CN203601562U - Boomerang quadrotor aircraft - Google Patents
Boomerang quadrotor aircraft Download PDFInfo
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- CN203601562U CN203601562U CN201320740231.7U CN201320740231U CN203601562U CN 203601562 U CN203601562 U CN 203601562U CN 201320740231 U CN201320740231 U CN 201320740231U CN 203601562 U CN203601562 U CN 203601562U
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- main beam
- located lateral
- beam member
- girder side
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Abstract
The utility model relates to the technical field of multi-rotor aircrafts and in particular relates to a boomerang quadrotor aircraft. The boomerang quadrotor aircraft comprises a frame, and is characterized in that the frame comprises four main beam components, wherein an upper cover plate and a lower cover plate are respectively and correspondingly arranged above and below the four main beam components; a flight control support is arranged on the upper cover plate through a supporting column; an electronic flight control board is arranged on the flight control support; a battery is arranged on the lower part of the flight control support; each main beam component comprises two main beam side plates; a buffer is arranged below the main beam component; an oblique reinforcing plate, an oblique positioning plate and a transverse positioning plate are arranged between the two main beam side plates; a motor mounting seat is arranged at the outer end of the main beam component; a motor is fixedly arranged on the motor mounting seat; a propeller is arranged on a power output shaft of the motor through a propeller cap; an electron speed regulator is arranged on the lower part of the lower cover plate. The boomerang quadrotor aircraft takes the boomerang appearance as reference, is manufactured by using laminates or basswood and other wood boards and has the characteristics of simple structure, elegant appearance and high strength and is simple to manufacture.
Description
Technical field:
The utility model relates to multi-rotor aerocraft technical field, specifically relates to a kind of Cyclic dart quadrotor.
Background technology:
Quadrotor is popular a kind of multi-rotor aerocraft that can vertical takeoff and landing in recent years.Multi-rotor aerocraft is a kind of to be driven by multiple oars that revolve, and controls the vertically taking off and landing flyer of attitude to revolve rotating speed size between oar.Because multi-rotor aerocraft has that screw propeller is less, flight safety, simple in structure, control the advantages such as flexible, in recent years, multi-rotor aerocraft is mainly used in enemy's situation scouting and supervision, battlefield is destroyed assessment, is used as counter radiation and miniature attack weapon, bait etc., also can be used for taking photo by plane, mapping, forest fire protection, sprays insecticide etc.But multi-rotor aerocraft of the prior art is made mainly with materials such as carbon beam, metal, duroplastss greatly, and cost of manufacture is too high, manufacture craft more complicated, causes being unfavorable for using and popularizing.
Utility model content:
The utility model is for complex manufacturing technology of the prior art, the defect that cost is high and a kind of Cyclic dart quadrotor of providing, thus efficiently solve the problems of the prior art.
The utility model solves the scheme that its technical matters adopts: described a kind of Cyclic dart quadrotor, comprise frame, be characterized in that described frame comprises four main beam members, four main beam members up and down respectively correspondence be provided with upper cover plate and lower cover, flying to control bearing is arranged on upper cover plate by pillar, fly to control and on bearing, be provided with electronics and fly to control plate, fly to control bearing bottom and be provided with battery; Described main beam member comprises two girder side plates, main beam member below is also provided with energy disperser, between two girder side plates, be provided with oblique stiffening plate, oblique locating plate and located lateral plate, motor mount is arranged on main beam member outer end, motor is fixedly mounted on motor mount, on the power take-off shaft of motor, by slurry cap, screw propeller is installed, described lower cover bottom is provided with electronic governor.
Described frame adopts the wooden connected structure of cantilever beam, on four main beam members of frame, be provided with the grafting boss corresponding with spliced eye on upper cover plate and lower cover, on two girder side plates of main beam member, be provided with the inserting groove corresponding with oblique stiffening plate, oblique locating plate and located lateral plate; On described motor mount, be also provided with the inserting groove corresponding with main beam member.
Described oblique stiffening plate is three, corresponding pegging graft is arranged on two girder side plate middle parts respectively, corresponding the pegging graft of described oblique locating plate is arranged on two girder side plate front ends, described located lateral plate comprises the first located lateral plate and the second located lateral plate, and the first located lateral plate and the second located lateral plate respectively corresponding pegging graft are arranged on two girder side plate front-end and back-end.
Described battery, electronics flies to control plate and is connected by wire with electronic governor.
Described main beam member is variable cross section-type structure.
The utility model passes through technique scheme, there is following effect: described a kind of Cyclic dart quadrotor, its take Cyclic dart profile as with reference to and use the planks such as laminate or linden to make, simple in structure, outward appearance is generous, intensity is large, make the characteristics such as simple.
Accompanying drawing explanation:
Fig. 1 is structure principle chart of the present utility model;
Fig. 2 is the main beam member structural representation of Fig. 1 of the present utility model;
Fig. 3 is the upper cover plate structural representation of Fig. 1 of the present utility model;
Fig. 4 is the girder lateral plate structure schematic diagram of Fig. 1 of the present utility model.
Shown in figure: 01. electronics flies to control plate; 02. flies to control bearing; 03. pillar; 04. battery; 05. upper cover plate; 06. slurry cap; 07. screw propeller; 08. motor; 09. motor mount; 10. girder side plate; 11. oblique locatings plate; 12. first located lateral plates; 13. oblique stiffening plates; 14. lower covers; 15. second located lateral plates; 16. energy dispersers; 17. electronic governors; 18. main beam members.
The specific embodiment
Be described in further detail below in conjunction with the most preferred embodiment shown in accompanying drawing
As shown in Figures 1 to 4, described a kind of Cyclic dart quadrotor, comprise frame, be characterized in that described frame comprises four main beam members 18, four main beam members 18 up and down respectively correspondence be provided with upper cover plate 05 and lower cover 14, fly to control bearing 02 and be arranged on upper cover plate 05 by pillar 03, fly to control and on bearing 02, be provided with electronics and fly to control plate 01, fly to control bearing 02 bottom and be provided with battery 04; Described main beam member 18 comprises two girder side plates 10, main beam member 18 belows are also provided with energy disperser 16, between two girder side plates 10, be provided with oblique stiffening plate 13, oblique locating plate 1l and located lateral plate, motor mount 09 is arranged on main beam member 18 outer ends, motor 08 is fixedly mounted on motor mount 09, on the power take-off shaft of motor 08, by slurry cap 06, screw propeller 07 is installed, described lower cover 14 bottoms are provided with electronic governor 17.
Described frame adopts the wooden connected structure of cantilever beam, on four main beam members 18 of frame, be provided with the grafting boss corresponding with spliced eye on upper cover plate 05 and lower cover 14, on two girder side plates 10 of main beam member 18, be provided with the inserting groove corresponding with oblique stiffening plate 13, oblique locating plate 11 and located lateral plate; On described motor mount 09, be also provided with the inserting groove corresponding with main beam member 18.
Described oblique stiffening plate 13 is three, corresponding pegging graft is arranged on two girder side plate 10 middle parts respectively, described corresponding the pegging graft of oblique locating plate 11 is arranged on two girder side plate 10 front ends, described located lateral plate comprise the first located lateral plate 12 and the second located lateral plate 15, the first located lateral plates 12 and the second located lateral plate 15 respectively corresponding pegging graft be arranged on two girder side plate 10 front-end and back-end.
Described battery 04, electronics flies to control plate 01 and is connected by wire with electronic governor 17.
Described main beam member 18 is variable cross section-type structure.
Described a kind of Cyclic dart quadrotor, relies on multi-rotor aerocraft control principle completely when flight, attitude is controlled by four motor speeds.This kind of Cyclic dart quadrotor is simple in structure, making material is cheap, outward appearance is generous, can meet airplane hobbyist and other players' operating needs completely.
Claims (5)
1. a Cyclic dart quadrotor, comprise frame, it is characterized in that described frame comprises four main beam members, four main beam members up and down respectively correspondence be provided with upper cover plate and lower cover, flying to control bearing is arranged on upper cover plate by pillar, fly to control and on bearing, be provided with electronics and fly to control plate, fly to control bearing bottom and be provided with battery; Described main beam member comprises two girder side plates, main beam member below is also provided with energy disperser, between two girder side plates, be provided with oblique stiffening plate, oblique locating plate and located lateral plate, motor mount is arranged on main beam member outer end, motor is fixedly mounted on motor mount, on the power take-off shaft of motor, by slurry cap, screw propeller is installed, described lower cover bottom is provided with electronic governor.
2. a kind of Cyclic dart quadrotor according to claim 1, it is characterized in that: described frame adopts the wooden connected structure of cantilever beam, on four main beam members of frame, be provided with the grafting boss corresponding with spliced eye on upper cover plate and lower cover, on two girder side plates of main beam member, be provided with the inserting groove corresponding with oblique stiffening plate, oblique locating plate and located lateral plate; On described motor mount, be also provided with the inserting groove corresponding with main beam member.
3. a kind of Cyclic dart quadrotor according to claim 1 and 2, it is characterized in that: described oblique stiffening plate is three, corresponding pegging graft is arranged on two girder side plate middle parts respectively, corresponding the pegging graft of described oblique locating plate is arranged on two girder side plate front ends, described located lateral plate comprises the first located lateral plate and the second located lateral plate, and the first located lateral plate and the second located lateral plate respectively corresponding pegging graft are arranged on two girder side plate front-end and back-end.
4. a kind of Cyclic dart quadrotor according to claim 1, is characterized in that: described battery, electronics flies to control plate and be connected by wire with electronic governor.
5. a kind of Cyclic dart quadrotor according to claim 1, is characterized in that: described main beam member is variable cross section-type structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320740231.7U CN203601562U (en) | 2013-11-15 | 2013-11-15 | Boomerang quadrotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320740231.7U CN203601562U (en) | 2013-11-15 | 2013-11-15 | Boomerang quadrotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203601562U true CN203601562U (en) | 2014-05-21 |
Family
ID=50714250
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320740231.7U Expired - Fee Related CN203601562U (en) | 2013-11-15 | 2013-11-15 | Boomerang quadrotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203601562U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105070140A (en) * | 2015-09-24 | 2015-11-18 | 中国矿业大学徐海学院 | Quad-rotor flight training rack |
| WO2016062223A1 (en) * | 2014-10-19 | 2016-04-28 | 吴建伟 | Vertical take-off and landing aircraft |
-
2013
- 2013-11-15 CN CN201320740231.7U patent/CN203601562U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016062223A1 (en) * | 2014-10-19 | 2016-04-28 | 吴建伟 | Vertical take-off and landing aircraft |
| CN105070140A (en) * | 2015-09-24 | 2015-11-18 | 中国矿业大学徐海学院 | Quad-rotor flight training rack |
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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: 20140521 Termination date: 20161115 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |