CN109572991A - A kind of unmanned vehicle and its wing components - Google Patents
A kind of unmanned vehicle and its wing components Download PDFInfo
- Publication number
- CN109572991A CN109572991A CN201811622482.9A CN201811622482A CN109572991A CN 109572991 A CN109572991 A CN 109572991A CN 201811622482 A CN201811622482 A CN 201811622482A CN 109572991 A CN109572991 A CN 109572991A
- Authority
- CN
- China
- Prior art keywords
- locking cylinder
- wing
- rotary locking
- rotation axis
- wing components
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
Abstract
The present invention relates to unmanned vehicle field, a kind of unmanned vehicle and its wing components are disclosed, wherein the wing components are used to be installed on the fuselage of unmanned vehicle, the wing components include: wing；And rotary locking cylinder, the rotary locking cylinder have rotation axis, one end of the rotary locking cylinder is installed on the wing, and the other end of the rotary locking cylinder is for being installed on the fuselage；Wherein, the rotary locking cylinder can be rotated around the rotation axis relative to the wing, so that the other end of the rotary locking cylinder is mutually dismantled with the fuselage.It by installing the rotary locking cylinder on the wing, is mutually dismantled by rotating the rotary locking cylinder with the fuselage, will be disassembled with wing slave with facilitating.
Description
[technical field]
The present invention relates to unmanned vehicle technical field more particularly to a kind of unmanned vehicles and its wing components.
[background technique]
Unmanned vehicle (Unmanned Aerial Vehicle, UAV) due to maneuverability, rapid reaction, nobody
It drives, operation requires low advantage and is widely used.
According to the difference of application scenarios, different types of wing is needed.However it is mounted on the appearance of the wing on unmanned vehicle
Easy to damage, unmanned vehicle, which continues to fly, after wing damage is likely to cause unmanned vehicle air crash.
[summary of the invention]
In view of this, the embodiment of the present invention provides a kind of unmanned vehicle and its wing components, to facilitate wing slave
It disassembles with it.
In order to solve the above-mentioned technical problem, the embodiment of the present invention the following technical schemes are provided:
On the one hand, a kind of wing components are provided, for being installed on the fuselage of unmanned vehicle, the wing components include:
Wing；And rotary locking cylinder, the rotary locking cylinder have rotation axis, one end of the rotary locking cylinder is installed on the wing,
The other end of the rotary locking cylinder is for being installed on the fuselage；Wherein, the rotary locking cylinder can be opposite around the rotation axis
It is rotated in the wing, so that the other end of the rotary locking cylinder is mutually dismantled with the fuselage.
In some embodiments, the wing has two opposite aerofoils, and between described two aerofoils
Mounting surface；Mounting groove is provided in the wing, the mounting groove is equipped with the first opening, the rotary locking cylinder in the mounting surface
One end be installed on the mounting groove, the other end of the rotary locking cylinder is stretched out from first opening.
In some embodiments, the mounting groove is provided with the second opening at least one of described two aerofoils；Institute
Stating wing components further includes driving idler wheel, and the center line of the driving idler wheel coincides with the rotation axis, the driving rolling
Wheel connects one end of the rotary locking cylinder, and the driving runner is revealed in second opening.
In some embodiments, in both one end of the driving idler wheel and the rotary locking cylinder, one of setting
There is fixing axle, another is provided with fixation hole；The fixing axle is matched with the fixation hole so that the driving idler wheel with
One end of the rotary locking cylinder is mutually fixed.
In some embodiments, described two aerofoils are each provided with second opening, two second openings
Relatively；The driving idler wheel is revealed in two second openings.
In some embodiments, the lateral cross-sectional dimension of the driving idler wheel is greater than the transversal cross-section ruler of the rotary locking cylinder
It is very little, so that prominent second opening of the driving idler wheel.
In some embodiments, the cell wall of the mounting groove is extended with support plate；The support plate is provided with rotating hole, institute
Rotating hole is stated along the rotation axis through the support plate；The other end of the rotary locking cylinder is matched with the rotating hole,
So that the rotary locking cylinder can be rotated around the rotation axis relative to the wing.
In some embodiments, the rotary locking cylinder includes the limiting section being sequentially connected, rotation section and fixed part；It is described
The cross sectional dimensions of the cross sectional dimensions of limiting section and the fixed part is all larger than the cross sectional dimensions of the rotation section, the rotation
Turn hole is matched with the rotation section, and the limiting section is connected to the two sides of the support plate with the fixed part respectively, so that
Obtaining the rotary locking cylinder cannot move along the rotation axis relative to the wing.
In some embodiments, the wing components further include elastic spacing one, and the elastic spacing one is for providing resistance
The resistance for hindering the rotary locking cylinder to rotate around the rotation axis relative to the wing.
In some embodiments, the elastic spacing one includes connecting rod and the gear-stopping bar for being connected to the connecting rod；
The rotary locking cylinder includes confined planes, and the confined planes are arranged backwards to the rotation axis, and two confined planes pass through rib portion
It is connected；When the rotary locking cylinder is rotated around the rotation axis relative to the wing, the rib portion can extrude the backstop
Bar simultaneously bends the gear-stopping bar relative to the connecting rod.
In some embodiments, the quantity of the gear-stopping bar is two；Two gear-stopping bars are opposite, the rotary locking cylinder
Between two gear-stopping bars.
In some embodiments, the quantity of the confined planes is four；Four confined planes are around the rotation axis point
Cloth.
In some embodiments, the rotary locking cylinder includes axle portion and the limiting section that is connected with the axle portion；The axis
The center line in portion coincides with the rotation axis, and the limiting section has at least one end along the side perpendicular to the rotation axis
To protruding from the axle portion.
In some embodiments, the limiting section has the both ends extended in the opposite direction, and the both ends of the limiting section are each
The axle portion is protruded from along the direction perpendicular to the rotation axis.
In some embodiments, the rotary locking cylinder includes stud portion；The center line in the stud portion and the rotary shaft
Line coincides, and the stud portion with the fuselage for being threadedly coupled.
On the other hand, a kind of unmanned vehicle is provided, the unmanned vehicle includes: fuselage；And with the fuselage
The wing components as described above of connection.
In some embodiments, the fuselage is provided with lockhole, and the other end of the rotary locking cylinder passes through the lockhole.
Compared with prior art, in the unmanned vehicle of the embodiment of the present invention and its wing components, wing components are used
In the fuselage for being installed on unmanned vehicle, the wing components include: wing；And rotary locking cylinder, the rotary locking cylinder have
Rotation axis, one end of the rotary locking cylinder are installed on the wing, and the other end of the rotary locking cylinder is described for being installed on
Fuselage, the rotary locking cylinder can be rotated around the rotation axis relative to the wing, so that the rotary locking cylinder is another
It is mutually dismantled with the fuselage at end.By installing the rotary locking cylinder on the wing, by rotating the rotary locking cylinder and institute
It states fuselage mutually to dismantle, will be disassembled with wing slave with facilitating.
[Detailed description of the invention]
One or more embodiments are illustrated by corresponding attached drawing, these exemplary illustrations not structure
The restriction of pairs of embodiment, the element with same reference numbers label is expressed as similar element in attached drawing, unless there are special
It declares, composition does not limit the figure in attached drawing.
Fig. 1 is a kind of perspective view of present invention unmanned vehicle that wherein an embodiment provides；
Fig. 2 is enlarged drawing at A shown in FIG. 1；
Fig. 3 is the plan view of the lockhole of unmanned vehicle shown in FIG. 1；
Fig. 4 is the lock core, elastic spacing one and the installation diagram for driving idler wheel of unmanned vehicle shown in FIG. 1；
Fig. 5 is the installation diagram of lock core shown in Fig. 4, elastic spacing one and driving idler wheel in another angle；
Fig. 6 is the fuselage of unmanned vehicle shown in FIG. 1 and the cross-sectional view of wing components junction；
Fig. 7 is the cross-sectional view of fuselage shown in fig. 6 and wing components junction in another state；
Fig. 8 is the limiting section of wing components shown in fig. 6 and the cross-sectional view of elastic spacing one；
Fig. 9 is the cross-sectional view of limiting section shown in Fig. 8 and elastic spacing one in another angle.
[specific embodiment]
To facilitate the understanding of the present invention, with reference to the accompanying drawings and detailed description, the present invention is carried out in more detail
It is bright.It should be noted that be expressed " being fixed on " another element when element, it can directly on the other element or
There may be one or more elements placed in the middle therebetween.When an element is expressed " connection " another element, it be can be directly
It is connected to another element in succession or there may be one or more elements placed in the middle therebetween.Term used in this specification
"vertical", "horizontal", "left" and "right", "inner", "outside" and similar statement are for illustrative purposes only.
Unless otherwise defined, technical and scientific term all used in this specification is led with technology of the invention is belonged to
The normally understood meaning of the technical staff in domain is identical.It is specific to be intended merely to description for used term in the description of the invention
Embodiment purpose, be not intended to limitation the present invention.Term "and/or" used in this specification includes one or more
Any and all combinations of relevant listed item.
Fig. 1 and Fig. 2 are please referred to, wherein an embodiment provides a kind of unmanned vehicle 500, including wing components to the present invention
100, fuselage 200, Power Component 300 and undercarriage 400.The wing components 100 are mounted on institute with the undercarriage 300
Fuselage 200 is stated, the Power Component 300 is installed on the wing components 100.
It include the control circuit component being made of electronic components such as MCU in the fuselage 200, the control circuit component packet
Multiple control modules are included, e.g., for controlling the Power Component work to control the flight of the unmanned vehicle flight attitude
Control module, for the locating module for the unmanned vehicle that navigates, and for handling ring acquired in related airborne equipment
The data processing module etc. of border information.The embodiment of the present invention for ease of description, attached drawing only show related to the embodiment of the present invention
Component.
The fuselage 200 has the first surface 201 towards the wing components 100 and the backwards to the wing components
Two surfaces 202, the fuselage 200 are provided with lockhole 203, and the lockhole 203 is through to described second from the first surface 201
Surface 202.
Also referring to Fig. 3, the lockhole 203 is irregularly-shaped hole namely the lockhole 203 is non-circular hole, for example, diamond shape
Hole, square hole, zigzag hole etc..
The lockhole 203 includes interconnected axis hole 204 and avoid holes 205.The axis hole 204 and the avoid holes
205 are through to the second surface 202 from the first surface 201.
Referring to Figure 4 together to Fig. 7, the wing components 100 include wing 10, and rotary locking cylinder 20 drives idler wheel 30, with
And limit elastic component 40.
The rotary locking cylinder 20 has rotation axis O, and the center line of the rotation axis O and the axis hole 204 coincide,
One end of the rotary locking cylinder 20 is installed on the wing 10, and the other end of the rotary locking cylinder 20 is installed on the fuselage 200
Lockhole 203, the rotary locking cylinder 20 can be rotated around the rotation axis O relative to the wing 10, so that the rotation
The other end of lock core 20 and 203 phase of lockhole of the fuselage 200 are dismantled.
The driving idler wheel 30 is installed on one end of the rotary locking cylinder 20, and the driving idler wheel 30 is for driving the rotation
Rotation cores 20 are rotated around the rotation axis O relative to the wing 10.In one embodiment, user is dynamic described with hand push
Idler wheel 30 is driven to rotate, so that rotary locking cylinder 20 be driven to rotate.It in another embodiment, can be by described in motor driven
Idler wheel 30 is driven to rotate, so that rotary locking cylinder 20 be driven to rotate.
The elastic spacing one 40 is installed on the wing 10, when the rotary locking cylinder 20 is opposite around the rotation axis O
When wing 10 rotates, the elastic spacing one 40 is used to provide the resistance for hindering the rotary locking cylinder O rotation.
The expansion direction of the wing 10 is basically parallel to the rotation axis O, and the wing 10 has opposite two
Aerofoil 11, and the mounting surface 12 between described two aerofoils 11.
Described two aerofoils 11 namely top airfoil and lower aerofoil, in 500 flight of unmanned vehicle, the wing
10 cross air, and the side of the top airfoil direction and the side of the lower aerofoil direction have air pressure difference, so that in institute
State the lift for generating on wing 10 and making 100 floating of unmanned vehicle.
The wing 10 is provided with mounting groove 13, and the mounting groove 13 offers the first opening on the mounting surface 12
14, the mounting groove 13 is each provided with the number of one second opening 15 namely second opening 15 in described two aerofoils 11
Amount is 2, and two second openings 15 are opposite.One end of the rotary locking cylinder 20 is installed in the mounting groove 13, the rotation
The other end of rotation cores 20 is stretched out from first opening 14.
The driving idler wheel 30 is located in the mounting groove 13, and the driving idler wheel 30 is revealed in two second openings
15.The driving idler wheel 30 of two second openings 15 can be revealed in by stirring, driving is located at the rotation in the mounting groove 13
Rotation cores 20 are rotated synchronously with the driving idler wheel 30.
The cross sectional dimensions of the driving idler wheel 30 is greater than the cross sectional dimensions of the rotary locking cylinder 20, so that the driving
Prominent two, idler wheel 30 second openings 15.It should be noted that so-called cross section normal direction is in the rotation axis O.
It is understood that according to the actual situation, the quantity of second opening 15 is not limited to two, described second
The quantity of opening 15 can also be with only one, as long as at least one of described two aerofoils 11 are provided with second opening 15
?.
In the present embodiment, the driving idler wheel 30 is provided with the fixation hole 31 along rotation axis O setting, the rotation
Rotation cores 20 are provided with the fixing axle 21 along rotation axis O setting, the fixing axle 21 and the fixed company of the fixation hole 31
It connects.It is understood that according to the actual situation, on the one hand, the position of the fixing axle 21 and the fixation hole 31 can be mutual
It changes namely the fixing axle 21 is set to the driving idler wheel 30, meanwhile, the fixation hole 31 is set to the rotary locking cylinder
20, therefore, as long as one in the driving idler wheel 30 and the rotary locking cylinder 20 is provided with the fixing axle 21, the driving
Another in idler wheel 20 and the rotary locking cylinder 30 is provided with the fixation hole 31.On the other hand, the driving rolling
Wheel 20 is not limited in being fixedly connected by the fixing axle 21 with the fixation hole 31 with the rotary locking cylinder 30, it is some its
In his embodiment, the driving idler wheel 30 is integrally formed with the rotary locking cylinder 20.
The cell wall of the mounting groove 13 is extended with support plate 16, and the support plate 16 is provided with rotating hole 17, the rotation
Hole 17 is matched with the rotary locking cylinder 20, so that the rotary locking cylinder 20 can be around the rotation axis O relative to the machine
The wing 10 rotates.
The rotary locking cylinder 20 includes the lock section 22 being sequentially connected, axle portion 23, limiting section 24, rotation section 25, fixed part 26
And the fixing axle 21.
The lock section 22 is whole in a rectangular parallelepiped shape, and the both ends of the lock section 22 are respectively along the side perpendicular to the rotation axis O
To protruding from the axle portion 23, it is to be understood that according to the actual situation, the lock section 22 is simultaneously not only limited to both ends respectively along vertical
In the prominent axle portion 23 in the direction of the rotation axis O, for example, one end of the lock section 22 is along perpendicular to the rotation axis
The direction of O protrudes from the axle portion 23, in another example, three ends of the lock section 22 are respectively along the direction perpendicular to the rotation axis O
Described axle portion 23, etc. is protruded from, as long as the lock section 22 has at least one end prominent along the direction perpendicular to the rotation axis O
For the axle portion 23.
The whole axle portion 23 is in cylindrical shape, and the center line of the axle portion 23 coincides with the rotation axis O.
Fig. 8 and Fig. 9 are please referred to, the whole limiting section 24 is in quadrangular, and there are four confined planes for the tool of limiting section 24
240, four confined planes 240 are distributed around the rotation axis O, two of arbitrary neighborhood in four confined planes 240
Between have rib portion 241.It is understood that according to the actual situation, the quantity of the confined planes 240 is not limited in four,
For example, the quantity of the confined planes 240 is two, three or four etc., as long as the quantity of the confined planes 240 is at least two
It is a, and there is a rib portion 241 between two confined planes 240.
The whole rotation section 25 is in cylindrical shape, and the center line of the rotation section 25 coincides with the rotation axis O,
The cross sectional dimensions of the rotation section 25 is less than the cross sectional dimensions of the limiting section 24, also, the rotation section 25 is transversal
Face size is less than the cross sectional dimensions of the fixed part 26.
The rotating hole 17 is matched with the rotation section 25, and the limiting section 24 is connected to respectively with the fixed part 26
The two sides of the support plate 16, so that the rotary locking cylinder 20 can be rotated around the rotation axis O relative to the wing 10,
And it cannot be moved along the rotation axis O relative to the wing 10.
The mounting surface 12 of the wing 10 and the first surface 201 of the fuselage 200 offset.
The axle portion 23 passes through the lockhole 203, and the axle portion 23 is matched with the axis hole 204 of the lockhole 203,
So that the rotary locking cylinder 20 can be rotated around the rotation axis O relative to the fuselage 200.
The both ends of the prominent axle portion 23 in the lock section 22 are connected to the second surface 202, so that the wing
10 is fixed on the direction along the rotation axis O with the fuselage 200.
When the rotary locking cylinder 20 is rotated around the rotation axis O relative to the fuselage 200, the lock section 22 is prominent
Both ends can be directed at the avoid holes 205 so that the both ends of the lock section 22 can along the rotation axis O pass through the evacuation
Hole 205 namely the rotary locking cylinder 20 and 203 phase of lockhole of the fuselage 200 are dismantled.
Further, in the present embodiment, the quantity of the rotary locking cylinder 20 is at least two, two rotary locking cylinders
20 rotation axis O is parallel to each other, so that the wing 10 and the fuselage 200 are relatively unrotatable.Some other
In embodiment, in the mounting surface 12 of the wing 10 and 201 the two of first surface of the fuselage 200, one is provided with calmly
Position pin (not shown), another is provided with location hole (not shown), by the cooperation of positioning pin and location hole, so that the machine
The wing 10 and the fuselage 200 are relatively unrotatable.
In some other embodiments, the lockhole 203 is threaded hole, the lock section 22 of the rotary locking cylinder 20 and axle portion
23 are substituted for stud portion 26, and the center line in the stud portion 26 coincides with the rotation axis O, the stud portion 26 with it is described
Lockhole is mutually threadedly engaged.
The elastic spacing one 40 is installed on the cell wall of the mounting groove 13, and the elastic spacing one 40 includes opposite two
A gear-stopping bar 41, and the connecting rod 42 being connected between described two gear-stopping bars 41, described two gear-stopping bars 41 can distinguish phase
The connecting rod 42 is flexibly bent, the limiting section 24 is between described two gear-stopping bars 41.
When the rotary locking cylinder 20 is rotated around the rotation axis O relative to the wing 10, as shown in figure 9, described
The rib portion 241 of limiting section 24 can extrude the gear-stopping bar 41 and bend the gear-stopping bar 41, and the bending of gear-stopping bar 41 is to mention
For the resistance for hindering the rotary locking cylinder 20 to rotate.
When the rotary locking cylinder 20 is rotated around the rotation axis O relative to the wing 10, described two gear-stopping bars
41 can offset with the two of them in four confined planes 240 respectively, so that the rotary locking cylinder 20 can be around the rotation
It is fixed relative to the wing 10 on the direction of axes O, it can avoid the rotary locking cylinder 20 and voluntarily turn relative to the wing 10
It is dynamic.
Further, when the rotary locking cylinder 20 is rotated around the rotation axis O relative to the wing 10, and it is described
When the both ends of the prominent axis body 23 in lock section 22 are directed at the avoid holes 205, described two gear-stopping bars 41 respectively with described four
Two of them in confined planes 240 offset, so that the both ends of the prominent axle portion 23 in the lock section 22 are convenient to alignment institute
State avoid holes 205.
Compared with prior art, a kind of unmanned vehicle 500 and its wing components 100 provided by the invention, wherein institute
Wing components 100 are stated for being installed on the fuselage 200 of the unmanned vehicle 500, described in installing on the wing 10
Rotary locking cylinder 20 is dismantled by rotating the rotary locking cylinder 20 with 200 phase of fuselage, to facilitate the wing components 100
It is disassembled from the fuselage 200.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；At this
It under the thinking of invention, can also be combined between the technical characteristic in above embodiments or different embodiment, step can be with
It is realized with random order, and there are many other variations of different aspect present invention as described above, for simplicity, they do not have
Have and is provided in details；Although the present invention is described in detail referring to the foregoing embodiments, the ordinary skill people of this field
Member is it is understood that it is still possible to modify the technical solutions described in the foregoing embodiments, or to part of skill
Art feature is equivalently replaced；And these are modified or replaceed, each reality of the present invention that it does not separate the essence of the corresponding technical solution
Apply the range of a technical solution.
Claims (17)
1. a kind of wing components, for being installed on the fuselage of unmanned vehicle, which is characterized in that the wing components include:
Wing；And
Rotary locking cylinder, the rotary locking cylinder have rotation axis, and one end of the rotary locking cylinder is installed on the wing, the rotation
The other end of rotation cores is for being installed on the fuselage；
Wherein, the rotary locking cylinder can be rotated around the rotation axis relative to the wing, so that the rotary locking cylinder
The other end is mutually dismantled with the fuselage.
2. wing components according to claim 1, which is characterized in that the wing has two opposite aerofoils, and
Mounting surface between described two aerofoils；
Mounting groove is provided in the wing, the mounting groove is equipped with the first opening in the mounting surface, the rotary locking cylinder
One end is installed on the mounting groove, and the other end of the rotary locking cylinder is stretched out from first opening.
3. wing components according to claim 2, which is characterized in that the mounting groove in described two aerofoils at least
One is provided with the second opening；
The wing components further include driving idler wheel, and the center line of the driving idler wheel coincides with the rotation axis, described
Driving idler wheel connects one end of the rotary locking cylinder, and the driving runner is revealed in second opening.
4. wing components according to claim 3, which is characterized in that in the driving idler wheel and the one of the rotary locking cylinder
It holds in the two, one of them is provided with fixing axle, another is provided with fixation hole；
The fixing axle is matched with the fixation hole, so that one end of the driving idler wheel and the rotary locking cylinder is mutually solid
It is fixed.
5. wing components according to claim 3 or 4, which is characterized in that described two aerofoils are each provided with described in one
Second opening, two second openings are opposite；
The driving idler wheel is revealed in two second openings.
6. wing components according to claim 3 or 4, which is characterized in that the lateral cross-sectional dimension of the driving idler wheel is big
In the lateral cross-sectional dimension of the rotary locking cylinder, so that prominent second opening of the driving idler wheel.
7. according to the described in any item wing components of claim 2 to 4, which is characterized in that the cell wall of the mounting groove is extended with
Support plate；
The support plate is provided with rotating hole, and the rotating hole runs through the support plate along the rotation axis；
The other end of the rotary locking cylinder is matched with the rotating hole, so that the rotary locking cylinder can be around the rotation axis phase
The wing is rotated.
8. wing components according to claim 7, which is characterized in that the rotary locking cylinder includes the limit being sequentially connected
Portion, rotation section and fixed part；
The cross sectional dimensions of the cross sectional dimensions of the limiting section and the fixed part is all larger than the cross section ruler of the rotation section
Very little, the rotating hole is matched with the rotation section, and the limiting section and the fixed part are connected to the support plate respectively
Two sides, so that the rotary locking cylinder cannot be moved along the rotation axis relative to the wing.
9. wing components according to any one of claims 1 to 4, which is characterized in that the wing components further include elasticity
Locating part, the elastic spacing one hinder the rotary locking cylinder to rotate around the rotation axis relative to the wing for providing
Resistance.
10. wing components according to claim 9, which is characterized in that the elastic spacing one includes connecting rod and company
It is connected to the gear-stopping bar of the connecting rod；
The rotary locking cylinder includes confined planes, and the confined planes are arranged backwards to the rotation axis, and two confined planes pass through
Rib portion is connected；
When the rotary locking cylinder is rotated around the rotation axis relative to the wing, the rib portion can extrude the gear-stopping bar
And bend the gear-stopping bar relative to the connecting rod.
11. wing components according to claim 10, which is characterized in that the quantity of the gear-stopping bar is two；
Two gear-stopping bars are opposite, and the rotary locking cylinder is located between two gear-stopping bars.
12. wing components according to claim 10, which is characterized in that the quantity of the confined planes is four；
Four confined planes are around the rotary axis distribution.
13. wing components according to any one of claims 1 to 4, which is characterized in that the rotary locking cylinder include axle portion with
And the limiting section being connected with the axle portion；
The center line of the axle portion coincides with the rotation axis, and the limiting section has at least one end along perpendicular to the rotation
The direction of shaft axis protrudes from the axle portion.
14. wing components according to claim 13, which is characterized in that the limiting section has to be extended in the opposite direction
The both ends at both ends, the limiting section respectively protrude from the axle portion along the direction perpendicular to the rotation axis.
15. wing components according to any one of claims 1 to 4, which is characterized in that the rotary locking cylinder includes stud
Portion；
The center line in the stud portion coincides with the rotation axis, and the stud portion with the fuselage for being threadedly coupled.
16. a kind of unmanned vehicle, which is characterized in that the unmanned vehicle includes:
Fuselage；And
Connect with the fuselage such as the described in any item wing components of claim 1 to 15.
17. unmanned vehicle according to claim 16, which is characterized in that the fuselage is provided with lockhole, the rotation
The other end of lock core passes through the lockhole.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811622482.9A CN109572991A (en) | 2018-12-28 | 2018-12-28 | A kind of unmanned vehicle and its wing components |
| PCT/CN2019/107550 WO2020134235A1 (en) | 2018-12-28 | 2019-09-24 | Unmanned aerial vehicle and wing assembly thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811622482.9A CN109572991A (en) | 2018-12-28 | 2018-12-28 | A kind of unmanned vehicle and its wing components |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109572991A true CN109572991A (en) | 2019-04-05 |
Family
ID=65933360
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811622482.9A Pending CN109572991A (en) | 2018-12-28 | 2018-12-28 | A kind of unmanned vehicle and its wing components |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN109572991A (en) |
| WO (1) | WO2020134235A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020134235A1 (en) * | 2018-12-28 | 2020-07-02 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle and wing assembly thereof |
| WO2021043336A3 (en) * | 2019-09-05 | 2021-04-22 | 深圳市道通智能航空技术股份有限公司 | Wing detachment assembly and aircraft |
| WO2021083152A1 (en) * | 2019-10-28 | 2021-05-06 | 深圳市道通智能航空技术股份有限公司 | Quick-release structure and aircraft |
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| WO2020134235A1 (en) * | 2018-12-28 | 2020-07-02 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle and wing assembly thereof |
| WO2021043336A3 (en) * | 2019-09-05 | 2021-04-22 | 深圳市道通智能航空技术股份有限公司 | Wing detachment assembly and aircraft |
| EP4023548A4 (en) * | 2019-09-05 | 2023-01-25 | Autel Robotics Co., Ltd. | Wing detachment assembly and aircraft |
| WO2021083152A1 (en) * | 2019-10-28 | 2021-05-06 | 深圳市道通智能航空技术股份有限公司 | Quick-release structure and aircraft |
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| WO2020134235A1 (en) | 2020-07-02 |
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