CN108248314A - A kind of land and air double-used quadrotor - Google Patents
A kind of land and air double-used quadrotor Download PDFInfo
- Publication number
- CN108248314A CN108248314A CN201810050711.8A CN201810050711A CN108248314A CN 108248314 A CN108248314 A CN 108248314A CN 201810050711 A CN201810050711 A CN 201810050711A CN 108248314 A CN108248314 A CN 108248314A
- Authority
- CN
- China
- Prior art keywords
- deflector
- land
- dual
- wing
- driving device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
Abstract
The present invention relates to a kind of land and air double-used quadrotors, and including control unit, rack and four groups of dual-purpose wheel wings, rack is equipped with the first driving means for the dual-purpose wheel wing to be driven to rotate；Every group of dual-purpose wheel wing includes annular wheel hub and sets rotor in the inner；The second driving device for being additionally provided with deflector on every group of dual-purpose wheel wing and the deflector being driven to rotate, the rotation of the second driving device driving deflector is to adjust the corner cut of deflector and air during aircraft landing and in flight course；First driving means and the second driving device are connect with control unit.Land rotation traveling can be realized in the setting of annular wheel hub, to save electric energy；Driving deflector rotation drives the dual-purpose wheel wing to rotate constantly to adjust the corner cut of deflector and air so that rotor rotational, to realize the landing of the aircraft；By the way that deflector is driven to rotate in flight course so that the aircraft can utilize atmospheric pressure to provide the lift needed for gliding, and deflector angle is fixed during gliding, so as to save electric energy.
Description
Technical field
The present invention relates to vehicle technology field, more particularly, to a kind of land and air double-used quadrotor.
Background technology
Due to quadrotor have operating cost it is low, without mortality risk, mobility is good, can carry out over the horizon flight
And the features such as easy to use efficient, be successfully applied at present video display take photo by plane, survey and draw aerial survey, high-voltage line inspection, remote monitoring,
The disaster relief is emerged as the times demand, pesticide spraying and business performance etc. fields.But existing quadrotor is entertained in the task of execution or for people
When, it can only fly in the air, and, so as to waste electric energy, quadrotor cruising ability cannot be reduced in ground running,
It is recreational to also reduce its.
Invention content
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of land and air double-used quadrotors, can save
Electric energy is saved, improves cruising ability.
In order to achieve the above objectives, the technical solution adopted by the present invention is：
A kind of land and air double-used quadrotor is provided, including control unit, rack and four groups of dual-purpose wheel wings, rack, which is equipped with, to be used
In the first driving means for driving dual-purpose wheel wing rotation；Every group of dual-purpose wheel wing includes annular wheel hub and sets rotor in the inner,
Annular wheel hub is for traveling of the aircraft on land；Deflector is additionally provided on every group of dual-purpose wheel wing and the deflector is driven to rotate
The second driving device, the rotation of the second driving device driving deflector is to adjust deflector during aircraft landing and in flight course
With the corner cut of air；First driving means and the second driving device are connect with control unit.
In said program, the dual-purpose wheel wing of first driving means driving rotates so that annular wheel hub and land generate friction, from
And realize that rotation of the aircraft on land travels, compared to flying in the air always, land traveling more saves electric energy；Second drives
Dynamic device driving deflector rotation is constantly to adjust the corner cut of deflector and air, while first driving means drive the dual-purpose wheel wing
It rotates so that rotor rotational, so as to fulfill the landing of the aircraft；Second driving device driving deflector rotation in flight course,
So that the aircraft can utilize atmospheric pressure to provide the lift needed for gliding, without the dual-purpose wheel wing rotation of first driving means driving
Lift is provided, and deflector angle is fixed during gliding, so as to save electric energy.
Preferably, every group of dual-purpose wheel wing includes a pair of rotation wing rotated coaxially, which includes the annulus wheel
Hub and set rotor in the inner；Deflector and the second driving device are set between a pair of of rotation wing.Setting is not only reduced and is somebody's turn to do in this way
Aircraft the space occupied so that appearance looks elegant, and also the rotation of deflector, anti-rotation stop are convenient in the space between a pair of of rotation wing
The deflector dual-purpose wheel wing of collision happens during dynamic.
It is further preferred that a pair of of rotation wing is connected by deflector and the second driving device.Setting is so that water conservancy diversion in this way
Plate and the second driving device play the role of the axis of a pair of of rotation wing of connection, directly eliminate axis, structure is simpler.
It is further preferred that rotor is cross structure, and the rotor of a pair of of rotation wing is just opposite.Setting was so that should in this way
Aircraft appearance looks elegant, and stability and wind resistance when can increase flight.
Preferably, four deflectors are uniformly provided between a pair of of rotation wing.Setting is so that air is applied to the flight in this way
The power of device is more balanced, convenient for ensureing stationarity during aircraft flight.
Preferably, four deflectors are respectively on the four edges of rotor cross structure, and deflector and cross structure
The length on the annular Hub side edge of link position distance is the 1/4-1/3 of deflector length.In this way setting so that adjacent baffle it
Between space it is larger, convenient for the flowing of air, so that the water conservancy diversion of deflector is better；If in addition, the distance is too small
When, deflector there is a situation where to pat ground when rotating, this be easy to cause the damage of deflector.
Preferably, for the angle that deflector is accurately controlled to rotate, the second driving device is set as servo motor.
Preferably, in order to simplify the structure of rack, the rack is set as H-type structure, the center of four dual-purpose wheel wings
It is respectively arranged on four end faces of H-type structure.
Preferably, the deflector is Bernoulli Jacob's fluidic structures.The streamline of deflector surrounding air point during aircraft flight
Cloth refers to the lower in shape asymmetric of deflector cross section, and the streamline above deflector is close, flow velocity is big, and the streamline of lower section is dredged, flowed
Speed is small；By Bernoulli equation it is found that the pressure above deflector is small, the pressure of lower section is big, and this creates the terminal act on water conservancy diversion
The lift in the direction on plate.
In the vertical direction from the beginning it is further preferred that the top and bottom of the deflector are arcuate structure, and deflector
Portion first thickens and is thinned to tail portion again backward.
Compared with prior art, the beneficial effects of the invention are as follows：
A kind of land and air double-used quadrotor of the present invention, the dual-purpose wheel wing of first driving means driving rotate so that annular wheel hub with
Land generates friction, is travelled so as to fulfill rotation of the aircraft on land, compared to flying in the air always, land travels more
Save electric energy；Second driving device driving deflector rotates constantly to adjust the corner cut of deflector and air, while pass through first
The dual-purpose wheel wing of driving device driving is rotated so that rotor rotational, so as to fulfill the landing of the aircraft；Second drives in flight course
Dynamic device driving deflector rotation, so that the aircraft can utilize atmospheric pressure to provide the lift needed for gliding, drives without first
It moves the dual-purpose wheel wing rotation of device driving and provides lift, and deflector angle is fixed during gliding, so as to save electric energy.
Description of the drawings
Fig. 1 is a kind of schematic diagram of land and air double-used quadrotor of the present embodiment.
Fig. 2 is the schematic diagram of one group of dual-purpose wheel wing.
Fig. 3 is the schematic diagram of deflector.
Specific embodiment
The present invention is further illustrated With reference to embodiment.Wherein, attached drawing only for illustration,
What is represented is only schematic diagram rather than pictorial diagram, it is impossible to be interpreted as the limitation to this patent；In order to which the reality of the present invention is better described
Example is applied, the certain components of attached drawing have omission, zoom in or out, and do not represent the size of actual product；To those skilled in the art
For, the omitting of some known structures and their instructions in the attached drawings are understandable.
The same or similar label correspond to the same or similar components in the attached drawing of the embodiment of the present invention；In retouching for the present invention
In stating, it is to be understood that if it is based on attached drawing to have the orientation of the instructions such as term " on ", " under ", "left", "right" or position relationship
Shown orientation or position relationship, are for only for ease of the description present invention and simplify description rather than instruction or imply meaning
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore position relationship described in attached drawing
Term is only for illustration, it is impossible to the limitation to this patent is interpreted as, it for the ordinary skill in the art, can
To understand the concrete meaning of above-mentioned term as the case may be.
Embodiment
A kind of land and air double-used quadrotor of the present embodiment, as shown in Figure 1 to Figure 3, including control unit, rack 1 and
Four groups of dual-purpose wheel wings 2, rack 1 are equipped with the first driving means 3 for the dual-purpose wheel wing 2 to be driven to rotate；Every group of dual-purpose wheel wing 2 is equal
Including annular wheel hub 21 and rotor 22 in the inner is set, annular wheel hub 21 is for traveling of the aircraft on land；Every group dual-purpose
The second driving device 5 for being additionally provided with deflector 4 on the wheel wing 2 and the deflector 4 being driven to rotate, during aircraft landing and flight course
In the second driving device 5 driving deflector 4 rotate corner cut to adjust deflector 4 and air；First driving means 3 and second are driven
Dynamic device 5 is connect with control unit.
First driving means 3 are four groups, are respectively used to that each group of dual-purpose wheel wing 2 is driven to rotate, by changing the different wheel wings 2
Stress realize aircraft in the aerial steering in land.
A kind of land and air double-used quadrotor of the present invention drives the dual-purpose wheel wing 2 to rotate, makes by first driving means 3
Annular wheel hub 21 and land generate friction, to realize that rotation of the aircraft on land travels, compared to flying in the air always
Row, land traveling more save electric energy；Deflector 4 is driven to rotate constantly to adjust deflector 4 and air by the second driving device 5
Corner cut, while by first driving means 3 drive it is dual-purpose wheel the wing 2 rotate so that rotor 22 rotates, to realize the aircraft
Landing；In flight course, deflector 4 is driven to rotate by the second driving device 5 so that the aircraft can be carried using atmospheric pressure
For the required lift that glides, lift, and deflector during gliding are provided without the dual-purpose wheel wing rotation of first driving means driving
Angle is fixed, so as to save electric energy.
Wherein, every group of dual-purpose wheel wing 2 includes a pair of rotation wing rotated coaxially, which includes the annular wheel hub
21 and set rotor 22 in the inner；4 and second driving device 5 of deflector is set between a pair of of rotation wing.Setting is not only contracted in this way
The small aircraft the space occupied so that appearance looks elegant, and also the rotation of deflector 4 is convenient in the space between a pair of of rotation wing,
Prevent deflector 4 in rotation process from colliding happening for the dual-purpose wheel wing 2.
In addition, a pair of of rotation wing is connected by 4 and second driving device 5 of deflector.Setting is so that deflector 4 and the in this way
Two driving devices 5 play the role of the axis of a pair of of rotation wing of connection, directly eliminate axis, structure is simpler.
Wherein, rotor 22 is cross structure, and the rotor 22 of a pair of of rotation wing is just opposite.Setting is so that the aircraft in this way
Appearance looks elegant, and stability and wind resistance when can increase flight.
In addition, it is uniformly provided with four deflectors 4 between a pair of of rotation wing.Setting is so that air is applied to the aircraft in this way
Power it is more balanced, convenient for ensure aircraft flight when stationarity.
Wherein, four deflectors 4 are respectively on the four edges of 22 cross structure of rotor, and deflector 4 and cross structure
Length of the link position apart from 21 edge of annular wheel hub be 4 length of deflector 1/4-1/3.Setting is so that adjacent guide in this way
Space between plate 4 is larger, convenient for the flowing of air, so that the water conservancy diversion of deflector 4 is better；It if in addition, should be away from
From it is too small when, deflector 4 rotate when there is a situation where pat ground, this be easy to cause the damage of deflector 4.
In addition, for the angle that deflector 4 is accurately controlled to rotate, the second driving device 5 is set as servo motor.
Wherein, in order to simplify the structure of rack 1, the rack 1 is set as H-type structure, the center of four dual-purpose wheel wings 2
It is respectively arranged on four end faces of H-type structure.
In addition, the deflector 4 is Bernoulli Jacob's fluidic structures.The streamline of 4 surrounding air of deflector point during aircraft flight
Cloth refers to the asymmetry lower in shape of 4 cross section of deflector, and the streamline of 4 top of deflector is close, flow velocity is big, the streamline of lower section dredges,
Flow velocity is small；By Bernoulli equation it is found that the pressure of 4 top of deflector is small, the pressure of lower section is big, and this creates the terminal act on to lead
The lift in the direction in flowing plate 4.
Wherein, as shown in figure 3, the top and bottom of the deflector 4 are arcuate structure, and deflector 4 is in the vertical direction
It is first thickened backward from head and is thinned to tail portion again.
Obviously, the above embodiment of the present invention be only to clearly illustrate example of the present invention, and not be pair
The restriction of embodiments of the present invention.For those of ordinary skill in the art, may be used also on the basis of the above description
To make other variations or changes in different ways.There is no necessity and possibility to exhaust all the enbodiments.It is all this
All any modification, equivalent and improvement made within the spirit and principle of invention etc., should be included in the claims in the present invention
Protection domain within.
Claims (10)
1. a kind of land and air double-used quadrotor, which is characterized in that including control unit, rack（1）And four groups of dual-purpose wheel wings
（2）, rack（1）It is equipped with to drive the dual-purpose wheel wing（2）The first driving means of rotation（3）；Every group of dual-purpose wheel wing（2）Wrap
Include annular wheel hub（21）With set rotor in the inner（22）, annular wheel hub（21）For traveling of the aircraft on land；Every group
The dual-purpose wheel wing（2）On be additionally provided with deflector（4）And drive the deflector（4）Second driving device of rotation（5）, aircraft landing
When and flight course in the second driving device（5）Drive deflector（4）It rotates to adjust deflector（4）With the corner cut of air；The
One driving device（3）And second driving device（5）It is connect with control unit.
A kind of 2. land and air double-used quadrotor according to claim 1, which is characterized in that every group of dual-purpose wheel wing（2）
Include a pair of rotation wing rotated coaxially, which includes the annular wheel hub（21）With set rotor in the inner（22）；
Deflector（4）And second driving device（5）Between a pair rotates the wing.
3. a kind of land and air double-used quadrotor according to claim 2, which is characterized in that a pair of rotation wing is by leading
Flowing plate（4）And second driving device（5）Connection.
A kind of 4. land and air double-used quadrotor according to claim 3, which is characterized in that rotor（22）For stauros
Structure, and the rotor of a pair of of rotation wing（22）It is just opposite.
5. a kind of land and air double-used quadrotor according to claim 4, which is characterized in that between a pair of rotation wing
It is even to set there are four deflector（4）.
A kind of 6. land and air double-used quadrotor according to claim 5, which is characterized in that four deflectors（4）Point
It Wei Yu not rotor（22）On the four edges of cross structure, and deflector（4）Link position with cross structure is apart from annular wheel hub
（21）The length at edge is deflector（4）The 1/4-1/3 of length.
A kind of 7. land and air double-used quadrotor according to claim 1, which is characterized in that the second driving device（5）
For servo motor.
A kind of 8. land and air double-used quadrotor according to claim 1, which is characterized in that the rack（1）For H-type
Structure, four dual-purpose wheel wings（2）Center be respectively arranged on four end faces of H-type structure.
9. according to a kind of land and air double-used quadrotor of claim 1 to 8 any one of them, which is characterized in that described to lead
Flowing plate（4）For Bernoulli Jacob's fluidic structures.
A kind of 10. land and air double-used quadrotor according to claim 9, which is characterized in that the deflector（4）'s
Top and bottom are arcuate structure, and deflector（4）It is first thickened backward from head in the vertical direction and is thinned to tail portion again.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810050711.8A CN108248314A (en) | 2018-01-18 | 2018-01-18 | A kind of land and air double-used quadrotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810050711.8A CN108248314A (en) | 2018-01-18 | 2018-01-18 | A kind of land and air double-used quadrotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108248314A true CN108248314A (en) | 2018-07-06 |
Family
ID=62741485
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810050711.8A Pending CN108248314A (en) | 2018-01-18 | 2018-01-18 | A kind of land and air double-used quadrotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108248314A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2889899Y (en) * | 2005-12-03 | 2007-04-18 | 李剑 | Wheel-wing airplane |
| CN104364154A (en) * | 2012-06-01 | 2015-02-18 | 洛高-蒂姆有限责任公司 | Aircraft, preferably unmanned |
| CN205381400U (en) * | 2016-02-22 | 2016-07-13 | 武汉智能鸟无人机有限公司 | Aircraft |
| CN107176297A (en) * | 2017-06-20 | 2017-09-19 | 北京迪鸥航空科技有限公司 | A kind of aircraft |
| CN107225925A (en) * | 2017-05-23 | 2017-10-03 | 南京航空航天大学 | Being dwelt a kind of rolling wing VTOL aircraft more |
| CN107284165A (en) * | 2017-05-31 | 2017-10-24 | 东北大学 | A kind of coaxial double-rotary wing land and air double-used aircraft |
-
2018
- 2018-01-18 CN CN201810050711.8A patent/CN108248314A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2889899Y (en) * | 2005-12-03 | 2007-04-18 | 李剑 | Wheel-wing airplane |
| CN104364154A (en) * | 2012-06-01 | 2015-02-18 | 洛高-蒂姆有限责任公司 | Aircraft, preferably unmanned |
| CN205381400U (en) * | 2016-02-22 | 2016-07-13 | 武汉智能鸟无人机有限公司 | Aircraft |
| CN107225925A (en) * | 2017-05-23 | 2017-10-03 | 南京航空航天大学 | Being dwelt a kind of rolling wing VTOL aircraft more |
| CN107284165A (en) * | 2017-05-31 | 2017-10-24 | 东北大学 | A kind of coaxial double-rotary wing land and air double-used aircraft |
| CN107176297A (en) * | 2017-06-20 | 2017-09-19 | 北京迪鸥航空科技有限公司 | A kind of aircraft |
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