CN105000163A - Downwards foldable-type multi-rotor wing unmanned aerial vehicle - Google Patents
Downwards foldable-type multi-rotor wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105000163A CN105000163A CN201510519756.1A CN201510519756A CN105000163A CN 105000163 A CN105000163 A CN 105000163A CN 201510519756 A CN201510519756 A CN 201510519756A CN 105000163 A CN105000163 A CN 105000163A
- Authority
- CN
- China
- Prior art keywords
- hold
- rotor unmanned
- downward
- unmanned aircrafts
- latch assembly
- 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.)
- Granted
Links
Abstract
The invention discloses a downwards foldable-type multi-rotor wing unmanned aerial vehicle (1000) which comprises a power device (200), a camera shooting device (300), a cell system (400), a control circuit (600), a plurality of support arms (110), a central mounting seat (120) and a locking component (150), wherein the power device (200), the camera shooting device (300) and the cell system (400) are connected with the control circuit (600) separately; the support arms (110) are rotationally connected onto the central mounting seat (120); the locking component (150) is used for locking all the support arms (110) on the central mounting seat (120) simultaneously when the support arms (110) are unfolded. As the support arms are rotationally connected onto the central mounting seat and can be folded downwards, the size of the unmanned aerial vehicle is reduced to the great extent.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, be specifically related to a kind of downward collapsible many rotor unmanned aircrafts.
Background technology
Unmanned vehicle has unique flight performance, and volume is little, taking photo by plane, air detection, traffic monitoring, resource exploration, electric inspection process, forest fire protection, agricultural, military etc. in there is prospect widely.Existing many rotor unmanned aircrafts usually rotate paddle by motor and obtain lift.The rotor of existing many rotor unmanned aircrafts is supported by hold-down arm, and the volume of whole aircraft becomes very large, causes very large inconvenience to carry, deposit etc.
Summary of the invention
The object of the invention is to, provide a kind of downward collapsible many rotor unmanned aircrafts, it can by the folding volume reducing aircraft to greatest extent.
The present invention is achieved through the following technical solutions: a kind of downward collapsible many rotor unmanned aircrafts, described downward collapsible many rotor unmanned aircrafts comprise engine installation, camera head, battery system, control circuit, many hold-down arms, center mount pad and latch assembly, wherein, described engine installation, described camera head and described battery system are connected with described control circuit respectively, described many hold-down arms are rotatably connected on the mount pad of described center, described latch assembly is for being locked at described center mount pad when described many hold-down arms launch by described many hold-down arms simultaneously.
As the further improvement of technique scheme, described control circuit to be arranged on the mount pad of described center and to be positioned at the top of described latch assembly.
As the further improvement of technique scheme, each hold-down arm of described many hold-down arms is cylindrical, and each hold-down arm is the pipe fitting of the spatial accommodation with the rechargeable battery holding described battery system.
As the further improvement of technique scheme, described downward collapsible many rotor unmanned aircrafts also comprise multiple alighting gear, described multiple alighting gear is rotatably connected on described multiple hold-down arm respectively, the shape of described multiple alighting gear is mated to be attached to when described many hold-down arms fold on the outside face of described multiple hold-down arm respectively with the shape of described multiple hold-down arm, and described multiple alighting gear is provided with antenna.
As the further improvement of technique scheme, described engine installation comprises multiple motor and multiple screw propeller, each motor of described multiple motor is fixedly installed on above the free end of each hold-down arm of described many hold-down arms, and described multiple screw propeller is fast disassembly type screw propeller or foldable propeller.
As the further improvement of technique scheme, described downward collapsible many rotor unmanned aircrafts are four rotor unmanned aircrafts, six rotor unmanned aircrafts or eight rotor unmanned aircrafts.
As the further improvement of technique scheme, described camera head comprises interconnective damping, quick detach The Cloud Terrace and camera successively, described damping has multiple furcation, and when described many hold-down arms fold, described quick detach The Cloud Terrace and described camera depart from described damping and described many hold-down arms lay respectively between described multiple furcation.
As the further improvement of technique scheme, on the mount pad of described center, circumference is evenly formed with multiple notch part, described many hold-down arms are correspondingly provided with multiple lug boss, and when described many hold-down arms launch, each lug boss of described multiple lug boss is correspondingly positioned at each notch part of described multiple notch part.
As the further improvement of technique scheme, described latch assembly is arranged to rotate freely around the center of described center mount pad, described latch assembly has multiple extension tight lock part, each extension tight lock part has the stopper section of stretching out downwards, when described latch assembly rotates to locked position, the inside face of described stopper section correspondingly abuts the outside face of each lug boss of described multiple lug boss, and the outside face of each lug boss of described multiple lug boss is the curved surfaces mated with the outside face of described center mount pad.
As the further improvement of technique scheme, described latch assembly has multiple extension tight lock part and force application part, described force application part is arranged to push described latch assembly towards the direction near described center mount pad, each extension tight lock part has the stopper section of stretching out downwards, and when described latch assembly is positioned at locked position, the inside face of described stopper section correspondingly abuts the outside face of each lug boss of described multiple lug boss.
The invention has the beneficial effects as follows: according to downward collapsible many rotor unmanned aircrafts of the present invention, many hold-down arms are rotatably connected on the mount pad of center, and many hold-down arms can fold gathering downwards, reduce the volume of aircraft to greatest extent.
Accompanying drawing explanation
Fig. 1 is the electric formation schematic block diagram of the downward collapsible many rotor unmanned aircrafts according to an embodiment of the invention;
Fig. 2 is the schematic perspective view of downward collapsible many rotor unmanned aircrafts of Fig. 1;
Fig. 3 is another schematic perspective view of downward collapsible many rotor unmanned aircrafts of Fig. 1;
Fig. 4 is a schematic perspective view again of downward collapsible many rotor unmanned aircrafts of Fig. 1, and show alighting gear and be in collapsed state, alighting gear is attached on hold-down arm;
Fig. 5 is the enlarged drawing at A place in Fig. 4, shows hold-down arm and launches but the state of the assembly locking that is not locked;
Fig. 6 is the another schematic perspective view of downward collapsible many rotor unmanned aircrafts of Fig. 1, and show alighting gear and be in collapsed state, alighting gear is attached on hold-down arm;
Fig. 7 is the enlarged drawing at B place in Fig. 6, shows hold-down arm and launches and the state of the assembly locking that is locked;
Fig. 8 shows the decomposing state of the latch assembly of center mount pad and the first embodiment;
Fig. 9 shows the assembled state of the latch assembly of center mount pad and the first embodiment;
Figure 10 is the front schematic view of the latch assembly of display first embodiment;
Figure 11 is the elevational schematic view of the latch assembly of display first embodiment;
Figure 12 is the another schematic perspective view of downward collapsible many rotor unmanned aircrafts of Fig. 1, shows hold-down arm and launches and the state of the assembly locking that is locked;
Figure 13 is the schematic top plan view of downward collapsible many rotor unmanned aircrafts of Fig. 1, shows hold-down arm and launches and the state of the assembly locking that is locked;
Figure 14 is the front schematic view of downward collapsible many rotor unmanned aircrafts of Fig. 1, shows hold-down arm and launches and the state of the assembly locking that is locked;
Figure 15 is the schematic perspective view of the rounding state of downward collapsible many rotor unmanned aircrafts of Fig. 1, shows the state that hold-down arm folds gathering;
Figure 16 is the schematic top plan view of the rounding state of downward collapsible many rotor unmanned aircrafts of Fig. 1, shows the state that hold-down arm folds gathering;
Figure 17 is the schematic perspective view of the hold-down arm of downward collapsible many rotor unmanned aircrafts of Fig. 1, and show alighting gear and be in collapsed state, alighting gear is attached on hold-down arm;
Figure 18 is the enlarged drawing at C place in Figure 17;
Figure 19 is the motor of engine installation and the schematic perspective view of foldable propeller of downward collapsible many rotor unmanned aircrafts of Fig. 1,
Figure 20 shows the decomposing state of the latch assembly of center mount pad and the second embodiment;
Figure 21 shows the assembled state of the latch assembly of center mount pad and the first embodiment;
Figure 22 shows the assembled state of the latch assembly of center mount pad and the first embodiment;
Figure 23 is the front schematic view of the pith of the latch assembly of display first embodiment;
Figure 24 is the elevational schematic view of the pith of the latch assembly of display first embodiment;
Number in the figure implication is as follows: the downward collapsible many rotor unmanned aircrafts of 1000-; 200-engine installation; 300-camera head; 400-battery system; 500-remote controller; 600-control circuit; 610-Department of Communication Force; 700-alighting gear; 110-hold-down arm; 111-rotating hole; 112-lug boss; 1120-outside face; 114-spatial accommodation; 120-center mount pad; 122-notch part; 124-second through wires hole; 126-first through wires hole; 150-latch assembly; 150A-latch assembly; 151-centre hole; 152-extends tight lock part; 154-second breakthrough portion; 156-first breakthrough portion; 158-stopper section; 1582-inside face; 151A-centre hole; 152A-extends tight lock part; 154A-second breakthrough portion; 156A-first breakthrough portion; 158A-stopper section; 1582A-inside face; 210-motor; 220-screw propeller; 310-damping; 311-rotating shaft; 320-quick detach The Cloud Terrace; 160-force application part; 162-guide pillar; 164-Compress Spring; 166-screw; 312-arc space; 314-furcation.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is further detailed.
Be described below in detail embodiments of the invention, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Accompanying drawing understands various embodiments of the present invention for helping, and the dimension scale of each figure in accompanying drawing may be different.Being exemplary below by the embodiment be described with reference to the drawings, only for explaining the present invention, and can not limitation of the present invention being interpreted as.On the contrary, embodiments of the invention comprise fall into attached claims spirit and intension within the scope of all changes, amendment and equivalent.In describing the invention, it is to be appreciated that term " first ", " second " etc. are only for describing object, and instruction or hint relative importance can not be interpreted as.
As shown in Figure 1, downward collapsible many rotor unmanned aircrafts 1000 of the present embodiment comprise engine installation 200, camera head 300, battery system 400, remote controller (not shown) 500, control circuit 600, many hold-down arms 110, center mount pad 120 and latch assemblies 150.Wherein, described engine installation 200, described camera head 300 and described battery system 400 are connected with described control circuit 600 respectively.
Described control circuit 600 covers protection by over cap (not shown).In the present embodiment, described control circuit 600 to be arranged on described center mount pad 120 and to be positioned at the top of described latch assembly 150.Described control circuit 600 has Department of Communication Force 610, is connected, the work such as carries out image passback, data back by Department of Communication Force 610 with two way communication such as external device such as remote controller 500 grade.Control circuit 600 is by CPU (Central ProcessingUnit, central processing unit), ROM (Read Only Memory read-only memory (ROM)), RAM (Random AccessMemory random access memory) and carry out the formations such as the IO interface of the transmitting-receiving of various signal with each parts be electrically connected to each other.The action control of the entirety of downward collapsible many rotor unmanned aircrafts 1000 is responsible for by control circuit 600.ROM stores the job procedure of the groundwork of downward collapsible many rotor unmanned aircrafts 1000.RAM is used as the work area etc. of downward collapsible many rotor unmanned aircrafts 1000.
In downward collapsible many rotor unmanned aircrafts 1000 of the present embodiment, described many hold-down arms 110 can be connected on described center mount pad 120 by rotating shaft rotatably.Described many hold-down arms 110 such as can fold 90 degree to about 100 degree.In the present embodiment, described many hold-down arms 110 can be collapsed into roughly vertically state (time folding) from approximate horizontal state (during expansion) is folding.
Described latch assembly 150 is for being locked at described center mount pad 120 when described many hold-down arms 110 launch by described many hold-down arms 110 simultaneously.As described later, described latch assembly can adopt various forms.As described later, this application provides the embodiment of two kinds of latch assemblies.Described latch assembly can uniformly by disposable for described many hold-down arms 110 and be locked on described center mount pad 120 simultaneously, convenient operation.
In the present embodiment, each hold-down arm 110 of described many hold-down arms 110 is cylindrical, and each hold-down arm 110 is for having the pipe fitting of the spatial accommodation 114 of the columniform rechargeable battery holding described battery system 400.Rechargeable battery can be built in the spatial accommodation 114 of hold-down arm 110.Rechargeable battery is such as 18650 type batteries, 26650 type batteries.Rechargeable battery is built in the spatial accommodation 114 of hold-down arm 110, the structure of aircraft can be simplified further.Like this, when multiple hold-down arm 110 folds 90 degree to about 100 degree downwards, the volume of aircraft can be reduced further.
In the present embodiment, described downward collapsible many rotor unmanned aircrafts 1000 also comprise multiple alighting gear 700, and described multiple alighting gear 700 is rotatably connected on described multiple hold-down arm 110 respectively by rotating shaft.The shape of described multiple alighting gear 700 is mated to be attached to when described many hold-down arms 110 fold on the outside face of described multiple hold-down arm 110 respectively with the shape of described multiple hold-down arm 110.Multiple alighting gear 700 is schistose texture.As shown in figure 15, like this, when folding 90 degree to about the 100 degree gatherings downwards of multiple hold-down arm 110, multiple alighting gear 700 is attached on the outside face of described multiple hold-down arm 110, substantially volume is not occupied, mutually do not interfere between multiple alighting gear 700, can reduce further aircraft folding after volume.In addition, described multiple alighting gear 700 is provided with antenna.Antenna can be such as FPC antenna, PCB antenna, spring antenna or feeder antenna etc.In addition, antenna also can be arranged on the mount pad of center or on The Cloud Terrace.
In the present embodiment, described engine installation 200 comprises multiple motor 210 and multiple screw propeller 220, each motor 210 of described multiple motor 210 is fixedly installed on above the free end of each hold-down arm 110 of described many hold-down arms 110, and described multiple screw propeller 220 is fast disassembly type screw propeller or foldable propeller.But the present invention is not limited thereto, screw propeller 220 also can be common paperback slurry.Figure 19 shows foldable propeller.The structure example of screw propeller 220 is as adopted the disclosed structure of Chinese utility model patent application CN201320311523.9 (applicant: Shenzhen Dajiang Innovation Technology Co., Ltd.).When multiple hold-down arm 110 folds 90 degree to about 100 degree downwards, multiple screw propeller 220 is pulled down from motor 210.
Although in the illustrated embodiment in which, downward collapsible many rotor unmanned aircrafts 1000 are four rotor unmanned aircrafts, but the present invention is not limited thereto, described downward collapsible many rotor unmanned aircrafts can be four rotor unmanned aircrafts, six rotor unmanned aircrafts or eight rotor unmanned aircrafts.
In the present embodiment, as shown in Figure 1, described camera head 300 comprises interconnective damping 310, quick detach The Cloud Terrace 320 and camera (not shown) successively.Described damping 310 has multiple furcation 314.When described many hold-down arms 110 folding gathering, described quick detach The Cloud Terrace 320 and described camera depart from described damping 310, and namely described quick detach The Cloud Terrace 320 and described camera are pulled down from described damping 310.Described damping 310 such as can adopt the disclosed structure of Chinese invention patent application CN201480001516.6 (applicant: Shenzhen Dajiang Innovation Technology Co., Ltd.).And described many hold-down arms 110 lay respectively between described multiple furcation 314.
Shown in composition graphs 8 and Figure 15, multiple hold-down arm 110 downwards folding 90 degree to about 100 degree time, in the arc space 312 of hold-down arm 110 just between multiple furcation 314.Like this, when multiple hold-down arm 110 folds 90 degree to about 100 degree downwards, the volume of aircraft can be reduced further.
In addition, quick detach The Cloud Terrace 320 can carry optical device, such as pick up camera, photographic camera, glass, remote camera and survey meter etc., in order to realize described optical device fixing, arbitrarily regulate the attitude of described optical device (such as: change the height of described optical device, inclination angle, shooting direction and/or described optical device is stablized in the attitude that remains on and determine), to realize special quality shooting and/or photograph etc.
As mentioned above, described latch assembly is used for launching, when preparing flight, described many hold-down arms 110 are locked at described center mount pad 120 simultaneously at described many hold-down arms 110.By operation latch assembly, can once lock many hold-down arms 110, fast and reliable.
Although the invention provides the latch assembly (revolving latch assembly 150 and portable latch assembly 150A) of two kinds of modes; but those of ordinary skill in the art easily can find out variation according to the present invention, these variation ought to fall into protection scope of the present invention.
The latch assembly of the first embodiment is introduced below in conjunction with accompanying drawing.The latch assembly of the first embodiment is revolving latch assembly.
As shown in Fig. 5, Fig. 8, Fig. 9, Figure 10, in this first embodiment, on described center mount pad 120, circumference is evenly formed with 4 notch parts 122.Each hold-down arm 110 of 4 hold-down arms 110 is correspondingly provided with lug boss 112.When described many hold-down arms 110 launch, each lug boss 112 is correspondingly positioned at notch part 122.
As shown in figure 18, hold-down arm 110 is provided with the rotating hole 111 for arranging rotating shaft.Thus, hold-down arm 110 can be connected on described center mount pad 120 by rotating shaft rotatably.Upwards launching hold-down arm 110, under the state that each lug boss 112 is correspondingly positioned at notch part 122, by rotational lock assembly 150, can once 4 hold-down arms be locked on center mount pad 120 simultaneously.
Specifically, described latch assembly 150 is rotatably installed in above center mount pad 120 by rotating shaft 311.The top of rotating shaft 311 has flange, and latch assembly 150 can not be come off from top.By this way, described latch assembly 150 is arranged to rotate freely around the center of described center mount pad 120.
As shown in Fig. 8, Fig. 9, Figure 10, Figure 11, described latch assembly 150 has centre hole the second breakthrough portion 154,156,4,151,4 the first breakthrough portions and 4 extension tight lock parts 152.
As shown in Figure 5, center mount pad 120 is provided with 4 the first through wires holes 126 and 4 the second through wires holes 124.The first wiring be connected with camera head 300 is connected with control circuit 600 through centre hole 151.The wiring be connected with motor 210 is connected with control circuit 600 through the first through wires hole 126 and the first breakthrough portion 156.Second through wires hole 124 is for arranging the stud of fixing control circuit 600.First breakthrough portion 156 and the second breakthrough portion 154 all curved, even if also can not interfere with wiring, stud so that latch assembly 150 rotates.
Each extension tight lock part 152 has the stopper section 158 of stretching out downwards.So, when described latch assembly 150 rotates to locked position, the inside face 1582 of described stopper section 158 correspondingly abuts the outside face 1120 of each lug boss 112.As shown in figure 18, the outside face 1120 of each lug boss 112 is the curved surfaces mated with the outside face of described center mount pad 120.
Then the latch assembly of the second embodiment is introduced by reference to the accompanying drawings.The latch assembly of the second embodiment is portable latch assembly.
As shown in Figure 20 to Figure 23, described latch assembly 150A has centre hole 151A, 4 the first breakthrough portion 156A, 4 the second breakthrough portion 154A, 4 extension tight lock part 152A and force application parts 160.The first wiring be connected with camera head 300 is connected with control circuit 600 through centre hole 151A.The wiring be connected with motor 210 is connected with control circuit 600 through the first through wires hole 126 and the first breakthrough portion 156A.Second through wires hole 124 is for arranging the stud of fixing control circuit 600.Different from the first embodiment, the first breakthrough portion 156A and the second breakthrough portion 154A is circular port.
Described force application part 160 has guide pillar 162, Compress Spring 164 and screw 166.Compress Spring 164 is set on guide pillar 162, screw 166 from below upward successively through center mount pad 120, extend tight lock part 152A and Compress Spring 164, then with guide pillar 162 screw threads for fastening.The two ends of Compress Spring 164 are pressed in the end flange of extension tight lock part 152A and guide pillar 162 respectively.By this way, force application part 160 Chang Shichao pushes described latch assembly 150A near the direction of described center mount pad 120.Each extension tight lock part 152A has the stopper section 158A stretched out downwards, and when described latch assembly 150A is positioned at locked position, the inside face 1582A of described stopper section 158A correspondingly abuts the outside face 1120 of each lug boss 112.
In this second embodiment, the outside face 1120 of each lug boss 112 can not be curved surfaces, such as, can be plane.And in this second embodiment, the outline of latch assembly 150A can be square.
When needs draw downward collapsible many rotor unmanned aircrafts in, latch assembly 150A is pushed against Compress Spring 164, make latch assembly 150A away from center mount pad 120, the inside face 1582A of described stopper section 158A is away from the outside face 1120 of each lug boss 112, then folding support arm 110 downwards.
In addition, in the embodiment of Figure 20 to Figure 23 display, latch assembly 150A also can not possess force application part 160.When not possessing force application part, such as, latch assembly itself is made up of engineering plastics elastomeric material, is directly pinned each lug boss of hold-down arm by elasticity.In this case, can unlock by exerting oneself or levering up stopper section by instrument.
Although illustrate and describe embodiments of the invention, those having ordinary skill in the art will appreciate that: can carry out multiple change, amendment, replacement and modification to these embodiments when not departing from principle of the present invention and aim, scope of the present invention is by claim and equivalents thereof.
In addition, the architectural feature illustrated in the form of above-mentioned enforcement can partly reconfigure.
Claims (10)
1. downward collapsible many rotor unmanned aircrafts, it is characterized in that, described downward collapsible many rotor unmanned aircrafts comprise engine installation, camera head, battery system, control circuit, many hold-down arms, center mount pad and latch assembly, wherein, described engine installation, described camera head and described battery system are connected with described control circuit respectively, described many hold-down arms are rotatably connected on the mount pad of described center, described latch assembly is for being locked at described center mount pad when described many hold-down arms launch by described many hold-down arms simultaneously.
2. downward collapsible many rotor unmanned aircrafts according to claim 1, is characterized in that, described control circuit to be arranged on the mount pad of described center and to be positioned at the top of described latch assembly.
3. downward collapsible many rotor unmanned aircrafts according to claim 1, is characterized in that, each hold-down arm of described many hold-down arms is cylindrical, and each hold-down arm is the pipe fitting of the spatial accommodation with the rechargeable battery holding described battery system.
4. downward collapsible many rotor unmanned aircrafts according to claim 1, it is characterized in that, described downward collapsible many rotor unmanned aircrafts also comprise multiple alighting gear, described multiple alighting gear is rotatably connected on described multiple hold-down arm respectively, the shape of described multiple alighting gear is mated to be attached to when described many hold-down arms fold on the outside face of described multiple hold-down arm respectively with the shape of described multiple hold-down arm, and described multiple alighting gear is provided with antenna.
5. downward collapsible many rotor unmanned aircrafts according to claim 1, it is characterized in that, described engine installation comprises multiple motor and multiple screw propeller, each motor of described multiple motor is fixedly installed on above the free end of each hold-down arm of described many hold-down arms, and described multiple screw propeller is fast disassembly type screw propeller or foldable propeller.
6. downward collapsible many rotor unmanned aircrafts according to claim 1, is characterized in that, described downward collapsible many rotor unmanned aircrafts are four rotor unmanned aircrafts, six rotor unmanned aircrafts or eight rotor unmanned aircrafts.
7. downward collapsible many rotor unmanned aircrafts according to claim 1, it is characterized in that, described camera head comprises interconnective damping, quick detach The Cloud Terrace and camera successively, described damping has multiple furcation, and when described many hold-down arms fold, described quick detach The Cloud Terrace and described camera depart from described damping and described many hold-down arms lay respectively between described multiple furcation.
8. downward collapsible many rotor unmanned aircrafts according to claim 1, it is characterized in that, on the mount pad of described center, circumference is evenly formed with multiple notch part, described many hold-down arms are correspondingly provided with multiple lug boss, and when described many hold-down arms launch, each lug boss of described multiple lug boss is correspondingly positioned at each notch part of described multiple notch part.
9. downward collapsible many rotor unmanned aircrafts according to claim 8, it is characterized in that, described latch assembly is arranged to rotate freely around the center of described center mount pad, described latch assembly has multiple extension tight lock part, each extension tight lock part has the stopper section of stretching out downwards, when described latch assembly rotates to locked position, the inside face of described stopper section correspondingly abuts the outside face of each lug boss of described multiple lug boss, and the outside face of each lug boss of described multiple lug boss is the curved surfaces mated with the outside face of described center mount pad.
10. downward collapsible many rotor unmanned aircrafts according to claim 8, it is characterized in that, described latch assembly has multiple extension tight lock part and force application part, described force application part is arranged to push described latch assembly towards the direction near described center mount pad, each extension tight lock part has the stopper section of stretching out downwards, and when described latch assembly is positioned at locked position, the inside face of described stopper section correspondingly abuts the outside face of each lug boss of described multiple lug boss.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510519756.1A CN105000163B (en) | 2015-08-23 | 2015-08-23 | A kind of more rotor unmanned aircrafts of fold-down formula |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510519756.1A CN105000163B (en) | 2015-08-23 | 2015-08-23 | A kind of more rotor unmanned aircrafts of fold-down formula |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105000163A true CN105000163A (en) | 2015-10-28 |
| CN105000163B CN105000163B (en) | 2017-12-08 |
Family
ID=54373099
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510519756.1A Expired - Fee Related CN105000163B (en) | 2015-08-23 | 2015-08-23 | A kind of more rotor unmanned aircrafts of fold-down formula |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105000163B (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105314088A (en) * | 2015-11-06 | 2016-02-10 | 珠海华迈航空科技有限公司 | Four-rotor craft |
| CN105346710A (en) * | 2015-11-30 | 2016-02-24 | 江苏优埃唯智能科技有限公司 | Six-rotor unmanned plane |
| CN105539827A (en) * | 2016-01-26 | 2016-05-04 | 南京航空航天大学 | Arm folding device of multi-axial air vehicle |
| CN105691589A (en) * | 2016-04-08 | 2016-06-22 | 北京博瑞爱飞科技发展有限公司 | Unmanned aerial vehicle |
| CN106184704A (en) * | 2016-08-08 | 2016-12-07 | 北京航空航天大学 | One is applicable to rocket-propelled quadrotor |
| CN106915431A (en) * | 2015-12-25 | 2017-07-04 | 北京臻迪机器人有限公司 | The skeleton mechanism of aircraft and aircraft |
| CN106927018A (en) * | 2017-04-07 | 2017-07-07 | 厦门南羽科技有限公司 | A kind of foldable unmanned plane |
| WO2017132982A1 (en) * | 2016-02-05 | 2017-08-10 | 胡家祺 | Rotor unmanned aerial vehicle |
| CN107521676A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | A kind of locking device of foot stool |
| WO2018119578A1 (en) * | 2016-12-26 | 2018-07-05 | SZ DJI Technology Co., Ltd. | Transformable apparatus |
| US10035597B2 (en) | 2015-08-17 | 2018-07-31 | Douglas Desrochers | Sonotube deployable multicopter |
| WO2018182883A1 (en) * | 2017-03-31 | 2018-10-04 | Qualcomm Incorporated | Double folding drone arms with landing gear |
| CN108713275A (en) * | 2017-02-24 | 2018-10-26 | 深圳市大疆创新科技有限公司 | RTK antenna installation stents and unmanned vehicle |
| WO2019015366A1 (en) * | 2017-07-21 | 2019-01-24 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN109278981A (en) * | 2018-11-16 | 2019-01-29 | 华东理工大学 | A kind of miniature foldable three-dimensional live modeling unmanned plane |
| CN109383739A (en) * | 2017-08-04 | 2019-02-26 | 深圳市道通智能航空技术有限公司 | A kind of horn and unmanned plane |
| CN110865404A (en) * | 2018-08-28 | 2020-03-06 | 北京理工大学 | Target positioning system for cooperative operation of multiple rotor unmanned aerial vehicles |
| US10661891B2 (en) | 2016-03-30 | 2020-05-26 | Samsung Electronics Co., Ltd. | Unmanned aerial vehicle |
| JP2020147055A (en) * | 2019-03-11 | 2020-09-17 | 株式会社プロドローン | Rotor aircraft |
| CN113370729A (en) * | 2021-07-08 | 2021-09-10 | 河北工业大学 | Air-ground deformable four-footed reconnaissance robot |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| EP2233393A2 (en) * | 2009-03-23 | 2010-09-29 | Gregor Schnoell | Locking system |
| CN203294313U (en) * | 2013-06-06 | 2013-11-20 | 儋州市公安局 | Police quadrotor type unmanned aerial vehicle |
| WO2014059549A1 (en) * | 2012-10-19 | 2014-04-24 | Aeryon Labs Inc | Hovering unmanned aerial vehicle |
| CN203681871U (en) * | 2013-12-20 | 2014-07-02 | 深圳市大疆创新科技有限公司 | Engine arm assembly and stander device of aircraft and aircraft |
| CN104379959A (en) * | 2014-03-31 | 2015-02-25 | 深圳市大疆创新科技有限公司 | Damping device and aircraft employing same |
| CN104691737A (en) * | 2015-03-05 | 2015-06-10 | 葛讯 | Support arm assembly for multi-rotor aircrafts, rack and aircraft |
-
2015
- 2015-08-23 CN CN201510519756.1A patent/CN105000163B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| EP2233393A2 (en) * | 2009-03-23 | 2010-09-29 | Gregor Schnoell | Locking system |
| WO2014059549A1 (en) * | 2012-10-19 | 2014-04-24 | Aeryon Labs Inc | Hovering unmanned aerial vehicle |
| CN203294313U (en) * | 2013-06-06 | 2013-11-20 | 儋州市公安局 | Police quadrotor type unmanned aerial vehicle |
| CN203681871U (en) * | 2013-12-20 | 2014-07-02 | 深圳市大疆创新科技有限公司 | Engine arm assembly and stander device of aircraft and aircraft |
| CN104379959A (en) * | 2014-03-31 | 2015-02-25 | 深圳市大疆创新科技有限公司 | Damping device and aircraft employing same |
| CN104691737A (en) * | 2015-03-05 | 2015-06-10 | 葛讯 | Support arm assembly for multi-rotor aircrafts, rack and aircraft |
Cited By (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10035597B2 (en) | 2015-08-17 | 2018-07-31 | Douglas Desrochers | Sonotube deployable multicopter |
| CN105314088A (en) * | 2015-11-06 | 2016-02-10 | 珠海华迈航空科技有限公司 | Four-rotor craft |
| CN105346710A (en) * | 2015-11-30 | 2016-02-24 | 江苏优埃唯智能科技有限公司 | Six-rotor unmanned plane |
| CN106915431A (en) * | 2015-12-25 | 2017-07-04 | 北京臻迪机器人有限公司 | The skeleton mechanism of aircraft and aircraft |
| CN105539827A (en) * | 2016-01-26 | 2016-05-04 | 南京航空航天大学 | Arm folding device of multi-axial air vehicle |
| WO2017132982A1 (en) * | 2016-02-05 | 2017-08-10 | 胡家祺 | Rotor unmanned aerial vehicle |
| US10661891B2 (en) | 2016-03-30 | 2020-05-26 | Samsung Electronics Co., Ltd. | Unmanned aerial vehicle |
| CN105691589A (en) * | 2016-04-08 | 2016-06-22 | 北京博瑞爱飞科技发展有限公司 | Unmanned aerial vehicle |
| CN107521676B (en) * | 2016-06-22 | 2021-11-30 | 北京臻迪机器人有限公司 | Locking device of foot rest |
| CN107521676A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | A kind of locking device of foot stool |
| CN106184704A (en) * | 2016-08-08 | 2016-12-07 | 北京航空航天大学 | One is applicable to rocket-propelled quadrotor |
| WO2018119578A1 (en) * | 2016-12-26 | 2018-07-05 | SZ DJI Technology Co., Ltd. | Transformable apparatus |
| JP2020501969A (en) * | 2016-12-26 | 2020-01-23 | エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ | Deformable device |
| CN108713275A (en) * | 2017-02-24 | 2018-10-26 | 深圳市大疆创新科技有限公司 | RTK antenna installation stents and unmanned vehicle |
| CN108713275B (en) * | 2017-02-24 | 2021-04-06 | 深圳市大疆创新科技有限公司 | RTK antenna installing support and unmanned vehicles |
| WO2018182883A1 (en) * | 2017-03-31 | 2018-10-04 | Qualcomm Incorporated | Double folding drone arms with landing gear |
| CN106927018A (en) * | 2017-04-07 | 2017-07-07 | 厦门南羽科技有限公司 | A kind of foldable unmanned plane |
| WO2019015366A1 (en) * | 2017-07-21 | 2019-01-24 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| US11492112B2 (en) | 2017-07-21 | 2022-11-08 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| CN109383739A (en) * | 2017-08-04 | 2019-02-26 | 深圳市道通智能航空技术有限公司 | A kind of horn and unmanned plane |
| CN110865404A (en) * | 2018-08-28 | 2020-03-06 | 北京理工大学 | Target positioning system for cooperative operation of multiple rotor unmanned aerial vehicles |
| CN110865404B (en) * | 2018-08-28 | 2022-02-18 | 北京理工大学 | Target positioning system for cooperative operation of multiple rotor unmanned aerial vehicles |
| CN109278981B (en) * | 2018-11-16 | 2021-11-16 | 华东理工大学 | Miniature foldable three-dimensional live-action modeling unmanned aerial vehicle |
| CN109278981A (en) * | 2018-11-16 | 2019-01-29 | 华东理工大学 | A kind of miniature foldable three-dimensional live modeling unmanned plane |
| JP2020147055A (en) * | 2019-03-11 | 2020-09-17 | 株式会社プロドローン | Rotor aircraft |
| CN113370729A (en) * | 2021-07-08 | 2021-09-10 | 河北工业大学 | Air-ground deformable four-footed reconnaissance robot |
| CN113370729B (en) * | 2021-07-08 | 2022-04-08 | 河北工业大学 | Air-ground deformable four-footed reconnaissance robot |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105000163B (en) | 2017-12-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105000163A (en) | Downwards foldable-type multi-rotor wing unmanned aerial vehicle | |
| CN108698685B (en) | Unmanned aerial vehicle, frame, kit, assembly method and operation method thereof | |
| US10988257B2 (en) | Aircraft-retrieval system | |
| CN109415120B (en) | Unmanned plane | |
| CN106628141B (en) | Variable geometry aircraft | |
| CN205131625U (en) | Small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle | |
| CN205168894U (en) | Rotor subassembly and have unmanned vehicles of rotor subassembly | |
| CN105366045A (en) | Multi-rotor-wing unmanned aerial vehicle | |
| CN105109679A (en) | Locking component and multi-rotor unmanned aerial vehicle | |
| CN204895844U (en) | Many rotor unmanned aerial vehicle | |
| CN104986329B (en) | Portable and collapsible double-rotor aerobat | |
| CN108001668A (en) | Propeller, propeller external member, Power Component, power external member and unmanned plane | |
| CN109552623A (en) | A kind of stable intelligent unmanned machine of landing suitable for mountainous region flight | |
| CN105905286A (en) | Unmanned aerial vehicle with thrust line variable device | |
| CN106240807A (en) | A kind of unmanned plane collecting photoelectric detection integrative | |
| CN109278981B (en) | Miniature foldable three-dimensional live-action modeling unmanned aerial vehicle | |
| CN209192260U (en) | A kind of chargeable landing stage apparatus of power patrol unmanned machine | |
| CN110550198A (en) | Rock wall fixed point type unmanned aerial vehicle | |
| CN207826552U (en) | A kind of portable V R panorama aerial photography unmanned aerial vehicles | |
| CN205366098U (en) | Rectilinear structure of every single move innovation cloud platform | |
| CN210191841U (en) | Five-lens camera device capable of achieving image data acquisition of aerial surveying and mapping photos of unmanned aerial vehicle oblique photography | |
| CN210618461U (en) | Unmanned aerial vehicle capable of being anchored on cliff | |
| CN209511518U (en) | Three dwell holder camera | |
| CN107253527B (en) | Composite fixed wing unmanned aerial vehicle capable of vertically taking off | |
| CN209192224U (en) | A kind of easy-to-dismount propeller of unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Dai Yihong Inventor before: Zhang Zilin Inventor before: Yuan Bo |
|
| CB03 | Change of inventor or designer information | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20171106 Address after: 262400, No. 7 administrative West Street, Changle County, Shandong, Weifang, Shandong, Changle Applicant after: Dai Yihong Address before: 510635 Tianhe District, Guangzhou, Zhongshan Road West, No. 105, building 401, room 191, No. Applicant before: Zhang Zilin Applicant before: Yuan Bo |
|
| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171208 Termination date: 20180823 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |