CN207328811U - Unmanned vehicle - Google Patents
Unmanned vehicle Download PDFInfo
- Publication number
- CN207328811U CN207328811U CN201721257041.4U CN201721257041U CN207328811U CN 207328811 U CN207328811 U CN 207328811U CN 201721257041 U CN201721257041 U CN 201721257041U CN 207328811 U CN207328811 U CN 207328811U
- Authority
- CN
- China
- Prior art keywords
- wing
- fuselage
- unmanned vehicle
- lock
- vehicle according
- 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.)
- Expired - Fee Related
Links
Landscapes
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
A kind of unmanned vehicle, including：Fuselage and the wing components for being rotationally connected with the fuselage, the wing components include：First wing, the second wing and the bindiny mechanism for the first wing to be connected to fuselage, first wing includes first end and the second end opposite with first end, bindiny mechanism is assemblied in the first end, and second wing is removably assemblied in the second end；Wherein, the first wing is rotationally connected with fuselage by bindiny mechanism, so that the first wing is unfolded or folds with respect to fuselage.The utility model devises a kind of unmanned vehicle, wing components in unmanned vehicle are divided into the multi-segment structure wing detachably assembled, and the wing being connected with fuselage is rotatably connected, so that wing components are under non-working condition, multi element wing detachably assembles, and the wing being connected with fuselage fuselage can fold relatively, so that size of the wing components shared by under non-working condition is smaller, in order to store and carry.
Description
Technical field
Unmanned air vehicle technique field is the utility model is related to, more particularly to a kind of unmanned vehicle with folding wing.
Background technology
With the rapid development of science and technology, the development of unmanned vehicle technology is more and more ripe, and the field of application is also more next
It is more extensive, such as：The field such as military affairs, scientific research, civilian, specifically can be used for photographing, explores, communicates, preventing and reducing natural disasters, border patrol
Etc..
For the unmanned vehicle of fixed-wing, it is typically due to that wing is longer, causes the body shared by unmanned vehicle entirety
Product is larger, it is necessary to which larger carrier packs the unmanned vehicle in storage or transportational process, is not easy to pack and transports
It is defeated.
Utility model content
The utility model proposes a kind of unmanned vehicle with folding wing to solve above-mentioned technical problem.
A kind of embodiment according to the present utility model, there is provided unmanned vehicle, it is characterised in that including：Fuselage and
The wing components of the fuselage are rotationally connected with, the wing components include：First wing, the second wing and for by institute
State the bindiny mechanism that the first wing is connected to the fuselage, first wing includes first end and opposite with the first end
Second end, the bindiny mechanism is assemblied in the first end, and second wing is removably assemblied in the second end；
Wherein, first wing is rotationally connected with the fuselage by the bindiny mechanism, so that first wing
Relatively described fuselage expansion folds.
Further, the bindiny mechanism includes being fixed on the first connector of the fuselage and is fixed on described the
Second connector of one end；Wherein, second connector is pivotally connected to first connector.
Further, first wing is further included arranged on the auxiliary section of the first end；Wherein, in first wing
When relatively described fuselage is unfolded, the auxiliary section coordinates with the fitting for lock on the fuselage to be locked.
Further, the wing components further include the first electric connector arranged on the second end, second wing
Equipped with the second electric connector being connected with first electric connector；
Wherein, when second wing is assemblied in first wing, by first electric connector and described second
Electric connector is connected, so that second wing is communicated to connect with first wing.
Further, the wing components further include the locking mechanism arranged on the second end, and second wing is equipped with
The lock coordinated with the locking mechanism matches somebody with somebody portion；
Wherein, when second wing is assemblied in first wing, latched by the locking mechanism in the lock
With portion, so that second wing is locked in first wing.
Further, the locking mechanism include be limited in the sliding slot of first end sliding part, be connected to the slip
The latch hook of part, the elastic component being sheathed on the sliding part and the regulating part being connected on the sliding part, the regulating part
Extend out of described sliding slot, when the elastic component is in original state, the latch hook is in lock in the shape of the lock with portion
State；
Wherein, under adjusting of the sliding part on width of the regulating part along first wing, institute is regulated and controled
State latch hook be assemblied in it is described lock with portion or be unlocked on it is described lock match somebody with somebody portion；The sliding part under the restoring force of the elastic component,
The latch hook lock is driven to match somebody with somebody portion in the lock.
Further, second wing one side opposite with the second end is additionally provided with guide rod, the second end
End face on be correspondingly provided with pilot hole so that second wing is matched with the rigging position of first wing.
Further, the wing components further include the rotor assemblies on first wing, for for the nothing
People's aircraft provides flying power.
Further, the rotor assemblies include be connected on first wing wing arm, be connected to the wing arm
The Power Component of free end and the propeller being connected on the Power Component.
Further, line channel is equipped with the wing arm, the Power Component and described first is connected to accommodate
The cable of wing.
Further, the unmanned vehicle further includes the empennage for being connected to fuselage, the empennage include empennage main body, with
And the linking arm of the empennage main body is connected to, the fuselage is equipped with the connecting portion being connected with the linking arm.
Further, the linking arm is equipped with lock pin, and the connecting portion is equipped with the lock distribution coordinated with the lock pin；
Wherein, by the lock pin and the cooperation of the lock distribution, the empennage is fixed on the fuselage.
Further, the 3rd electric connector being connected with the empennage main body, the fuselage are additionally provided with the linking arm
The 4th electric connector being adapted to the 3rd electric connector is equipped with, so that the empennage leads to while being assemblied in the fuselage
Letter is connected to the fuselage.
The technical solution that the embodiment of the utility model provides can include the following benefits：The utility model devises
A kind of unmanned vehicle, which is divided into wing components on the multi-segment structure wing detachably assembled, and connects with fuselage
The wing connect is rotatably connected so that wing components, under non-working condition, multi element wing detachably assembles, and with fuselage phase
Wing even can be folded with respect to fuselage, so that size of the wing components shared by under non-working condition is smaller, in order to
Storage and carrying.
It should be appreciated that the general description and following detailed description of the above are only exemplary and explanatory, not
The utility model can be limited.
Brief description of the drawings
It is required in being described below to embodiment in order to illustrate more clearly of the technical scheme in the embodiment of the utility model
Attached drawing to be used is briefly described, it should be apparent that, drawings in the following description are only some realities of the utility model
Example is applied, for those of ordinary skill in the art, without having to pay creative labor, can also be attached according to these
Figure obtains other attached drawings.
Fig. 1 is a kind of overall structure diagram of unmanned vehicle shown in one exemplary embodiment of the utility model；
Fig. 2 is a kind of removable knot of wing components of unmanned vehicle shown in one exemplary embodiment of the utility model
Structure schematic diagram；
Fig. 3 is that wing is folded with respect to fuselage in a kind of unmanned vehicle shown in one exemplary embodiment of the utility model
Structure diagram；
Fig. 4 be in a kind of unmanned vehicle shown in the utility model further example embodiment the first wing with respect to fuselage
The structure diagram of folding；
Fig. 5 is the structural representation of bindiny mechanism in a kind of wing components shown in one exemplary embodiment of the utility model
Figure；
Fig. 6 is that the first wing of a kind of wing components shown in one exemplary embodiment of the utility model is connected with the second wing
Partial structure diagram；
Fig. 7 is the enlarged drawing of part B in Fig. 6；
Fig. 8 is the enlarged drawing of the part A in Fig. 3；
Fig. 9 is a kind of structure diagram of the empennage of unmanned vehicle shown in one exemplary embodiment of the utility model.
Embodiment
The following is a combination of the drawings in the embodiments of the present utility model, and the technical scheme in the embodiment of the utility model is carried out
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are without making creative work
All other embodiments obtained, shall fall within the protection scope of the present invention.
Below in conjunction with the accompanying drawings, the structure of the utility model wing components and the unmanned vehicle with the wing components is made
Describe in detail, in the case where there is no conflict, the feature in following embodiment and embodiment can be mutually combined.
As shown in Figures 1 to 5, the unmanned vehicle 100 of the utility model embodiment includes：Fuselage 101 and the company of rotation
It is connected to the wing components 10 of fuselage 101.The wing components 10 include：First wing 11, the second wing 12 and for by first
Wing 11 is connected to the bindiny mechanism 13 of the fuselage 101 of unmanned vehicle 100.First wing 11 can pass through bindiny mechanism 13
Fold and pack up with respect to fuselage 101, so as to reduce the volumetric spaces shared by whole unmanned vehicle 100, in order to store
And carry.
Specifically, which includes first end 111 and the second end 112 opposite with first end 111, connects machine
Structure 13 is assemblied in first end 111, and the second wing 12 is removably assemblied in second end 112.In the utility model, the first wing
11 are rotationally connected with fuselage 101 by bindiny mechanism 13, so that 11 opposite fuselage 101 of the first wing is unfolded or folds.When
When one wing, 11 opposite fuselage 101 is unfolded, which is in use state；When 11 101 folding of opposite fuselage of the first wing
When folded, wing components 10 are in non-working condition at this time.In the utility model, wing components 10 are not limited to 11 He of the first wing
Second wing 12, according to the size design of unmanned vehicle 100, wing components 10 can also include the 3rd wing, the 4th wing
Deng, between those wings connection it is identical with the connection mode of the first wing 11 and the second wing 12.
As shown in Figures 3 to 5, which includes being fixed on the first connector 131 of fuselage 101 and fixes
In the second connector 132 of first end 111, which is pivotally connected to the first connector 131 so that this second
Connector 132 can be rotated relative to the first connector 131.In the embodiment, the first connector 131 can pass through screw, rivet
Or card with etc. mode be fixed on fuselage 101, similarly, the second connector 132 can also by screw, rivet or card match somebody with somebody
Etc. the end face for the first end 111 that mode is fixed on the first wing 11, the first connector 131 and the second connector 132 pass through shaft
Connection.
In the present embodiment, by bindiny mechanism 13, (machine bottom direction) is rotated with opposite fuselage 101 the first wing 11 downwards
Fold, when the first wing 11 is converted to non-working condition, the self gravitation of the first wing 11 can be utilized so that wing is opposite
Fuselage 101 folds.In the embodiment, when 11 opposite fuselage 101 of the first wing folds, the first wing 11 of 101 both sides of fuselage
101 both sides of fuselage are fitted in respectively, such that to be in volumetric spaces shared during non-working condition smaller for wing components 10.
Wherein, rotational angle of first wing 11 with respect to fuselage 101 can be limited to the spacing of the first wing 11 by fuselage 101.
Certainly, in the other embodiment of the utility model, according to the difference of the type of unmanned vehicle 100, this first
Wing 11 can also (machine top direction) rotation be turned folding with opposite fuselage 101 upwards by bindiny mechanism 13, first wing
11 can be unfolded with use state using self gravitation with respect to fuselage 101.In addition, first wing 11 can also pass through company
With opposite fuselage 101, (heading) turns folding or (20 direction of empennage) turns folding backward connection mechanism 13 forward, specifically
Ground can be depending on the composition of 101 shape of fuselage.
Further, the first wing 11 is further included arranged on the auxiliary section of first end 111 (not shown), accordingly, fuselage
Fitting for lock (not shown) is additionally provided with 101.Wherein, when 11 second opposite fuselage 101 of the first wing is unfolded, auxiliary section and fuselage
Fitting for lock on 101 coordinates locking, which can also be that the first wing 11 provides support force, with the first wing of enhancing 11 with
The bonding strength of fuselage 101.It is of course also possible to which auxiliary section is arranged on fuselage 101, fitting for lock is arranged on first end 111.
In an alternative embodiment, which can be carbon pipe, and auxiliary section is the connecting hole coordinated with carbon pipe.The lock
Accessory can be similar with the fit system of latch and pin hole with the fit system of auxiliary section, and carbon pipe is arranged on fuselage 101, can be by
Move into relative adjustment auxiliary section or remove auxiliary section, so that the first wing 11 is fixed on fuselage 101.Wherein, the carbon pipe is also
Can through fuselage 101 to be matched with the first wing 11 of both sides at the same time, in assembling, by the position of mobile carbon pipe with
Make the first wing 11 of both sides that assembling be fixed.
In another embodiment, carbon pipe is arranged on the first wing 11, and connecting hole is arranged on fuselage 101, in 11 phase of the first wing
When fuselage 101 is unfolded, by the fixation that carbon pipe insertion connecting hole is realized to the first wing 11 and fuselage 101.Wherein, the carbon
Pipe may also extend through the first wing 11, so as to the second wing 12 can be fixed on the first wing 11 by the carbon pipe, then will
First wing 11 is fixed on fuselage 102.Certainly, the fitting for lock of the utility model and the structure of auxiliary section are not limited to this, other
It can be used for the first wing 11 keeping the opposite fitting for lock being unfolded with fuselage 101 and auxiliary section suitable for the utility model
In embodiment.
The communications cable (not shown) is also associated between first wing 11 and fuselage 101, so that wing components 10 can be with
It is communicatively coupled to fuselage 101.Preferably, which can not only realize the communication between wing components 10 and fuselage 101
But also can be that wing components 10 provide power supply.In order to avoid the communications cable influences the corresponding fuselage 101 of wing components 10
Fold, which has certain amount of redundancy between the first wing 11 and fuselage 101.Wherein, which can be
FPC (Flexible Printed Circuit, flexible PCB) lines or coaxial line.
As shown in Fig. 1, Fig. 6 and Fig. 7, the first electric connector which further includes arranged on second end 112 (is not schemed
Show), the second wing 12 is equipped with the second electric connector 121 being connected with the first electric connector.Wherein, filled in the second wing 12
During assigned in the first wing 11, the first electric connector and the second electric connector 121 are connected, so that the second wing 12 and first
Wing 11 communicates to connect.When using stronger first connector of rigidity and the second connector, first connector and second connects
Connect device to be connected also with the effect being fixedly connected, the second wing 12 can be made to be connected on first wing 11.
In the utility model, steering engine 113 is respectively equipped with the first wing 11 and the second wing 12, to control the first machine
Rudder face on 11 and second wing 12 of the wing, so as to control the flight of unmanned vehicle 100.In the present embodiment, first company
Connect device selects aviation to be connected male connector and aviation connection female mating connection with the second connector, to realize the first wing 11 and second
Communication between wing 12.Certainly, first connector of the utility model is not limited to select aviation to be connected with the second connector
Male connector connects female with aviation, and other kinds of connector is also applied in the utility model.
Wing components 10 further include the locking mechanism arranged on second end 112, and the second wing 12 is equipped with to be coordinated with locking mechanism
Lock match somebody with somebody portion 122.Wherein, when the second wing 12 is assemblied in the first wing 11, portion 122 is matched somebody with somebody in lock by locking mechanism lock,
So that the second wing 12 is locked in the first wing 11.In the present embodiment, being coordinated by locking mechanism with lock with portion 122 can be into one
Step ensures the connection rigidity of the first wing 11 and the second wing 12.Certainly, in another embodiment, which can also set
In the second wing 12, lock is arranged on second end 112 with portion 122.
In embodiment, locking mechanism include be limited in the sliding slot of first end 111 sliding part 141, be connected to slip
The latch hook 142 of part 141, the elastic component 143 being sheathed on sliding part 141 and the regulating part 144 being connected on sliding part 141.
The regulating part 144 extends out of sliding slot, and when elastic component 143 is in original state, latch hook 142 is in lock and matches somebody with somebody portion 122 in lock
State.Wherein, under adjusting of the sliding part 141 on width of the regulating part 144 along the first wing 11, latch hook 142 is regulated and controled
It is assemblied in lock to match somebody with somebody portion 122 or be unlocked on lock and matches somebody with somebody portion 122；Sliding part 141 drives latch hook 142 under the restoring force of elastic component 143
Latch and match somebody with somebody portion 122 in lock.
Further, second wing 12 one side opposite with second end 112 is additionally provided with guide rod (not shown), and second
Pilot hole (not shown) is correspondingly provided with the end face at end 112, so that the second wing 12 is matched with the rigging position of the first wing 11.
Can be that the second wing 12 is connected to the first wing 11 offer intensity by the connection of guide rod and pilot hole in the embodiment,
Strengthen the rigidity that the second wing 12 is connected with the first wing 11.
As depicted in figs. 1 and 2, wing components 10 further include the rotor assemblies 15 on the first wing 11, for for nothing
People's aircraft 100 provides flying power, can make 100 VTOL of unmanned vehicle.Specifically, which includes connecting
The wing arm 151 that is connected on the first wing 11, be connected to the wing arm 151 free end Power Component 152 and be connected to institute
State the propeller 153 on Power Component 152.Wherein, the wing arm 151 is close to the second end 112 of the first wing 11, the second end
112 are equipped with to fix the holding section of the wing arm 151, the axial direction of armshaft and the head of unmanned vehicle 100 towards the side of tail
To consistent.
Further, line channel (not shown) is equipped with the wing arm 151, Power Component and first is connected to accommodate
The cable of wing 11, so as to provide power supply by the circuit in the first wing 11 for Power Component.In addition, the cable further include it is logical
Believe cable, the information such as the rotating speed of the acquisition propeller of fuselage 101 can be made by the connection of the communications cable.
As shown in Fig. 3, Fig. 8 and Fig. 9, unmanned vehicle 100 further includes the empennage 20 for being connected to fuselage 101, and empennage 20 wraps
Include empennage main body 21 and be connected to the linking arm 22 of empennage main body 21, fuselage 101 is equipped with what is be connected with linking arm 22
Connecting portion 102.In the present embodiment, the empennage 20 is by the cooperation of linking arm 22 and connecting portion 102, so that empennage 20 is removably
It is assemblied on fuselage 101, so as to further reduce the volumetric spaces shared by the unmanned vehicle 100, easy to user
Storage and carry, and dismantle and assemble it is relatively simple, it is easy to use.
Further, which is equipped with lock pin 23, and connecting portion 102 is equipped with the lock distribution coordinated with lock pin 23
1021.Wherein, by lock pin 23 and the cooperation of lock distribution 1021, empennage 20 is fixed on fuselage 101.Specifically, the lock pin
23 be elastic construction, which includes axis pin and be matched with the spring of axis pin, and in original state, spring is in natural resiliency
Under power the axis pin can be driven to protrude out linking arm 22.When user needs the empennage 20 being installed on fuselage 101, pass through pressing
The axis pin is so that in axis pin retraction linking arm 22, and spring is in compressive state at this time, so as to so that 22 company of being assemblied in of linking arm
In socket part 102.When the axis pin corresponds to lock distribution 1021, axis pin protrudes out linking arm 22 under the elastic-restoring force of spring,
And then be inserted in lock distribution 1021, it is locked in fuselage 101 so as to fulfill empennage 20.When dismantling the empennage 20, similarly lead to
Cross user and press axis pin, so that axis pin exits lock distribution 1021, dismantled so as to fulfill empennage 20 from fuselage 101, this kind coordinates
Mode quickly and easily can be assembled and dismantle without instrument.
Wherein, the 3rd electric connector (not shown) being connected with empennage main body 21 is additionally provided with linking arm 22, on fuselage 101
Equipped with the 4th electric connector (not shown) being adapted to the 3rd electric connector, so that empennage 20 leads to while being assemblied in fuselage 101
Letter is connected to fuselage 101.Steering engine 211 is equipped with the empennage 20, to coordinate the flight of control unmanned vehicle 100.This implementation
In example, communication is realized by the 3rd electric connector and the 4th electric connector, so that control module control empennage 20 is matched somebody with somebody in fuselage 101
Close flight.Alternatively, the 3rd electric connector and the 4th electric connector select aviation connection male connector to connect female with aviation.
The unmanned vehicle 100 further includes two shutdown framves 104 arranged on 101 both sides of fuselage, shuts down framves 104 for two and coordinates
With for support fuselage 101.Preferably, after 11 opposite fuselage 101 of the first wing folds, between the first wing of both sides 11
Maximum takes no more than two the maximum of shutdown framves 104 of size and takes sizes, such that protection the can be played by shutting down frame 104
The effect of one wing 11.
For the unmanned vehicle 100 of the utility model in assembling, the assembling sequence of wing components 10 and empennage 20 is simultaneously unlimited
Fixed, can first assemble wing components 10 can also first assemble empennage 20., can be first by the first wing when assembling wing components 10
11 are rotated by bindiny mechanism 13 and are unfolded with opposite fuselage 101, are then inserted in auxiliary section by fitting for lock with by the first wing
11 fix, and then the second wing 12 is assemblied on the first wing 11, can be beforehand through the guide rod on the second wing 12
It is assemblied in the pilot hole of second end 112 and is pre-positioned, and correspondence docks the first connector with the second connector 121, and
Coordinated afterwards by locking mechanism 13 with lock with portion 122 the second wing 12 is further secured on the first wing 11；Certainly,
The second wing 12 first can be assemblied in the first wing 11, then 11 opposite fuselage 101 of the first wing is unfolded again, the assembling side
Formula is same as the previously described embodiments, is only that the difference of assemble sequence.
When wing components 10 are dismantled, by stirring the regulating part 144 of locking mechanism 13 so that the unlock of latch hook 142 matches somebody with somebody portion with lock
122, then in the second wing 12 away from disassembling the second wing 12 from the first wing 11 on 11 direction of the first wing, this
When the first connector loosened with the second connector 121, guide rod is also extracted out of pilot hole, and the second wing 12 is from the first wing 11
On disassemble, then adjust fitting for lock so that fitting for lock is detached from the first wing 11, the first wing 11 is at itself at this time
Opposite fuselage 101 folds under gravity, so that the first wing 11 is close to fuselage 101.
When assembling empennage 20, pressing lock pin 23 then plants linking arm 22 so that in 23 retraction linking arm 22 of lock pin
Enter in the connecting portion 102 of fuselage 101, and the 3rd connector and the 4th connector are corresponded into connection, while correspond to lock pin 23
Lock distribution 1021 on connecting portion 102, lock pin 23, which is upspring, at this time locks assigned in locking in distribution 1021, so as to fulfill empennage 20 and fuselage
101 being fixedly connected and communicate to connect.When dismantling empennage 20, by pressing lock pin 23 so that lock pin 23 is unlocked on lock distribution
1021, the direction that linking arm 22 is directed away to fuselage 101 at this time is extracted, so that the 3rd connector and the 4th connector are split
Open, and then linking arm 22 is departed from connecting portion 102, so as to complete the dismounting of empennage 20.
The utility model devises a kind of unmanned vehicle, which has folding wing components, wing
Component is divided into the multi-segment structure wing detachably assembled, and the wing being connected with fuselage is rotatably connected, so that wing components exist
Under non-working condition, multi element wing detachably assembles, and the wing being connected with fuselage fuselage can fold relatively, so that machine
Wing component size shared under non-working condition is smaller, in order to store and carry.In addition, the unmanned vehicle also has
Can quick dismantling connection empennage, can quickly be dismantled by empennage, can further reduce the occupancy ruler of unmanned vehicle
It is very little.
Those skilled in the art will readily occur to this practicality after considering specification and putting into practice utility model disclosed herein
New other embodiments.This application is intended to cover any variations, uses, or adaptations of the utility model, these
Variations, uses, or adaptations follow the general principle of the utility model and including undocumented skills of the utility model
Common knowledge or conventional techniques in art field.Description and embodiments be considered only as it is exemplary, the utility model
True scope and spirit are pointed out by claims hereof.
It should be appreciated that the accurate knot that the utility model is not limited to be described above and is shown in the drawings
Structure, and various modifications and changes may be made without departing from the scope thereof.The scope of the utility model only will by appended right
Ask to limit.
Claims (13)
- A kind of 1. unmanned vehicle, it is characterised in that including：Fuselage and the wing components for being rotationally connected with the fuselage, institute Stating wing components includes：First wing, the second wing and the connection machine for first wing to be connected to the fuselage Structure, first wing include first end and the second end opposite with the first end, and the bindiny mechanism is assemblied in described First end, second wing are removably assemblied in the second end；Wherein, first wing is rotationally connected with the fuselage by the bindiny mechanism, so that first wing is opposite The fuselage expansion folds.
- 2. unmanned vehicle according to claim 1, it is characterised in that the bindiny mechanism includes being fixed on the fuselage The first connector and be fixed on the second connector of the first end；Wherein, second connector is pivotally connected to institute State the first connector.
- 3. unmanned vehicle according to claim 2, it is characterised in that first wing is further included arranged on described first The auxiliary section at end；Wherein, in first wing fuselage expansion relatively, the auxiliary section is matched somebody with somebody with the lock on the fuselage Part coordinates locking.
- 4. unmanned vehicle according to claim 1, it is characterised in that the wing components are further included arranged on described second First electric connector at end, second wing are equipped with the second electric connector being connected with first electric connector；Wherein, when second wing is assemblied in first wing, first electric connector and described second are electrically connected Device mating connection is connect, so that second wing is communicated to connect with first wing.
- 5. unmanned vehicle according to claim 4, it is characterised in that the wing components are further included arranged on described second The locking mechanism at end, second wing are equipped with the lock coordinated with the locking mechanism and match somebody with somebody portion；Wherein, when second wing is assemblied in first wing, portion is matched somebody with somebody in the lock by locking mechanism lock, So that second wing is locked in first wing.
- 6. unmanned vehicle according to claim 5, it is characterised in that the locking mechanism includes being limited in first end Sliding part in sliding slot, be connected to the latch hook of the sliding part, the elastic component being sheathed on the sliding part and be connected to institute The regulating part on sliding part is stated, the regulating part extends out of described sliding slot, described when the elastic component is in original state Latch hook is in lock in the state of the lock with portion；Wherein, under adjusting of the sliding part on width of the regulating part along first wing, the lock is regulated and controled Hook be assemblied in it is described lock with portion or be unlocked on it is described lock match somebody with somebody portion；The sliding part drives under the restoring force of the elastic component The latch hook lock matches somebody with somebody portion in the lock.
- 7. unmanned vehicle according to claim 4, it is characterised in that second wing is opposite with the second end One side is additionally provided with guide rod, and pilot hole is correspondingly provided with the end face of the second end, so that second wing is matched with institute State the rigging position of the first wing.
- 8. unmanned vehicle according to claim 1, it is characterised in that the wing components are further included arranged on described first Rotor assemblies on wing, for providing flying power for the unmanned vehicle.
- 9. unmanned vehicle according to claim 8, it is characterised in that the rotor assemblies include being connected to described first Wing arm on wing, be connected to the wing arm free end Power Component and be connected to spiral on the Power Component Paddle.
- 10. unmanned vehicle according to claim 9, it is characterised in that line channel is equipped with the wing arm, to hold Receive the cable for being connected to the Power Component and first wing.
- 11. unmanned vehicle according to claim 1, it is characterised in that the unmanned vehicle further includes the machine of being connected to The empennage of body, the empennage include empennage main body and are connected to the linking arm of the empennage main body, the fuselage be equipped with The connecting portion that the linking arm is connected.
- 12. unmanned vehicle according to claim 11, it is characterised in that the linking arm is equipped with lock pin, the company Socket part is equipped with the lock distribution coordinated with the lock pin；Wherein, by the lock pin and the cooperation of the lock distribution, by described in Empennage is fixed on the fuselage.
- 13. unmanned vehicle according to claim 11, it is characterised in that be additionally provided with the linking arm and the empennage 3rd electric connector of main body connection, the fuselage are equipped with the 4th electric connector being adapted to the 3rd electric connector, with The empennage is set to be communicatively coupled to the fuselage while being assemblied in the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721257041.4U CN207328811U (en) | 2017-09-27 | 2017-09-27 | Unmanned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721257041.4U CN207328811U (en) | 2017-09-27 | 2017-09-27 | Unmanned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207328811U true CN207328811U (en) | 2018-05-08 |
Family
ID=62366654
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721257041.4U Expired - Fee Related CN207328811U (en) | 2017-09-27 | 2017-09-27 | Unmanned vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207328811U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108513557A (en) * | 2017-09-27 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Wing components and unmanned vehicle |
-
2017
- 2017-09-27 CN CN201721257041.4U patent/CN207328811U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108513557A (en) * | 2017-09-27 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Wing components and unmanned vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108513557A (en) | Wing components and unmanned vehicle | |
| CN111655578B (en) | Fixed wing vertical take-off and landing hybrid UAV | |
| CN205131625U (en) | Small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle | |
| CN109515706A (en) | A kind of Modularized unmanned machine | |
| CN109703738A (en) | Manual wingfold mechanism | |
| CN104691749A (en) | Transversely staggered four-rotor aircraft | |
| CN205615703U (en) | Unmanned aerial vehicle folds horn | |
| CN106628107A (en) | Folding four-rotor unmanned aerial vehicle | |
| CN208412131U (en) | Vertical take-off and landing drone | |
| CN207328811U (en) | Unmanned vehicle | |
| CN205872438U (en) | Folding horn and unmanned aerial vehicle | |
| CN108438215A (en) | It is a kind of to have the vector four-axle aircraft for keeping organism level ability | |
| CN206984352U (en) | Changeable type unmanned vehicle | |
| CN114212249A (en) | Multi-rotor unmanned aerial vehicle | |
| CN109018332A (en) | A kind of folding three rotors mixed layout unmanned plane | |
| CN206125405U (en) | Fin reaches fixed wing uavs including it | |
| CN206407117U (en) | Folding multi-rotor unmanned aerial vehicle | |
| CN209454991U (en) | A kind of Modularized unmanned machine | |
| WO2019037242A1 (en) | Arm assembly, frame, and unmanned aerial vehicle | |
| CN209192221U (en) | A kind of modularized multipurpose unmanned plane | |
| CN209192222U (en) | A kind of convertible unmanned plane of flight attitude | |
| CN209225381U (en) | A kind of coaxial wingfold mechanism | |
| CN207826537U (en) | A kind of dynamic rotor structure of new type foldable oil | |
| CN114560084B (en) | Autonomous folding and unfolding deformation wing of bionic ornithopter | |
| CN207450221U (en) | A kind of unmanned plane of variable aerodynamic arrangement |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180508 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |