CN105109666A - Air vehicle with folding arms - Google Patents
Air vehicle with folding arms Download PDFInfo
- Publication number
- CN105109666A CN105109666A CN201510614134.7A CN201510614134A CN105109666A CN 105109666 A CN105109666 A CN 105109666A CN 201510614134 A CN201510614134 A CN 201510614134A CN 105109666 A CN105109666 A CN 105109666A
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- arm
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- folding arm
- folding
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Abstract
The invention discloses an air vehicle with folding arms. The air vehicle comprises a vehicle body (1); the air vehicle further comprises the multiple folding arms (2); each folding arm (2) comprises a first arm (21) connected with the vehicle body (1), a second arm (22) and a rotating mechanism (23) allowing the second arm (22) to rotate relative to the first arm (21); and each first arm (21) is provided with a rotor wing (3), and each second arm (22) is provided with a rotor wing (3). The air vehicle has the beneficial effects that the structure of the first arms and the second arms which can be rotationally connected is adopted in the air vehicle, and when the air vehicle is used, the external dimension of the air vehicle can be changed, so that the air vehicle can be suitable for different flight spaces, and the application area of the air vehicle is further wider.
Description
Technical field
The present invention relates to unmanned vehicle technical field, more particularly, relate to a kind of aircraft with folding arm.
Background technology
Unmanned vehicle has that volume is little, lightweight, expense is low, flexible operation and the high feature of safety, can be widely used in taking photo by plane, monitor, search and rescue, the field such as resource exploration.
Multi-axis aircraft of the prior art generally includes body, is arranged on multiple horns of body surrounding, and each horn is all provided with rotor.But, the horn of existing Multi-axis aircraft is generally relatively-stationary structure, when flight space or environment change (such as flight space diminishes) of Multi-axis aircraft, because the oad of Multi-axis aircraft can not change, and Multi-axis aircraft is made to be difficult to use in the flight space diminished.
Summary of the invention
The technical problem to be solved in the present invention is, for the above-mentioned defect of prior art, provides a kind of aircraft with folding arm that can change own profile size.
The technical solution adopted for the present invention to solve the technical problems is: construct a kind of aircraft with folding arm, comprise body; Described aircraft also comprises multiple folding arm; Each described folding arm comprises and is connected the first arm, the second arm with described body, and is provided for the rotating mechanism that described second arm can rotate relative to described first arm; Each described first arm and each described second arm are all provided with rotor.
Have in the aircraft of folding arm of the present invention, described rotating mechanism comprises the anchor shaft being arranged on described first arm one end, is arranged on the rotary sleeve of described second arm one end; Described rotary sleeve is rotatably sleeved on the outer wall of described anchor shaft.
Have in the aircraft of folding arm of the present invention, described rotating mechanism also comprises and being arranged on described rotary sleeve outer wall and the transmission gear coaxially arranged with described rotary sleeve, be arranged on the motor on described second arm, and the gear cluster between described motor and described transmission gear that is in transmission connection.
Have in the aircraft of folding arm of the present invention, described gear cluster comprise be sleeved on described motor rotating shaft on the first gear, to be installed in rotation on described second arm and and the annular rack of described first meshed transmission gear, be connected on described annular rack and and described annular rack coaxially arrange the second gear, be engaged on the 3rd gear between described second gear and described transmission gear.
Have in the aircraft of folding arm of the present invention, the number of teeth of described annular rack is greater than the number of teeth of described second gear.
Have in the aircraft of folding arm of the present invention, described rotating mechanism also comprises the resilient pin stop gear be arranged on described second arm; Described resilient pin stop gear comprises telescopically and is arranged on removable pin on described second arm; One end of described removable pin can be passed described rotary sleeve and support on the outer wall of described anchor shaft.
Have in the aircraft of folding arm of the present invention, the outer wall of described anchor shaft offers several spacing holes relative with the position of described removable pin; When rotating described second arm, described removable pin can be made to support in described spacing hole.
Have in the aircraft of folding arm of the present invention, described resilient pin stop gear also comprises the erecting frame be arranged on described second arm, and elasticity is connected to the spring between described erecting frame and described removable pin; Described removable pin telescopically is arranged on described erecting frame.
Have in the aircraft of folding arm of the present invention, described rotary sleeve and described anchor shaft frictional fit.
Have in the aircraft of folding arm of the present invention, described folding arm is four; Four described folding arms are evenly distributed in the surrounding of described body.
Implement the aircraft with folding arm of the present invention, there is following beneficial effect: described aircraft adopts the structure of the first arm and the second arm be rotatably connected, during use, this aircraft can be made to change its overall dimensions, thus different flight spaces can be adapted to, and then make the application of described aircraft wider.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the invention will be further described, in accompanying drawing:
Fig. 1 is the perspective view with the aircraft of folding arm that one of present pre-ferred embodiments provides;
Constructional drawing when Fig. 2 is the folding arm bending had in the aircraft of folding arm shown in Fig. 1;
Fig. 3 is the cut-away view with the aircraft of folding arm shown in Fig. 1;
Fig. 4 is the A portion enlarged drawing in Fig. 3;
Fig. 5 is the local structural graph with the rotating mechanism in the aircraft of folding arm shown in Fig. 1;
Fig. 6 is the perspective view with the aircraft of folding arm that two of present pre-ferred embodiments provides;
Constructional drawing when Fig. 7 is the folding arm bending had in the aircraft of folding arm shown in Fig. 6;
Fig. 8 is the cut-away view with the aircraft of folding arm shown in Fig. 6;
Fig. 9 is the B portion enlarged drawing in Fig. 8;
Figure 10 is the local structural graph with the rotating mechanism in the aircraft of folding arm shown in Fig. 6;
Figure 11 is the local structural graph with the rotating mechanism in the aircraft of folding arm that three of present pre-ferred embodiments provides.
Detailed description of the invention
In order to there be understanding clearly to technical characteristic of the present invention, object and effect, now contrast accompanying drawing and describe the specific embodiment of the present invention in detail.
As shown in Figure 1, Figure 2 and shown in Fig. 3, one of preferred embodiment of the present invention provides a kind of aircraft with folding arm, and it comprises body 1, folding arm 2 and rotor 3.
Particularly, as shown in Figure 1, body 1 is the main element of aircraft, and it is structure common in prior art, does not repeat them here.
Consult shown in Fig. 2 as Fig. 3, folding arm 2 is provided with multiple, it is connected to the surrounding of body 1.In the present embodiment, folding arm 2 is four, and four folding arms 2 are evenly distributed in the surrounding of body 1.Folding arm 2 comprises the first arm 21, second arm 22 and rotating mechanism 23.
Wherein, first arm 21 and the second arm 22 are roughly the structure of vertical bar shaped, each first arm 21 and each second arm 22 are all provided with rotor 3, first arm 21 and the rotational plane of the second arm 22 and the rotating shaft of rotor 3 mutually vertical, this rotor 3 is structure common in prior art, does not repeat them here.
Consult shown in Fig. 2 as Fig. 3, Fig. 4, Fig. 5, rotating mechanism 23 is connected between the first arm 21 and the second arm 22, to realize both being rotationally connected.In the present embodiment, rotating mechanism 23 comprises anchor shaft 231, rotary sleeve 232, transmission gear 233, motor 234 and gear cluster 235.
This anchor shaft 231 is roughly cylindrical-shaped structure, and it is arranged on one end of the first arm 21, and in the present embodiment, anchor shaft 231 and the first arm 21 are integrated.This rotary sleeve 232 is roughly the circular ring structure of hollow, and it is arranged on one end of the second arm 22, and rotary sleeve 232 is rotatably sleeved on the outer wall of anchor shaft 231.In the present embodiment, rotary sleeve 232 and the second arm 22 are integrated.This transmission gear 233 to be arranged on rotary sleeve 232 outer wall and coaxially to arrange with rotary sleeve 232, and the outer circumference of also i.e. rotary sleeve 232 offers the coaxial gear structure arranged with rotary sleeve 232.In the present embodiment, transmission gear 233 is cylindrical wheel, and the rotating shaft of itself and rotor 3 is coaxially arranged.This motor 234 is arranged on the second arm 21, and it rotates for being with nutating gear 233.
This gear cluster 235 is in transmission connection between motor 234 and transmission gear 233, and particularly, gear cluster 235 comprises the first gear 2351, annular rack 2352, second gear 2353 and the 3rd gear 2354.Wherein, first gear 2351 is sleeved in the rotating shaft of motor 234, annular rack 2352 to be installed in rotation on the second arm 21 and with the first gear 2351 engaged transmission, second gear 2353 to be connected on annular rack 2352 and coaxially to arrange with annular rack 2352, and the 3rd gear 2354 is engaged between the second gear 2353 and transmission gear 233.In the present embodiment, the number of teeth of annular rack 2352 is greater than the number of teeth of the second gear 2353, and also namely annular rack 2352 and the second gear 2353 form train of reduction gears, to play the effect of deceleration.
In the present embodiment, rotating mechanism 23 also comprises the control setup (not shown) rotated for controlling motor 234, the remote controller (not shown) of described aircraft can this control setup of wireless operated, with the rotation making user can control folding arm 2 in use.This control setup is structure common in prior art, does not repeat them here.
Use the aircraft that as above embodiment provides, because described aircraft adopts the structure of the first arm 21 and the second arm 22 be rotatably connected, make this aircraft can change its overall dimensions, thus different flight spaces can be adapted to, to improve the application of described aircraft; Moreover, when the oad of described aircraft changes, the variation of aircraft flight state can be brought equally, to make the application of described aircraft wider.
As shown in Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Figure 10, two of preferred embodiment of the present invention provides a kind of aircraft with folding arm, and one of itself and embodiment institute difference is the drive mechanism between anchor shaft 231 and rotary sleeve 232.In the present embodiment, rotating mechanism 23 comprises anchor shaft 231, rotary sleeve 232 and resilient pin stop gear 236.The structure of anchor shaft 231, rotary sleeve 232 is identical with the structure of anchor shaft 231, rotary sleeve 232 in embodiment one.This resilient pin stop gear 236 is arranged on the second arm 22, it comprises telescopically and is arranged on the removable pin 2361 on the second arm 22, the erecting frame 2362 be arranged on the second arm 22, and elasticity is connected to the spring 2363 between erecting frame 2362 and removable pin 2361.Removable pin 2361 is roughly cylindrical-shaped structure, and its telescopically is arranged on erecting frame 2362, and one end of removable pin 2361 can be passed rotary sleeve 232 and support on the outer wall of anchor shaft 231.In the present embodiment, when anchor shaft 231 turns an angle with rotary sleeve 232, removable pin 2361 supports on the outer wall of anchor shaft 231, by the friction force between removable pin 2361 and the outer wall of anchor shaft 231, can realize anchor shaft 231 and keep relatively-stationary state with rotary sleeve 232.The aircraft with folding arm described in the present embodiment can realize the overall dimensions changing described aircraft equally, and to adapt to different flight spaces, the aircraft described in the present embodiment is compared with one of embodiment, and its structure is more simple, and manufacturing cost is lower.
As shown in figure 11, three of preferred embodiment of the present invention provides a kind of aircraft with folding arm, and two differences of itself and embodiment are the structure of anchor shaft 231.In the present embodiment, the outer wall of anchor shaft 231 offers several spacing holes relative with the position of removable pin 2,361 2311, and this spacing hole 2311 is borehole structure, and the external diameter of itself and removable pin 2361 is suitable.In the present embodiment, several spacing holes 2311 are evenly distributed on the outer wall of anchor shaft 231.When rotation the second arm 22, removable pin 2361 can be made to support in spacing hole 2311.Adopt the structure that above-mentioned removable pin 2361 matches with spacing hole 2311, make the friction force between the outer wall of removable pin 2361 and anchor shaft 231 larger, anchor shaft 231 is more firm with the connection of rotary sleeve 232, and the first arm 21 and the second arm 22 more can be made to keep relatively-stationary state.
Four of preferred embodiment of the present invention provides a kind of aircraft with folding arm, and two differences of itself and embodiment are the structure eliminating resilient pin stop gear 236.In the present embodiment, rotary sleeve 232 and anchor shaft 231 frictional fit, when rotation first arm 21 and the second arm 22 form certain angle, by the friction force between rotary sleeve 232 and anchor shaft 231, the first arm 21 and the second arm 22 also can be made to keep relatively-stationary state.
By reference to the accompanying drawings embodiments of the invention are described above; but the present invention is not limited to above-mentioned detailed description of the invention; above-mentioned detailed description of the invention is only schematic; instead of it is restrictive; those of ordinary skill in the art is under enlightenment of the present invention; do not departing under the ambit that present inventive concept and claim protect, also can make a lot of form, these all belong within protection of the present invention.
Claims (10)
1. there is an aircraft for folding arm, comprise body (1); It is characterized in that: described aircraft also comprises multiple folding arm (2); Each described folding arm (2) comprises and is connected the first arm (21), the second arm (22) with described body (1), and is provided for the rotating mechanism (23) that described second arm (22) can rotate relative to described first arm (21); Each described first arm (21) and each described second arm (22) are all provided with rotor (3).
2. the aircraft with folding arm according to claim 1, it is characterized in that: described rotating mechanism (23) comprises the anchor shaft (231) being arranged on described first arm (21) one end, be arranged on the rotary sleeve (232) of described second arm (22) one end; Described rotary sleeve (232) is rotatably sleeved on the outer wall of described anchor shaft (231).
3. the aircraft with folding arm according to claim 2, it is characterized in that: described rotating mechanism (23) also comprises and being arranged on described rotary sleeve (232) outer wall and the transmission gear (233) that arrange coaxial with described rotary sleeve (232), be arranged on the motor (234) on described second arm (21), and the gear cluster (235) between described motor (234) and described transmission gear (233) that is in transmission connection.
4. the aircraft with folding arm according to claim 3, it is characterized in that: described gear cluster (235) comprise be sleeved on described motor (234) rotating shaft on the first gear (2351), be installed in rotation on described second arm (21) upper and with the annular rack (2352) of described first gear (2351) engaged transmission, be connected to described annular rack (2352) to go up and second gear (2353) that arrange coaxial with described annular rack (2352), be engaged on the 3rd gear (2354) between described second gear (2353) and described transmission gear (233).
5. the aircraft with folding arm according to claim 4, is characterized in that: the number of teeth of described annular rack (2352) is greater than the number of teeth of described second gear (2353).
6. the aircraft with folding arm according to claim 2, is characterized in that: described rotating mechanism (23) also comprises the resilient pin stop gear (236) be arranged on described second arm (22); Described resilient pin stop gear (236) comprises telescopically and is arranged on removable pin (2361) on described second arm (22); One end of described removable pin (2361) can be passed described rotary sleeve (232) and support on the outer wall of described anchor shaft (231).
7. the aircraft with folding arm according to claim 6, is characterized in that: the outer wall of described anchor shaft (231) offers several spacing holes (2311) relative with the position of described removable pin (2361); When rotating described second arm (22), described removable pin (2361) can be made to support in described spacing hole (2311).
8. the aircraft with folding arm according to claim 6, it is characterized in that: described resilient pin stop gear (236) also comprises the erecting frame (2362) be arranged on described second arm (22), and elasticity is connected to the spring (2363) between described erecting frame (2362) and described removable pin (2361); Described removable pin (2361) telescopically is arranged on described erecting frame (2362).
9. the aircraft with folding arm according to claim 2, is characterized in that: described rotary sleeve (232) and described anchor shaft (231) frictional fit.
10. the aircraft with folding arm according to any one of claim 1 ~ 9, is characterized in that: described folding arm (2) is four; Four described folding arms (2) are evenly distributed in the surrounding of described body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510614134.7A CN105109666A (en) | 2015-03-24 | 2015-09-24 | Air vehicle with folding arms |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510131547X | 2015-03-24 | ||
| CN201510131547 | 2015-03-24 | ||
| CN201510614134.7A CN105109666A (en) | 2015-03-24 | 2015-09-24 | Air vehicle with folding arms |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105109666A true CN105109666A (en) | 2015-12-02 |
Family
ID=54657859
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510614134.7A Pending CN105109666A (en) | 2015-03-24 | 2015-09-24 | Air vehicle with folding arms |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105109666A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106240813A (en) * | 2016-08-15 | 2016-12-21 | 张琬彬 | A kind of unmanned plane rotor anti-collision structure |
| CN106347668A (en) * | 2016-11-30 | 2017-01-25 | 叶强 | Anti-haze unmanned plane |
| CN106945830A (en) * | 2017-03-23 | 2017-07-14 | 深圳市星河时代控股有限公司 | A kind of flying power structure, aircraft and flying method |
| WO2017205997A1 (en) * | 2016-05-28 | 2017-12-07 | SZ DJI Technology Co., Ltd. | A foldable uav |
| CN108163182A (en) * | 2018-02-24 | 2018-06-15 | 高琴 | A kind of folding deinsectization unmanned plane |
| CN108482660A (en) * | 2018-04-16 | 2018-09-04 | 钱文娟 | A kind of community security defence unmanned plane |
| CN108557053A (en) * | 2018-02-05 | 2018-09-21 | 叶哲企 | A kind of telescopic device of unmanned plane horn |
| CN110481755A (en) * | 2019-07-12 | 2019-11-22 | 广东工业大学 | A kind of two degrees of freedom rotary folding unmanned plane horn |
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| CN203528812U (en) * | 2013-09-06 | 2014-04-09 | 天津云友科技有限公司 | Foldable four-rotor aircraft |
| CN104085530A (en) * | 2014-06-10 | 2014-10-08 | 南京航空航天大学 | Ducted coaxial multi-rotor type aircraft |
| CN203921199U (en) * | 2014-06-07 | 2014-11-05 | 珠海羽人飞行器有限公司 | Agricultural unmanned plane |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
| CN205044941U (en) * | 2015-03-24 | 2016-02-24 | 林日壮 | Aircraft with folding arm |
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2015
- 2015-09-24 CN CN201510614134.7A patent/CN105109666A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203528812U (en) * | 2013-09-06 | 2014-04-09 | 天津云友科技有限公司 | Foldable four-rotor aircraft |
| CN203921199U (en) * | 2014-06-07 | 2014-11-05 | 珠海羽人飞行器有限公司 | Agricultural unmanned plane |
| CN104085530A (en) * | 2014-06-10 | 2014-10-08 | 南京航空航天大学 | Ducted coaxial multi-rotor type aircraft |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
| CN205044941U (en) * | 2015-03-24 | 2016-02-24 | 林日壮 | Aircraft with folding arm |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017205997A1 (en) * | 2016-05-28 | 2017-12-07 | SZ DJI Technology Co., Ltd. | A foldable uav |
| US11124298B2 (en) | 2016-05-28 | 2021-09-21 | SZ DJI Technology Co., Ltd. | Foldable UAV |
| US10793270B2 (en) | 2016-05-28 | 2020-10-06 | SZ DJI Technology Co., Ltd. | Foldable UAV |
| CN106240813A (en) * | 2016-08-15 | 2016-12-21 | 张琬彬 | A kind of unmanned plane rotor anti-collision structure |
| CN106347668B (en) * | 2016-11-30 | 2018-09-25 | 叶亚男 | A kind of haze unmanned plane |
| CN106347668A (en) * | 2016-11-30 | 2017-01-25 | 叶强 | Anti-haze unmanned plane |
| CN106945830A (en) * | 2017-03-23 | 2017-07-14 | 深圳市星河时代控股有限公司 | A kind of flying power structure, aircraft and flying method |
| CN108557053A (en) * | 2018-02-05 | 2018-09-21 | 叶哲企 | A kind of telescopic device of unmanned plane horn |
| CN108163182A (en) * | 2018-02-24 | 2018-06-15 | 高琴 | A kind of folding deinsectization unmanned plane |
| CN108482660B (en) * | 2018-04-16 | 2020-07-31 | 铜陵市兆林工贸有限责任公司 | Community security protection unmanned aerial vehicle |
| CN108482660A (en) * | 2018-04-16 | 2018-09-04 | 钱文娟 | A kind of community security defence unmanned plane |
| CN110481755A (en) * | 2019-07-12 | 2019-11-22 | 广东工业大学 | A kind of two degrees of freedom rotary folding unmanned plane horn |
| CN110481755B (en) * | 2019-07-12 | 2021-03-09 | 广东工业大学 | Two-degree-of-freedom rotary folding unmanned aerial vehicle arm |
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Application publication date: 20151202 |