CN205707324U - A kind of folding quadrotor - Google Patents
A kind of folding quadrotor Download PDFInfo
- Publication number
- CN205707324U CN205707324U CN201620329248.7U CN201620329248U CN205707324U CN 205707324 U CN205707324 U CN 205707324U CN 201620329248 U CN201620329248 U CN 201620329248U CN 205707324 U CN205707324 U CN 205707324U
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- China
- Prior art keywords
- flight
- cantilever
- aircraft body
- lifting support
- aircraft
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Abstract
This utility model relates to vehicle technology field, specifically disclose a kind of folding quadrotor, including aircraft body, described aircraft body be hinged with flight cantilever and for locking the locking mechanism of flight cantilever, described aircraft body is provided with the accommodating recess for housing flight cantilever, described flight cantilever connects propeller set, and described propeller set is electrically connected with aircraft body；Locking mechanism, when packaging and transport, can be opened by this aircraft, makes flight cantilever be folded in accommodating recess, so, aircraft body can accomplish minimum as far as possible, alleviates deadweight, improves flying power, simultaneously, also reduce the volume of aircraft, be conducive to packaging and transport, carry convenient.
Description
Technical field
This utility model relates to vehicle technology field, particularly relates to a kind of folding quadrotor.
Background technology
At present, quadrotor principally falls into the one in unmanned vehicle, and this kind of quadrotor widely should
For model plane, take photo by plane, agricultural etc. is in field, for the most large-scale quadrotor, the most also has bigger body
Long-pending, so cause when packaging and transport, it appears suitable inconvenience, therefore, inventor makes structure for present problems and improves.
Summary of the invention
The purpose of this utility model is for the deficiencies in the prior art, it is provided that a kind of folding quadrotor,
This quadrotor uses the structure of collapsible flight cantilever, thus reduces the volume and weight of whole aircraft, thus
Longer cruising time is provided.
For achieving the above object, the folding quadrotor of one of the present utility model, including aircraft body, institute
That states aircraft body is hinged with flight cantilever and for locking the locking mechanism of flight cantilever, and described aircraft body is provided with
For housing the accommodating recess of flight cantilever, described flight cantilever connects propeller set, described propeller set and flight
Device main body is electrically connected with.
Further, the hinged end of described flight cantilever is provided with multiple lockhole, and described locking mechanism includes pressing piece, institute
The upper end stating pressing piece is provided with the first accommodating hole, and described first accommodating hole passes fly equipped with spring, the lower end of described pressing piece
Row device main body, described pressing piece is additionally provided with the lock that can coordinate with lockhole.
Further, the hinged end of described flight cantilever is provided with latch, and described locking mechanism includes thrust piece, described in push away
The rear end of casting die is provided with the second accommodating hole, and described second accommodating hole is provided with passes equipped with spring, the front end of described thrust piece
The button of aircraft body, described thrust piece is additionally provided with the restriction tooth that can engage with latch.
Further, described propeller set removably connects with flight cantilever.
Further, the bottom of described aircraft body connects lifting support, described lifting support and aircraft body
Collapsible connection.
Preferably, described lifting support is U-shaped, and one end of described lifting support is hinged with aircraft body damping, described
Aircraft body is additionally provided with the screens for clamping lifting support.
Further preferably, described lifting support is respectively arranged at the corner of aircraft body.
The beneficial effects of the utility model: compared with prior art, folding four rotors of one of the present utility model fly
Row device, including aircraft body, described aircraft body be hinged with flight cantilever and for locking the locking machine of flight cantilever
Structure, described aircraft body is provided with the accommodating recess for housing flight cantilever, and described flight cantilever connects has propeller to fill
Putting, described propeller set is electrically connected with aircraft body；Locking mechanism, when packaging and transport, can be beaten by this aircraft
Opening, make flight cantilever be folded in accommodating recess, so, aircraft body can accomplish minimum as far as possible, alleviates deadweight, improves continuous
Boat ability, meanwhile, also reduces the volume of aircraft, is conducive to packaging and transport, carries convenient.
Accompanying drawing explanation
Fig. 1 is the axonometric chart of this utility model embodiment one.
Fig. 2 is the axonometric chart at another visual angle of this utility model embodiment one.
Fig. 3 is the foldable structure schematic diagram of this utility model embodiment one.
Fig. 4 is the fit structure schematic diagram of the locking mechanism of this utility model embodiment one.
Fig. 5 is the fit structure schematic diagram of the locking mechanism of this utility model embodiment two.
Reference includes:
Aircraft body--1, accommodating recess--11, screens--12,
Flight cantilever--2, lockhole--21, latch--22,
Locking mechanism--3, pressing piece--31, the first accommodating hole--32,
Lock--33, thrust piece--34, the second accommodating hole--35,
Button--36, limit tooth--37, propeller set--4,
Lifting support--5.
Detailed description of the invention
Below in conjunction with the accompanying drawings this utility model is described in detail.
Embodiment one.
Seeing Fig. 1 to Fig. 4, a kind of folding quadrotor, including aircraft body 1, described aircraft body 1
Be hinged with flight cantilever 2 and for locking the locking mechanism 3 of flight cantilever 2, described aircraft body 1 is provided with for housing
The accommodating recess 11 of flight cantilever 2, described flight cantilever 2 connects propeller set 4, described propeller set 4 and aircraft
Main body 1 is electrically connected with；Locking mechanism 3, when packaging and transport, can be opened, make flight cantilever 2 be folded to house by this aircraft
In recess 11, so, aircraft body 1 can accomplish minimum as far as possible, alleviates deadweight, improves flying power, also reduces meanwhile
The volume of aircraft, is conducive to packaging and transport, carries convenient.
In the technical program, the hinged end of described flight cantilever 2 is provided with multiple lockhole 21, and described locking mechanism 3 wraps
Including pressing piece 31, the upper end of described pressing piece 31 is provided with the first accommodating hole 32, and described first accommodating hole 32 is equipped with spring, described
The lower end of pressing piece 31 passes aircraft body 1, and described pressing piece 31 is additionally provided with the lock 33 coordinated with lockhole 21.Described lock
Hole 21 is preferably provided four, and described lock 33 is two, and so, two corresponding two of which lockholes 21 of lock 33, its locking is imitated
The most relatively reliable, specifically, when flight cantilever 2 is in and stretches out state, said two lock 33 snaps in two lockholes 21, real
Now locking, when needs fold, pin pressing piece 31, make lock 33 exit lockhole 21, at this moment, flight cantilever 2 can realize folding
Folded, to straight, four flight cantilevers 2 are all folded in accommodating recess 11, when folding puts in place, said two lock 33 blocks again
Enter in two other lockhole 21, prevent flight cantilever 2 to be opened accidentally, easy to use.
In the technical program, described propeller set 4 removably connects with flight cantilever 2.So, when packaging, can
Pulling down from flight cantilever 2 with propeller set 4, transport safer, be convenient to mount and dismount, described propeller set 4 uses existing skill
Art, does not do at this and emphasizes further.
In the technical program, the bottom of described aircraft body 1 connects lifting support 5, described lifting support 5 with fly
The collapsible connection of row device main body 1.Owing to aircraft is when landing, being required for preferably support, this programme is real by lifting support 5
Now fold, reduce the volume of aircraft further.
Further improving, described lifting support 5 is U-shaped, and one end of described lifting support 5 damps with aircraft body 1
Hinged, described aircraft body 1 is additionally provided with the screens 12 for clamping lifting support 5.During use, lifting support 5 is pulled out
Open, the effect of undercarriage can be realized.When not using, fold lifting support 5, reduce space hold, it is simple to storage.
Further preferably, described lifting support 5 is respectively arranged at the corner of aircraft body 1.Lifting support 5 is arranged at
The corner of aircraft body 1, lifting support 5 is when folding, it is possible to achieve engages with aircraft body 1, is more uniformly stressed, and rises
The stability that falls is more preferable.
Embodiment two.
Seeing Fig. 5, the present embodiment is with the difference of embodiment one: the hinged end of described flight cantilever 2 is provided with
Latch 22, described locking mechanism 3 includes that thrust piece 34, the rear end of described thrust piece 34 are provided with the second accommodating hole 35, described
Two accommodating holes 35 are provided with the button 36 passing aircraft body 1, described thrust piece equipped with spring, the front end of described thrust piece 34
34 are additionally provided with the restriction tooth 37 engaged with latch 22.When flight cantilever 2 is opened, described restriction tooth 37 is under the action of the spring
Engage with latch 22, formed and limit, make flight cantilever 2 remain on；When needs fold, pin thrust piece 34, make limit
Tooth 37 processed separates with latch 22, and so, flight cantilever 2 can realize rotary folding, after being rotated in place, decontrols thrust piece 34, limit
Tooth 37 processed engages with latch 22 again, makes flight cantilever 2 keep folded state.
Other parts of the present embodiment are identical with embodiment one, do not repeat them here.
Above content is only preferred embodiment of the present utility model, for those of ordinary skill in the art, according to this reality
By novel thought, the most all will change, this specification content should not be construed as
To restriction of the present utility model.
Claims (7)
1. a folding quadrotor, including aircraft body (1), it is characterised in that: described aircraft body (1)
Be hinged with flight cantilever (2) and be used for locking the locking mechanism (3) of flight cantilever (2), described aircraft body (1) is provided with
For housing the accommodating recess (11) of flight cantilever (2), described flight cantilever (2) connects propeller set (4), described spiral
Oar device (4) is electrically connected with aircraft body (1).
The folding quadrotor of one the most according to claim 1, it is characterised in that: described flight cantilever (2)
Hinged end be provided with multiple lockhole (21), described locking mechanism (3) includes pressing piece (31), the upper end of described pressing piece (31)
Being provided with the first accommodating hole (32), described first accommodating hole (32) passes flight equipped with spring, the lower end of described pressing piece (31)
Device main body (1), described pressing piece (31) is additionally provided with the lock (33) coordinated with lockhole (21).
The folding quadrotor of one the most according to claim 1, it is characterised in that: described flight cantilever (2)
Hinged end be provided with latch (22), described locking mechanism (3) includes thrust piece (34), and the rear end of described thrust piece (34) is arranged
The second accommodating hole (35), described second accommodating hole (35) is had to be provided with to pass fly equipped with spring, the front end of described thrust piece (34)
The button (36) of row device main body (1), described thrust piece (34) is additionally provided with the restriction tooth (37) engaged with latch (22).
The folding quadrotor of one the most according to claim 1, it is characterised in that: described propeller set
(4) removably connect with flight cantilever (2).
The folding quadrotor of one the most according to claim 1, it is characterised in that: described aircraft body
(1) bottom connects lifting support (5), and described lifting support (5) is collapsible with aircraft body (1) to be connected.
The folding quadrotor of one the most according to claim 5, it is characterised in that: described lifting support (5)
For U-shaped, one end of described lifting support (5) damps hinged with aircraft body (1), and described aircraft body (1) is additionally provided with
For limiting the screens (12) of lifting support (5).
The folding quadrotor of one the most according to claim 6, it is characterised in that: described lifting support (5)
It is respectively arranged at the corner of aircraft body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620329248.7U CN205707324U (en) | 2016-04-19 | 2016-04-19 | A kind of folding quadrotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620329248.7U CN205707324U (en) | 2016-04-19 | 2016-04-19 | A kind of folding quadrotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205707324U true CN205707324U (en) | 2016-11-23 |
Family
ID=57298112
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620329248.7U Expired - Fee Related CN205707324U (en) | 2016-04-19 | 2016-04-19 | A kind of folding quadrotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205707324U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018112798A1 (en) * | 2016-12-21 | 2018-06-28 | XDynamics Limited | Unmanned aerial vehicle |
| CN109110118A (en) * | 2017-06-23 | 2019-01-01 | 昊翔电能运动科技(昆山)有限公司 | Unmanned plane and its frame assembly |
-
2016
- 2016-04-19 CN CN201620329248.7U patent/CN205707324U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018112798A1 (en) * | 2016-12-21 | 2018-06-28 | XDynamics Limited | Unmanned aerial vehicle |
| CN109110118A (en) * | 2017-06-23 | 2019-01-01 | 昊翔电能运动科技(昆山)有限公司 | Unmanned plane and its frame assembly |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161123 Termination date: 20180419 |