CN203681867U - Separation type multi-rotor aircraft - Google Patents
Separation type multi-rotor aircraft Download PDFInfo
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- CN203681867U CN203681867U CN201320786682.4U CN201320786682U CN203681867U CN 203681867 U CN203681867 U CN 203681867U CN 201320786682 U CN201320786682 U CN 201320786682U CN 203681867 U CN203681867 U CN 203681867U
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Abstract
The utility model provides a separation type multi-rotor aircraft and belongs to the technical field of mini-type multi-rotor aircrafts. The separation type multi-rotor aircraft is composed of a connection plate and a plurality of single-rotor subsystems 1 mounted on the connection plate, wherein each single-rotor subsystem comprises a rotor (5), a motor (7), an electron speed regulator (15), a battery (10) and a control circuit (13). The separation type multi-rotor aircraft with different quantity of rotors and different structural layouts can be assembled according to different flight mission requirements.
Description
Technical field
The present invention is a kind of microminiature multi-rotor aerocraft that adopts separate type.
Background technology
Microminiature multi-rotor aerocraft be a kind of simple in structure, maneuverability is very high, unmanned vehicle that can vertical takeoff and landing.Taking photo by plane, search and rescue, have compared with widespread use aspect transportation.Above-mentioned application all has higher mission payload requirement to multi-rotor aerocraft.But now widely used multi-rotor aerocraft, all adopts the integrated structure design of fixing rotor quantity, fixed sturcture size.This integrated structure design, all has strict restriction to size and the weight of multi-rotor aerocraft institute vehicle equipment, has therefore limited the range of use of multi-rotor aerocraft.
Summary of the invention
In order to overcome the defect of existing microminiature multi-rotor aerocraft integrated structure design, the present invention proposes a kind of microminiature multi-rotor aerocraft that adopts separate type.It is made up of multiple single rotor subsystems and connecting panel, can, according to different aerial mission requirements, be assembled into the multi-rotor aerocraft of different rotor quantity, different structure layout.
The present invention realizes the technical scheme that its function adopts: separation type multi-rotor aerocraft is by connecting panel, and is installed on the some single rotor subsystem composition on connecting panel; Wherein each single rotor subsystem comprises rotor, motor, electronic governor, battery, control circuit.
By control signal, can realize the independent control to each single rotor subsystem.Several single rotor subsystems, by connecting floor installation in connecting panel, form many rotors fabricate block.Can select single rotor subsystem of varying number to be arranged on the connecting panel of different size and shape, be assembled into the multi-rotor aerocraft of different structure layout, thereby meet the requirement of different aerial missions.In flight course, by control signal, adjust respectively the gyroplane rotate speed of each rotor subsystem, different gyroplane rotate speeds produces different rotor lifts and anti-twisted moment, thereby realizes the attitude control to many rotors fabricate block.
The invention has the beneficial effects as follows: overcome existing multi-rotor aerocraft and be subject to fixing scantling of structure and rotor to count quantitative limitation; Multi-rotor aerocraft can require to adjust topology layout according to different aerial missions, thereby is applicable to field of application widely.
accompanying drawing explanationbelow in conjunction with drawings and Examples, the present invention is further described;
Fig. 1 is the overall schematic of separation type multi-rotor aerocraft embodiment 1, is four rotor fabricate blocks;
Fig. 2 is the overall schematic of separation type multi-rotor aerocraft embodiment 2, is six rotor fabricate blocks;
Fig. 3 is the overall schematic of separation type multi-rotor aerocraft embodiment 3, is eight rotor fabricate blocks;
Fig. 4 is the organigram of single rotor subsystem embodiment;
1. single rotor subsystems in figure, 2. four rotor connecting panels, 3. six rotor connecting panels, 4. eight rotor connecting panels, 5. rotor, 6. motor fixing plate, 7. motor, 8. hexagonal negative thread insulated column, 9. motor mounting plate, 10. battery, 11. battery adapter plates, 12. connect base, 13. control circuits, 14. wires, 15. electronic governors.
The specific embodiment
In Fig. 1, embodiment 1 is made up of four single rotor subsystems 1 and criss cross four rotor connecting panels 2, is four rotor fabricate blocks.
In Fig. 2, embodiment 2 is made up of six each and every one single rotor subsystems 1 and six rotor connecting panels 3, is six rotor fabricate blocks.
In Fig. 3, embodiment 3 is made up of eight rotor connecting panels 4 of eight each and every one single rotor subsystems 1 and M shape, is eight rotor fabricate blocks.
In Fig. 4, the structure of single rotor subsystem 1 comprises: rotor 5, and motor fixing plate 6, motor 7, hexagonal negative thread insulated column 8, motor mounting plate 9, battery 10, battery adapter plate 11, connects base 12, control circuit 13, wire 14, electronic governor 15.Rotor 5 is arranged on motor 7; Motor 7 is arranged on motor mounting plate 9 and located by motor fixing plate 6; Electronic governor 15 is arranged on battery adapter plate 11 with battery 10; Control circuit 13 is arranged on and connects on base 12; Motor mounting plate 9, motor fixing plate 6, battery adapter plate 11 and be connected base 12 and connect successively and fix by bolt and hexagonal negative thread insulated column 8; Control circuit 13 is connected respectively by wire 14 with electronic governor 15, battery 10 and electronic governor 15, motor 7 and electronic governor 15; Single rotor subsystem 1 is arranged on four rotor connecting panels 2 or six rotor connecting panels 3 or eight rotor connecting panels 4 by connecting base 12, can be assembled into many rotors fabricate block: four rotor fabricate block embodiment 1 or six rotor fabricate blocks (embodiment 2) or eight rotor fabricate blocks (embodiment 3).
When single rotor subsystem 1 is worked, control circuit 13 reception control signals, convert corresponding adjustment signal to; By wire 14, adjustment signal is input on electronic governor 15; Electronic governor 15, according to adjustment signal, is adjusted the rotating speed of motor 7; Rotor 5 and motor 7 are because the difference of rotating speed, by producing different lift and anti-twisted moment, therefore can realize the attitude control to many rotors fabricate block.
Claims (4)
1. a separation type multi-rotor aerocraft, is characterized in that: by connecting panel, and the some single rotor subsystem 1 being installed on connecting panel forms; Wherein each single rotor subsystem comprises rotor (5), motor (7), electronic governor (15), battery (10), control circuit (13).
2. separation type multi-rotor aerocraft according to claim 1, is characterized in that: described single rotor subsystem (1) is 4, and described connecting panel is criss cross four rotor connecting panels (2).
3. separation type multi-rotor aerocraft according to claim 1, is characterized in that: described single rotor subsystem (1) is 6, and described connecting panel is six rotor connecting panels (3).
4. separation type multi-rotor aerocraft according to claim 1, is characterized in that: described single rotor subsystem (1) is 8, the eight rotor connecting panels (4) that described connecting panel is M shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320786682.4U CN203681867U (en) | 2013-12-04 | 2013-12-04 | Separation type multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320786682.4U CN203681867U (en) | 2013-12-04 | 2013-12-04 | Separation type multi-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203681867U true CN203681867U (en) | 2014-07-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201320786682.4U Expired - Fee Related CN203681867U (en) | 2013-12-04 | 2013-12-04 | Separation type multi-rotor aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN203681867U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104386248A (en) * | 2014-11-03 | 2015-03-04 | 成都好飞机器人科技有限公司 | Double-layer separation type unmanned aerial vehicle |
| CN104787318A (en) * | 2015-04-20 | 2015-07-22 | 吴李海 | Multi-rotor unmanned aerial vehicle with function of loaded long-time flying |
| CN104816822A (en) * | 2015-04-23 | 2015-08-05 | 张�杰 | Aircraft with four fixed rotor wings |
| CN105438437A (en) * | 2015-11-30 | 2016-03-30 | 无锡觅睿恪科技有限公司 | Separated unmanned aerial vehicle wing |
| WO2016065512A1 (en) * | 2014-10-27 | 2016-05-06 | 深圳市尚腾影科技有限公司 | Model aeroplane and electronic speed control assembly structure for same |
| CN106155075A (en) * | 2016-08-22 | 2016-11-23 | 上海交通大学 | A kind of detachable unmanned aerial vehicle control system |
| CN106477053A (en) * | 2016-04-13 | 2017-03-08 | 北京天宇新超航空科技有限公司 | A kind of oil electricity mixes many rotor unmanned aircrafts |
| CN106741908A (en) * | 2017-03-20 | 2017-05-31 | 西北工业大学 | A kind of array multi-rotor aerocraft |
| CN108275279A (en) * | 2018-04-10 | 2018-07-13 | 辽宁壮龙无人机科技有限公司 | Unmanned plane transmission component and unmanned plane |
-
2013
- 2013-12-04 CN CN201320786682.4U patent/CN203681867U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016065512A1 (en) * | 2014-10-27 | 2016-05-06 | 深圳市尚腾影科技有限公司 | Model aeroplane and electronic speed control assembly structure for same |
| CN106458321A (en) * | 2014-10-27 | 2017-02-22 | 深圳市尚腾影科技有限公司 | Model aeroplane and electronic speed control assembly structure for same |
| CN104386248A (en) * | 2014-11-03 | 2015-03-04 | 成都好飞机器人科技有限公司 | Double-layer separation type unmanned aerial vehicle |
| CN104787318A (en) * | 2015-04-20 | 2015-07-22 | 吴李海 | Multi-rotor unmanned aerial vehicle with function of loaded long-time flying |
| CN104816822A (en) * | 2015-04-23 | 2015-08-05 | 张�杰 | Aircraft with four fixed rotor wings |
| CN105438437A (en) * | 2015-11-30 | 2016-03-30 | 无锡觅睿恪科技有限公司 | Separated unmanned aerial vehicle wing |
| CN106477053A (en) * | 2016-04-13 | 2017-03-08 | 北京天宇新超航空科技有限公司 | A kind of oil electricity mixes many rotor unmanned aircrafts |
| CN106155075A (en) * | 2016-08-22 | 2016-11-23 | 上海交通大学 | A kind of detachable unmanned aerial vehicle control system |
| CN106155075B (en) * | 2016-08-22 | 2020-07-14 | 上海交通大学 | Separable unmanned aerial vehicle control system |
| CN106741908A (en) * | 2017-03-20 | 2017-05-31 | 西北工业大学 | A kind of array multi-rotor aerocraft |
| CN106741908B (en) * | 2017-03-20 | 2023-09-08 | 西北工业大学 | Array type multi-rotor aircraft |
| CN108275279A (en) * | 2018-04-10 | 2018-07-13 | 辽宁壮龙无人机科技有限公司 | Unmanned plane transmission component and unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140702 Termination date: 20141204 |
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| EXPY | Termination of patent right or utility model |