CN203681871U - Engine arm assembly and stander device of aircraft and aircraft - Google Patents
Engine arm assembly and stander device of aircraft and aircraft Download PDFInfo
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- CN203681871U CN203681871U CN201320851294.XU CN201320851294U CN203681871U CN 203681871 U CN203681871 U CN 203681871U CN 201320851294 U CN201320851294 U CN 201320851294U CN 203681871 U CN203681871 U CN 203681871U
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- horn
- mount pad
- locking piece
- aircraft
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- 238000007373 indentation Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 5
- 238000012856 packing Methods 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- RKTYLMNFRDHKIL-UHFFFAOYSA-N copper;5,10,15,20-tetraphenylporphyrin-22,24-diide Chemical compound [Cu+2].C1=CC(C(=C2C=CC([N-]2)=C(C=2C=CC=CC=2)C=2C=CC(N=2)=C(C=2C=CC=CC=2)C2=CC=C3[N-]2)C=2C=CC=CC=2)=NC1=C3C1=CC=CC=C1 RKTYLMNFRDHKIL-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 230000009916 joint effect Effects 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
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Abstract
The utility model discloses an engine arm assembly and stander device of an aircraft and the aircraft. The engine arm assembly comprises a locking component, a mounting seat and an engine arm, wherein the engine arm is rotatably connected with the mounting seat and rotates relative to the mounting seat so as to be switched between an unfolding state and a folding state, and the locking component is arranged on the mounting seat and is used for cooperatively locking the engine arm in the unfolding state so as to maintain the unfolding state of the engine arm. According to the engine arm assembly, the engine arm can be folded at the folding state in a carrying process, so that the engine arm is beneficially carried and stored.
Description
Technical field
The utility model relates to aeronautical technology field, particularly relates to a kind of horn assembly, stand arrangement and aircraft of aircraft.
Background technology
The rotor of existing multi-rotor aerocraft is supported by horn, and horn is fixedly installed in frame conventionally, reach six axles even when eight axles at aircraft thus, the wheelbase of whole aircraft can become very large and volume and be accompanied by and become large, gives to carry, deposit etc. and causes very large inconvenience.
Utility model content
The technical matters that the utility model mainly solves is to provide a kind of horn assembly, stand arrangement and aircraft of aircraft, can change the volume of stand arrangement or aircraft, is convenient to carry, deposits etc.
For solving the problems of the technologies described above, the technical scheme that the utility model embodiment adopts is: the horn assembly that a kind of aircraft is provided, this horn assembly comprises locking piece, mount pad and horn, described horn and described mount pad are rotationally connected, to rotate relative to described mount pad and then to switch between deployed condition and collapsed state, described locking piece is arranged on described mount pad, to lock described horn at described horn during in described deployed condition, make described horn keep described deployed condition.
Wherein, horn assembly also comprises the horn attaching parts with described mount pad pivotal joint, and described horn attaching parts is connected to realize being rotationally connected between described horn and described mount pad with described horn.
Wherein, at horn, during in deployed condition, horn extends laterally to mount pad, and at horn, during in collapsed state, horn extends to below or the top of mount pad.
Wherein, mount pad comprises mount pad main body and is arranged at the first pivotal mounting portion of mount pad main body one side, in the first pivotal mounting portion, be provided with the first pivot hole, horn attaching parts comprises connector main body and is arranged at the second pivotal mounting portion of connector main body, in the second pivotal mounting portion, correspondence is provided with the second pivot hole, horn assembly further comprises the pivot connector being arranged in the first pivot hole and the second pivot hole, with by horn attaching parts pivotal joint to mount pad.
Wherein, connector main body with mount pad main body away from arrange end be provided with containing cavity, horn part is accommodated and is socketed in containing cavity.
Wherein, locking piece relatively rotates and is connected with mount pad.
Wherein, locking piece comprises locking piece main body and is arranged at the first engagement section of the bottom of locking piece main body, horn attaching parts comprises the second engagement section that is arranged at top, and the first engagement section rotates top to horn attaching parts during in deployed condition mutually to lock and to engage with the second engagement section at horn.
Wherein, locking piece also comprises the first projection of the bottom that is arranged at described locking piece main body, in described the first projection, be provided with the first mounting hole, the top of described mount pad is provided with the second projection and is arranged at the second mounting hole in described the second projection, described the first projection is arranged in described the second mounting hole, described horn assembly further comprises fixed connecting piece, and described fixed connecting piece runs through described the first mounting hole so that described locking piece is rotated and to be installed on described mount pad.
Wherein, on the snap-latch surface being in contact with one another of the first engagement section and the second engagement section, be respectively arranged with the location indentations and the location teat that cooperatively interact.
Wherein, mount pad further comprises first limiting section at the top that is arranged at mount pad, locking piece further comprises the second limiting section and the 3rd limiting section of the bottom that is arranged at intervals at locking piece main body, the first limiting section is between the second limiting section and the 3rd limiting section, to limit the rotational angle of locking piece.
For solving the problems of the technologies described above, another technical scheme that the utility model embodiment adopts is: a kind of stand arrangement of aircraft is provided, and this stand arrangement disposes horn assembly as previously described.
For solving the problems of the technologies described above, another technical scheme that the utility model embodiment adopts is: a kind of aircraft is provided, and this aircraft comprises stand arrangement, and this stand arrangement disposes horn assembly as previously described.
Wherein, aircraft is quadrotor, six rotorcraft or eight-rotary wing aircraft.
The beneficial effects of the utility model are: the situation that is different from prior art, aircraft of the present utility model is rotationally connected by mount pad and horn, horn is rotated relative to mount pad, and then switch between deployed condition and collapsed state, further, locking piece is arranged on mount pad, to lock horn at horn during in deployed condition, makes horn keep deployed condition.Therefore, horn assembly of the present utility model can not only guarantee the normal work (in deployed condition) of horn, also can, in the time of carrying, make horn folding, in collapsed state, has reduced volume, is convenient to carry, deposits etc.
Accompanying drawing explanation
Fig. 1 is that the horn assembly of aircraft of the utility model embodiment is at the structural representation of deployed condition;
Fig. 2 is that the horn assembly of aircraft of the utility model embodiment is at the structural representation of collapsed state;
The birds-eye view of the horn assembly of the aircraft of Fig. 3 the utility model embodiment;
Fig. 4 is the lateral plan of the mount pad of the utility model embodiment horn assembly;
Fig. 5 is the birds-eye view of the mount pad of the utility model embodiment horn assembly;
Fig. 6 is a lateral plan of the horn attaching parts of the utility model embodiment horn assembly;
Fig. 7 is the opposite side view of the horn attaching parts of the utility model embodiment horn assembly;
Fig. 8 is the front view of the locking piece of the utility model embodiment horn assembly;
Fig. 9 is the birds-eye view of the bottom of the locking piece of the utility model embodiment horn assembly.
The specific embodiment
Refer to Fig. 1, Fig. 1 is that the horn assembly of aircraft of the utility model embodiment is at the structural representation of deployed condition.As shown in Figure 1, the horn assembly 10 of the aircraft of the present embodiment comprises locking piece 11, mount pad 12 and horn 13.
Wherein, horn 13 is rotationally connected with mount pad 12, to rotate relative to mount pad 12, and then switches between deployed condition (as shown in Figure 1) and collapsed state (as shown in Figure 2).Concrete, when horn 13 is during in deployed condition, horn 13 extends laterally to mount pad 12, when horn 13 is during in collapsed state, horn 13 extends to below or the top of mount pad 12, in the present embodiment, horn 13 is in the time of collapsed state, and horn 13 extends (as shown in Figure 2) to the below of mount pad 12.
Therefore, the horn assembly 10 of the utility model aircraft can not only guarantee the normal work (in deployed condition) of horn 13, also can be in the time of carrying, and make horn 13 folding, in collapsed state, reduce volume, be convenient to carry, deposit etc.
Optionally, the horn assembly 10 of the present embodiment also comprises the horn attaching parts 14 with mount pad 12 pivotal joints, and horn attaching parts 14 is connected to realize being rotationally connected between horn 13 and mount pad 12 with horn 13.
In other embodiments, the horn 13 of horn assembly 10 can also directly coordinate realization to be rotationally connected by rivet, screw, protruding projection etc. with mount pad 12.
Refer to Fig. 4-Fig. 9, Fig. 4 is the lateral plan of mount pad 12, and Fig. 5 is the birds-eye view of mount pad 12, Fig. 6 is a lateral plan of horn attaching parts 14, Fig. 7 is the opposite side view of horn attaching parts 14, and Fig. 8 is the front view of locking piece 11, and Fig. 9 is the birds-eye view of the bottom of locking piece 11.
First as shown in Figure 4 and Figure 6, mount pad 12 comprises mount pad main body 121 and is arranged at the first pivotal mounting portion 122 of mount pad main body 121 1 sides, in the first pivotal mounting portion 122, be provided with the first pivot hole 1221, horn attaching parts 14 comprises connector main body 141 and is arranged at the second pivotal mounting portion 142 of connector main body 141, in the second pivotal mounting portion 142, correspondence is provided with the second pivot hole 1421, horn assembly 10 further comprises that the pivot connector 15(that is arranged in the first pivot hole 1221 and the second pivot hole 1421 as shown in Figure 1), with by horn attaching parts 14 pivotal joints to mount pad 12.
Optionally, pivot connector 15 can be screw bolt and nut, or other play the element of pivotal joint effect.
Optionally, pivot connector 15 along continuous straight runs settings, and at horn 13 during in deployed condition, a side butt of the first pivotal mounting portion 122 that is provided with connector main body 141 and the ends 121 adjacent settings of mount pad main body and mount pad main body 121.
Optionally, horn attaching parts 14 further comprises the 4th limiting section 145, the 4th limiting section 145 is arranged on the second pivot hole 1421 belows, for in the time that the relative mount pad 12 of horn attaching parts 14 rotates, prop up the bottom of mount pad 12, the angle that limits the rotation of horn attaching parts 14, makes horn 13 if the position of Fig. 2 is in collapsed state.
Further, when horn attaching parts 14 turns to behind the position of Fig. 2, N horn 13 plays pendulum when preventing from carrying, for example, upwards swing, and another locking piece (not shown) can also be set on mount pad 12, makes horn 13 keep collapsed state.
Refer to Fig. 7, connector main body 141 with mount pad main body 121 away from arrange end be provided with containing cavity 144, horn 13 parts are accommodated and are socketed in containing cavity 144.
In the present embodiment, locking piece 11 direction as shown in Figure 3 relatively rotates and is connected with mount pad 12.Particularly, refer to Fig. 5, Fig. 8 and Fig. 9, locking piece 11 comprises locking piece main body 111 and is arranged in first projection 112, the first projections 112 of bottom of locking piece main body 111 and is provided with the first mounting hole 1121.The top of mount pad 12 is provided with the second mounting hole 123, concrete, and the top of mount pad 12 is provided with the second projection 124(as shown in Figure 4), the second mounting hole 123 is arranged in the second projection 124.The first projection 112 is arranged in the second mounting hole 123 by the second projection 124.
Optionally, the first mounting hole 1121 is screw hole, and fixed connecting piece comprises screw and packing ring.In installation process, screw rotates into the first mounting hole 1121, and packing ring is arranged between second periphery of mounting hole 123 and the step of screw.The not locked locking piece 11 of screw and packing ring, can rotate with respect to mount pad 12 locking piece 11.
In other embodiments, can also the second projection 124 be arranged in the first mounting hole 1121 by the first projection 112, fixed connecting piece runs through the second mounting hole 123 so that locking piece 11 is rotated and to be installed on mount pad 12.
Should be understood that object that locking piece 11 and mount pad 12 relatively rotate connection is in order to rotate so that horn 13 is locked horn attaching parts 14 during in deployed condition relative to mount pad 12 at horn attaching parts 14, to make horn 13 keep deployed condition.Therefore, refer to Fig. 7 and Fig. 9, the locking piece 11 of the present embodiment also comprises that 113, the first engagement sections 113, the first engagement section of the bottom that is arranged at locking piece main body 111 are preferably arcuate structure, and horn attaching parts 14 comprises the second engagement section 143 that is arranged at top.The first engagement section 113 rotate during in deployed condition at horn 13 to the top of horn attaching parts 14 with the second engagement section 143 mutually locking engage.On the snap-latch surface being in contact with one another of the first engagement section 113 and the second engagement section 143, be respectively arranged with the location indentations 1131 and the location teat 1431 that cooperatively interact.Thus, when locking piece 11 rotates with respect to mount pad 12 and engages with horn attaching parts 14, location teat 1431 and location indentations 1131 cooperatively interact, and play locking effect.
Further, in order to limit locking piece 11 anglecs of rotation.The present embodiment is not in the time that locking piece 11 engages with horn attaching parts 14, and arcuate structure (i.e. the first engagement section 113) extends to the center of circle direction of the circle at this arcuate structure place away from one end of horn attaching parts 14, forms extension 1132.The second engagement section 143 is outwards given prominence to and is formed projection 1432 in the position corresponding with extension 1132.Thus, when locking piece 11 rotates with respect to mount pad 12 and engages with horn attaching parts 14, extension 1132 props up projection 1432, limits the angle that locking piece 11 rotates; , be not difficult to find out meanwhile, in conjunction with the mating reaction of location teat 1431 and location indentations 1131, can effectively prevent that locking piece 11 from producing loosening situation, avoid horn assembly 10 to meet accident etc. due to loosening in flight course.
Refer to Fig. 5 and Fig. 9, mount pad 12 further comprises first limiting section 125 at the top that is arranged at mount pad main body 121, locking piece 11 further comprises the second limiting section 115 and the 3rd limiting section 116 of the bottom that is arranged at intervals at locking piece main body 111, the first limiting section 125, between the second limiting section 115 and the 3rd limiting section 116, and then carries out spacing to the rotational angle of locking piece 11.
Optionally, the first limiting section 125 is tetragonal body, and the second limiting section 115 is cylindrical, and the 3rd limiting section 116 is trapezoidal protrusion.
To sum up, in the present embodiment, when horn attaching parts 14 rotates while making horn 13 in deployed condition relative to mount pad 12, locking piece 11 rotates with respect to mount pad 12 and then locks horn attaching parts 14, in the time that horn attaching parts 14 makes horn 13 in collapsed state with respect to mount pad 12 rotations, the 4th limiting section 145 on horn attaching parts 14 can limit the rotation of horn attaching parts 14, makes horn 13 keep the collapsed state shown in Fig. 2, is convenient to carry, deposits etc.
It should be noted that, in other embodiments, locking piece 11 also can arrange some elastic bumps by pressing to press on mount pad 12 or release from a side of mount pad 12 toward the opposite side being connected with horn 13 with spacing horn 13 or mount pad 12 is interior, and locking piece 11 directly pushes and closely cooperates with mount pad 12 elasticity.
The utility model embodiment also provides a kind of stand arrangement of aircraft, and this stand arrangement disposes previously described horn assembly 10.
The utility model embodiment also provides a kind of aircraft, and this aircraft comprises stand arrangement, and wherein, stand arrangement disposes horn assembly 10 as previously described.Aircraft of the present utility model is quadrotor, six rotorcraft or eight-rotary wing aircraft.
The foregoing is only embodiment of the present utility model; not thereby limit the scope of the claims of the present utility model; every equivalent structure or conversion of equivalent flow process that utilizes the utility model specification sheets and accompanying drawing content to do; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present utility model.
Claims (13)
1. the horn assembly of an aircraft, it is characterized in that, described horn assembly comprises locking piece, mount pad and horn, described horn and described mount pad are rotationally connected, to rotate relative to described mount pad, and then switch between deployed condition and collapsed state, described locking piece is arranged on described mount pad, to lock described horn at described horn during in described deployed condition, make described horn keep described deployed condition.
2. horn assembly according to claim 1, it is characterized in that, described horn assembly also comprises the horn attaching parts with described mount pad pivotal joint, and described horn attaching parts is connected to realize being rotationally connected between described horn and described mount pad with described horn.
3. horn assembly according to claim 1, it is characterized in that, at described horn, during in described deployed condition, described horn extends laterally to described mount pad, at described horn, during in described collapsed state, described horn extends to below or the top of described mount pad.
4. horn assembly according to claim 2, it is characterized in that, described mount pad comprises mount pad main body and is arranged at the first pivotal mounting portion of described mount pad main body one side, in described the first pivotal mounting portion, be provided with the first pivot hole, described horn attaching parts comprises connector main body and is arranged at the second pivotal mounting portion of described connector main body, in described the second pivotal mounting portion, correspondence is provided with the second pivot hole, described horn assembly further comprises the pivot connector being arranged in described the first pivot hole and described the second pivot hole, with by described horn attaching parts pivotal joint to described mount pad.
5. horn assembly according to claim 4, is characterized in that, described connector main body with described mount pad main body away from arrange end be provided with containing cavity, described horn part is accommodated and is socketed in described containing cavity.
6. according to the horn assembly described in claim 2-5 any one, it is characterized in that, described locking piece relatively rotates and is connected with described mount pad.
7. horn assembly according to claim 6, it is characterized in that, described locking piece comprises locking piece main body and is arranged at the first engagement section of the bottom of described locking piece main body, described horn attaching parts comprises the second engagement section that is arranged at top, described the first engagement section described horn in described deployed condition time rotation to the top of described horn attaching parts mutually to lock and to engage with described the second engagement section.
8. horn assembly according to claim 6, it is characterized in that, described locking piece also comprises the first projection of the bottom that is arranged at described locking piece main body, in described the first projection, be provided with the first mounting hole, the top of described mount pad is provided with the second projection and is arranged at the second mounting hole in described the second projection, described the first projection is arranged in described the second mounting hole, described horn assembly further comprises fixed connecting piece, and described fixed connecting piece runs through described the first mounting hole so that described locking piece is rotated and to be installed on described mount pad.
9. horn assembly according to claim 7, is characterized in that, is respectively arranged with the location indentations and the location teat that cooperatively interact on the snap-latch surface being in contact with one another of described the first engagement section and described the second engagement section.
10. horn assembly according to claim 7, it is characterized in that, described mount pad further comprises first limiting section at the top that is arranged at described mount pad, described locking piece further comprises the second limiting section and the 3rd limiting section of the bottom that is arranged at intervals at described locking piece main body, described the first limiting section is between described the second limiting section and described the 3rd limiting section, to limit the rotational angle of described locking piece.
The stand arrangement of 11. 1 kinds of aircraft, is characterized in that, described stand arrangement disposes the horn assembly as described in claim 1-10 any one.
12. 1 kinds of aircraft, is characterized in that, described aircraft comprises stand arrangement, and described stand arrangement disposes the horn assembly as described in claim 1-10 any one.
13. aircraft according to claim 12, is characterized in that, described aircraft is quadrotor, six rotorcraft or eight-rotary wing aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320851294.XU CN203681871U (en) | 2013-12-20 | 2013-12-20 | Engine arm assembly and stander device of aircraft and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320851294.XU CN203681871U (en) | 2013-12-20 | 2013-12-20 | Engine arm assembly and stander device of aircraft and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203681871U true CN203681871U (en) | 2014-07-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320851294.XU Expired - Fee Related CN203681871U (en) | 2013-12-20 | 2013-12-20 | Engine arm assembly and stander device of aircraft and aircraft |
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| CN (1) | CN203681871U (en) |
Cited By (16)
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| CN105000163A (en) * | 2015-08-23 | 2015-10-28 | 张子林 | Downwards foldable-type multi-rotor wing unmanned aerial vehicle |
| CN105000165A (en) * | 2015-07-23 | 2015-10-28 | 致导科技（北京）有限公司 | Locking device for folding type unmanned aerial vehicle arm |
| CN105059528A (en) * | 2015-07-23 | 2015-11-18 | 致导科技（北京）有限公司 | Foldable unmanned aerial vehicle |
| CN105109679A (en) * | 2015-08-23 | 2015-12-02 | 张子林 | Locking component and multi-rotor unmanned aerial vehicle |
| CN105366042A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Unmanned aerial vehicle |
| WO2017107752A1 (en) * | 2015-12-25 | 2017-06-29 | 广州亿航智能技术有限公司 | Multirotor manned aerial vehicle having foldable arms |
| WO2017132803A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Unmanned aerial vehicle folding structure |
| CN107031815A (en) * | 2015-12-25 | 2017-08-11 | 北京臻迪机器人有限公司 | Unmanned plane horn locking tripper and unmanned plane |
| CN107323651A (en) * | 2015-06-01 | 2017-11-07 | 深圳市大疆创新科技有限公司 | Horn component, frame and unmanned plane |
| WO2018076470A1 (en) * | 2016-10-27 | 2018-05-03 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| EP3202662A4 (en) * | 2015-07-31 | 2018-05-16 | Guangzhou Xaircraft Technology Co., Ltd. | Unmanned aerial vehicle |
| WO2019041502A1 (en) * | 2017-08-30 | 2019-03-07 | 深圳市大疆创新科技有限公司 | Vehicle arm assembly of unmanned aerial vehicle and unmanned aerial vehicle |
| CN110546476A (en) * | 2018-04-27 | 2019-12-06 | 深圳市大疆创新科技有限公司 | Folding equipment |
| CN110723273A (en) * | 2019-07-02 | 2020-01-24 | 翔升（上海）电子技术有限公司 | Arm locking device and aircraft |
| CN111319751A (en) * | 2020-04-27 | 2020-06-23 | 南京安元科技有限公司 | Portable industrial unmanned aerial vehicle who easily stretches out and draws back and accomodate |
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| CN107323651A (en) * | 2015-06-01 | 2017-11-07 | 深圳市大疆创新科技有限公司 | Horn component, frame and unmanned plane |
| CN105000165A (en) * | 2015-07-23 | 2015-10-28 | 致导科技（北京）有限公司 | Locking device for folding type unmanned aerial vehicle arm |
| CN105059528A (en) * | 2015-07-23 | 2015-11-18 | 致导科技（北京）有限公司 | Foldable unmanned aerial vehicle |
| CN105059528B (en) * | 2015-07-23 | 2017-12-12 | 致导科技（北京）有限公司 | A kind of folding unmanned plane |
| US10526087B2 (en) | 2015-07-31 | 2020-01-07 | Guangzhou Xaircraft Technology Co., Ltd. | Unmanned aerial vehicle and unmanned aerial vehicle body configured for unmanned aerial vehicle |
| EP3202662A4 (en) * | 2015-07-31 | 2018-05-16 | Guangzhou Xaircraft Technology Co., Ltd. | Unmanned aerial vehicle |
| AU2016303994B2 (en) * | 2015-07-31 | 2019-06-06 | Guangzhou Xaircraft Technology Co., Ltd. | Unmanned aerial vehicle and unmanned aerial vehicle body configured for unmanned aerial vehicle |
| CN105000163A (en) * | 2015-08-23 | 2015-10-28 | 张子林 | Downwards foldable-type multi-rotor wing unmanned aerial vehicle |
| CN105109679A (en) * | 2015-08-23 | 2015-12-02 | 张子林 | Locking component and multi-rotor unmanned aerial vehicle |
| CN105109679B (en) * | 2015-08-23 | 2017-06-16 | 无锡龙腾创新科技有限公司 | A kind of latch assembly and many rotor unmanned aircrafts |
| CN105366042A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Unmanned aerial vehicle |
| WO2017107752A1 (en) * | 2015-12-25 | 2017-06-29 | 广州亿航智能技术有限公司 | Multirotor manned aerial vehicle having foldable arms |
| CN107031815A (en) * | 2015-12-25 | 2017-08-11 | 北京臻迪机器人有限公司 | Unmanned plane horn locking tripper and unmanned plane |
| CN107031815B (en) * | 2015-12-25 | 2021-01-29 | 北京臻迪机器人有限公司 | Unmanned aerial vehicle horn locking unlocking device and unmanned aerial vehicle |
| WO2017132803A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Unmanned aerial vehicle folding structure |
| US10696383B2 (en) | 2016-08-12 | 2020-06-30 | Coretronic Intelligent Robotics Corporation | Flight device |
| CN109153439A (en) * | 2016-10-27 | 2019-01-04 | 深圳市大疆创新科技有限公司 | Unmanned vehicle |
| WO2018076470A1 (en) * | 2016-10-27 | 2018-05-03 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN109153439B (en) * | 2016-10-27 | 2022-05-03 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN109923035A (en) * | 2017-08-30 | 2019-06-21 | 深圳市大疆创新科技有限公司 | The horn component and unmanned vehicle of unmanned vehicle |
| WO2019041502A1 (en) * | 2017-08-30 | 2019-03-07 | 深圳市大疆创新科技有限公司 | Vehicle arm assembly of unmanned aerial vehicle and unmanned aerial vehicle |
| CN110546476A (en) * | 2018-04-27 | 2019-12-06 | 深圳市大疆创新科技有限公司 | Folding equipment |
| CN110723273A (en) * | 2019-07-02 | 2020-01-24 | 翔升（上海）电子技术有限公司 | Arm locking device and aircraft |
| CN111319751A (en) * | 2020-04-27 | 2020-06-23 | 南京安元科技有限公司 | Portable industrial unmanned aerial vehicle who easily stretches out and draws back and accomodate |
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