CN103721421A - Aircraft with a plurality of rotors - Google Patents
Aircraft with a plurality of rotors Download PDFInfo
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- CN103721421A CN103721421A CN201210393958.2A CN201210393958A CN103721421A CN 103721421 A CN103721421 A CN 103721421A CN 201210393958 A CN201210393958 A CN 201210393958A CN 103721421 A CN103721421 A CN 103721421A
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- 230000001141 propulsive effect Effects 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 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
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Abstract
The invention discloses an aircraft with a plurality of rotors. The aircraft with the rotors comprises the horizontal rotors and a main support, wherein the horizontal rotors are used for applying power in the first direction to the main support, and the first direction and the main support are perpendicular to each other. The aircraft with the rotors further comprises a propulsion device, wherein the propulsion device is used for applying power in the second direction to the main support, and the second direction and the first direction are perpendicular to each other. Due to the fact that the propulsion device is added, the horizontal rotors only need to apply flight lifting power perpendicular to the ground, horizontal and forward flight power is provided by the propulsion device, and the aircraft with the rotors can keep the posture and fly horizontally and forwards; in addition, due to the fact that the power provided by the propulsion device can be completely used for horizontal and forward flight, power of the aircraft with the rotors is high.
Description
Technical field
The present invention relates to electronic toy field, particularly a kind of multi-rotor aerocraft.
Background technology
Along with improving constantly of scientific and technological development 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 deeply subject to liking of numerous airplane hobbyists.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 using, it is moving and electronic that these aircraft can be divided into again oil.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 high.Therefore, in market sale, electronic model plane occupy main status, become the universal main flow of model plane.
In numerous electronic model plane, the multi-rotor aerocraft that comprises four rotors is subject to liking of numerous airplane hobbyists deeply.By controlling the speed difference between flight attitude and four rotors, these multi-rotor aerocrafts can complete translation flight forward, backward, and to the right left, also can do take heading as axis main part clockwise or be rotated counterclockwise.
As shown in Figure 1, existing multi-rotor aerocraft comprises four rotors 1.While flying forward, as shown in Figure 2, by controlling the rotary speed of four rotors 1, make two rotors in front produce the first flight forces F1, make two rotors at rear produce the second flight forces F2.Form the change of flight attitude, the front end 31 of the main support 3 of multi-rotor aerocraft rear end 32 downward-sloping and main support 3 is 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 in the case of keeping the direction of rotation of four rotors all parallels with ground, this multi-rotor aerocraft cannot fly forward, can only fly forward obliquely and cannot flatly fly forward.Therefore, flatly flight becomes model plane research and development field problem demanding prompt solution forward.
Summary of the invention
The technical problem to be solved in the present invention is the defect that cannot flatly fly forward in order to overcome multi-rotor aerocraft of the prior art, and a kind of multi-rotor aerocraft that can flatly fly is forward provided.
The present invention solves above-mentioned technical problem by following technical proposals:
A kind of multi-rotor aerocraft, it comprises multiple rotors and a main support, those rotors all for the power that applies first direction in this main support, this first direction is mutually vertical with this main support, its feature is, 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 mutually vertical with this first direction.
Preferably, this propulsion plant is a tail-rotor, and this tail-rotor comprises a drive link and be fixed on the screw on this drive link, and this drive link is used for driving this screw rotation.
Preferably, 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 for rotating on one end of this support bar.
Preferably, on this screw, annular array has multiple blades.
Preferably, on this screw, annular array has two blades.
Preferably, be provided with one and fly to control plate on this main support, this flies to control on 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 for controlling the rotary speed of those rotors and/or this tail-rotor.
Preferably, this flies to control on plate and is also provided with a gyroscope, and this gyroscope is for detection of the deflection angle of this main support, and this controller is for controlling the rotary speed of those rotors and correcting this deflection angle.
Preferably, this gyroscope is a three-axis gyroscope, six axle gyroscopes or nine axle gyroscopes.
Positive progressive effect of the present invention is:
By increasing this propulsion plant, only need those rotors to apply the flight lift perpendicular to ground, horizontal forward flying power is provided by this propulsion plant, thereby this multi-rotor aerocraft can keep flatly flight forward of attitude.In addition, the power that this propulsion plant provides can be completely for flatly flight forward, therefore this multi-rotor aerocraft powerful.
Accompanying drawing explanation
Fig. 1 is the structural representation of existing multi-rotor aerocraft.
Fig. 2 is the force analysis figure of multi-rotor aerocraft when flight in Fig. 1.
Fig. 3 is the structural representation of the multi-rotor aerocraft of preferred embodiment of the present invention.
Fig. 4 is the force analysis figure of multi-rotor aerocraft when flight in Fig. 3.
Description of reference numerals:
Existing multi-rotor aerocraft:
Rotor: 1 first flight forces: F1
The second flight forces: F2 the first horizontal component: F10
The second horizontal component: F20 main support: 3
Front end: 31 rear ends: 32
Speed: V
The multi-rotor aerocraft of the present embodiment:
Rotor: 1 tail-rotor: 2
Screw: 21 drive links: 22
Flight lift: F3 propulsive force: F4
The specific embodiment
Below in conjunction with accompanying drawing, provide preferred embodiment of the present invention, to describe technical scheme of the present invention in detail.
As shown in Figure 3, the multi-rotor aerocraft of the present embodiment also comprises a tail-rotor 2 compared with existing multi-rotor aerocraft, and this tail-rotor 2 comprises a drive link 22 and be fixed on the screw 21 on this drive link 22, and this drive link 22 is for driving this screw 21 to rotate.On this screw 21, be provided with two blades, 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 aerial, and this drive link 22 drives these screw 21 High Rotation Speeds, produces the propulsive force F4 advancing.Under the acting in conjunction of flight lift F3 and propulsive force F4, this multi-rotor aerocraft can keep flatly flight forward of attitude.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.Changing after direction, this multi-rotor aerocraft continues to keep flatly flight forward of attitude.It will be appreciated by those skilled in the art that the power of first direction and the power of second direction are relevant with the placing attitude of this multi-rotor aerocraft.Because first direction is mutually vertical with second direction, therefore at first direction in the situation that perpendicular to the ground, the power of this first direction is just equivalent to the flight lift F3 in the present embodiment, this main support can suspend, now the power of second direction must be parallel to the ground, also has and promote the possibility that this main support is parallel to ground motion.Therefore, meet this multi-rotor aerocraft and there is the possibility that keeps attitude flatly to fly forward, but not necessarily at every moment all will keep flatly flight forward of attitude, have this function, but needn't all use this function all the time.
Therefore,, by increasing this propulsion plant, this multi-rotor aerocraft can keep flatly flight forward of attitude.In addition, the power that this propulsion plant provides can be completely for flatly flight forward, therefore 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 one end of this drive link 22, and this drive link 22 needn't rotate and only play supporting function, effect is equivalent to support bar, only makes this screw 21 rotations.In addition, on this screw, can also show more multi-disc blade by circular array, for example three blades or six blades.
On this main support, be also provided with one and fly to control plate, this flies to control on 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 for controlling the rotary speed of those rotors and this tail-rotor.
During use, user only need use a remote controller to fly to control plate transmission steering order or assisted instruction to this.This signal transmitting and receiving unit can be used commercially available wireless transceiver device.
In order to increase flight stability degree, this flies to control and on plate, is also provided with nine axle gyroscopes, and this nine axles gyroscope is for detection of the deflection of flight attitude, i.e. rotation in horizontal plane or the rotation along flight axis.This controller can also be according to the real-time rectification flight attitude of the gyrostatic testing result of this nine axle, makes the horizontal error of this main support when flight only in 1 °.Therefore, the self-control of the multi-rotor aerocraft of the present embodiment is strong and flight stability is high.
During actual production, this gyroscope can also be elected three-axis gyroscope or six axle gyroscopes as.This propulsion plant can also be selected existing jet propeller.
Although more than described the specific embodiment of the present invention, it will be understood by those of skill in the art that these only illustrate, protection scope of the present invention is limited by appended claims.Those skilled in the art is not deviating under the prerequisite of principle of the present invention and essence, can make various changes or modifications to these embodiments, but these changes and modification all fall into protection scope of the present invention.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210393958.2A CN103721421A (en) | 2012-10-16 | 2012-10-16 | Aircraft with a plurality of rotors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210393958.2A CN103721421A (en) | 2012-10-16 | 2012-10-16 | Aircraft with a plurality of rotors |
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| Publication Number | Publication Date |
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| CN103721421A true CN103721421A (en) | 2014-04-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210393958.2A Pending CN103721421A (en) | 2012-10-16 | 2012-10-16 | Aircraft with a plurality of rotors |
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| CN (1) | CN103721421A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217033A (en) * | 2015-09-23 | 2016-01-06 | 蓝劲松 | Amphibious rotor wing unmanned aerial vehicle |
| WO2017133302A1 (en) * | 2016-02-01 | 2017-08-10 | 广州亿航智能技术有限公司 | Manned aerial vehicle |
| CN108502155A (en) * | 2018-05-22 | 2018-09-07 | 张立强 | VTOL formula aircraft and hovercar |
| WO2019037036A1 (en) * | 2017-08-24 | 2019-02-28 | 田瑜 | Aerial device |
| CN110861763A (en) * | 2019-11-12 | 2020-03-06 | 汉中天行智能飞行器有限责任公司 | A tail structure suitable for multi-rotor UAV |
| CN112485832A (en) * | 2020-12-16 | 2021-03-12 | 深圳市广域鹏翔研究开发有限公司 | Suspension type active stabilization platform |
| CN115230839A (en) * | 2022-09-19 | 2022-10-25 | 中国铁路设计集团有限公司 | Thrust control method for wall-climbing robot |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10167192A (en) * | 1996-12-16 | 1998-06-23 | Torachika Kouda | Large heli-plane of parallel engine type |
| WO2006066561A1 (en) * | 2004-12-23 | 2006-06-29 | Julian Kuntz | Flying device with improved maneuverability on the ground |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| CN102627146A (en) * | 2011-02-04 | 2012-08-08 | 贝尔直升机泰克斯特龙公司 | Tilt rotor aircraft with fixed engine arrangement |
| CN203220761U (en) * | 2012-10-16 | 2013-10-02 | 田瑜 | Multi-rotor aircraft |
-
2012
- 2012-10-16 CN CN201210393958.2A patent/CN103721421A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10167192A (en) * | 1996-12-16 | 1998-06-23 | Torachika Kouda | Large heli-plane of parallel engine type |
| WO2006066561A1 (en) * | 2004-12-23 | 2006-06-29 | Julian Kuntz | Flying device with improved maneuverability on the ground |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| CN102627146A (en) * | 2011-02-04 | 2012-08-08 | 贝尔直升机泰克斯特龙公司 | Tilt rotor aircraft with fixed engine arrangement |
| CN203220761U (en) * | 2012-10-16 | 2013-10-02 | 田瑜 | Multi-rotor aircraft |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217033A (en) * | 2015-09-23 | 2016-01-06 | 蓝劲松 | Amphibious rotor wing unmanned aerial vehicle |
| WO2017133302A1 (en) * | 2016-02-01 | 2017-08-10 | 广州亿航智能技术有限公司 | Manned aerial vehicle |
| WO2019037036A1 (en) * | 2017-08-24 | 2019-02-28 | 田瑜 | Aerial device |
| CN108502155A (en) * | 2018-05-22 | 2018-09-07 | 张立强 | VTOL formula aircraft and hovercar |
| CN110861763A (en) * | 2019-11-12 | 2020-03-06 | 汉中天行智能飞行器有限责任公司 | A tail structure suitable for multi-rotor UAV |
| CN112485832A (en) * | 2020-12-16 | 2021-03-12 | 深圳市广域鹏翔研究开发有限公司 | Suspension type active stabilization platform |
| CN115230839A (en) * | 2022-09-19 | 2022-10-25 | 中国铁路设计集团有限公司 | Thrust control method for wall-climbing robot |
| CN115230839B (en) * | 2022-09-19 | 2023-01-17 | 中国铁路设计集团有限公司 | Thrust control method for wall-climbing robot |
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Free format text: FORMER OWNER: JIANG WENYAN Effective date: 20150714 Owner name: YUNEEC INTERNATIONAL CO.,LTD. Free format text: FORMER OWNER: TIAN YU Effective date: 20150714 |
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Effective date of registration: 20150714 Address after: Jinxi town Wei Road in Kunshan city Suzhou city Jiangsu province 215324 No. 388 Applicant after: Yuneec International co.,Ltd. Address before: The town of Jiuting Songjiang District 201615 Shanghai City Shenglong Road No. 960 Applicant before: Tian Yu Applicant before: Jiang Wenyan |
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Application publication date: 20140416 |