CN203220761U - Multi-rotor aircraft - Google Patents
Multi-rotor aircraft Download PDFInfo
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- CN203220761U CN203220761U CN 201220530271 CN201220530271U CN203220761U CN 203220761 U CN203220761 U CN 203220761U CN 201220530271 CN201220530271 CN 201220530271 CN 201220530271 U CN201220530271 U CN 201220530271U CN 203220761 U CN203220761 U CN 203220761U
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- rotor
- rotor aerocraft
- main support
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- 238000001514 detection method Methods 0.000 claims description 3
- 239000012467 final product Substances 0.000 description 4
- 230000001141 propulsive effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002950 deficient Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000013519 translation Methods 0.000 description 1
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Abstract
The utility model discloses a multi-rotor aircraft, comprising a plurality of horizontal rotors and a main rack. The horizontal rotors are all used for applying power of the first direction to the main rack, and the first direction is mutually vertical to the main rack. The multi-rotor aircraft also comprises a propelling device, used for applying power of the second direction to the main rack. The second direction is mutually vertical to the first direction. With the arrangement of the propelling device, the horizontal rotors apply a flying lift force vertical to the ground. The horizontal and forward flying lift force is provided by the propelling device. The multi-rotor aircraft can maintain posture and fly horizontally and forwardly. The power supplied by the propelling device can be fully used for flying horizontally and forwardly, and thereby the power of the multi-rotor aircraft is strong.
Description
Technical field
The utility model relates to the electronic toy field, particularly a kind of multi-rotor aerocraft.
Background technology
Along with improving constantly of development of science and technology and people's living standard, the kind of electronic toy is more and more abundanter, and function also from strength to strength.In these electronic toys, aircraft is as a kind of electronic toy of top grade and be subjected to liking of numerous airplane hobbyists deeply.These aircraft can wireless long-distance remote control, and according to the difference of its purposes and performance, these aircraft can be divided into several classes such as toy, model plane, civil and military.According to the difference of the fuel that uses, it is moving and electronic that these aircraft can be divided into oil again.The moving largest benefit of oil is that cruising time is long, and needing only timely oiling can fly, and horsepower is powerful.But the danger coefficient of servomotor is higher, safeguard relative complex and price comparison height.Therefore, in market sale, electronic model plane occupy main status, become the main flow that model plane are popularized.
In numerous electronic model plane, the multi-rotor aerocraft that comprises four rotors is subjected to liking of numerous airplane hobbyists deeply.By the speed difference between control flight attitude and four rotors, these multi-rotor aerocrafts can be finished forward, the flight of translation backward, left and to the right, also can do clockwise or be rotated counterclockwise for the axis main part with the heading.
As shown in Figure 1, existing multi-rotor aerocraft comprises four rotors 1.When flying forward, as shown in Figure 2, make two rotors in the place ahead produce the first flight forces F1 by the rotary speed of controlling four rotors 1, make two rotors at rear produce the second flight forces F2.Form the change of flight attitude, namely front end 31 rear ends 32 downward-sloping and main support 3 of the main support 3 of multi-rotor aerocraft are upturned.The first flight forces F1 has one first horizontal component F10, and the second flight forces F2 has one second horizontal component F20.Under the acting in conjunction of the first horizontal component F10 and the second horizontal component F20, this multi-rotor aerocraft is with speed V flight forward obliquely.
But, the direction of rotation that keeps four rotors all with situation that ground parallels under, this multi-rotor aerocraft can't fly forward, namely can only fly forward obliquely and can't flatly fly forward.Therefore, flatly forward flight become model plane research and development field problem demanding prompt solution.
The utility model content
The technical problems to be solved in the utility model is in order to overcome the defective that multi-rotor aerocraft of the prior art can't flatly fly forward, a kind of multi-rotor aerocraft that can flatly fly forward to be provided.
The utility model solves above-mentioned technical problem by following technical proposals:
A kind of multi-rotor aerocraft, it comprises a plurality of rotors and a main support, those rotors all be used to the power that applies first direction in this main support, this first direction is vertical mutually with this main support, its characteristics are, this multi-rotor aerocraft also comprises a propulsion plant, and the power that this propulsion plant is used for applying a second direction is in main support, and this second direction is vertical mutually with this first direction.
Preferable, this propulsion plant is a tail-rotor, and this tail-rotor comprises a drive link and the screw that is fixed on this drive link, and this drive link is used for driving this screw rotation.
Preferable, this propulsion plant is a tail-rotor, and this tail-rotor comprises a support bar and a screw, and this support bar is fixed on this main support, and this screw is used for rotating on an end of this support bar.
Preferable, circular array is shown a plurality of blades on this screw.
Preferable, circular array is shown two blades on this screw.
Preferable, this main support is provided with one and flies to control plate, and this flies to control plate and is provided with a signal transmitting and receiving unit and a controller, and this signal transmitting and receiving unit is used for receiving a control signal, and this controller is used for the rotary speed of those rotors of control and/or this tail-rotor.
Preferable, this flies to control and also is provided with a gyroscope on the plate, and this gyroscope is for detection of the deflection angle of this main support, and this controller is used for the rotary speed of those rotors of control and corrects this deflection angle.
Preferable, this gyroscope is a three-axis gyroscope, six gyroscopes or nine gyroscopes.
Positive progressive effect of the present utility model is:
By increasing this propulsion plant, the flight lift that only needs those rotors to apply perpendicular to ground gets final product, and level flying power is forward provided by this propulsion plant, thereby this multi-rotor aerocraft can keep attitude flight forward flatly.In addition, the power that this propulsion plant provides can be used for flatly flight forward fully, so this multi-rotor aerocraft powerful.
Description of drawings
Fig. 1 is the structural representation of existing multi-rotor aerocraft.
Fig. 2 is the force analysis figure of multi-rotor aerocraft when flight among Fig. 1.
Fig. 3 is the structural representation of the multi-rotor aerocraft of the utility model preferred embodiment.
Fig. 4 is the force analysis figure of multi-rotor aerocraft when flight among Fig. 3.
Description of reference numerals:
Existing multi-rotor aerocraft:
Rotor: 1 first flight forces: F1
Second flight forces: F2, first horizontal component: F10
Second horizontal component: F20 main support: 3
Front end: 31 rear ends: 32
Speed: V
The multi-rotor aerocraft of present embodiment:
Rotor: 1 tail-rotor: 2
Screw: 21 drive links: 22
Flight lift: F3 propulsive force: F4
The specific embodiment
Provide the utility model preferred embodiment below in conjunction with accompanying drawing, to describe the technical solution of the utility model in detail.
As shown in Figure 3, the multi-rotor aerocraft of present embodiment is compared with existing multi-rotor aerocraft and is comprised that also a tail-rotor 2, this tail-rotor 2 comprise a drive link 22 and the screw 21 that is fixed on this drive link 22, and this drive link 22 is used for driving this screw 21 rotations.This screw 21 is provided with two blades, and the angle of those blades is 180 °.
During use, as shown in Figure 4, those rotors all apply flight lift F3 perpendicular to ground on this main support, make to be suspended on this main support in the air, and this drive link 22 drives this screw 21 rotation at a high speed, produces the propulsive force F4 that advances.Under the acting in conjunction of flight lift F3 and propulsive force F4, this multi-rotor aerocraft can keep attitude flight forward flatly.When needs change direction, only need to regulate the rotary speed of those rotors 1, form rotation torque, make this multi-rotor aerocraft tilt to change direction.After changing direction, this multi-rotor aerocraft continues to keep attitude flight forward flatly.The power that it will be appreciated by those skilled in the art that the power of first direction and second direction is relevant with the placing attitude of this multi-rotor aerocraft.Because first direction is vertical mutually with second direction, therefore at first direction under situation perpendicular to the ground, the power of this first direction just is equivalent to the flight lift F3 in the present embodiment, this main support namely can suspend, this moment, the power of second direction must be parallel to the ground, also namely has to promote the possibility that this main support is parallel to ground motion.Therefore, satisfy this multi-rotor aerocraft and have the possibility that keeps attitude flatly to fly forward, but not necessarily at every moment all will keep attitude flight forward flatly, namely have this function and get final product, but needn't all will use this function all the time.
Therefore, by increasing this propulsion plant, this multi-rotor aerocraft can keep attitude flight forward flatly.In addition, the power that this propulsion plant provides can be used for flatly flight forward fully, so this multi-rotor aerocraft powerful.
During actual production, can also adopt drive link 22 to be fixed on this main support, this screw rotates on the structure of an end of this drive link 22, and namely this drive link 22 needn't rotate and only play the support effect, effect is equivalent to support bar, only makes these screw 21 rotations get final product.In addition, can also show more multi-disc blade by circular array on this screw, for example three blades or six blades.
Also be provided with one on this main support and fly to control plate, this flies to control plate and is provided with a signal transmitting and receiving unit and a controller, and this signal transmitting and receiving unit is used for receiving a control signal, and this controller is used for the rotary speed of those rotors of control and this tail-rotor.
During use, the user only need use a remote controller to fly to control that plate sends steering order or assisted instruction gets final product to this.This signal transmitting and receiving unit can use commercially available wireless transceiver device.
In order to increase the flight stability degree, this flies to control and also is provided with nine gyroscopes on the plate, and these nine gyroscopes are for detection of the deflection of flight attitude, i.e. rotation in horizontal plane or along the rotation of flight axis.This controller can also make the horizontal error of this main support when flight only in 1 ° according to the real-time rectification flight attitude of these nine gyrostatic testing results.Therefore, the strong and flight stability height of the self-control of the multi-rotor aerocraft of present embodiment.
During actual production, this gyroscope can also be elected three-axis gyroscope or six gyroscopes as.This propulsion plant can also be selected existing jet propeller.
Though more than described the specific embodiment of the present utility model, it will be understood by those of skill in the art that these only illustrate, protection domain of the present utility model is limited by appended claims.Those skilled in the art can make numerous variations or modification to these embodiments under the prerequisite that does not deviate from principle of the present utility model and essence, but these changes and modification all fall into protection domain of the present utility model.
Claims (8)
1. multi-rotor aerocraft, it comprises a plurality of rotors and a main support, those rotors all be used to the power that applies first direction in this main support, this first direction is vertical mutually with this main support, it is characterized in that, this multi-rotor aerocraft also comprises a propulsion plant, and the power that this propulsion plant is used for applying a second direction is in main support, and this second direction is vertical mutually with this first direction.
2. multi-rotor aerocraft as claimed in claim 1 is characterized in that, this propulsion plant is a tail-rotor, and this tail-rotor comprises a drive link and the screw that is fixed on this drive link, and this drive link is used for driving this screw rotation.
3. multi-rotor aerocraft as claimed in claim 1 is characterized in that, this propulsion plant is a tail-rotor, and this tail-rotor comprises a support bar and a screw, and this support bar is fixed on this main support, and this screw is used for rotating on an end of this support bar.
4. as any described multi-rotor aerocraft among the claim 2-3, it is characterized in that circular array is shown a plurality of blades on this screw.
5. multi-rotor aerocraft as claimed in claim 4 is characterized in that, circular array is shown two blades on this screw.
6. multi-rotor aerocraft as claimed in claim 5, it is characterized in that, this main support is provided with one and flies to control plate, this flies to control plate and is provided with a signal transmitting and receiving unit and a controller, this signal transmitting and receiving unit is used for receiving a control signal, and this controller is used for the rotary speed of those rotors of control and/or this tail-rotor.
7. multi-rotor aerocraft as claimed in claim 6 is characterized in that, this flies to control and also is provided with a gyroscope on the plate, and this gyroscope is for detection of the deflection angle of this main support, and this controller is used for the rotary speed of those rotors of control and corrects this deflection angle.
8. multi-rotor aerocraft as claimed in claim 7 is characterized in that, this gyroscope is a three-axis gyroscope, six gyroscopes or nine gyroscopes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220530271 CN203220761U (en) | 2012-10-16 | 2012-10-16 | Multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220530271 CN203220761U (en) | 2012-10-16 | 2012-10-16 | Multi-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203220761U true CN203220761U (en) | 2013-10-02 |
Family
ID=49247779
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220530271 Expired - Lifetime CN203220761U (en) | 2012-10-16 | 2012-10-16 | Multi-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203220761U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103721421A (en) * | 2012-10-16 | 2014-04-16 | 田瑜 | Aircraft with a plurality of rotors |
| CN104670486A (en) * | 2013-12-03 | 2015-06-03 | 曹卓荣 | Manipulator for osprey aircraft |
| WO2017197603A1 (en) * | 2016-05-18 | 2017-11-23 | 深圳市创客工场科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN108995800A (en) * | 2018-09-07 | 2018-12-14 | 佛山皖和新能源科技有限公司 | A kind of novel rotor wing unmanned aerial vehicle structure |
-
2012
- 2012-10-16 CN CN 201220530271 patent/CN203220761U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103721421A (en) * | 2012-10-16 | 2014-04-16 | 田瑜 | Aircraft with a plurality of rotors |
| CN104670486A (en) * | 2013-12-03 | 2015-06-03 | 曹卓荣 | Manipulator for osprey aircraft |
| WO2017197603A1 (en) * | 2016-05-18 | 2017-11-23 | 深圳市创客工场科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN108995800A (en) * | 2018-09-07 | 2018-12-14 | 佛山皖和新能源科技有限公司 | A kind of novel rotor wing unmanned aerial vehicle structure |
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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: YUNEEC INTERNATIONAL CO.,LTD. Free format text: FORMER OWNER: TIAN YU Effective date: 20150709 Free format text: FORMER OWNER: JIANG WENYAN Effective date: 20150709 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20150709 Address after: Jinxi town Wei Road in Kunshan city Suzhou city Jiangsu province 215324 No. 388 Patentee after: HAOXIANG ELECTRIC ENERGY (KUNSHAN) Co.,Ltd. Address before: The town of Jiuting Songjiang District 201615 Shanghai City Shenglong Road No. 960 Patentee before: Tian Yu Patentee before: Jiang Wenyan |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160314 Address after: Hongkong Hongguang Road, Kowloon Bay China billion centre 10 floor Patentee after: YUNEEC TECHNOLOGY Co.,Ltd. Address before: Jinxi town Wei Road in Kunshan city Suzhou city Jiangsu province 215324 No. 388 Patentee before: HAOXIANG ELECTRIC ENERGY (KUNSHAN) Co.,Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20131002 |