CN203958614U - Integral type multi-rotor aerocraft - Google Patents
Integral type multi-rotor aerocraft Download PDFInfo
- Publication number
- CN203958614U CN203958614U CN201420422129.7U CN201420422129U CN203958614U CN 203958614 U CN203958614 U CN 203958614U CN 201420422129 U CN201420422129 U CN 201420422129U CN 203958614 U CN203958614 U CN 203958614U
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- main body
- underframe
- integral type
- type multi
- rotor aerocraft
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Abstract
Integral type multi-rotor aerocraft, comprise main body upper cover, main body, main body lower cover, underframe and Long-distance Control mechanism, main body upper cover and main body lower cover are fixed on main body upper and lower surface, the extension of main body surrounding is connected with some horns, the end of each horn is installed a motor, a pair of blade is installed respectively on every motor, and the interior volume that main body upper cover and main body lower cover form is provided with control box, and main body and underframe are bolted.The main body of the present utility model structure that is formed in one, does not need to use too many bolt operation easy for installation succinct, has solved existing aircraft installing component too much, and the problem of complex installation process, has advantages of compact conformation, easy for installation and high stability.
Description
Technical field
The utility model relates to aeronautical product technical field, is specifically related to a kind of integral type multi-rotor aerocraft.
Background technology
Multi-rotor aerocraft operates on it control by wireless remote control system and independent flight control system, to realize the landing of aircraft, flight all around, acceleration and deceleration and direction control etc.Manipulative capability, stability, effective mission payload and cruise duration are the important indicators of investigating multi-rotor aerocraft, and under identical manipulative capability and stability condition, user pursues larger effective mission payload and long-time duration flight ability.
Multi-rotor aerocraft on market is mainly made up of driving engine, drive link, blade and Long-distance Control mechanism now, driving engine is connected with multiple blades by drive link, a steering wheel is installed on each drive link, it between each assembly, is sectional construction, assembly is more, complex installation process, and the stability of the aircraft of sectional construction is desirable not to the utmost.
Utility model content
The utility model provides a kind of integral type multi-rotor aerocraft, to solve the problem that the assembly that prior art exists is more, loaded down with trivial details and poor stability are installed.
The utility model solves the technical scheme that its technical matters adopts:
A kind of integral type multi-rotor aerocraft, comprise main body upper cover, main body, main body lower cover, underframe and Long-distance Control mechanism, main body upper cover and main body lower cover are fixed on main body upper and lower surface, the extension of main body surrounding is connected with some horns, the end of each horn is installed a motor, a pair of blade is installed respectively on every motor, and the interior volume that main body upper cover and main body lower cover form is provided with control box, and main body and underframe are bolted.
Graphicinformation projector and picture monitor are set in above-mentioned control box.
Above-mentioned underframe comprises the bend pipe of falling U of two parallel interval settings, for connecting the connection pipe of the bend pipe of falling U end and the reinforced pipe between two bend pipes of falling U, on two bend pipe of falling U tops, directly with bolt, underframe is fixed on to main body bottom surface.
Above-mentioned Long-distance Control mechanism comprises central process unit, gps antenna, signal projector, data-interface, picture sensor and control desk, wherein gps antenna, signal projector, data-interface, picture sensor and control desk are all connected with central process unit, and gps antenna is connected with the graphicinformation launcher signal at top center dish top by central process unit; In control desk, be provided with computing machine, computing machine is connected with signal controller, and signal controller is connected with picture monitor.
Aforementioned body adopts cellular composite material to make; Blade material is carbon fiber.
Than prior art, the main body of the present utility model structure that is formed in one, does not need to use too many bolt operation easy for installation succinct, has solved existing aircraft installing component too much, the problem of complex installation process, has advantages of compact conformation, easy for installation and high stability.
Brief description of the drawings
Below in conjunction with drawings and Examples, the utility model is further illustrated.
Fig. 1 is the structural representation of the utility model device;
Fig. 2 is the front elevational schematic of the utility model device;
Fig. 3 is the fundamental diagram of the utility model device Long-distance Control mechanism;
Fig. 4 is the structural representation of the utility model device underframe.
1 main body upper cover, 2 control boxs, 3 main bodys, 4 blades, 5 motors, 6 main body lower covers, 7 underframe, 8 horns, 9 graphicinformation projectors, 10 central process units, 11GPS antenna, 12 signal projectors, 13 data-interfaces, 14 control deskes, 15 computing machines, 16 signal controllers, 17 picture sensors, 18 picture monitors, 701 bend pipes of falling U, 702 reinforced pipes, 703 connection pipes in figure.
Detailed description of the invention
As Fig. 1, Fig. 2, shown in Fig. 3 and Fig. 4, a kind of integral type multi-rotor aerocraft, comprise main body upper cover 1, main body 3, main body lower cover 6, underframe 7 and Long-distance Control mechanism, main body upper cover 1 and main body lower cover 6 are fixed on main body 3 upper and lower surfaces, main body 3 surroundings extensions are connected with some horns 8, the end of each horn 8 is installed a motor 5, a pair of blade 4 is installed respectively on every motor 5, the interior volume that main body upper cover 1 and main body lower cover 6 form is provided with control box 2, main body 3 is bolted with underframe 7, interior graphicinformation projector 9 and the picture monitor 18 of arranging of control box 2, main body 3 adopts cellular composite material to make, blade 4 materials are carbon fiber.
Underframe 7 comprises the bend pipe of falling U 701 of two parallel interval settings, for connecting the connection pipe 703 of the bend pipe of falling U 701 ends and directly with bolt, underframe is fixed on to main body 3 bottom surfaces on 702, two bend pipe of falling U 701 top of the reinforced pipe between two bend pipes of falling U 701.
Above-mentioned Long-distance Control mechanism comprises central process unit 10, gps antenna 11, signal projector 12, data-interface 13 and graphicinformation projector 9; Wherein graphicinformation projector 9, gps antenna 11, signal projector 12, data-interface 13 and picture sensor 17 are all connected with central process unit 10, and gps antenna 11 is connected with graphicinformation projector 9 by central process unit 10; Aircraft also comprises the control desk 14 that is provided with computing machine 15; Computing machine 15 is connected with signal controller 16, and signal controller 16 is connected with picture monitor 18 again.
Claims (4)
1. an integral type multi-rotor aerocraft, it is characterized in that comprising main body upper cover, main body, main body lower cover, underframe and Long-distance Control mechanism, main body upper cover and main body lower cover are fixed on main body upper and lower surface, the extension of main body surrounding is connected with some horns, the end of each horn is installed a motor, a pair of blade is installed respectively on every motor, and the interior volume that main body upper cover and main body lower cover form is provided with control box, and main body and underframe are bolted.
2. integral type multi-rotor aerocraft according to claim 1, is characterized in that arranging in control box graphicinformation projector and picture monitor.
3. integral type multi-rotor aerocraft according to claim 1, it is characterized in that underframe comprise the bend pipe of falling U of two parallel interval settings, for connecting the connection pipe of the bend pipe of falling U end and the reinforced pipe between two bend pipes of falling U, on two bend pipe of falling U tops, directly with bolt, underframe is fixed on to main body bottom surface.
4. integral type multi-rotor aerocraft according to claim 1, it is characterized in that Long-distance Control mechanism comprises central process unit, gps antenna, signal projector, data-interface, picture sensor and control desk, wherein gps antenna, signal projector, data-interface, picture sensor and control desk are all connected with central process unit, and gps antenna is connected with the graphicinformation launcher signal at top center dish top by central process unit; In control desk, be provided with computing machine, computing machine is connected with signal controller, and signal controller is connected with picture monitor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420422129.7U CN203958614U (en) | 2014-07-24 | 2014-07-24 | Integral type multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420422129.7U CN203958614U (en) | 2014-07-24 | 2014-07-24 | Integral type multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203958614U true CN203958614U (en) | 2014-11-26 |
Family
ID=51919234
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420422129.7U Expired - Fee Related CN203958614U (en) | 2014-07-24 | 2014-07-24 | Integral type multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203958614U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590555A (en) * | 2015-01-28 | 2015-05-06 | 王文有 | Electrodynamic multi-rotor helicopter |
| CN105799919A (en) * | 2016-03-22 | 2016-07-27 | 山东乾通航空科技有限公司 | Oil-driven multi-rotor wing air vehicle |
| CN106081085A (en) * | 2016-07-09 | 2016-11-09 | 精功（绍兴）复合材料有限公司 | A kind of composite multi-rotor aerocraft body and preparation method |
| CN107600391A (en) * | 2017-10-18 | 2018-01-19 | 沈阳旋飞航空技术有限公司 | A kind of electronic unmanned plane undercarriage |
-
2014
- 2014-07-24 CN CN201420422129.7U patent/CN203958614U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590555A (en) * | 2015-01-28 | 2015-05-06 | 王文有 | Electrodynamic multi-rotor helicopter |
| CN105799919A (en) * | 2016-03-22 | 2016-07-27 | 山东乾通航空科技有限公司 | Oil-driven multi-rotor wing air vehicle |
| CN106081085A (en) * | 2016-07-09 | 2016-11-09 | 精功（绍兴）复合材料有限公司 | A kind of composite multi-rotor aerocraft body and preparation method |
| CN107600391A (en) * | 2017-10-18 | 2018-01-19 | 沈阳旋飞航空技术有限公司 | A kind of electronic unmanned plane undercarriage |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: SHANDONG TIANXI AVIATION TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: SHANDONG NEW MORNING TECHNOLOGY CO., LTD. Effective date: 20150424 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 253000 DEZHOU, SHANDONG PROVINCE TO: 250000 DEZHOU, SHANDONG PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20150424 Address after: 250000, No. 5-7, A District, Dong Zi Culture Street, 1118 Dongfanghong Road, Dezhou Economic Development Zone, Shandong, China Patentee after: Shandong Tianxi Aviation Technology Co. Ltd. Address before: 253000 Shandong city in Dezhou Province Economic Development Zone East Road north of the King River west of Dong culture street block A 7 Patentee before: SHANDONG XINCHEN TECHNOLOGY CO., LTD. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141126 Termination date: 20180724 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |