fastening structure includes backing plate, through backing plate and the spiral shell being connected column end connection
Bolt；During use, owing to cushion is provided with the installation portion inserted in installing hole, cushion and peace can be strengthened
The switching performance in dress hole, prevents abjection, and is provided with flange on post increases and the contacting of cushion connecting
Area, it is possible to strengthen damping effect, moment of flexure size suffered by bolt can be reduced and prevent from fractureing, solve damping
Pad easily abjection and the problem of bolt easy fracture, it is possible to increase damping effect increases the service life.
Accompanying drawing explanation
Fig. 1 is the sectional structure schematic diagram of electromotor of the present utility model and the damping connection mechanism of fuselage；
Fig. 2 is the perspective view of electromotor of the present utility model and the damping connection mechanism of fuselage；
Wherein, 10, fuselage, 20, electromotor, 30, connect post, 31, flange, 40, bolt, 41,
Backing plate, 50, pad body, 51, installation portion, 60, installing plate.
Detailed description of the invention
In order to make the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with accompanying drawing
And embodiment, this utility model is further elaborated.Should be appreciated that described herein specifically
Embodiment, only in order to explain this utility model, is not used to limit this utility model.
Fig. 1 and Fig. 2 is the structural representation of electromotor of the present utility model and the damping connection mechanism of fuselage,
Wherein, Fig. 1 shows the sectional structure signal of electromotor of the present utility model and the damping connection mechanism of fuselage
Figure, Fig. 2 shows the perspective view of electromotor of the present utility model and the damping connection mechanism of fuselage,
For the ease of statement, figure only gives the part relevant to this utility model.
From Fig. 1 and Fig. 2, the damping connection mechanism of this electromotor and fuselage include being arranged on fuselage 10 with
Some connection posts 30 between electromotor 20, are provided with flange 31 connecting on post 30 at installing hole,
Between flange 31 and fuselage 10, between flange 31 and installing plate 60, it is respectively equipped with stepped damping
Pad；It is respectively equipped with tight be connected post 30 connection away from the side connecting post 30 at fuselage 10, installing plate 60
Fixing structure, between fastening structure and fuselage 10, is respectively equipped with in rank between fastening structure and installing plate 60
The cushion of scalariform；This cushion includes that pad body 50 and pad body 50 are wholely set and insert installing hole
Interior installation portion 51, the diameter of pad body 50 is more than the diameter of installation portion 51；This fastening structure includes backing plate
41, through backing plate 41 and the bolt 40 being connected the connection of post 30 end.
During use, owing to cushion is provided with the installation portion 51 inserted in installing hole, can strengthen cushion with
The switching performance of installing hole, prevents abjection, and is provided with flange 31 on connection post 30 and increases and damping
The contact area of pad, it is possible to strengthen damping effect, moment of flexure size suffered by bolt 40 can be reduced and prevent from fractureing,
Solve cushion easily to deviate from and the problem of bolt easy fracture, it is possible to increase damping effect increases the service life.
In the present embodiment, the both ends of this connection post 30 insert the installing plate 60 of electromotor 20, machine respectively
In installing hole on body 10, connection post 30 inserts the diameter of the interior part of installing hole and is not inserted into less than connecting post 30
In installing hole, the diameter of part, can reduce moment of flexure size suffered by bolt 40 further, so can be further
Strengthen switching performance, damping performance and increase the service life.
In the present embodiment, this fastening structure can also be only a bolt, it is also possible to realize connecting.
In the present embodiment, installing plate 60 is fixed together with electromotor 20, just by multiple bolts
In realizing connecting the connection of post 30 and electromotor 20.
In the present embodiment, connect post 30 and be set to four, circumferentially divide equally layout, naturally it is also possible to according to
It is actually needed and arranges three or more.
The electromotor that this utility model provides includes being arranged on total time, airframe, and engine with the damping connection mechanism of fuselage
Installing plate between some connection posts, at installing hole, be provided with flange connecting on post, flange with
Stepped cushion it is respectively equipped with between fuselage, between flange and installing plate；Remote at fuselage, installing plate
It is respectively equipped with from the side connecting post and is connected the fastening structure that post connects, between fastening structure and fuselage,
Stepped cushion it is respectively equipped with between fastening structure and installing plate；Cushion includes pad body and pad
Body fixes the installation portion connecting and inserting in installing hole, and the diameter of pad body is more than the diameter of installation portion；
Fastening structure includes backing plate, through backing plate and the bolt being connected column end connection；During use, due to cushion
It is provided with the installation portion inserted in installing hole, the switching performance of cushion and installing hole, anti-anti-avulsion can be strengthened
Go out, and on connection post, be provided with flange increase the contact area with cushion, it is possible to strengthen damping effect,
Moment of flexure size suffered by bolt can be reduced prevent from fractureing, solve cushion and easily deviate from and the asking of bolt easy fracture
Topic, it is possible to increase damping effect increases the service life.
The foregoing is only preferred embodiment of the present utility model, not in order to limit this utility model,
All any amendment, equivalent and improvement etc. made within spirit of the present utility model and principle, all should
Within being included in protection domain of the present utility model.
Claims (5)
1. electromotor and a damping connection mechanism for fuselage, including being arranged on described fuselage and described electromotor
Installing plate between some connection posts, it is characterised in that near described installing hole on described connection post
Place is provided with flange, between described flange and described fuselage, sets respectively between described flange and described installing plate
There is stepped cushion；Set respectively away from the side of described connection post at described fuselage, described installing plate
Have and be connected the fastening structure that post connects, between described fastening structure and described fuselage, described fastening with described
Stepped cushion it is respectively equipped with between structure and described installing plate；Described cushion include pad body,
Fix the installation portion being connected and inserting in described installing hole with described pad body, the diameter of described pad body is big
Diameter in described installation portion；Described fastening structure includes backing plate, is connected styletable through described backing plate with described
The bolt that portion connects.
Electromotor the most according to claim 1 and the damping connection mechanism of fuselage, it is characterised in that institute
The both ends stating connection post are inserted in the installing hole on described installing plate, described fuselage respectively.
Electromotor the most according to claim 2 and the damping connection mechanism of fuselage, it is characterised in that institute
State and connect post and insert the diameter of part in described installing hole and be not inserted into part in installing hole less than described connection post
Diameter.
4., according to the damping connection mechanism of the electromotor described in any one of claims 1 to 3 Yu fuselage, it is special
Levying and be, described pad body and described installation portion are integral type structure.
Electromotor the most according to claim 1 and the damping connection mechanism of fuselage, it is characterised in that institute
State connection post and be set to four, circumferentially divide equally layout.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620388443.7U CN205554613U (en) | 2016-04-29 | 2016-04-29 | Shock attenuation coupling mechanism of engine and fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620388443.7U CN205554613U (en) | 2016-04-29 | 2016-04-29 | Shock attenuation coupling mechanism of engine and fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205554613U true CN205554613U (en) | 2016-09-07 |
Family
ID=56804562
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620388443.7U Active CN205554613U (en) | 2016-04-29 | 2016-04-29 | Shock attenuation coupling mechanism of engine and fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205554613U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791909A (en) * | 2018-07-16 | 2018-11-13 | 飞瑞航空科技（江苏）有限公司 | A kind of unmanned vehicle engine installing mechanism |
-
2016
- 2016-04-29 CN CN201620388443.7U patent/CN205554613U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791909A (en) * | 2018-07-16 | 2018-11-13 | 飞瑞航空科技（江苏）有限公司 | A kind of unmanned vehicle engine installing mechanism |
| CN108791909B (en) * | 2018-07-16 | 2023-09-22 | 飞瑞航空科技（江苏）有限公司 | Unmanned aerial vehicle engine installation mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |