CN105173076B - A kind of vertical take-off and landing drone - Google Patents
A kind of vertical take-off and landing drone Download PDFInfo
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- CN105173076B CN105173076B CN201510639108.XA CN201510639108A CN105173076B CN 105173076 B CN105173076 B CN 105173076B CN 201510639108 A CN201510639108 A CN 201510639108A CN 105173076 B CN105173076 B CN 105173076B
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Abstract
A kind of vertical take-off and landing drone, including：Fuselage and wing, aileron, aileron are hinged with wing；The quantity of vertical fin, vertical fin is three or three or more, at least one vertical fin is set on the upside of vertical take-off and landing drone, at least one vertical fin is set on the downside of vertical take-off and landing drone, and at least partly vertical fin rear is located at trailing edge rear portion；Motor, motor are connect with wing, and the motor includes motor bearings；Propeller, propeller are connect with motor bearings.At least partly vertical fin rear is located at trailing edge rear portion so that when vertical take-off and landing drone is placed vertically, vertical fin rear plays vertical take-off and landing drone as gear support.Aileron is hinged with wing, vertical take-off and landing drone vertical takeoff, landing or high-altitude can be made to hover by rotating aileron, can also vertical take-off and landing drone high-speed horizontal flight.
Description
Technical field
The present invention relates to a kind of unmanned planes, are related specifically to a kind of vertical take-off and landing drone.
Background technology
Since unmanned plane has the advantages such as small, at low cost, and with flight control technique, the communication technology and electronic technology
Fast development, the performance of unmanned plane constantly enhances, type is on the increase, and makes its application in military domain and civil field
Demand constantly increases.
Unmanned plane is typically divided into fixed-wing unmanned plane and rotary wings unmanned plane.
Wherein fixed-wing unmanned plane is pushed by engine, and engine driving generates the horizontal thrust for being parallel to fuselage axis, makes
Unmanned plane can high-speed flight in the air.But since engine cannot generate the lift perpendicular to fuselage axis, so fixed-wing
Unmanned plane can only obtain lift by the relative motion between fixed-wing and air, to overcome the gravity of fixed-wing unmanned plane, rise
There are positive correlations for speed of related movement between the size and fixed-wing and air of power, and speed of related movement is bigger, fixed-wing
The lift that unmanned plane is obtained is also bigger.In the prior art, there is two disadvantages for fixed-wing unmanned plane：First, it is needed when taking off
Want longer runway just fixed-wing unmanned plane can be made to obtain enough horizontal velocities, so that fixed-wing unmanned plane obtains enough liters
Power is taken off；Second, fixed-wing unmanned plane need to keep after take off enough flying speeds could obtain enough lift with gram
Take the gravity of itself.
Rotary wings unmanned plane makes rotary wings around own axes rotation by engine, and when rotary wings rotation generates opposite with air
Movement obtains lift.Since the lift that rotary wings unmanned plane generates directly transfers generation, rotation certainly by engine driving rotary wings
Rotor unmanned plane takes off need not have horizontal flight speed, that is, eliminates the reliance on runway, overcome fixed-wing unmanned plane rely on it is longer
The shortcomings that runway.Meanwhile rotary wings unmanned plane also overcomes after fixed-wing unmanned plane takes off and needs to keep enough flying speeds
The shortcomings that, rotary wings unmanned plane can be vertically moved up or down, hovering, left and right is flown forwards, backwards, have flight attitude diversified
Advantage.But due to the mainly lift that rotary wings provide, the level for being parallel to fuselage axis of rotary wings unmanned plane acquisition pushes away
Power is smaller, so horizontal flight speed is slower.
In conclusion in the prior art, or unmanned plane needs to rely on long runway, and needing holding is enough to fly after taking off
Scanning frequency degree；Horizontal flight speed is slower.
Invention content
Or problems solved by the invention is that unmanned plane needs to rely on long runway in the prior art, and needs to keep after taking off
Enough flying speeds；Horizontal flight speed is slower.
To solve the above problems, the present invention provides a kind of vertical take-off and landing drone, including：Fuselage and wing further include：
Aileron, aileron are hinged with wing；
Vertical fin, the quantity of vertical fin are three or three or more, at least one vertical fin be set to VTOL without
Man-machine upside, at least one vertical fin is set on the downside of vertical take-off and landing drone, at least partly after vertical fin
Edge is located at trailing edge rear portion；
Motor, motor are connect with wing, and the motor includes motor bearings；
Propeller, propeller are connect with motor bearings.
Further, aileron and wing tail portion are hinged, and aileron can be rotated around the rotary shaft perpendicular to fuselage axis；In wing
It is provided with steering engine, steering engine can drive aileron to rotate.
Further, vertical fin rear sweepback.
Further, the quantity of vertical fin is four, and two of which vertical fin is set on the upside of vertical take-off and landing drone, two vertical fins
It is set on the downside of vertical take-off and landing drone.
Further, two vertical fins on the upside of vertical take-off and landing drone are set to be symmetrical arranged along the fuselage plane of symmetry；
Two vertical fins on the downside of vertical take-off and landing drone are set to be symmetrical arranged along the fuselage plane of symmetry.
Further, the quantity of motor is four, is connect on the upside of two of which motor and wing, two motors and wing downside
Connection.
Further, two motors on the upside of wing are set to be symmetrical arranged along the fuselage plane of symmetry；It is set on the downside of wing
Two motors are symmetrical arranged along the fuselage plane of symmetry.
Further, the distance for being set to motor to the fuselage plane of symmetry on the upside of wing is more than the motor being set on the downside of wing
To the distance of the fuselage plane of symmetry.
Further, further include：Motor support arm, motor are connect by motor support arm with wing.
Further, further include：Electric machine support, motor are placed in electric machine support, and electric machine support is connect with motor support arm.
Compared with prior art, technical scheme of the present invention has the following advantages：
In technical scheme of the present invention, at least partly vertical fin rear is located at trailing edge rear portion so that vertical take-off and landing unmanned
When machine is placed vertically, trailing edge higher than at least partly vertical fin rear, vertical fin rear as gear support VTOL without
It is man-machine.
Aileron is hinged with wing, can change the flight attitude of vertical take-off and landing drone by rotating aileron, so as to hang down
Vertical takeoff, landing or high-altitude hovering may be implemented in straight landing unmanned plane, can make realization vertical take-off and landing drone high speed water
Flat flight.
Further, the motor is connect with wing, and the quantity of motor is four, is connected on the upside of two of which motor and wing
It connects, is connect on the downside of two motors and wing.This be designed with keeps stablizing conducive to vertical take-off and landing drone in vertical place.
Description of the drawings
Fig. 1 is a kind of structural schematic diagram of vertical take-off and landing drone of the present invention；
Structural schematic diagram when Fig. 2 is a kind of vertical take-off and landing drone VTOL of the invention；
Fig. 3 is the schematic diagram that a kind of vertical take-off and landing drone of the present invention is transitioned into level flight stage by takeoff phase；
Fig. 4 is a kind of level flight condition schematic diagram of vertical take-off and landing drone of the present invention.
Specific implementation mode
Or unmanned plane needs to rely on long runway in the prior art, and needs to keep enough horizontal flight speed after taking off
Degree；Horizontal flight speed is slower.
To make the above purposes, features and advantages of the invention more obvious and understandable, below in conjunction with the accompanying drawings to the present invention
Specific embodiment be described in detail.
Compared with fixed-wing unmanned plane, vertical take-off and landing drone can have hovering ability with zero velocity takeoff and anding, and
It can the horizontal flight in such a way that fixed-wing flies.Vertical take-off and landing drone to runway without dependence, and with the advantage that can hover.
Compared with rotary wings unmanned plane, vertical take-off and landing drone has much higher forward flight speed, and the boat with bigger
Journey.
These advantages are based on, vertical take-off and landing drone is particularly suitable for needing to hover or has special want to landing site
The occasion asked.
With reference to figure 1, the present invention provides a kind of vertical take-off and landing drone, including：
Fuselage 1 and wing 2.
The inside of the fuselage 1 is equipped with lithium battery, flight control system.The lithium battery, which provides energy, makes the motor drive
Dynamic propeller 6, generates the power for being parallel to fuselage axis.Flight control system is for remote controler to vertical take-off and landing drone flight shape
The control of state.
Wing 2 and fuselage 1 smoothly transit to meet fluid mechanical design.The wing 2 is set to 1 both sides of fuselage, and edge
The plane of symmetry is symmetrical arranged in minute surface, and the plane of symmetry is known as the fuselage plane of symmetry.
In a particular embodiment, motor support arm 7 is provided on the wing 2, motor support arm 7 is connect with electric machine support 5.Such as
7 one end of motor support arm and wing 2 be connected either be structure as a whole 7 other end of motor support arm connect with electric machine support 5 it is connected or
It is structure as a whole.
Motor is housed, motor includes motor bearings, and motor bearings is pierced by electric machine support 5 and spiral in the electric machine support 5
Paddle 6 connects.Propeller 6 can certainly be transferred to provide power around own axes by motor driving.
In other embodiments, motor can also be connected directly in wing, you can with no electric machine support 5 and motor
Support arm 7.
In the present embodiment, the quantity of the motor is four, and two of which motor is connect with 2 upside of wing, two electricity
Machine is connect with 2 downside of wing.
Wherein 2 upside of wing refers to the side that vertical take-off and landing drone is located above in horizontal flight, and 2 downside of wing is
Refer to vertical take-off and landing drone underlying side in horizontal flight.
Two motors for being set to 2 upside of wing are symmetrical arranged along the fuselage plane of symmetry；It is set to two electricity of 2 downside of wing
Machine is symmetrical arranged along the fuselage plane of symmetry.It can ensure that the power that 6 rotation of propeller generates is symmetrical along the fuselage plane of symmetry in this way, hang down
Straight landing unmanned plane being capable of smooth flight；On the other hand, this design can ensure vertical take-off and landing drone in vertical place
Stress balance.
In the present embodiment, the distance for being set to motor to the fuselage plane of symmetry of the upside of wing 2 is more than and is set under wing 2
The motor of side to the fuselage plane of symmetry distance.
The distance of motor to the fuselage plane of symmetry can be on motor any one position to the fuselage plane of symmetry distance, but it is each
Motor should select identical position to ensure that distance is comparable.
This load-carrying being designed with conducive to vertical take-off and landing drone in horizontal flight on wing be both symmetrically divided into it is scattered, can
Improve the stationarity of vertical take-off and landing drone.
In other embodiments, the distance for being set to motor to the fuselage plane of symmetry of the upside of wing 2 is less than and is set to wing 2
The motor of downside to the fuselage plane of symmetry distance.
In the present embodiment, winglet 3 is provided on the wing 2, winglet 3 is fixedly connected with wing 2.
Aileron 8 is hinged on the wing 2, aileron 8 is hinged with 2 tail portion of wing, and steering engine, institute are provided in the wing 2
Stating steering engine can drive aileron 8 around the rotary shaft rotation perpendicular to fuselage axis.
In the present invention, it perpendicular to the straight line of fuselage axis is not only only referred to intersect with fuselage axis and vertical straight
Line；And can be the straight line for meeting the following conditions：By a plane and fuselage axis phase can be found in the plane of the straight line
Vertically.
The quantity of the aileron 8 is two, hinged with two wings 2 respectively, and two ailerons 8 are in mirror along the fuselage plane of symmetry
Face is symmetrical arranged.
The vertical take-off and landing drone of the present embodiment further includes vertical fin 4, and the quantity of the vertical fin 4 is at least three, and at least
There are one vertical fins to be set on the upside of vertical take-off and landing drone, at least one vertical fin is set on the downside of vertical take-off and landing drone.Its
Refer to the side being located above when vertical take-off and landing drone horizontal flight, vertical take-off and landing drone on the upside of middle vertical take-off and landing drone
Downside underlying side when referring to vertical take-off and landing drone horizontal flight.
In the present embodiment, the quantity of vertical fin 4 is four, and two of which vertical fin is set on the upside of vertical take-off and landing drone,
Two vertical fins are set on the downside of vertical take-off and landing drone.
It is set to two vertical fins on the upside of vertical take-off and landing drone to be symmetrical arranged along the fuselage plane of symmetry, that is, is set to vertical rise
The distance for dropping two vertical fins to the fuselage planes of symmetry on the upside of unmanned plane is equal；Two on the downside of vertical take-off and landing drone are set to hang down
Tail is symmetrical arranged along the fuselage plane of symmetry, that is, is set to two vertical fins on the downside of vertical take-off and landing drone to the distance of the fuselage plane of symmetry
It is equal.
In the present embodiment, the distance for being located at two vertical fins to the fuselage planes of symmetry of fuselage plane of symmetry the same side is equal.
In the present embodiment, vertical fin 4 is fixedly connected with wing 2.
It is this to be designed with conducive to the stability of vertical take-off and landing drone is improved when using vertical fin as undercarriage.
In the present embodiment, at least partly vertical fin rear is located at 2 rear rear portion of wing, that is to say, that vertical fin 4 at least one
The distance of portion to fuselage head is bigger than the distance of any position to the fuselage head of 2 rear of wing.It can protect in this way
When demonstrate,proving the vertical placement of vertical take-off and landing drone in the horizontal plane, vertical fin 4 can be grounded as undercarriage, and 2 rear of wing is appointed
One position is all suspended.
In the present embodiment, 4 rear sweepback of vertical fin, i.e. 4 rear of vertical fin stretch backward.And the leading edge of vertical fin 4 can also
It is arranged to sweepback, wing 2 can also be swept-back wing.The Aerodynamic Characteristics of vertical take-off and landing drone can be improved in this way.
The operating method of the vertical take-off and landing drone in the present embodiment is described below：
With reference to figure 1 and Fig. 2, when taking off, first vertical take-off and landing drone to be placed vertically, fuselage axis is perpendicular to the ground, and four
A vertical fin 4 lands as undercarriage；4 motor rotations are driven under the control of flight control system by lithium battery, and drive 4
Propeller 6 is around own axes rotation.And 4 propellers 6 is made to be divided into two groups according to diagonal line, two groups of propellers 6 rotation
Direction on the contrary, with offset propeller 6 rotation generate anti-paddle power.Propeller 6 is parallel to fuselage around own axes rotation generation
The pulling force of axis, makes vertical take-off and landing drone that gravity be overcome to take off.
With reference to figure 1 and Fig. 3, after vertical take-off and landing drone rises to certain altitude, lithium battery is in flight control system
The lower driving steering engine of control simultaneously drives aileron 8 around the rotary shaft rotation perpendicular to fuselage axis, by adjusting aileron 8 so that vertical
Landing unmanned aerial vehicle body head pulls down, and vertical take-off and landing drone enters flies to horizontal flight transition stage vertically.
With reference to figure 1 and Fig. 4, as vertical take-off and landing drone fuselage head pulls down, the power that propeller 6 generates gradually changes
For horizontal flight power, vertical take-off and landing drone enters the high-speed horizontal flight stage.
When vertical take-off and landing drone needs landing, lithium battery drives steering engine and is driven under the control of flight control system
Aileron 8 around perpendicular to fuselage axis rotary shaft rotation, pass through adjust aileron 8 so that vertical take-off and landing drone fuselage head to
Pull-up, as the unmanned chain-drive section of landing is constantly pulled up, the horizontal flight power that propeller 6 provides is gradually converted into upward drawing
Power, pulling force and the vertical take-off and landing drone its own gravity that final propeller 6 generates on one wire, when the drawing that propeller 6 generates
When power is less than landing unmanned plane its own gravity, vertical take-off and landing drone slowly vertical landing.It can be with continued reference to Fig. 2 when landing.
Although present disclosure is as above, present invention is not limited to this.Any those skilled in the art are not departing from this
It in the spirit and scope of invention, can make various changes or modifications, therefore protection scope of the present invention should be with claim institute
Subject to the range of restriction.
Claims (4)
1. a kind of vertical take-off and landing drone, including：Fuselage and wing, which is characterized in that further include：
The wing is set to fuselage both sides, and is symmetrical arranged in minute surface along the fuselage plane of symmetry；It is provided with wing tip on the wing
Winglet, winglet are fixedly connected with wing；
Aileron, aileron are hinged with wing；
Vertical fin, vertical fin are fixedly connected with wing, and the quantity of vertical fin is four, and two of which vertical fin is set to vertical take-off and landing drone
Upside, two vertical fins are set on the downside of vertical take-off and landing drone, and at least partly vertical fin rear is located at trailing edge rear portion；Positioned at machine
The distance of two vertical fins to the fuselage planes of symmetry of body plane of symmetry the same side is equal；
Four motors, motor are connect with wing, and the motor includes motor bearings；It is connect on the upside of two of which motor and wing,
It is connect on the downside of two motors and wing；Two motors on the upside of wing are set to be symmetrical arranged along the fuselage plane of symmetry；It is set to machine
Two motors on the downside of the wing are symmetrical arranged along the fuselage plane of symmetry；The distance for being set to motor to the fuselage plane of symmetry on the upside of wing is big
In the motor being set on the downside of wing to the distance of the fuselage plane of symmetry；
Four propellers, each propeller are connect with a motor bearings respectively；
Four motor support arms, each motor are connect by a motor support arm with wing；
Four electric machine supports, each motor are placed in an electric machine support, and each electric machine support is connect with a motor support arm.
2. vertical take-off and landing drone as described in claim 1, which is characterized in that aileron is hinged with wing tail portion,
Aileron can be rotated around the rotary shaft perpendicular to fuselage axis；
Steering engine is provided in wing, steering engine can drive aileron to rotate.
3. vertical take-off and landing drone as described in claim 1, which is characterized in that vertical fin rear sweepback.
4. vertical take-off and landing drone as described in claim 1, which is characterized in that two be set on the upside of vertical take-off and landing drone
A vertical fin is symmetrical arranged along the fuselage plane of symmetry；
Two vertical fins on the downside of vertical take-off and landing drone are set to be symmetrical arranged along the fuselage plane of symmetry.
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| CN201510639108.XA CN105173076B (en) | 2015-09-29 | 2015-09-29 | A kind of vertical take-off and landing drone |
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| CN201510639108.XA CN105173076B (en) | 2015-09-29 | 2015-09-29 | A kind of vertical take-off and landing drone |
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| CN105173076B true CN105173076B (en) | 2018-09-14 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| NL2017611B1 (en) * | 2016-10-12 | 2018-04-20 | Univ Delft Tech | Aerial vehicle with angularly displaced propulsion units |
| CN106428548B (en) * | 2016-10-12 | 2019-09-27 | 曹萍 | A kind of vertical take-off and landing unmanned aerial vehicle |
| CN106494614B (en) * | 2016-10-28 | 2018-08-28 | 清华大学 | Aircraft with horizontal take-off and landing and vertical take-off and landing functions |
| CN107499506B (en) * | 2017-07-07 | 2021-03-09 | 清华大学 | Distributed propulsion tailstock type vertical take-off and landing fixed-wing aircraft |
| CN111846226B (en) * | 2020-07-28 | 2022-09-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and control method thereof |
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| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| GB0613887D0 (en) * | 2006-07-13 | 2006-08-23 | Hoverwing Ltd | Aircraft |
| US20100032947A1 (en) * | 2008-03-06 | 2010-02-11 | Bevirt Joeben | Apparatus for generating power using jet stream wind power |
| US20110042508A1 (en) * | 2009-08-24 | 2011-02-24 | Bevirt Joeben | Controlled take-off and flight system using thrust differentials |
| US8800931B2 (en) * | 2010-03-24 | 2014-08-12 | Google Inc. | Planform configuration for stability of a powered kite and a system and method for use of same |
| CN202728574U (en) * | 2011-10-17 | 2013-02-13 | 田瑜 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
| CN102514712A (en) * | 2011-12-07 | 2012-06-27 | 上海大学 | Vertical take-off and landing aircraft |
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Inventor after: Zhang Jie Inventor before: Zhang Jie Inventor before: Yu Chunguang Inventor before: Liu Zhuobin Inventor before: Zhou Yi Inventor before: Zhang Wang |
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Effective date of registration: 20180409 Address after: 530007 Building No. 23, building No. 8, building No. 23, the Guangxi Zhuang Autonomous Region high tech Zone, the Guangxi Zhuang Autonomous Region, No. 208 Applicant after: Guangxi Saint Yao Aeronautical Science and Technology Co., Ltd. Address before: 200000 Free Trade Zone, Shanghai, Pudong New Area new Jinqiao Road, building 27, building 2, floor 13 Applicant before: SHANGHAI SHENGYAO INTELLIGENT TECHNOLOGY CO., LTD. |
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Denomination of invention: A vertical take off and landing UAV Effective date of registration: 20210422 Granted publication date: 20180914 Pledgee: Nanning United Innovation Venture Capital Co.,Ltd. Pledgor: Guangxi Sheng Yao science and technology of aviations Co.,Ltd. Registration number: Y2021450000010 |
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Address after: 530007 floor 102, block B, building 8, No. 23, Chuangxin Road, high tech Zone, Nanning, Guangxi Zhuang Autonomous Region Patentee after: Guangxi Shengyao Intelligent Technology Co.,Ltd. Address before: 530007 No. 208, building 8, 23 innovation road, hi tech Zone, Nanning, the Guangxi Zhuang Autonomous Region, B Patentee before: Guangxi Sheng Yao science and technology of aviations Co.,Ltd. |
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