CN109677600A - A kind of shrinkable unmanned plane rotor protective device and unmanned plane - Google Patents
A kind of shrinkable unmanned plane rotor protective device and unmanned plane Download PDFInfo
- Publication number
- CN109677600A CN109677600A CN201810936269.9A CN201810936269A CN109677600A CN 109677600 A CN109677600 A CN 109677600A CN 201810936269 A CN201810936269 A CN 201810936269A CN 109677600 A CN109677600 A CN 109677600A
- Authority
- CN
- China
- Prior art keywords
- rotor
- outline border
- unmanned plane
- support
- protective device
- 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.)
- Pending
Links
- 230000001681 protective effect Effects 0.000 title claims abstract description 50
- 230000006698 induction Effects 0.000 claims abstract description 72
- 230000008602 contraction Effects 0.000 claims abstract description 12
- 230000007246 mechanism Effects 0.000 claims description 81
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 17
- 230000000903 blocking effect Effects 0.000 claims description 12
- 239000013013 elastic material Substances 0.000 claims description 5
- 230000003993 interaction Effects 0.000 claims description 3
- 230000006978 adaptation Effects 0.000 claims 1
- 210000001331 nose Anatomy 0.000 description 16
- 238000010586 diagram Methods 0.000 description 8
- 230000004308 accommodation Effects 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 7
- 230000006870 function Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 4
- 239000002360 explosive Substances 0.000 description 4
- 230000005693 optoelectronics Effects 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000001939 inductive effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- CVOFKRWYWCSDMA-UHFFFAOYSA-N 2-chloro-n-(2,6-diethylphenyl)-n-(methoxymethyl)acetamide;2,6-dinitro-n,n-dipropyl-4-(trifluoromethyl)aniline Chemical compound CCC1=CC=CC(CC)=C1N(COC)C(=O)CCl.CCCN(CCC)C1=C([N+]([O-])=O)C=C(C(F)(F)F)C=C1[N+]([O-])=O CVOFKRWYWCSDMA-UHFFFAOYSA-N 0.000 description 1
- 239000011358 absorbing material Substances 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005674 electromagnetic induction Effects 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 210000003128 head Anatomy 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000005622 photoelectricity Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The present invention discloses a kind of shrinkable unmanned plane rotor protective device and unmanned plane, the protection applied to unmanned plane rotor, comprising: outline border: being set in outside rotor, and outline border is the scalable type structure of size；Rotor position induction device: for determining the position of rotor；Rotor positioner: for controlling rotor wing rotation to the designated position shunk for outline border, so that rotor does not interfere the contraction of outline border according to the sensed data of rotor position induction device.Rotor protective device, which is arranged, in the present invention makes to avoid foreign object strike when rotor flying and hurt sb.'s feelings, and flight stability is higher and safety is more preferable；The outline border of protective device is folding structure, carries unmanned plane more convenient；Protective device is equipped with rotor position induction device and rotor positioner, when needing to store outline border, the orientation of adjustable rotor folds rotor, interferes to avoid rotor when outline border is stored and outline border recurring structure, ensure that the contractility of protective device outline border.
Description
[technical field]
The present invention relates to air vehicle technique field more particularly to a kind of contractile unmanned plane rotor protective device and nobody
Machine.
[background technique]
In recent years, the miniature consumer level rotor wing unmanned aerial vehicle the next common in life.It is miniature compared to large-scale unmanned plane of taking photo by plane
Unmanned plane is used to meet the self-timer demand of people, flies very low, exposed rotor is a very big security risk.
In order to solve this problem, rotor is wrapped up with a closed rotor protective frame in the prior art, but
Rotor protective frame can but bring pretty troublesome portability problem, because of occupied area very little when the rotor of unmanned plane does not rotate, folding
Poststack hardly accounts for area, it ensure that the portability of miniature drone, still, if being wrapped up with a fixed rotor protective frame
Rotor, then the size needs of rotor protective frame are big as the rotary wings disk of rotor, the size of unmanned plane will become very big,
Lose portability.If each folding and unfolding unmanned plane requires first to dismount rotor protection using dismountable rotor protective frame
Frame, it is clear that this mode is not suitable for needing the consumer level unmanned plane of high frequency folding and unfolding.
[summary of the invention]
To solve the above-mentioned problems, the present invention discloses a kind of shrinkable unmanned plane rotor protective device and unmanned plane, setting
One protective device protects rotor, and the protective device can be shunk to be convenient for carrying.
The application discloses a kind of shrinkable unmanned plane rotor protective device, the protection of the rotor applied to unmanned plane, comprising:
Outline border: being set in outside the rotor, and the outline border is the scalable type structure of size；
Rotor position induction device: for determining the position of the rotor；
Rotor positioner: for controlling the rotor wing rotation according to the sensed data of the rotor position induction device
To the designated position shunk for outline border, so that the rotor does not interfere the contraction of the outline border.
Further, the outline border include main frame and at least one from frame, the main frame is connect with from frame by movable part,
So that the expansion or contraction for realizing the outline border relative to main frame activity from frame.
Further, further include locking mechanism, the locking mechanism is mounted on the outline border, with lock the main frame and
The relative position from frame.
Further, the locking mechanism includes the first lock body and the second lock body, is provided with first on first lock body
Fixed part, the second fixed part being adapted to first fixed part is provided on second lock body, and second fixed part moves
The main frame and the relative position from frame are locked when moving to first fixed part, it is solid that second fixed part is detached from first
First lock body described in when determining portion and second lock body opposite can slide.
Further, the locking mechanism includes the first lock body, the second lock body and locking piece, and first lock body is equipped with
Locking bit, the locking piece include a movable block, and the locking piece, which is mounted on, can be placed in the movable block on first lock
The position of the locking bit of body, the movable block lock the main frame and the relative position from frame when being placed in the locking bit；
First lock body described in when the movable block removes the locking bit and the second lock body opposite can slide.
Further, shrinkable unmanned plane rotor protective device according to claim 3, which is characterized in that described
Locking mechanism includes push-rod electric machine, and the both ends of the push-rod electric machine are separately mounted to the both ends of outline border, and the push-rod electric machine is released
Push rod, the both ends of the push-rod electric machine are relatively distant to drive the main frame to be unfolded with from the opposite sliding of frame, work as retraction
The push rod, the main frame are slided with from frame is opposite to be shunk, and the push-rod electric machine stops pushing away described in release or contraction
Current main frame and the relative position from frame are locked when bar.
Further, the rotor position induction device include first induction component and second induction component, described first
Incude component and the rotor to rotate synchronously, described in the second induction component and the first induction component interaction determine
The position of first induction component, and then determine the position of the rotor.
Further, the rotor includes pedestal and blade, and the pedestal is mounted on motor, and the blade and pedestal connect
It connects, the blade is at least provided with three pieces, and the blade a piece of at least within is foldable blade, the foldable blade
Wherein one end is connect by articulated structure with the pedestal, and the foldable blade is rolled over using articulated structure as axis relative to pedestal
It is folded.
Further, including blade blocking mechanism, the blade blocking mechanism are arranged inside the outline border, the blade
Blocking mechanism directly acts on the foldable blade, to stop the foldable blade to continue to rotate and carry out along direction of rotation
It folds.
It further, further include protection net cover, the protection net cover is made by elastic material, and the protection net cover is mounted on
The outer of the outline border.
A kind of unmanned plane is also disclosed in the application, and the rotor including shrinkable unmanned plane described in above-mentioned any one protects dress
It sets, rotor, flight controller, fuselage, first support, second support, the first rotating mechanism and the second rotating mechanism, the rotor
Protective device and the rotor are mounted in first support, and the first support is rotated with the second support by described first
Mechanism connection and can relative rotation, the second support connect with the fuselage by the second rotating mechanism and can relative rotation,
The flight controller controls the inclination angle of the rotor by controlling first rotating mechanism and second rotating mechanism.
Further, first rotating mechanism includes the first spindle nose, first bearing and the first servomechanism, the first axle
Head is fixedly connected with the first support, and the first bearing and first servomechanism are fixedly connected with the second support,
Or first spindle nose is fixedly connected with the second support, the first bearing and first servomechanism and described first
Bracket is fixedly connected, and the first support is connected by the first bearing with first spindle nose with the second support, institute
Stating the first servomechanism can control the first support to rotate around connecting shaft；
Second rotating mechanism include the second spindle nose, second bearing and the second servomechanism, second spindle nose with it is described
Second support is fixedly connected, and the second bearing and second servomechanism are fixedly connected or described second with the fuselage
Bearing and second servomechanism are fixedly connected with the second support, and second spindle nose is fixedly connected with the fuselage, institute
It states second support and is connected by the second bearing with second spindle nose with the fuselage, second servomechanism can control institute
Second support is stated to rotate around connecting shaft.
Compared with prior art, the invention has the benefit that
The present invention discloses a kind of protective device and unmanned plane applied to unmanned plane rotor to be made to revolve by surrounding rotor
Foreign object strike is avoided when wing flight and accidentally injures people, and flight stability and safety are more preferable；The outline border of the protective device is that can roll over
Folded structure, small and exquisite after folding and folding mode is simple, carries unmanned plane more convenient.
[Detailed description of the invention]
Above-mentioned and/or additional aspect and advantage of the invention will become from the following description of the accompanying drawings of embodiments
Obviously and it is readily appreciated that, in which:
Fig. 1 is protective device entirety control module block diagram of the present invention；
Fig. 2 is that first embodiment of the invention rotor protective device structure combines expanded view；
Fig. 3 is first embodiment of the invention rotor protective device explosive view；
Fig. 4 is second embodiment of the invention rotor protective device explosive view；
Fig. 5 is that second embodiment of the invention rotor protective device combines contractible graph；
Fig. 6 is third embodiment of the invention rotor protective device explosive view；
Fig. 7 is that third embodiment of the invention rotor protective device combines contractible graph；
Fig. 8 is that third embodiment of the invention rotor protective device peripheral hardware protects net cover figure；
Fig. 9 is the schematic diagram of first embodiment of the invention locking mechanism；
Figure 10 is second embodiment of the invention locking mechanism schematic diagram；
Figure 11 is rotor unfolded state schematic diagram of the present invention；
Figure 12 is rotor folded state schematic diagram of the present invention；
Figure 13 is rotor position induction device module diagram of the present invention；
Figure 14 is unmanned plane first embodiment constitutional diagram of the present invention；
Figure 15 is unmanned plane first embodiment explosive view of the present invention；
Figure 16 is unmanned plane second embodiment constitutional diagram of the present invention.
[specific embodiment]
The present invention is further described with exemplary embodiment with reference to the accompanying drawing, wherein identical label in attached drawing
All refer to identical component.In addition, if the detailed description of known technology is for showing the invention is characterized in that unnecessary
, then it omits it.The embodiments described below with reference to the accompanying drawings are exemplary, for explaining only the invention, and cannot
It is construed to limitation of the present invention.
Those skilled in the art of the present technique are appreciated that unless expressly stated, singular " one " used herein, " one
It is a ", " described " and "the" may also comprise plural form.It is to be further understood that being arranged used in specification of the invention
Diction " comprising " refer to that there are the feature, integer, step, operation, element and/or component, but it is not excluded that in the presence of or addition
Other one or more features, integer, step, operation, element, component and/or their group.It should be understood that when we claim member
Part is " connected " or when " coupled " to another element, it can be directly connected or coupled to other elements, or there may also be
Intermediary element.In addition, " connection " used herein or " coupling " may include being wirelessly connected or wirelessly coupling.It is used herein to arrange
Diction "and/or" includes one or more associated wholes for listing item or any cell and all combinations
The direction term on relational terms such as first and second and the like and "upper" "lower" " left side " " right side ", is used merely to
It distinguishes one entity or operation from another entity or operation, without necessarily requiring or implying these entities or behaviour
There are any this actual relationship, sequence and directions between work.
Fig. 1-Fig. 2 is please referred to, the present invention discloses a kind of shrinkable unmanned plane rotor protective device 100, is applied to unmanned plane
Rotor 200 protection, comprising:
Outline border 10: being set in outside the rotor 200, and the outline border 10 is the scalable type structure of size；
Rotor position induction device 20: for determining the position of the rotor 200；
Rotor positioner 30: for controlling the rotor according to the sensed data of the rotor position induction device 20
200 rotations are to the designated position shunk for outline border 10, so that the rotor 200 does not interfere the contraction of the outline border 10.
The unmanned plane rotor protective device 100 of the application mainly for the protection of rotor 200 from other objects shock and
It avoids rotor 200 from hurting sb.'s feelings, while normal unmanned plane during flying work can not also be influenced.The unmanned plane rotor protective device 100
Outline border 10 is engraved structure, in order to air motion, guarantees that the pneumatic efficiency of rotor 200 can further wrap on outline border 10
One layer of sound-absorbing material is included, the aerodynamic noise of rotor 200 can be reduced.
Further, the also mountable flow deflector (not shown) on outline border 10, realize using single rotor 200 and flow deflector as
The unmanned plane of power device, flow deflector are used to offset the torque that the rotation of single rotor 200 generates and realize yaw control.
In order to facilitate carrying, reduces the recycling size of entire unmanned plane, outline border 10 is also arranged to contractile structure, this
The contractile structure of kind can be accomplished in several ways,
In one embodiment, which is whole foldable type, is divided into the sub- frame of more piece, and the sub- frame is equipped with sliding slot,
It is connected between adjacent sub- frame with support rod, the end of the support rod is slide block structure, supports the sliding block of boom end to be installed on described
On the sliding slot of sub- frame, when stretching outline border 10, the sliding block of above-mentioned support boom end slides in the sliding slot of sub- frame expands outline border 10
Volume supports the sliding block of boom end to slide the volume that can reduce outline border 10 in the sliding slot of sub- frame when compressing outline border 10.Work as outline border
10 when being deployed into certain position, is locked by locking mechanism 14.
In another embodiment, a kind of structure of contractile outline border 10 is disclosed, Fig. 2-Fig. 3, including one are please referred to
Main frame 11 and one connect from frame 12, the main frame 11 with from frame 12 by movable part 13 so that it is described from frame 12 relative to master
The movable expansion or contraction to realize the outline border of frame 11.A kind of feasible embodiment is that the movable part 13 includes guide rail
131 and slide bar 132, guide rail 131 be mounted on main frame 11, slide bar 132 is mounted on from frame 12, and guide rail 131 is mounted in turn
From frame 12, slide bar 132 is mounted on main frame 11 and also may be used.It is adapted to by guide rail 131 with slide bar 132 and is slided relatively, make main frame 11
With from 12 relative motion of frame, the contraction of outline border 10 is realized, when main frame 11 and from 12 relative motion of frame to certain position, pass through lock
Determine mechanism 14 to be locked.
In another embodiment, a kind of structure of contractile outline border 10 of circle is disclosed, Fig. 4-Fig. 5 is please referred to, it is described
For contractile outline border 10 including a main frame 11A and two from frame 12A, the main frame 11A is centrally located, described from frame
12A is located at both sides, described that multiple support rod 121A are provided with from frame 12A, is provided with accommodating support rod on the main frame 11A
The accommodation groove 111A of 121A, the support rod 121A is inserted into the accommodation groove 111A and opposite sliding, to realize 10 phase of outline border
To shrinking or stretching, when shrinking or being stretched to certain position, locked by locking mechanism 14.
In another embodiment, the structure of another round contractile outline border 10 is disclosed, Fig. 6-Fig. 7, institute are please referred to
Stating contractile outline border 10 includes that a main frame 11B and five slide from frame 12B from frame 12B relative to the main frame 11B, with
It realizes and shrinks, the mode slided from frame 12B relative to main frame 11B is similar with the structure of above-mentioned Fig. 4, is provided with from frame 12B
Multiple support rod 121B are provided with the accommodation groove 111B for support rod 121B insertion and opposite sliding on main frame 11B, difference
Be in, main frame 11B and from the edge of frame 12B be also provided with can opposite sliding movable part, including from the edge of frame 12B
The sliding shoe 122B of setting and contacted with the sliding shoe 122B it is adjacent be arranged from frame 12B or main frame 11B for sliding shoe
The sliding groove 123B of 122B sliding, so that stable structure when being slided from frame 12B.
Above be wherein several outline borders 10 disclosed in the present application contraction structure, but be not limited in the application with
It is upper several, it can also be other structures that can be shunk, for example not only can be set from frame 12 multiple, and between each other may be used
Mutually to shrink, main frame 11 can also be divided into multiple, be shunk between each other, the shape of outline border 10 can be it is rectangular can also
To be round or any other feasible shape, as long as applying in unmanned plane rotor protective device 100 of the invention
On, using technical solution disclosed by the invention, realization is shrinkable, and the function of rotor is protected then to be included in protection scope of the present invention.
A variety of contractile outline borders 10 disclosed above are after being stretched to certain position, usually in maximum tension position
It sets, it is also necessary to which locking mechanism 14 locks current position, so as to there is enough spaces to revolve inside outline border 10 for rotor 200
Turn, locking mechanism 14 there will be very high reliability, guarantee during unmanned plane during flying, and outline border 10 will not accidentally shrink and fall
Machine.
Further regard to Fig. 3, Fig. 4, Fig. 6 and Fig. 9, a kind of structure of locking mechanism 14 disclosed herein will lock
Mechanism 14 is mounted on outline border 10, and locking mechanism 14 includes first latch fitting 141 and second latch fitting 142, the first latch fitting
141 and second latch fitting 142 be separately fixed at main frame 11 and from frame 12, to support two components.
In one embodiment, it main frame 11 and the first support 500 of rotor is installed is fixed together, therefore by the first latch fitting
141 are arranged in first support 500, and from the second latch fitting of installation settings 142 on frame 12, the second latch fitting 142 is fixed on the first lock
When on part 141, the locking from frame 12 relative to main frame 11 is realized.Incorporated by reference to Fig. 3, Fig. 4, Fig. 6 and Fig. 9 disclosed above, first
Latch fitting 141 is the sliding rail for a groove structure being arranged in first support 500, the end sliding rail inlet of the first latch fitting 141
Equipped with the first fixed part 1411, the apical position from frame 12 is arranged in the second latch fitting 142, is a high-intensitive slide bar,
The second fixed part 1421 is arranged in the end of slide bar, and the groove structure sliding rail of the first latch fitting 141 is for the second fixed part 1421
The second latch fitting 142 sliding, when the second fixed part 1421 of the second latch fitting 142 slides into the end inlets of the first latch fitting 141
When, by rotating the second latch fitting 142, the second fixed part 1421 is inserted into the first fixed part 1411, the second latch fitting 142 can be prevented
It is slided on the first latch fitting 141, to realize the locking from frame 12 and main frame 11.Equally, when needs are shunk from frame 12 and main frame
When 11, the second fixed part 1421 is detached from the first fixed part 1411, rotates the second latch fitting 142 again, can continue to allow the
Two latch fittings 142 slide in the groove structure of the first latch fitting 141.It should be noted that locking mechanism 14, which is at least arranged one, to be made
Outline border 10 is in the latched position of maximum volume, sliding in the groove structure of the first latch fitting 141 as shown in Fig. 3, Fig. 4, Fig. 6 and Fig. 9
The first fixed part 1411 is arranged in the inlet of rail, and the second fixed part 1421 of the second latch fitting 142 is placed in first fixed part 1411
When outline border 10 will be locked on maximum volume.Multiple first fixed parts 1411 can also be set on the first latch fitting 141, with reality
The now locking from frame 12 with main frame 11 in multiple positions.
In another embodiment, based on above-mentioned locking mechanism 14, the groove structure sliding rail of first latch fitting 141 is changed to
A nut structure part is arranged as the first fixed part 1411 in round sliding rail in sliding rail, and the end of second latch fitting 142 is set
One section of screw-rod structure part is set as the second fixed part 1421, when the screw-rod structure part of the second latch fitting 142 is slided to the first latch fitting 141
Nut structure part and by screw rod screw in nut when, locked.It should be noted that since screw-rod structure part is only arranged
Second latch fitting 142 it is wherein a bit of on, allow screw-rod structure part to be detached from first latch fitting 141 when continuing to rotate the second latch fitting 142
When nut structure part, the second lock body 142 can continue to slide in the sliding rail of the first above-mentioned lock body 141.
In another embodiment, a nut in first support 500, the second lock is generally arranged in the first lock body 141
The end of body 142 is that a nut is arranged in the sliding rail of screw-rod structure or the first lock body 141, and the second lock body 142 is whole to be all
Screw-rod structure, is adapted to fix the relative position from frame 12 and main frame 11 by the rotation of screw rod and nut, using this structure, from
Frame 12 and main frame 11 can be fixed at an arbitrary position.Using the fixed lock mode that is adapted to of above-mentioned screw rod and nut, reduction
The gap of latched position, since round sliding rail is smaller than groove structure sliding rail size, thus can reduce locking mechanism 14
Volume.
The locking mechanism of above structure is also provided with when using in the case where two of Fig. 4 structure from frame 12A
Two groups of locking mechanisms 14, two the second lock bodies 142 are separately mounted to two from frame 12A, and the first lock body 141 is then arranged in master
The plane of symmetry of frame 11A locks two the second lock bodies 142 respectively.
In another embodiment, the locking mechanism 14 can also be push-rod electric machine, at this point, pacifying in first support 500
Fill push-rod electric machine main body, the push rod end of push-rod electric machine is fixedly connected with from frame 12, or by push-rod electric machine main body be installed on from
Frame 12, push rod end are fixedly connected with first support 500, and identical function may be implemented in the two.For outline border 10 shown in Fig. 4,
Push-rod electric machine main body and push rod end can also be respectively and fixedly installed to two from frame 12A, when push rod is pushed out,
It stretches from frame 12 and main frame 11, when pusher retracted, is shunk from frame 12 and main frame 11, when push-rod electric machine stops push-and-pull push rod, from
Frame 12 and main 11 latched position relationship of frame further by controlling push-rod electric machine, can control and pushing away from frame 12 and main frame 11
Any position of the length range of bar locks.
In another embodiment, referring to Fig. 10,10 structure of outline border shown in Fig. 10 is same as shown in Figure 6, using not
With locking mechanism 14A, the locking mechanism 14A includes the first lock body 141A, the second lock body 142A and locking piece 143A, first
Lock body 141A is a round sliding rail in the supporting beam of main frame 11C, and the second lock body 142A is provided at from one on frame 12C
Root high intensity slide bar, locking piece 143A is set on main frame 11C, including a movable block in an accommodation groove and accommodation groove
The sliding rail of 1431A, the first lock body 141A intersect with the accommodation groove of locking piece 143A in some position, and the crossover sites are
The locking bit of one lock body 141A, movable block 1431A can be slided in accommodation groove, when movable block 1431A slides into the first lock body
When the locking bit of 141A, the sliding rail of the first lock body 141A will be blocked, the second lock body 142A can not be slided on the slide rail, lock main frame
11C with from the relative position of frame 12C.
Further, the locking piece 143A of above-described embodiment also may include the movable block that can be moved vertically
1431A opens the hole of the sliding rail of a through first lock body 141A, the hole in another embodiment in main frame 11C supporting beam
Hole is the locking bit of the first lock body 141A, and a push-rod electric machine is arranged as locking piece 143A, and push rod is directed at above-mentioned hole,
The push rod of push-rod electric machine is the movable block 1431A of locking piece 143A, and push rod, which is inserted into above-mentioned hole, can block the first lock body
The sliding rail of 141A makes the second lock body 142A that can not slide the main frame 11C of realization and the locking from the relative position of frame 12C.
Please refer to Figure 11-Figure 12, in the application, rotor 200 is mounted in first support 500, since outline border 10 is can to receive
Contracting, therefore outline border 10, when shrinking, internal rotor 200 should be rotated to the position for not stopping outline border 10 to shrink.Rotation
The wing 200 includes pedestal 210 and blade 220, and the rotor 200 is mounted on motor 230, and motor 230 controls rotor 200 and rotates.
In the application, the rotor 200 of two panels blade 220 can be used, when outline border 10 needs to shrink, it is only necessary to by two panels blade
220 rotations are extremely the contraction that can avoid stopping outline border 10 with the perpendicular position of 10 shrinkage direction of outline border.In the application, it can make
More rotors also can be used with single rotor, when for more rotors, each rotor 200 is operated respectively, with single rotor 200
Working principle be it is the same, be introduced hereinafter by example of single rotor.
But in addition to the rotor structure of above-mentioned two panels blade 220, it is also provided with three pieces and three pieces or more.It please join
Figure 11-Figure 12 is read, when being provided with multi-disc blade 220, it is foldable blade that at least a piece of blade 220, which is arranged, passes through control
It makes the blade 220 to fold, the contraction of Lai Shiying outline border 10.
In one embodiment, the structure of foldable blade is that the root of blade 220 and the link position of pedestal 210 are arranged to
Articulated structure 250 is rotated up to the purpose of blade folding storage by the blade 220 around the axis of articulated structure 250.Foundation
The structure of above-mentioned contractile outline border 10, the part blade of rotor 200, which may not be needed to fold, can compress outline border 10, this portion
Blade is divided to can be set to fixed blades.
Further, in the wherein side of the hinge position of above-mentioned folding blade 220, it is additionally provided with limit baffle
231, it is made toward excessive deflection on non-collapsible direction so that blade blocking mechanism 240 can not stop the blade to avoid blade 220
It can not be folded at the blade.
When the quantity of blade 220 is greater than two panels, before carrying out outline border 10 and shrinking, need first by folding blade 220
It is folded.There are many ways to blade 220 folds is controlled, in the embodiment of the application, please refers to Figure 11-Figure 12, is led to
It crosses setting blade blocking mechanism 240 and promotes the blade 220 to carry out to apply a barrier force to the foldable blade 220 of rotation
It folds.
Further, the blade blocking mechanism 240 is push-rod electric machine structure, when blade 220 needs to be folded,
Rotor positioner 30 controls rotor 200 and rotates, before the blade 220 rotation to blocking mechanism 240, rotor positioner
30 control push-rod electric machines stretch out push rod 241, and push-rod electric machine as shown in figure 11 has stretched out push rod 241, when blade 220 continues along push rod
When direction is mobile, the push rod 241 of the push-rod electric machine stops the blade 220, since blade 220 can be with articulated structure
Axis rotation, which is folded, further, if foldable blade 220 contacted after being folded behind blade be also that can roll over
Folded blade, will push subsequent foldable blade 220 and is also folded, be as shown in figure 12 folded rotor.
Further, when needing to fold multiple blades 220, above-mentioned blade folding process is repeated, so that it may complete all
The folding of blade.
In another embodiment, blade blocking mechanism can use magnetic means also to realize, specific control method are as follows:
Magnet or ferromagnet are installed on folding blade 220, install one in the first support 500 of installation rotor 200 or outline border 10
A electromagnet, when needing to carry out the folding of blade 220, be powered to electromagnet generates magnetic force, is mounted with magnet or iron
When the blade of magnet passes through electromagnet, above-mentioned magnetic force stops folding blade 220 to continue to rotate, to fold the paddle being blocked
Leaf 220.
Further, in this application, rotor 200 rotate specific location and blade blocking mechanism 240 work when
Machine is controlled by rotor position induction device 20 and the mutual cooperation of rotor positioner 30.Rotor position induction device 20
The specific location being presently in for determining the rotor 200；Rotor positioner 30 is used to be felt according to the rotor position
It answers the sensed data of device 20 to control the rotor 200 to rotate to target position, so that blade blocking mechanism 240 can accurately stop
The blade 220 to be folded simultaneously is completed to fold, and after all folding blades 220 are folded, then rotor 200 is rotated and extremely recycles position
It sets, it is made not interfere the storage of outline border 10.
Figure 13 is please referred to, the rotor position induction device 20 includes that the first induction component 21 and second incude component 22,
In one embodiment, the rotor position induction device 20 can use contact induction mode, i.e., the first induction 21 He of component
Second induction component 22 is contact electrical connection, and when the first induction component 21 rotates, the second induction component 22 can pass through
The on-off or resistance variations that detect electrical connection determine the position of rotor 200.Since the revolving speed of rotor 200 is very high, using contact
Induction mode reliability is not high.The preferred design of the rotor position induction device 20 is to use non-contact inductive mode, non-
Contact induction mode includes a passive indicator and an active inductor, and the inductor can non-contactly incude
The position of rotor 200 is determined to the state change of indicator.Using contactless inductive mode, component 21 can be incuded by first
It is set to indicate that device and the second induction component 22 are set as inductor, or the first induction component 21 can be set as inductor and second
Induction component 22 is set to indicate that device, and the two working principle is identical.It should be understood that since inductor is active device,
If inductor is rotated with rotor 200, power supply and data transmission are more troublesome, and preferred design is to set passive indicator to
First induction component 21 is with rotor wing rotation.
In one embodiment, rotor position induction device 20 is to be based on photoelectric sense technology, under such structure, is implemented one
In example, the first induction component 21 is a baffle being arranged on pedestal 210, and the second induction component 22 is an optoelectronic transceiver
Device can shelter from a part of light, at this time optoelectronic transceivers when above-mentioned baffle is rotated to the light transceiver channel of optoelectronic transceivers
Receive light be blocked generation pulse information to determine the current position of rotor 200.
Further, if rotor 200 itself has had identifiable feature, above-mentioned baffle is not needed, can directly be utilized
The identifiable feature is come the specific location that judges rotor wing rotation, such as when rotor 200 only has two panels blade 220, directly
It connecing using blade 220 as the first induction component 21, a kind of feasible scheme is, the first induction component 21 is blade 220, second
Induction component 22 is detachable optoelectronic transceivers, including photoemitter and photelectric receiver, can pacify photoemitter
On outline border 10, photelectric receiver is mounted in first support 500, when the rotation of blade 220 to photoemitter and photoelectricity
Between receiver, then stop the transmission of light, the position that rotor 200 rotates is determined with this.
Further, magnetosensitive sensing technology can be used in the position induction device 20.Component 21 and second is incuded by first
Magnet and magnetic inductor is respectively adopted in induction component 22, any one for allowing in magnet and magnetic inductor is mounted on pedestal 210,
And rotor 200 is followed to rotate, another is fixed, and can determine the specific position that rotor 200 rotates when magnetic inductor senses magnet
It sets.Since the induction region of magnet and magnetic induction device may be a regional value, but the magnetic flux that generates of different distance or
Person's magnetic strength dynamics be it is different, precise positioning can also be carried out by the characteristic.
Further, the rotor position induction device 20 can also use magnetic force induction mode, by ferromagnet and electromagnetism
Iron is constituted.It is mounted on ferromagnet as the first induction component 21 on rotor 200, electromagnet is installed as the second induction component 22
On outline border 10 or first support 500, its working principle is that: rotor positioner 30 controls electromagnet power-up and generates magnetic
, the resistance that ferromagnet rotation is rotated by will increase rotor 200 when electromagnet, the persistently detection input of rotor positioner 30
The power change of motor can determine that ferromagnet passes through near electromagnet when the electric energy of input reaches the threshold value of a setting,
And then determine the position of rotor.
It is worth noting that the rotor position induction device 20 and the blade noted earlier using magnetic force using magnetic force stop
Mechanism 240 can share physical unit in specific implementation, and the magnetic force between ferromagnet and electromagnet can be used to incude rotation
Wing position can be used for stopping blade rotation.
Further, non-contact sensing technology is there are also electromagnetic induction technology, electric field induction technology etc., these induction technologies are all
It can be used for realizing rotor position induction device 20, working principle is same as the previously described embodiments.
Further, what control rotor 200 rotated is motor 230, and motor 230 includes stator and rotor, in another implementation
In example, the first induction component 21 and the second induction component 22 can be installed respectively on the stator and rotor of motor 230, in motor
The induction of 200 position of rotor can be realized in 230 inside.
Further, the first above-mentioned induction component 21 and the second induction component 22 are not limited to distinguish only one, also
Can be respectively arranged with it is multiple, to realize the function of multipoint positioning.A kind of feasible embodiment is to be arranged on pedestal 210
When a series of first induction component 21, each first induction component 21 and the second induction component 22 generate interaction, then send out
A positioning signal out, rotor 200 rotates a circle under this mode, can receive a series of positioning signals, realizes the more of rotor 200
Point location.
In another embodiment, it is arranged a circular magnet in the rotary shaft of motor 230 as first and incudes component 21,
The magnet is rotated with rotor 200, and magnetic direction and then rotates, which would indicate that the position of rotor 200, corresponding
, a magnetic inductor is set on outline border 10 or first support 500 as the second induction component 22, magnetic induction device passes through induction
Rotating magnetic direction can continuously determine the position of rotor 200.
In another embodiment, a characteristic point is set on the pedestal 210 of rotor 200 as first and incudes component 21,
Use a camera as the second induction component 22, camera shoots the image of pedestal 210, exists by the characteristic point for analyzing above-mentioned
Position in image is assured that the position of rotor, such as with 60 frames/second camera, is assured that within every 1/60 second
Rotor position, can continuously determine the position of rotor 200.
After the accurate location of rotor 200 has been determined by rotor position induction device 20, foldable blade 220 is being carried out
Folding or by the rotation of rotor 200 to the designated position for facilitating outline border 10 to store when, need rotor positioner 30 to carry out
Control.
In one embodiment, rotor positioner 30 is an electronic module, includes microprocessor and motor control electricity
Road, comprising realizing the folding of foldable blade 220 and by the soft of the rotation of rotor 200 to the functions such as recyclable position in microprocessor
Part module.The position for the rotor 200 that rotor positioner 30 is fed back according to rotor position induction device 20, judges rotor 200
The angle in the direction and rotation that need to rotate makes the rotation of rotor 200 complete above-mentioned function to control 230 low speed rotation of motor.Into
One step, rotor positioner 30 can be independent functional module, be also possible to the motor control with control unmanned plane during flying
The functional module that molding block integrates, quovis modo exist, its working principle is that the same.
Further, the outer of the outline border 10 of the application is also arranged with a protection net cover 15, and shown in Fig. 8 is shown in Fig. 7
Outline border 10 on be arranged protection net cover.The protection net cover 15 is made by elastic material, and elastic material is suitable for outline border 10
Scaling, and main frame 11 can be tensed with from the gap of frame 12, the vibration of outline border 10 is reduced, meanwhile, using elastic material, pressing
When contracting outline border 10, protection net cover 15 can make pushing force more balanced.Net cover 15 is protected to be arranged to mesh-structured, structure is simply light
Just.
Further, the rotor protective device 100 of the application further includes that the position induction device of an outline border 10 (is schemed not
Show), for determining whether outline border 10 is deployed into maximum volume, and then determine whether to start to drive rotor wing rotation.One kind can
Capable embodiment is the switching regulator component being arranged on locking mechanism 14, when outline border 10 is locked in maximum volume, switching regulator
Component exports indication signal；Another feasible embodiment is that a label is arranged in outline border 10, and sense is arranged in first support 500
Device is answered, when outline border 10 is in maximum volume, the inductor can sense the label output indication signal.
The present invention discloses a kind of unmanned plane, please refers to Figure 14-Figure 15, including described in above-mentioned any one it is shrinkable nobody
100, two motors of rotor protective device, two rotors 200 of machine, flight controller (not shown), fuselage 400, first support
500, second support 600, the first rotating mechanism 700 and the second rotating mechanism 800, described two motors are mounted on one on the other
On one bracket 500, described two rotors 200 are separately mounted on two motors, and the direction of rotation of two rotors 200 is opposite；Institute
It states rotor protective device 100 to be mounted in first support 500, wherein by upper and lower two rotors 200 package；The first support
500 connect simultaneously relative rotation, the second support 600 and machine by first rotating mechanism 700 with the second support 600
Body 400 is by the connection of the second rotating mechanism 800 and relative rotation, and the flight controller is by controlling first rotating mechanism
700 and second rotating mechanism 800 control the rotor 200 around the rotary shaft of the first rotating mechanism 700 and second rotate
The inclination angle of the rotary shaft of mechanism 800.
In one embodiment, flight controller is accommodated in inside fuselage 400, and fuselage 400 is whole L-shaped, and one end is hanging,
The other end is connect by the second rotating mechanism 800 with second support 600, and the second support 600 is also L-shaped, and one end passes through
Second rotating mechanism 800 is connect with fuselage 400, and the other end is connect by the first rotating mechanism 700 with first support 500, and second
Bracket 600 can relative to fuselage 400 around Y-axis rotate, first support 500 drive outline border 100 relative to second support 600 around
X-axis rotation.
Further, first rotating mechanism 700 includes the first spindle nose 710, first bearing 720 and the first servomechanism
730, first spindle nose 710 is fixedly connected with first support 500, the first bearing 720 and first servomechanism 730 with
Second support 600 is fixedly connected or first spindle nose 710 is fixedly connected with the second support 600, the first bearing
720 and first servomechanism 730 be fixedly connected with the first support 500；First servomechanism 730 is by direct current generator and deceleration
Transmission mechanism composition, flight controller control the first servomechanism 730 driving first support 500 and rotate around X-axis.
Second rotating mechanism 800 includes the second spindle nose 810, second bearing 820 and the second servomechanism 830, and described the
Two spindle noses 810 are fixedly connected with the second support 600, the second bearing 820 and second servomechanism 830 and fuselage
400 are fixedly connected or the second bearing 820 and second servomechanism 830 are fixedly connected with the second support 600,
Second spindle nose 810 is fixedly connected with the fuselage 400.Second servomechanism 830 is by direct current generator and reduction gearing mechanism group
At flight controller controls the second servomechanism 830 driving second support 600 and rotates around Y-axis.
The working principle of above structure is: the thrust center of the rotor 200 of unmanned plane is on the intersection point of X-axis and Y-axis, nothing
Man-machine fuselage 400 is in 200 lower section of rotor, since fuselage 400 includes the functional module of most of unmanned plane, such as flight control
Device, battery, camera etc. are assigned with most of weight of unmanned plane, and based on the supporting role of fuselage gravity, flight controller can be with
Second support 500 is controlled by the first servomechanism 730 and the second servomechanism 830 to rotate around X-axis and Y-axis, and then controls rotor
Protective device 100 verts along X-axis and Y-axis, realizes the pitch angle control of rotor.
Flight controller controls rotor 200 in pitch axis and rolling by the first rotating mechanism 700 and the second rotating mechanism 800
Inclination angle in shaft, the revolving speed by controlling described two motors adjust the lift and yawing that rotor 200 generates, complete nothing
Man-machine flight control.
In another embodiment, Figure 16 is please referred to, which uses a circular rotor protective device 100B, fuselage
400B is in U-typed structure, and second support 600B is also in U-typed structure, first support 500B by the first rotating mechanism 700B with
Second support 600B connection, one end of fuselage 400B are connect with the second rotating mechanism 800B, and third rotation is provided on the other end
Mechanism 900B, the third rotating mechanism 900B include third spindle nose and 3rd bearing, and third spindle nose and 3rd bearing are mutually suitable
With so that the second support 600B relative to fuselage 400B rotate, due to no servomechanism on third rotating mechanism 900B, and
One of them is mounted on second support 600B for third spindle nose or 3rd bearing, therefore the rotation of third rotating mechanism 900B
Synchronous rotary is kept with the second rotating mechanism 800B.This fuselage 400B is more balanced in its stress of " U " font structure, is suitable for
Large volume of unmanned plane.Its working principle is similar with the structure of the first above-mentioned unmanned plane, and details are not described herein again.
Although having been illustrated with some exemplary embodiments of the invention above, those skilled in the art will be managed
Solution can make a change these exemplary embodiments, this hair in the case where not departing from the principle or spirit that the present invention invents
The range of bright invention is defined by the claims and their equivalents.
Claims (12)
1. a kind of shrinkable unmanned plane rotor protective device, which is characterized in that the protection of the rotor applied to unmanned plane, comprising:
Outline border: being set in outside the rotor, and the outline border is the scalable type structure of size；
Rotor position induction device: for determining the position of the rotor；
Rotor positioner: extremely may be used for controlling the rotor wing rotation according to the sensed data of the rotor position induction device
For the designated position that outline border is shunk, so that the rotor does not interfere the contraction of the outline border.
2. shrinkable unmanned plane rotor protective device according to claim 1, which is characterized in that the outline border includes main frame
With at least one from frame, the main frame is connect from frame by movable part with described, so that described living relative to the main frame from frame
Dynamic expansion or contraction to realize the outline border.
3. shrinkable unmanned plane rotor protective device according to claim 2, which is characterized in that it further include locking mechanism,
The locking mechanism is mounted on the outline border, to lock the main frame and the relative position from frame.
4. shrinkable unmanned plane rotor protective device according to claim 3, which is characterized in that the locking mechanism includes
First lock body and the second lock body are provided with the first fixed part on first lock body, be provided on second lock body with it is described
First fixed part adaptation the second fixed part, second fixed part locked when being moved to first fixed part main frame and
First lock body described in when the relative position from frame, second fixed part are detached from the first fixed part and second lock body can
Opposite sliding.
5. shrinkable unmanned plane rotor protective device according to claim 3, which is characterized in that the locking mechanism includes
First lock body, the second lock body and locking piece, first lock body are equipped with locking bit, and the locking piece includes a movable block,
The locking piece is mounted on the position that the movable block can be placed in the locking bit of first lock body, and the movable block is placed in institute
The main frame and the relative position from frame are locked when stating locking bit；First described in when the movable block removal locking bit
Lock body sliding opposite with second lock body.
6. shrinkable unmanned plane rotor protective device according to claim 3, which is characterized in that the locking mechanism includes
Push-rod electric machine, the both ends of the push-rod electric machine are separately mounted to the both ends of the outline border, and the push-rod electric machine releases push rod, described
The both ends of push-rod electric machine are relatively distant to drive the main frame to be unfolded with from the opposite sliding of frame, when retracting the push rod,
The main frame is slided with from frame is opposite to be shunk, and locking is worked as when the push-rod electric machine stops releasing or shrinking the push rod
Preceding main frame and the relative position from frame.
7. shrinkable unmanned plane rotor protective device according to claim 1, which is characterized in that the rotor location sensitive
Device includes the first induction component and the second induction component, and the first induction component and the rotor rotate synchronously, and described the
Two induction components and the first induction component interaction determine the position of the first induction component, and then determine the rotation
The position of the wing.
8. shrinkable unmanned plane rotor protective device according to claim 1, which is characterized in that the rotor includes pedestal
And blade, the pedestal are mounted on motor, the blade is connect with pedestal, and the blade is at least provided with three pieces, and at least
Wherein a piece of blade is foldable blade, and the wherein one end of the foldable blade passes through articulated structure and the pedestal
Connection, the foldable blade are folded using articulated structure as axis relative to pedestal.
9. shrinkable unmanned plane rotor protective device according to claim 8, which is characterized in that stop machine including blade
Structure, the blade blocking mechanism are arranged inside the outline border, and the blade blocking mechanism acts on the foldable blade, with
The foldable blade is stopped to continue to rotate and folded along direction of rotation.
10. shrinkable unmanned plane rotor protective device described in -9 any one according to claim 1, which is characterized in that also wrap
Protection net cover is included, the protection net cover is made by elastic material, and the protection net cover is mounted on the outer of the outline border.
11. a kind of unmanned plane, which is characterized in that including shrinkable unmanned plane described in the claims 1-10 any one
Rotor protective device, rotor, flight controller, fuselage, first support, second support, the first rotating mechanism and the second whirler
Structure, the rotor protective device and the rotor are mounted in first support, and the first support passes through with the second support
The first rotating mechanism connection and relative rotation, the second support is connect with the fuselage by the second rotating mechanism and phase
To rotation, the flight controller controls the rotor by controlling first rotating mechanism and second rotating mechanism
Inclination angle.
12. unmanned plane according to claim 11, which is characterized in that first rotating mechanism includes the first spindle nose, the
One bearing and the first servomechanism, first spindle nose are fixedly connected with the first support, the first bearing and described first
Servomechanism is fixedly connected with the second support or first spindle nose is fixedly connected with the second support, and described first
Bearing and first servomechanism are fixedly connected with the first support, and the first support and the second support are described in
First bearing is connected with first spindle nose, and first servomechanism can control the first support to rotate around connecting shaft；
Second rotating mechanism includes the second spindle nose, second bearing and the second servomechanism, second spindle nose and described second
Bracket is fixedly connected, the second bearing and second servomechanism is fixedly connected with the fuselage or the second bearing
It being fixedly connected with second servomechanism with the second support, second spindle nose is fixedly connected with the fuselage, and described
Two brackets are connected by the second bearing with second spindle nose with the fuselage, and second servomechanism can control described
Two brackets are rotated around connecting shaft.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810936269.9A CN109677600A (en) | 2018-08-16 | 2018-08-16 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
| PCT/CN2019/100519 WO2020034980A1 (en) | 2018-08-16 | 2019-08-14 | Retractable unmanned aerial vehicle rotor protection device and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810936269.9A CN109677600A (en) | 2018-08-16 | 2018-08-16 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109677600A true CN109677600A (en) | 2019-04-26 |
Family
ID=66185646
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810936269.9A Pending CN109677600A (en) | 2018-08-16 | 2018-08-16 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN109677600A (en) |
| WO (1) | WO2020034980A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020034980A1 (en) * | 2018-08-16 | 2020-02-20 | 深圳市格上格创新科技有限公司 | Retractable unmanned aerial vehicle rotor protection device and unmanned aerial vehicle |
| CN114852331A (en) * | 2022-06-15 | 2022-08-05 | 清华大学 | Manned flying automobile with form intelligence |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB852841A (en) * | 1957-12-10 | 1960-11-02 | Westland Aircraft Ltd | Improvements in or relating to rotary wing aircraft |
| US3484175A (en) * | 1967-10-12 | 1969-12-16 | United Aircraft Corp | Means and method of synchronously folding helicopter blades |
| CN205150234U (en) * | 2015-10-21 | 2016-04-13 | 黄彰标 | Rotor protector and use device's unmanned aerial vehicle |
| CN106585975A (en) * | 2017-01-22 | 2017-04-26 | 云南集优科技有限公司 | Compact unmanned aerial vehicle |
| CN106741943A (en) * | 2016-12-23 | 2017-05-31 | 歌尔科技有限公司 | A kind of unmanned plane |
| WO2018090790A1 (en) * | 2016-11-11 | 2018-05-24 | 杨超峰 | Rotor control mechanism and dual-rotor blade unmanned aerial vehicle |
| CN208813503U (en) * | 2018-08-16 | 2019-05-03 | 深圳市格上格创新科技有限公司 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020104922A1 (en) * | 2000-12-08 | 2002-08-08 | Mikio Nakamura | Vertical takeoff and landing aircraft with multiple rotors |
| US20100224723A1 (en) * | 2009-03-03 | 2010-09-09 | Jacob Apkarian | Aerial vehicle |
| CN205707325U (en) * | 2016-04-26 | 2016-11-23 | 普宙飞行器科技（深圳）有限公司 | Telescopic blade driving means and unmanned plane |
| CN107054622B (en) * | 2016-12-05 | 2023-12-05 | 普宙科技有限公司 | Telescopic unmanned aerial vehicle |
| CN107108026B (en) * | 2016-12-30 | 2019-05-31 | 深圳市大疆创新科技有限公司 | Multi-rotor aerocraft and its expansion of propeller protective cover and/or folding method |
| CN206826934U (en) * | 2017-05-13 | 2018-01-02 | 兰州大学 | A kind of concertina type protection device of unmanned plane screw wing |
| CN107472532A (en) * | 2017-08-01 | 2017-12-15 | 河南省酷农航空植保科技有限公司 | A kind of scalable comprehensive protection device of unmanned plane |
| CN109677600A (en) * | 2018-08-16 | 2019-04-26 | 深圳市格上格创新科技有限公司 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
-
2018
- 2018-08-16 CN CN201810936269.9A patent/CN109677600A/en active Pending
-
2019
- 2019-08-14 WO PCT/CN2019/100519 patent/WO2020034980A1/en active Application Filing
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB852841A (en) * | 1957-12-10 | 1960-11-02 | Westland Aircraft Ltd | Improvements in or relating to rotary wing aircraft |
| US3484175A (en) * | 1967-10-12 | 1969-12-16 | United Aircraft Corp | Means and method of synchronously folding helicopter blades |
| CN205150234U (en) * | 2015-10-21 | 2016-04-13 | 黄彰标 | Rotor protector and use device's unmanned aerial vehicle |
| WO2018090790A1 (en) * | 2016-11-11 | 2018-05-24 | 杨超峰 | Rotor control mechanism and dual-rotor blade unmanned aerial vehicle |
| CN106741943A (en) * | 2016-12-23 | 2017-05-31 | 歌尔科技有限公司 | A kind of unmanned plane |
| CN106585975A (en) * | 2017-01-22 | 2017-04-26 | 云南集优科技有限公司 | Compact unmanned aerial vehicle |
| CN208813503U (en) * | 2018-08-16 | 2019-05-03 | 深圳市格上格创新科技有限公司 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020034980A1 (en) * | 2018-08-16 | 2020-02-20 | 深圳市格上格创新科技有限公司 | Retractable unmanned aerial vehicle rotor protection device and unmanned aerial vehicle |
| CN114852331A (en) * | 2022-06-15 | 2022-08-05 | 清华大学 | Manned flying automobile with form intelligence |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2020034980A1 (en) | 2020-02-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109677600A (en) | A kind of shrinkable unmanned plane rotor protective device and unmanned plane | |
| CN208813503U (en) | A kind of shrinkable unmanned plane rotor protective device and unmanned plane | |
| CN104580606B (en) | A kind of mobile phone shell that can be changed into unmanned plane | |
| CN105416578B (en) | wearable unmanned aerial vehicle | |
| JP5826837B2 (en) | Hexapod | |
| KR101410492B1 (en) | Solar photovoltaic power generation device | |
| CN107406141A (en) | Carrier with the motor rotated between raised position and propulsion position configures | |
| CN210681128U (en) | Foldable survey and drawing unmanned aerial vehicle | |
| CN106341023A (en) | Multi-Degree Of Freedom Spherical Actuator | |
| CN103072687A (en) | Landing gear, an aircraft, and a method implemented by landing gear | |
| CN108162795B (en) | Aerial aircraft is with supporting aerial power supply unit of solar energy | |
| CN206202711U (en) | A kind of head and unmanned plane | |
| CN206906771U (en) | A kind of picture shooting assembly | |
| US9172287B2 (en) | Actuator configuration for a rotary drive | |
| ES2768376T3 (en) | Performance optimized turbine | |
| CN204235896U (en) | A kind of three-dimensional printer | |
| JP6919514B2 (en) | Aircraft for power generation | |
| CN106005453A (en) | Unmanned aerial vehicle nacelle retracting mechanism and assembly method | |
| WO2018201417A1 (en) | Deformable aircraft, mobile platform and operating method therefor | |
| CN108758513A (en) | A kind of intelligent wind and light complementary road lamp that the generating efficiency with detection function is high | |
| JP3338065B2 (en) | Apparatus for displaying alphanumeric and / or graphic codes | |
| CN104459935A (en) | Thin film condensing lens structure with lens face automatically folded, unfolded, positioned and spliced | |
| CN206117467U (en) | Two degrees of freedom of non - spherical orthohormbic structure hybrid step motor | |
| CN109436306A (en) | A kind of unmanned plane rotor protective cover with Fast Installation structure | |
| CN110104199A (en) | A kind of lifting gear for unmanned plane Air Launched Platform |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20240605 Address after: 325500 Shangyuan Village, Sixi Town, Taishun County, Wenzhou City, Zhejiang Province Applicant after: Zeng Daxun Country or region after: China Address before: 518035, Block B, Runchuangxing Era Apartment, Bantian Street, Longgang District, Shenzhen City, Guangdong Province, China 1220 Applicant before: SHENZHEN GRIDMORE INNOVATIVE TECHNOLOGY Co.,Ltd. Country or region before: China |