CN205186518U - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
- Publication number
- CN205186518U CN205186518U CN201520839079.7U CN201520839079U CN205186518U CN 205186518 U CN205186518 U CN 205186518U CN 201520839079 U CN201520839079 U CN 201520839079U CN 205186518 U CN205186518 U CN 205186518U
- Authority
- CN
- China
- Prior art keywords
- horn
- fuselage
- unmanned plane
- fixed block
- erecting frame
- 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.)
- Active
Links
Abstract
The utility model discloses an unmanned aerial vehicle includes the fuselage to and through the mounting bracket with the horn that the fuselage is connected, wherein the folding back of horn, the top surface of horn the protrusion in the top surface of fuselage, the bottom surface of horn the protrusion in the bottom surface of fuselage. Can reduce so the folding back of horn its with the fuselage in ascending intersection of perpendicular to fuselage side to reduce unmanned aerial vehicle in the ascending length in perpendicular to fuselage side, thereby reduce the volume of unmanned aerial vehicle on the space, and then reduce unmanned aerial vehicle's the volume that takies, and can reduce at the in -process of for example carrying unmanned aerial vehicle to colliding with of horn etc..
Description
Technical field
The utility model relates to unmanned air vehicle technique field, particularly a kind of horn structure of unmanned plane.
Background technology
Unmanned plane is the not manned aircraft utilizing radio robot and self-contained program to carry out control setup manipulation.General unmanned plane can Reusability, and can be widely used in the occasions such as aerial reconnaissance, supervision, communication, antisubmarine and electro countermeasure.
The horn that existing unmanned plane generally comprises fuselage and is connected with fuselage.When using unmanned plane, horn launches relative to fuselage.When not needing to use unmanned plane, generally horn being folded relative to fuselage, taking volume with what reduce unmanned plane, and reducing colliding with of horn.At present, when folding or launch horn, horn generally rotates perpendicular on the direction of fuselage on edge, and still and between fuselage is leaving certain angle perpendicular on the direction of fuselage after horn folds.Cause the volume of unmanned plane after folding horn comparatively large like this, thus cause taking up room of unmanned plane larger.Therefore, how to solve existing unmanned plane after horn is folding, its larger problem that takes up room is those skilled in the art's technical issues that need to address.
Utility model content
The utility model provides a kind of unmanned plane, and after horn is folding, horn and fuselage are in same level, and both be arranged in parallel, and therefore the overall volume of unmanned plane is less, take up room little.
The utility model unmanned plane comprises fuselage, and by the horn that erecting frame is connected with described fuselage, wherein, after described horn is folding, the end face of described horn does not protrude from the end face of described fuselage, and the bottom surface of described horn does not protrude from the bottom surface of described fuselage.
In one embodiment, described erecting frame is fixedly connected with described fuselage, and described horn and described erecting frame are rotatably connected.
In one embodiment, after described horn is folding, described horn is arranged in the holding tank of described fuselage.
In one embodiment, described horn is provided with hold down groove, and described erecting frame is provided with the fixed block being compressed in also fixing described horn in described hold down groove after described horn folds by elastic component.
In one embodiment, described fixed block to be arranged in the chute of described erecting frame and to be connected with the slide bar of described erecting frame, described elastic component is be set in the Compress Spring on described slide bar, and described chute extends towards described horn length direction upon deployment.
In one embodiment, described hold down groove is sector structure, and wherein after described horn is folding, described fixed block is connected to the knuckle place of described hold down groove.
In one embodiment, after described horn launches, the sector draw-in groove of described horn and described fixed block and described erecting frame clamping are with fixing described horn, wherein, the first card access surface that the moving direction along described fixed block of described sector draw-in groove extends abuts with described fixed block, and second card access surface be connected with described first card access surface of described sector draw-in groove abuts with described erecting frame.
In one embodiment, one end away from described second card access surface of described first card access surface tilts towards described second card access surface.
In one embodiment, in described horn rotation process, described fixed block abuts with the arcwall face of described horn, wherein said hold down groove is arranged on the end of described arcwall face, and described sector draw-in groove is arranged on the initiating terminal of described arcwall face, and described first card access surface is connected with described arcwall face.
In one embodiment, the rotation pin described erecting frame is connected with described horn is perpendicular to the bottom surface of described fuselage.
Relative to prior art, unmanned plane of the present utility model is after folding horn, and the end face of horn does not protrude from the end face of fuselage, and the bottom surface of horn does not protrude from the bottom surface of fuselage.Can reduce like this horn fold after its with fuselage perpendicular to intersecting on fuselage direction, to reduce unmanned plane perpendicular to the length on fuselage direction, thus reduce unmanned plane volume spatially, and then reduce unmanned plane take volume, and colliding with to horn in the process of such as carrying unmanned plane can be reduced.
Accompanying drawing explanation
Also will be described in more detail the utility model with reference to accompanying drawing based on embodiment hereinafter.
Fig. 1 is the horn deployed configuration schematic diagram of the unmanned plane of the present embodiment.
Fig. 2 is the horn foldable structure schematic diagram of the unmanned plane of the present embodiment.
Fig. 3 is the exploded perspective view of horn in the present embodiment and erecting frame.
Fig. 4 is the structural representation sketch of horn when folding in the present embodiment.
Fig. 5 is the horn structural representation upon deployment in the present embodiment.
Fig. 6 is the schematic diagram of the horn other direction upon deployment in the present embodiment.
Fig. 7 is the horn structural representation sketch upon deployment in the present embodiment.
Fig. 8 is the structural representation of horn in expansion process in the present embodiment.
Fig. 9 is the structural representation sketch of horn in expansion process in the present embodiment.
In the accompanying drawings, identical parts use identical Reference numeral.Accompanying drawing is not according to the scale of reality.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in further detail.
As shown in Figure 1, Figure 2 and Figure 3, the unmanned plane of the present embodiment comprises fuselage 8, and the horn 2 be connected with fuselage 8 by erecting frame 1.Erecting frame 1 can be fixedly connected with fuselage 8, and horn 2 is connected with erecting frame 1 by rotating pin 3, to realize horn 2 relative to the folding of fuselage 8 or expansion, and is convenient to install erecting frame 1 and horn 2.
After folding horn 2, the end face of horn 2 does not protrude from the end face of fuselage 8, and the bottom surface of horn 2 does not protrude from the bottom surface of fuselage 8.That is, after folding horn 2, the space of the bottom surface extended surface that horn 2 is arranged in fuselage 1 and end face extended surface (through the vertex of end face and parallel with bottom surface extended surface) sandwiched.Can reduce like this horn 2 folding after its with fuselage 8 perpendicular to intersecting on the direction E (described in Fig. 2) of fuselage 8, to reduce unmanned plane perpendicular to the length on fuselage 8 direction, thus reduce unmanned plane volume spatially, and then reduce unmanned plane take volume, and colliding with to horn 2 in the process of such as carrying unmanned plane can be reduced.
When installing rotation pin 3, the axis of rotation pin 3 is made to be approximately perpendicular to the bottom surface of fuselage 8.Namely rotate pin 3 axis direction roughly with the E in Fig. 2 to parallel.Like this, in the process rotating horn 2, horn 2 can be made all roughly to be arranged in the end face extended surface of fuselage 8 and the space of bottom surface extended surface sandwiched, to reduce the volume of unmanned plane, and structure is simple, easy for installation.After setting horn 2, horn 2 namely can along the C in Fig. 1 to rotation, also can along the D in Fig. 1 to rotation.
Further, holding tank 83 can also be set on fuselage 8.After horn 2 is folding, it is arranged in holding tank 83.After horn 2 is folding, horn 2 does not protrude from two sides 84 adjacent with horn 2 on fuselage 8.The volume of unmanned plane after horn 2 is folding can be reduced so further.
As shown in Figure 4, horn 2 is provided with hold down groove 21, erecting frame 1 is also provided with the fixed block 4 suitable with hold down groove 21.And fixed block 4 is connected with elastic component 5, produce motion with the effect by elastic component 5.Horn 2 is folding put in place after, fixed block 4 is fixed in hold down groove 21 by the elastic force of elastic component 5 by compression, thus fixes horn 2.When needing to launch horn 2, direct mobile fixed block 4, fixed block 4 and hold down groove 21 are departed from, and now horn 2 is in free state, directly launches horn 2.Arrange by the way, when folding or launch horn 2, mobile fixed block 4, makes when folding or launch horn 2, easy to operate, time saving and energy saving.
As shown in Figure 1, when arranging fixed block 4, can fixed block 4 be arranged in the chute 11 of erecting frame 1, to be limited the sense of motion of fixed block 4 by chute 11.Erecting frame 1 is provided with the slide bar 6 that can be mounted opposite frame 1 movement.One end of slide bar 6 is fixed in fixed block 4, to be connected by slide bar 6 and to support fixed block 4.The other end of slide bar 6 is provided with sheath 7, to be limited the motion of slide bar 6 by sheath 7, prevents slide bar 6 from coming off from erecting frame 1.Elastic component 5 can for being set in the Compress Spring on slide bar 6.Arrange by the way, structure is simple, and cost is low, and fixed block 4 is comparatively steady when mobile.Certainly, elastic component 5 can also be shell fragment etc.When arranging chute 11, the bearing of trend of chute 11 roughly the same with horn 2 length direction upon deployment (as shown in Figure 5 and Figure 6) can be made, fix horn 2 to facilitate by fixed block 4.Certainly, chute 11 can and horn 2 upon deployment between have certain angle, differing, it is completely parallel to be decided to be.
Further, fixed block 4 can, roughly in rectangular-shaped, cause horn 2 to fix the generation of unstable situation to reduce because fixed block 4 rotates in chute 11.When arranging fixed block 4, the two ends of fixed block 4 can being made all to protrude from erecting frame 1, moving fixed block 4 to facilitate the two ends by contacting fixed block 4.
When arranging horn 2, of horn 2 spring can be converted into knuckle limit, thus make this knuckle limit form hold down groove 21.After horn 2 is folding, hold down groove 21 is fitted with the corner of fixed block 4 and fixes horn 2 in the mode of shape complementarity.Setting like this, structure is simple, and easy to process, cost is low.Wherein, knuckle limit refers to, this hold down groove 21 refers to there are two limits, and two limits can be formed as obtuse angle, right angle or acute angle.
In addition, as shown in Figure 7, horn 2 is also provided with sector draw-in groove 22.After horn 2 launches, fix horn 2 by sector draw-in groove 22 and fixed block 4 and erecting frame 1 clamping.Sector draw-in groove 22 is provided with the first card access surface 221 roughly extended along the direction (i.e. the moving direction of fixed block 4) of chute 11 and the second card access surface 222 be connected with the first card access surface 221.First card access surface 221 is roughly positioned at the side margins of chute 11, and the second card access surface 222 is roughly positioned at an end margin of chute 11.Angle between first card access surface 221 and the second card access surface 222 is roughly acute angle.After horn 2 expansion puts in place, fixed block 4 abuts with the first card access surface 221 by the pressure of elastic component 5, to limit the rotation of horn 2 along first direction A by fixed block 4.Erecting frame 1 abuts with the second card access surface 222, to limit the rotation of horn 2 along second direction B by erecting frame 1.Wherein, first direction A and second direction B is contrary both direction.Setting like this, structure is simple, and easy to process, cost is low, and can be improved the fix tightly solidity of fixed block 4 and attachment face by the shape arranging sector draw-in groove 22.Certainly, when arranging the first card access surface 221, the first card access surface 221 also can and chute 11 between have certain angle, not necessarily completely parallel.
In one example in which, one end away from the second card access surface 222 of the first card access surface 221 tilts towards the second card access surface 222.Namely the first card access surface 221 tilts towards near the direction of the second card access surface 222.Like this, when horn 2 produces vibration, fixed block 4 can move towards the direction near the second card access surface 222 because of the restriction of vibratory force and the first card access surface 221, make the oscillation frequency of horn 2 more frequent, the cooperation of fixed block 4 and sector draw-in groove 22 will be tightr, thus play the effect of auto lock, reduce situation fixed block 4 and horn 2 being departed from because horn 2 vibrates and occur.
In addition, as shown in Figure 8 and Figure 9, in horn 2 rotation process, fixed block 4 abuts with the arcwall face 23 of horn 2.Namely the face of smooth transition is arranged in the face of horn 2 between hold down groove 21 and sector draw-in groove 22.When arranging hold down groove 21, be arranged on the end of arcwall face 23.When arranging sector draw-in groove 22, be arranged on the initiating terminal of arcwall face 23, and the first card access surface 221 of sector draw-in groove 22 is connected with arcwall face 23.Like this, in the process of rotating horn 2, do not need to drag fixed block 4 again, make fixed block 4 be in free state, simple to operate, easy to use, save trouble and labor.
Although be described the utility model with reference to preferred embodiment, when not departing from scope of the present utility model, various improvement can be carried out to it and parts wherein can be replaced with equivalent.Especially, only otherwise there is structural hazard, the every technical characteristic mentioned in each embodiment all can combine in any way.The utility model is not limited to specific embodiment disclosed in literary composition, but comprises all technical schemes fallen in the scope of claim.
Claims (10)
1. a unmanned plane, is characterized in that, comprises fuselage, and by the horn that erecting frame is connected with described fuselage, wherein, after described horn is folding, the end face of described horn does not protrude from the end face of described fuselage, and the bottom surface of described horn does not protrude from the bottom surface of described fuselage.
2. unmanned plane according to claim 1, is characterized in that, described erecting frame is fixedly connected with described fuselage, and described horn and described erecting frame are rotatably connected.
3. unmanned plane according to claim 1, is characterized in that, after described horn is folding, described horn is arranged in the holding tank of described fuselage.
4. unmanned plane according to claim 1, is characterized in that, described horn is provided with hold down groove, and described erecting frame is provided with the fixed block being compressed in also fixing described horn in described hold down groove after described horn folds by elastic component.
5. unmanned plane according to claim 4, it is characterized in that, described fixed block to be arranged in the chute of described erecting frame and to be connected with the slide bar of described erecting frame, described elastic component is be set in the Compress Spring on described slide bar, and described chute extends towards described horn length direction upon deployment.
6. unmanned plane according to claim 4, is characterized in that, described hold down groove is sector structure, and wherein after described horn is folding, described fixed block is connected to the knuckle place of described hold down groove.
7. the unmanned plane according to any one of claim 4-6, it is characterized in that, after described horn launches, the sector draw-in groove of described horn and described fixed block and described erecting frame clamping are with fixing described horn, wherein, the first card access surface that the moving direction along described fixed block of described sector draw-in groove extends abuts with described fixed block, and second card access surface be connected with described first card access surface of described sector draw-in groove abuts with described erecting frame.
8. unmanned plane according to claim 7, is characterized in that, one end away from described second card access surface of described first card access surface tilts towards described second card access surface.
9. unmanned plane according to claim 7, it is characterized in that, in described horn rotation process, described fixed block abuts with the arcwall face of described horn, wherein said hold down groove is arranged on the end of described arcwall face, and described sector draw-in groove is arranged on the initiating terminal of described arcwall face, and described first card access surface is connected with described arcwall face.
10. the unmanned plane according to any one of claim 1-6, is characterized in that, the rotation pin that described erecting frame is connected with described horn is perpendicular to the bottom surface of described fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520839079.7U CN205186518U (en) | 2015-10-27 | 2015-10-27 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520839079.7U CN205186518U (en) | 2015-10-27 | 2015-10-27 | Unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205186518U true CN205186518U (en) | 2016-04-27 |
Family
ID=55779538
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520839079.7U Active CN205186518U (en) | 2015-10-27 | 2015-10-27 | Unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205186518U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106240793A (en) * | 2016-08-16 | 2016-12-21 | 葛讯 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
| CN107472507A (en) * | 2017-07-13 | 2017-12-15 | 海鹰航空通用装备有限责任公司 | A kind of new unmanned plane horn folding device |
| WO2018112798A1 (en) * | 2016-12-21 | 2018-06-28 | XDynamics Limited | Unmanned aerial vehicle |
| CN108513556A (en) * | 2017-10-31 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| WO2019037242A1 (en) * | 2017-08-25 | 2019-02-28 | 深圳市大疆创新科技有限公司 | Arm assembly, frame, and unmanned aerial vehicle |
-
2015
- 2015-10-27 CN CN201520839079.7U patent/CN205186518U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106240793A (en) * | 2016-08-16 | 2016-12-21 | 葛讯 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
| CN106240793B (en) * | 2016-08-16 | 2019-04-26 | 葛讯 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
| WO2018112798A1 (en) * | 2016-12-21 | 2018-06-28 | XDynamics Limited | Unmanned aerial vehicle |
| CN107472507A (en) * | 2017-07-13 | 2017-12-15 | 海鹰航空通用装备有限责任公司 | A kind of new unmanned plane horn folding device |
| CN107472507B (en) * | 2017-07-13 | 2020-06-23 | 海鹰航空通用装备有限责任公司 | Novel unmanned aerial vehicle horn is folding device |
| WO2019037242A1 (en) * | 2017-08-25 | 2019-02-28 | 深圳市大疆创新科技有限公司 | Arm assembly, frame, and unmanned aerial vehicle |
| CN108513556A (en) * | 2017-10-31 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| WO2019084815A1 (en) * | 2017-10-31 | 2019-05-09 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN108513556B (en) * | 2017-10-31 | 2021-12-21 | 深圳市大疆创新科技有限公司 | Unmanned plane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205186518U (en) | Unmanned aerial vehicle | |
| CN105197228B (en) | Foot stool and unmanned vehicle | |
| US10906640B2 (en) | Multi-rotor unmanned aerial vehicle | |
| CN106450649B (en) | A kind of H configuration satellite antenna development agency | |
| CN109502006B (en) | Unmanned aerial vehicle frame, unmanned aerial vehicle and using method thereof | |
| CN207010742U (en) | Foldable mobile terminal | |
| CN105691637A (en) | Modularized satellite | |
| KR20180042405A (en) | Folding wing unmanned aircraft | |
| CN205574258U (en) | Unmanned aerial vehicle | |
| CN109153439A (en) | Unmanned vehicle | |
| CN108216603A (en) | A kind of foldable four axis unmanned plane of long wheelbase | |
| CN204916204U (en) | Aircraft damping device and have aircraft damping device's aircraft | |
| CN107336826A (en) | A kind of collapsible unmanned plane of more rotors | |
| CN205707294U (en) | Folding piece in a kind of horn on Multi-axis aircraft | |
| CN108190003B (en) | Unmanned aerial vehicle with buffer gear | |
| CN206914627U (en) | A kind of collapsible unmanned plane undercarriage | |
| CN108248820B (en) | Split type foldable engine propeller protection frame and using method thereof | |
| CN106314300A (en) | Smart phone holder for vehicle | |
| CN109625257A (en) | Logistics unmanned plane | |
| CN207683765U (en) | Variable area vertical fin for folding wings unmanned plane | |
| CN207943167U (en) | A kind of collapsible connection module and unmanned plane of unmanned aerial vehicle body and horn | |
| CN206602445U (en) | Vibration component and vibrating motor | |
| JP2019501051A (en) | Foldable frame and folding car | |
| CN203655673U (en) | Foldable circulating fan | |
| CN208453254U (en) | A kind of transport case of unmanned aerial vehicle ejecting support |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160622 Address after: 310052, 1, 2, 5, 700 east stream Road, Hangzhou, Zhejiang, Binjiang District Patentee after: HANGZHOU HIKROBOT TECHNOLOGY Co.,Ltd. Address before: Hangzhou City, Zhejiang province 310000 Binjiang District Qianmo Road No. 555 Patentee before: Hangzhou Hikvision Digital Technology Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 310051 room 304, B / F, building 2, 399 Danfeng Road, Binjiang District, Hangzhou City, Zhejiang Province Patentee after: Hangzhou Hikvision Robot Co.,Ltd. Address before: Floor 5, No. 1, Building 2, No. 700, Dongliu Road, Binjiang District, Hangzhou, Zhejiang 310052 Patentee before: HANGZHOU HIKROBOT TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230713 Address after: No.555, Qianmo Road, Binjiang District, Hangzhou City, Zhejiang Province Patentee after: Hangzhou Hikvision Digital Technology Co.,Ltd. Address before: 310051 room 304, B / F, building 2, 399 Danfeng Road, Binjiang District, Hangzhou City, Zhejiang Province Patentee before: Hangzhou Hikvision Robot Co.,Ltd. |