CN205837164U - The frame of unmanned vehicle and unmanned vehicle - Google Patents
The frame of unmanned vehicle and unmanned vehicle Download PDFInfo
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- CN205837164U CN205837164U CN201620516164.4U CN201620516164U CN205837164U CN 205837164 U CN205837164 U CN 205837164U CN 201620516164 U CN201620516164 U CN 201620516164U CN 205837164 U CN205837164 U CN 205837164U
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- arm
- paragraph
- shock insulation
- fuselage
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Abstract
The frame of a kind of unmanned vehicle, including fuselage and the horn that is connected with described fuselage.Described horn is provided with the installation portion for installing Power Component.The electronic component that can electrically connect it is provided with described Power Component in described fuselage.The frame of described unmanned vehicle also includes that shock insulation part, described shock insulation part are located on described horn, and between described installation portion and described fuselage, to intercept the vibrations of described Power Component.This utility model further relates to the unmanned vehicle of a kind of frame with described unmanned vehicle.
Description
Technical field
This utility model relates to aircraft field, particularly relates to frame and the unmanned vehicle of a kind of unmanned vehicle.
Background technology
Nowadays, unmanned vehicle have been widely used for taking photo by plane, monitor, explore, recover, the field such as agricultural plant protection.For performing
Aerial mission and the needs of self flight, described unmanned vehicle is generally equipped with a number of functional module, such as
Sensor, Inertial Measurement Unit (IMU), flight control modules, shooting unit etc..But, existing unmanned vehicle is the most
Rotor type unmanned vehicle, the operation of its power unit (such as rotor) can produce vibrations, and then described functional module is caused shadow
Ring, cause described functional module not work orderly and even damage.
Utility model content
In view of this, it is necessary to frame and the unmanned vehicle of a kind of unmanned vehicle avoiding the problems referred to above are provided.
The frame of a kind of unmanned vehicle, including fuselage and the horn that is connected with described fuselage.Described horn is provided with use
In the installation portion installing Power Component.The electric installation portion for installing electronic component, described electronics unit it is provided with in described fuselage
Part can electrically connect with described Power Component.The frame of described unmanned vehicle also includes that shock insulation part, described shock insulation part are located at institute
State on horn, and between described installation portion and described fuselage, to intercept the vibrations of described Power Component.
A kind of unmanned vehicle, including described frame and Power Component.
Relative to prior art, the frame of described unmanned vehicle and described unmanned vehicle are by arranging described shock insulation
Part, to avoid the vibrations of Power Component to be transferred to described fuselage through described horn, therefore, it is possible to the unit ensured in described fuselage
Part is from the impact of described vibrations.
Accompanying drawing explanation
Fig. 1 is the axonometric chart of the unmanned vehicle of this utility model embodiment.
Fig. 2 is the exploded view of the horn of the unmanned vehicle of Fig. 1.
Fig. 3 is the further exploded view of the horn of the unmanned vehicle of Fig. 2.
Fig. 4 to Fig. 6 is the schematic diagram that the horn of the unmanned vehicle to Fig. 3 assembles.
Fig. 7 is the unmanned vehicle schematic diagram of this utility model the second embodiment.
Fig. 8 is the schematic diagram of the unmanned vehicle of this utility model the 3rd embodiment.
Main element symbol description
| Aircraft | 100、200、300 |
| Fuselage | 10、10’、10’’ |
| Upper casing | 11 |
| Lower casing | 12 |
| Horn | 20、20’、20’’ |
| First paragraph | 21 |
| End face | 210 |
| Limiting section | 211 |
| Support member | 2111 |
| Stop part | 2112 |
| First stitching section | 21a |
| Second stitching section | 21b |
| Second segment | 22 |
| Arm | 201 |
| First arm | 221 |
| First snaps in projection | 2211 |
| First connects post | 2212 |
| Connecting hole | 2212a |
| Second arm | 223 |
| Second connects post | 2232 |
| Through hole | 2233 |
| Installation portion | 202 |
| First installation portion | 222 |
| Second installation portion | 224 |
| Fixed structure | 2241 |
| Perforation | 2221 |
| 3rd stitching section | 22a |
| 4th stitching section | 22b |
| Shock insulation part | 30、30’、30’’ |
| Set apertured | 301 |
| Abutting part | 31 |
| Power Component | 40、40’ |
| Foot rest | 50 |
| Connector | 60 |
Following detailed description of the invention will further illustrate this utility model in conjunction with above-mentioned accompanying drawing.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole
Embodiment.Based on the embodiment in this utility model, those of ordinary skill in the art are not under making creative work premise
The every other embodiment obtained, broadly falls into the scope of this utility model protection.
It should be noted that when assembly is referred to as " being fixed on " another assembly, and it can be directly on another assembly
Or assembly placed in the middle can also be there is.When an assembly is considered as " connection " another assembly, and it can be to be directly connected to
To another assembly or may be simultaneously present assembly placed in the middle.When an assembly is considered as " being arranged at " another assembly, it
Can be to be set directly on another assembly or may be simultaneously present assembly placed in the middle.Term as used herein is " vertical
", " level ", "left", "right" and similar statement for illustrative purposes only.
Unless otherwise defined, all of technology used herein and scientific terminology are led with belonging to technology of the present utility model
The implication that the technical staff in territory is generally understood that is identical.At term used in the description of the present utility model it is simply herein
The purpose of specific embodiment is described, it is not intended that in limiting this utility model.Term as used herein " and/or " include
Arbitrary and all of combination of one or more relevant Listed Items.
Referring to Fig. 1, the unmanned vehicle 100 of this utility model embodiment includes fuselage 10, horn 20, shock insulation part
30, Power Component 40 and foot rest 50.In present embodiment, described unmanned vehicle 100 is four rotor unmanned aircrafts, therefore
Described Power Component 40 is four for rotor assemblies and quantity, and four described Power Components 40 are by corresponding described horn 20
Support and be distributed in the rectangular area around described fuselage 10, and each described Power Component 40 is positioned at one, described rectangle
On summit.According to aerodynamic principle, for avoiding described Power Component 40 to produce flow-disturbing when rotating, adjacent is described dynamic
Power assembly 40 rotation direction operationally is different, and the rotation direction of relative described Power Component 40 is identical.
Certainly, according to different demands, the quantity of described Power Component 40 can suitably change, the most described power
The quantity of assembly 40 can be two, three, six, eight, 16 etc., even, the quantity of described Power Component 40 is permissible
It is only one.
Described fuselage 10 is the bearing part of described unmanned vehicle 100, on described fuselage 10 or inside can be provided with
Electrically installation portion, described electric installation portion is used for installing, carrying the electricity such as sensor, circuit board, processor, communication module and battery
Sub-element.The shell (non-label) of described fuselage 10, in streamlined, can reduce air drag during flight.Enforcement at other
Mode, the shell of described fuselage 10 can be other shapes, such as polygon, circle, ellipse etc..It is appreciated that described machine
The shell of body 10 can also omit, and only forms described fuselage 10 with support overlap joint.
In present embodiment, described fuselage 10 includes upper casing 11 and lower casing 12, described upper casing 11 and described lower casing 12
Mutually splicing fastens the monolithic case forming described fuselage 10.It is appreciated that described upper casing 11 can use with described lower casing 12
The modes such as engaging, securing member connect, gluing are connected with each other.
It is formed with cavity (sign) between described upper casing 11 and described lower casing 12, described biography in described cavity, can be housed
The elements such as sensor, circuit board, processor, communication module and battery.
Described horn 20 is used for supporting described Power Component 40 and making described Power Component 40 be distributed in institute with predetermined pattern
State around fuselage 10.In present embodiment, the quantity of described horn 20 is corresponding with the quantity of described Power Component 40, is four
Individual.
Being appreciated that in other implementations, the quantity of the quantity of described horn 20 and described Power Component 40 can
To differ.Such as, each described horn 20 can support two or more described Power Components 40, specifically, each
Can form two or more branches on individual described horn 20, each described branch can support a described Power Component
40.The most such as, each described horn 20 can not also include branch, as long as described horn 20 and described Power Component 40
Size allows, and each described horn 20 can also arrange multiple described Power Component 40.
Seeing also Fig. 2 and Fig. 3, described horn 20 is connected to described fuselage 10 sidepiece, and multiple described horn 20 is in spoke
Penetrating shape and be connected to 10 weeks sides of described fuselage, in present embodiment, between adjacent described horn 20, the angle at interval is identical.Each
Individual described horn 20 includes first paragraph 21, second segment 22.Described first paragraph 21 is connected to described fuselage 10, described second segment 22
The described Power Component 40 that support is corresponding.Described shock insulation part 30 is arranged between described first paragraph 21 and described second segment 22.Institute
Stating and separated by described shock insulation part 30 between first paragraph 21 and described second segment 22, in other words, described first paragraph 21 is with described second
Section 22 is not directly contacted with.
One end end face 210 deviating from described fuselage 10 of each described first paragraph 21 is convexly equipped with a limiting section 211, described
Limiting section 211 includes support member 2111 and stop part 2112.Described support member 2111 is for being formed at the institute of described first paragraph 21
Stating the projection of end face 210, in present embodiment, described support member 2111 is cylindrical projection, it will be understood that described support member
2111 can also be the projection of prism or other shapes.The cross sectional dimensions of described support member 2111 is less than described first paragraph 21
Described end face 210 size so that all sides protruding from described first paragraph 21 of at least part of described end face 210.Described block
Part 2112 is the flange of the end being formed at described support member 2111, and in present embodiment, described stop part 2112 is substantially vertical
Protruding from all sides of described support member 2111, described stop part 2112 is the flange that continuous print is circular, it will be understood that at it
In his embodiment, described stop part 2112 can also be discontinuous, and such as, described stop part 2112 can be that multiple arcuation is convex
Edge forms.
In present embodiment, described support member 2111 is formed in one with described stop part 2112, and described support member
2111 are formed in one with described first paragraph 21.It is appreciated that described support member 2111, described stop part 2112 and described
Can also distinguish molding for one section 21, then assemble with above-mentioned structure and form, above-mentioned connection can be connected together, glued even
Connect and welding etc., repeat the most one by one.
In present embodiment, described first paragraph 21 is hollow structure, and inside it, the inner space with described fuselage 10 is connected
Logical.
In present embodiment, described first paragraph 21 includes that multiple stitching section, multiple described stitching sections are spliced to form described
One section 21.Specifically, described first paragraph 21 includes the first stitching section 21a and the second stitching section 21b, described first stitching section
21a is spliced to form described first paragraph 21 with described second stitching section 21b is the most involutory.Described first stitching section 21a and described machine
The upper casing 11 of body 10 is one-body molded, and described second stitching section 21b is one-body molded with the lower casing 12 of described fuselage 10.Described upper casing 11
And described lower casing 12 mutually splices and fastens the monolithic case forming described fuselage 10.It is appreciated that described first stitching section 21a
With described second stitching section 21b can with use engaging, securing member be connected, gluing etc. mode be connected with each other.It is appreciated that described
Other stitching sections in addition to described first stitching section 21a and described second stitching section 21b can also be included for one section 21, no
Repeat again.
Described second segment 22 is hollow structure, and it is opening towards the end of described first paragraph 21.Described second segment 22
Including can the 3rd stitching section 22a and the 4th stitching section 22b of mutual involutory splicing.Described 3rd stitching section 22a includes
One arm 221 and the first installation portion 222 being connected with described first arm 221, described 4th stitching section 22b includes the second arm
Portion 223 and the second installation portion 224 being connected with described second arm 223.Spell with the described 4th at described 3rd stitching section 22a
After the portion 22b of connecing mutually is fastened and connected, described first arm 221 and described second arm 223 collectively form described horn 20
Overall arm 201, described first installation portion 222 and described second installation portion 224 collectively form the entirety of described horn 20
Installation portion 202.Described arm 201 can be connected with described first paragraph 21, and described arm 201 has certain length, so that right
The described Power Component 40 answered can be supported on pre-position.
In present embodiment, the length of described second segment 22 is more than the length of described first paragraph 21.
In present embodiment, described arm 201 is substantially in frustum-like shape, and described arm 201 is away from the one of described fuselage 10
The cross sectional dimensions of end is less than the cross sectional dimensions of the one end towards described first paragraph 21.The inner surface of described arm 201 is substantially
Tapered, the inside dimension of described arm 201 near the one of described first paragraph 21 be laterally away from the side of described fuselage 10 by
Tapered subtract.
The inner surface of described first arm 221 forms multiple first in the one end near described first paragraph 21 and snaps in projection
2211.In present embodiment, the described first quantity snapping in projection 2211 is two, and two described first snap in protruding 2211 phases
The most parallel and be spaced, specifically, described first snaps in protruding 2211 arranges along the length direction of described first arm 221.
In present embodiment, described first snaps in protruding 2211 is semi-annular shape projection.
Be appreciated that the embodiment at other, described first snap in the quantity of protruding 2211 be readily modified as one, three
Individual, other quantity such as four；It addition, at least one described first snaps in protruding 2211 and can also be made up of multistage arcuation projection.
The inner surface of described first arm 221 is also formed with the first connection post 2212, and described first connects post 2212 from institute
The surface stating the first arm 221 extends to described second arm 223, and described first connects post 2212 towards described second arm
The end face of 223 offers connecting hole 2212a.In present embodiment, the described first quantity connecting post 2212 is two, described company
Meeting hole 2212a is screwed hole.
Described first installation portion 222 is positioned at described first arm 221 and deviates from the end of described fuselage 10.Described first installs
Portion 222 offers perforation 2221, and described perforation 2221 can pass for the part-structure of described Power Component 40.
Described second arm 223 has the structure substantially similar with described first arm 221, and it includes and described first card
Enter protruding 2211 corresponding second and snap in projection (non-label) and corresponding with described first connection post 2212 second even
Connect post 2232.Described second snap in protruding and described first snap in protruding 2211 structure substantially similar, no longer describe in detail.Described
Two arms 223 offer corresponding to the described second through hole 2233 connecting post 2232, and described through hole 2233 is from described second arm
The outer surface of 223 is through to the described second connection post 2232 end face towards described first arm 221 of correspondence.
Described second installation portion 224 is positioned at described second arm 223 and deviates from the end of described fuselage 10.Described first installs
Portion 222 and the second installation portion 224 collectively form the mounting groove structure for installing Power Component 40.Described mounting groove structure and institute
State the internal connection of first paragraph 21.Being provided with fixed structure 2241 on described second installation portion 224, described fixed structure 2241 is used for
Fixing described Power Component 40.
Described shock insulation part 30 is used for the vibrations eliminating described Power Component 40 impact on described fuselage 10.Described shock insulation part
30 use elastomeric material to make, and alternatively, the material of described shock insulation part 30 can be flexible glue, rubber, silica gel etc..Described shock insulation part
30 substantially in sleeve-shaped, and it is internally formed set apertured 301.In present embodiment, described set apertured 301 is circular port, described set
The internal diameter of apertured 301 is suitable with the external diameter of described support member 2111, and the internal diameter of described set apertured 301 is less than described stop part
The external diameter of 2112.It is formed with abutting part 31 on all sides of described shock insulation part 30.In present embodiment, described abutting part 31 is many
The flange of individual all sides evagination relative to described shock insulation part 30, multiple described flanges are along the central shaft of described set apertured 301
Interval, direction is arranged.In present embodiment, the external diameter of described flange is different, and deviates from described fuselage along described shock insulation part 30
The direction of 10, the outside dimension of described flange is sequentially reduced.The amplitude of successively decreasing of the outside dimension of described flange and described arm 201
The tapering of inner surface suitable.Outside dimension farthest away from the flange of described fuselage 10 is more than the external diameter of described stop part 2112
Size.
In present embodiment, the quantity of described flange is three, the spacing distance between described flange and described first card
Entering protruding 2211 and described second, to snap in the thickness of projection suitable；Correspondingly, the thickness of described flange snaps in described first
The interval that the interval and described second of protruding 2211 snaps in projection is suitable.In other words, described flange can be with described first card
Enter protruding 2211 and described second snap in projection clamp mutually cooperation.
It is appreciated that the quantity of described flange can also do other changes, such as, four, five, six according to demand
Deng, the most described flange can also be overall one.
Referring to Fig. 4 to Fig. 6, during assembling, described shock insulation part 30 is sheathed on described support member 2111, described stop part
2112 can keep out the end deviating from described fuselage 10 in described shock insulation part 30, to prevent described shock insulation part 30 from departing from described support
On part 2111；Described 4th stitching section 22b is sheathed on described shock insulation part 30 from the lower section of described fuselage 10, and described second snaps in
Protruding and described shock insulation part 30 abutting part 31 mutually abuts cooperation, and specifically, described flange snaps in described second and snaps in projection
Between interval, described second snaps in projection snaps in the interval between described flange, near the described flange of described fuselage 10
Between described fuselage 10 and described 4th stitching section 22b；Described 3rd stitching section 22a is sheathed from the top of described fuselage 10
On described shock insulation part 30, described first snaps in protruding 2211 mutually abuts cooperation with the abutting part 31 of described shock insulation part 30, tool
Body ground, described flange snaps in described first and snaps in the interval between protruding 2211, and described first snaps in projection 2211 snaps in described
Interval between flange, the described flange near described fuselage 10 be positioned at described fuselage 10 and described 3rd stitching section 22a it
Between；Described 3rd stitching section 22a and described 4th stitching section 22b mutually fastens the described second segment 22 of composition, described second segment 22
Internal and described first paragraph 21 is connected, the electronic component in described fuselage 10 can by be arranged in described first paragraph 21 and
Conducting wire (not shown) in described second segment 22 electrically connects with described Power Component 40；Described first connects post 2212 and institute
Stating the second connection post 2232 to align, described 3rd stitching section 22a and described 4th stitching section 22b is mutual by connector 60
Fixing connecting, in present embodiment, described connector 60 is bolt, it is possible to is connected post 2212 with described first and carries out screw thread and join
Close, so that described horn 20 clamps described shock insulation part 30；Described shock insulation part 30 be positioned at described fuselage 10 and described horn 20 it
Between, it is possible to avoiding directly contacting between described fuselage 10 with described horn 20, the most described shock insulation part 30 can eliminate
From the vibrations of described horn 20 impact on described fuselage 10.
Referring again to Fig. 1, described Power Component 40 for providing the power of flight for described unmanned vehicle 100.Described
Power Component 40 includes motor 41 and propeller 42.Described motor 41 includes stator 411 and can be relative to described stator 411
The rotor 412 rotated.Specifically, incorporated by reference to Fig. 3, described stator 411 is fixed on second installation portion of described 4th stitching section 22b
On 224, described rotor 412 and the described stator of part 411 pass the perforation of first installation portion 222 of described 3rd stitching section 22a
2221。
In present embodiment, described motor 41 can be the motor of any type such as brushless electric machine, brush motor.
Described motor 41 can electrically connect with the electronic component (control like flying, power supply etc.) of described fuselage 10, it is achieved.
Described propeller 42 is connected on described rotor 412, and can be rotated by described rotation 412 and rotate.Described spiral shell
Rotation oar 42 can be collapsible oar.
Described foot rest 50 is the described unmanned vehicle 100 supporting construction when landing.Described foot rest 50 is connected to described machine
The bottom of body 10 and deviate from described fuselage 10 and extend preset distance, the quantity of described foot rest 50 is two.In one embodiment, institute
State foot rest 50 can adjust relative to the connection angle of described fuselage 10, when described unmanned vehicle 100 is in state of flight,
Described foot rest 50 can be packed up by the most described fuselage 10, to prevent described foot rest 50 from blocking the negative of carry below described fuselage 10
Carry (not shown), such as, sensor, camera, video camera etc..In another embodiment, described foot rest 50 either internally or externally sets
Being equipped with the antenna (not shown) of described unmanned vehicle 100, so, described antenna may be located remotely from the electronics unit in described fuselage 10
Part, it is to avoid the described electronic component interference to described antenna.
Described unmanned vehicle 100 uses described shock insulation part 30 to isolate described horn 20 and described fuselage 10, therefore institute
State shock insulation part 30 and can eliminate the vibrations impact on described fuselage 10 from described horn 20, it is to avoid the merit in described fuselage 10
Can module dysfunction or damage by described vibration influence.
Refer to Fig. 7, show the schematic diagram of this utility model the second embodiment unmanned vehicle 200.Described unmanned
Aircraft 200 has the structure similar to the unmanned vehicle 100 described in the first embodiment.Additionally, described unmanned vehicle
The length of the first paragraph 21 ' of the horn 20 ' of 200 is more than the length of described second segment 22 ', therefore compared to the first embodiment,
Described shock insulation part 30 ' is arranged closer to corresponding described Power Component 40 ', owing to arranging closer to described Power Component 40 ', and institute
The weight stating second segment 22 ' can reduce, and the most described second segment 22 ' and described Power Component 40 ' act on described shock insulation part
Diminishing of moment on 30 '.Therefore, the horn 20 ' of described unmanned vehicle 200 is not likely to produce shake.
Refer to Fig. 8, show the schematic diagram of the unmanned vehicle 300 of this utility model the 3rd embodiment.Described nothing
People's aircraft 300 has the structure similar with the unmanned vehicle 100 described in the first embodiment.Additionally, described unmanned flight
The shock insulation part 30 ' of device 300 ' be arranged at horn 20 ' ' and fuselage 10 ' ' between, described unmanned vehicle 300 is same it can be avoided that institute
' in functional module by described Power Component 40 ' ' vibration influence of stating fuselage 10 ' and dysfunction or damage.
Described shock insulation part 30 ' ' concrete structure and described shock insulation part 30 ' ' and described horn 20 ' ' between connection side
Formula can be identical with the shock insulation part 30 described in the first embodiment, is not described in detail.
It is understood that those skilled in the art also can do other change etc. in this utility model spirit is used in this reality
With novel design, without departing from technique effect of the present utility model.These are done according to this utility model spirit
Change, all should be included in this utility model claimed within the scope of.
Claims (29)
1. a frame for unmanned vehicle, including fuselage and the horn that is connected with described fuselage, described horn be provided with for
The installation portion of Power Component is installed, in described fuselage, is provided with the electric installation portion for installing electronic component, described electronic component
Can electrically connect with described Power Component, it is characterised in that: the frame of described unmanned vehicle also includes shock insulation part, described shock insulation
Part is located on described horn, and between described installation portion and described fuselage, to intercept the vibrations of described Power Component.
2. the frame of unmanned vehicle as claimed in claim 1, it is characterised in that: described horn includes first paragraph and second
Section, described first paragraph is connected with described fuselage, and described installation position is on described second segment, and described shock insulation part is arranged at described the
Between one section and second segment, to be spaced described first paragraph and described second segment.
3. the frame of unmanned vehicle as claimed in claim 2, it is characterised in that: described shock insulation part is sheathed on described first paragraph
On, described second segment is sheathed on described shock insulation.
4. the frame of unmanned vehicle as claimed in claim 2, it is characterised in that: the distal end faces of described first paragraph is convexly equipped with
One limiting section, described shock insulation part is arranged on described limiting section, and the periphery of described limiting section passes through described shock insulation part with described
Horn flexibly supports.
5. the frame of unmanned vehicle as claimed in claim 4, it is characterised in that: described limiting section includes support member and gear
Stop member, described support member is the projection of the described end face being formed at described first paragraph, and described stop part is for being formed at described support
The flange of the end of part, described shock insulation part is sheathed on described support member, described stop part keep out deviate from described shock insulation part described
The side of fuselage.
6. the frame of unmanned vehicle as claimed in claim 5, it is characterised in that: described stop part is relative to described support
Part week side protrude collar flange.
7. the frame of unmanned vehicle as claimed in claim 6, it is characterised in that: described stop part is that continuous print is circular convex
Edge；Or described stop part is that circular row forms by multiple arcuation flanges.
8. the frame of unmanned vehicle as claimed in claim 2, it is characterised in that: described first paragraph is hollow structure, and
Including multiple stitching sections, connection can be dismantled in the plurality of stitching section, to form described first paragraph.
9. the frame of unmanned vehicle as claimed in claim 8, it is characterised in that: described fuselage includes upper casing and with described
The lower casing of the involutory setting of upper casing；The stitching section of described first paragraph is two, the respectively first stitching section and the second stitching section, institute
Stating the first stitching section to be connected with described upper casing, described second stitching section is connected with described lower casing.
10. the frame of unmanned vehicle as claimed in claim 9, it is characterised in that: described first stitching section and described upper casing
One-body molded, described second stitching section is one-body molded with described lower casing.
The frame of 11. unmanned vehicles as claimed in claim 2, it is characterised in that: described second segment and described first paragraph phase
End even is opening, and the opening of described first paragraph is set on described shock insulation part.
The frame of 12. unmanned vehicles as claimed in claim 11, it is characterised in that: described shock insulation part and described second segment
Opening phase clamping；
And/or, described first paragraph is hollow structure, and described first paragraph is connected with the opening of described second segment.
The frame of 13. unmanned vehicles as claimed in claim 2, it is characterised in that: the length of described second segment is less than described
The length of first paragraph.
The frame of 14. unmanned vehicles as claimed in claim 2, it is characterised in that: described second segment includes arm and position
Deviate from the described installation portion of the end of described first paragraph in described second segment, described arm passes through described shock insulation part and described first
Duan Xianglian, described installation portion is used for installing and support described Power Component.
The frame of 15. unmanned vehicles as claimed in claim 14, it is characterised in that: described arm is hollow form, described arm
The inner surface in portion pushes against the outer peripheral edge of described shock insulation part.
The frame of 16. unmanned vehicles as claimed in claim 15, it is characterised in that: the inner surface of described arm is taper
Face, all sides of described shock insulation part are the taper surface suitable with the inner surface of described arm.
The frame of 17. unmanned vehicles as claimed in claim 15, it is characterised in that: the inner surface of described arm is formed with card
Entering projection, all sides of described shock insulation part are formed and snap in protruding suitable abutting part with described, described in snap in protruding and described
The mutual clamping of abutting part coordinates.
The frame of 18. unmanned vehicles as claimed in claim 17, it is characterised in that snap in protruding for multiple described in:, multiple
The described projection that snaps in is parallel to each other and is spaced, and described abutting part is the flange of multiple all sides evagination from described shock insulation part,
Described flange coordinates with the described projection mutually clamping that snaps in.
The frame of 19. unmanned vehicles as claimed in claim 18, it is characterised in that: near the described flange of described fuselage
It is flexibly supported between the end face of described first paragraph and the end face of described arm.
The frame of 20. unmanned vehicles as claimed in claim 17, it is characterised in that snap in protruding along described arm described in:
Length direction arrangement；
And/or, described in snap in projection to be semi-annular shape protruding.
The frame of 21. unmanned vehicles as claimed in claim 18, it is characterised in that: the external diameter of multiple described flanges the most not phase
With, and the direction of described fuselage is deviated from along described shock insulation part, the outside dimension of described flange is sequentially reduced, the external diameter of described flange
The amplitude of successively decreasing of size is suitable with the tapering of the inner surface of described arm.
The frame of 22. unmanned vehicles as claimed in claim 17, it is characterised in that: described second segment includes mutually detaining
Close connect the 3rd stitching section and the 4th stitching section, described 3rd stitching section include the first arm and with described first arm
The first installation portion being connected, described 4th stitching section includes the second arm and the second installation being connected with described second arm
Portion, after described 3rd stitching section and described 4th stitching section are mutually fastened and connected, described first arm and described second arm
Portion collectively forms described arm, described first installation portion and described second installation portion and collectively forms described installation portion.
The frame of 23. unmanned vehicles as claimed in claim 22, it is characterised in that: the inner surface of described first arm is formed
First snaps in projection, and the inner surface of described second arm forms second and snaps in projection, described first snap in protruding with described second
Snap in projection collectively form described in snap in projection.
The frame of 24. unmanned vehicles as claimed in claim 23, it is characterised in that: the inner surface also shape of described first arm
Becoming and have the first connection post, described first connects post extends to described second arm from the surface of described first arm, and described second
Arm includes connecting the second connection post that post is corresponding with described first, and described first arm and described second arm are by described
First connects post is connected cooperating fixing connection of post with described second.
The frame of 25. unmanned vehicles as claimed in claim 24, it is characterised in that: described first connects post towards described the
The end face of two arms offers connecting hole, and described second arm offers corresponding to the described second through hole connecting post, described logical
Hole is through to described the second of correspondence from the outer surface of described second arm and connects the post end face towards described first arm, described
Horn includes connector, and described connector is through described through hole and is fixedly connected in described connecting hole.
The frame of 26. unmanned vehicles as claimed in claim 2, it is characterised in that: described installation portion is for being located at described first
The mounting groove of one end deviating from described second segment of section, described mounting groove is for Power Component described in containing section.
The frame of 27. unmanned vehicles as claimed in claim 26, it is characterised in that: described first paragraph is equal with described second segment
For hollow structure and be interconnected, described mounting groove is connected with described second segment, so that the current supply line of described Power Component
Described first paragraph and described second segment can be passed.
The frame of 28. unmanned vehicles as claimed in claim 1, it is characterised in that: described shock insulation part is flexibly supported on described
Between horn and described fuselage and separate described horn and described fuselage.
29. 1 kinds of unmanned vehicles, including frame and Power Component, described frame is described in any one of claim 1～28
The frame of unmanned vehicle.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620516164.4U CN205837164U (en) | 2016-05-31 | 2016-05-31 | The frame of unmanned vehicle and unmanned vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620516164.4U CN205837164U (en) | 2016-05-31 | 2016-05-31 | The frame of unmanned vehicle and unmanned vehicle |
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| CN205837164U true CN205837164U (en) | 2016-12-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP7137885B1 (en) | 2022-03-30 | 2022-09-15 | 株式会社石川エナジーリサーチ | Manufacturing method of flight device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP7137885B1 (en) | 2022-03-30 | 2022-09-15 | 株式会社石川エナジーリサーチ | Manufacturing method of flight device |
| JP2023148302A (en) * | 2022-03-30 | 2023-10-13 | 株式会社石川エナジーリサーチ | Method of manufacturing flying device |
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