CN205633005U - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
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- CN205633005U CN205633005U CN201620427113.4U CN201620427113U CN205633005U CN 205633005 U CN205633005 U CN 205633005U CN 201620427113 U CN201620427113 U CN 201620427113U CN 205633005 U CN205633005 U CN 205633005U
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- wing
- bracing piece
- unmanned plane
- groove
- fuselage
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Abstract
The utility model discloses an unmanned aerial vehicle. Unmanned aerial vehicle includes: fuselage (1), be provided with actuating mechanism in fuselage (1), be provided with wing draw -in groove (11) on the surface of fuselage (1), aircraft nose (2), aircraft nose (2) with actuating mechanism drives the connection, be provided with screw (21) on aircraft nose (2), wing (3), wing (3) are including interconnect stiffener (31) and flexible airfoil (32), flexible airfoil (32) can be out of shape by the atress, wherein, actuating mechanism is used for the drive the screw, stiffener (31) are suitable for in order can the dismantlement mode setting up in wing draw -in groove (11). The utility model discloses an unmanned aerial vehicle's wing is flexible airfoil, when carrying, can dismantle the wing get off and folding shrink to reduce and carry the area.
Description
Technical field
This utility model relates to technical field of aerospace, particularly relates to a kind of unmanned plane.
Background technology
The fixed-wing unmanned plane of prior art carries and is difficult to, although some parts of some fixed-wing unmanned plane
Can remove and install, then carry the most relatively difficulty.
Wish that a kind of technical scheme overcomes or at least alleviates at least one drawbacks described above of prior art.
Utility model content
The purpose of this utility model is provide a kind of unmanned plane to overcome or at least alleviate prior art extremely
A few drawbacks described above.
For achieving the above object, this utility model provides a kind of unmanned plane, and described unmanned plane includes: fuselage,
It is provided with drive mechanism in described fuselage, the outer surface of described fuselage is provided with wing draw-in groove；Head, institute
State head and described drive mechanism drive connection, described head is provided with propeller；Wing, described wing
Including interconnective bracing piece and flexible aerofoil, described flexible aerofoil can stress deformation；Wherein, institute
State drive mechanism for driving described propeller；Described bracing piece is suitable to removably be arranged on described machine
In wing draw-in groove.
Preferably, described bracing piece includes first paragraph and second segment, described first paragraph and described second segment
Hinged.
Preferably, described first paragraph and described second segment in axial direction equal sized.
Preferably, described flexible aerofoil is removably connected with described bracing piece.
Preferably, described flexible aerofoil is made up of plastic sheeting or braided material.
Preferably, described flexible aerofoil being provided with receiving opening, described bracing piece is contained in described receiving
In through hole.
Preferably, the wing draw-in groove on the outer surface of described fuselage is provided with multiple；The number of described bracing piece
Measure corresponding with the quantity of described wing draw-in groove；Each described bracing piece is suitable to be arranged on a described wing card
In groove.
The wing of unmanned plane of the present utility model is flexible aerofoil, when carrying, it is possible under being dismantled by wing
Come and folding shrinking, thus reduce and carry area.
Accompanying drawing explanation
Fig. 1 is the STRUCTURE DECOMPOSITION figure of the unmanned plane according to this utility model one embodiment.
Reference
| 1 | Fuselage | 3 | Wing |
| 11 | Wing draw-in groove | 31 | Bracing piece |
| 2 | Head | 32 | Flexible aerofoil |
| 21 | Propeller |
Detailed description of the invention
Clearer for the purpose making this utility model implement, technical scheme and advantage, below in conjunction with this
Accompanying drawing in utility model embodiment, is carried out in further detail the technical scheme in this utility model embodiment
Description.In the accompanying drawings, the most same or similar label represents same or similar element or tool
There is the element of same or like function.Described embodiment is a part of embodiment of this utility model, and
It is not all, of embodiment.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to be used for
Explain this utility model, and it is not intended that to restriction of the present utility model.Based in this utility model
Embodiment, those of ordinary skill in the art obtained under not making creative work premise all its
His embodiment, broadly falls into the scope of this utility model protection.Below in conjunction with the accompanying drawings to reality of the present utility model
Execute example to be described in detail.
In description of the present utility model, it is to be understood that term " " center ", " longitudinally ",
" laterally ", "front", "rear", "left", "right", " vertically ", " level ",
" push up ", " end " " interior ", the orientation of the instruction such as " outward " or position relationship are based on shown in the drawings
Orientation or position relationship, be for only for ease of description this utility model and simplify describe rather than instruction or
The hint device of indication or element must have specific orientation, with specific azimuth configuration and operation, because of
This is it is not intended that restriction to this utility model protection domain.
Fig. 1 is the STRUCTURE DECOMPOSITION figure of the unmanned plane according to this utility model one embodiment.
Unmanned plane as shown in Figure 1 includes fuselage 1, head 2 and wing 3, is provided with and drives in fuselage 1
Motivation structure, the outer surface of fuselage 1 is provided with wing draw-in groove 11；Head 2 and drive mechanism drive connection,
Propeller 21 it is provided with on head 2；Wing 3 includes interconnective bracing piece 31 and flexible aerofoil 32,
Flexible aerofoil 32 can stress deformation；Wherein, drive mechanism is used for driving propeller；Bracing piece 31 is suitable to
Removably it is arranged in wing draw-in groove 11.
In an alternative embodiment, bracing piece includes first paragraph and second segment, first paragraph and second segment
Hinged.Using this structure, bracing piece can fold, thus reduce whole unmanned plane further and carrying
Size in journey.
Advantageously, first paragraph and second segment in axial direction equal sized.So, can guarantee that first
The position of centre of gravity of section is identical with the position of centre of gravity of second segment.
In the present embodiment, flexible aerofoil 32 is removably connected with bracing piece 31.Use this
Structure, it is possible to whole wing is split again, further facilitates and carry.
In the present embodiment, flexible aerofoil is made up of plastic sheeting.It is understood that flexible aerofoil is also
Other materials can be used to support, such as, be made up of braided material.
In an alternative embodiment, flexible aerofoil being provided with receiving opening, bracing piece is contained in receiving
In through hole.It is understood that other sides of removably connecting can also be used between flexible aerofoil and bracing piece
Formula.Such as, by being provided with draw-in groove on flexible aerofoil, bracing piece is provided with and the holding section of card slot fit,
So that both connect.
In the present embodiment, the wing draw-in groove 11 on the outer surface of fuselage 1 is provided with multiple；Bracing piece 31
Quantity corresponding with the quantity of wing draw-in groove 11；Each bracing piece 31 is suitable to be arranged on a wing draw-in groove
In 11.It is understood that the quantity of wing draw-in groove is the most, fuselage is the most firm with the connection of wing.
Last it is noted that above example is only in order to illustrate the technical solution of the utility model, and
Non-to its restriction.Although this utility model being described in detail with reference to previous embodiment, this area
Those of ordinary skill it is understood that the technical scheme described in foregoing embodiments still can be entered by it
Row amendment, or wherein portion of techniques feature is carried out equivalent；And these amendments or replacement, and
The essence not making appropriate technical solution departs from the spirit and scope of this utility model each embodiment technical scheme.
Claims (7)
1. a unmanned plane, it is characterised in that described unmanned plane includes:
Fuselage (1), is provided with drive mechanism, the outer surface of described fuselage (1) in described fuselage (1)
On be provided with wing draw-in groove (11)；
Head (2), described head (2) and described drive mechanism drive connection, on described head (2)
It is provided with propeller (21)；
Wing (3), described wing (3) includes interconnective bracing piece (31) and flexible aerofoil (32),
Described flexible aerofoil (32) can stress deformation；Wherein,
Described drive mechanism is used for driving described propeller；Described bracing piece (31) is suitable to detachable side
Formula is arranged in described wing draw-in groove (11).
2. unmanned plane as claimed in claim 1, it is characterised in that described bracing piece include first paragraph with
And second segment, described first paragraph is hinged with described second segment.
3. unmanned plane as claimed in claim 2, it is characterised in that described first paragraph and described second segment
In axial direction equal sized.
4. unmanned plane as claimed in claim 3, it is characterised in that described flexible aerofoil (32) and institute
State bracing piece (31) removably to connect.
5. unmanned plane as claimed in claim 4, it is characterised in that described flexible aerofoil is by plastic sheeting
Or braided material makes.
6. unmanned plane as claimed in claim 4, it is characterised in that be provided with appearance on described flexible aerofoil
Receiving through hole, described bracing piece is contained in described receiving opening.
7. unmanned plane as claimed in claim 5, it is characterised in that the outer surface of described fuselage (1)
On wing draw-in groove (11) be provided with multiple；The quantity of described bracing piece (31) and described wing draw-in groove (11)
Quantity corresponding；
Each described bracing piece (31) is suitable to be arranged in a described wing draw-in groove (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620427113.4U CN205633005U (en) | 2016-05-12 | 2016-05-12 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620427113.4U CN205633005U (en) | 2016-05-12 | 2016-05-12 | Unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205633005U true CN205633005U (en) | 2016-10-12 |
Family
ID=57059146
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620427113.4U Active CN205633005U (en) | 2016-05-12 | 2016-05-12 | Unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205633005U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106672206A (en) * | 2016-12-23 | 2017-05-17 | 南京航空航天大学 | 180-degree folded wing unfolding mechanism |
-
2016
- 2016-05-12 CN CN201620427113.4U patent/CN205633005U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106672206A (en) * | 2016-12-23 | 2017-05-17 | 南京航空航天大学 | 180-degree folded wing unfolding mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |