CN206358361U - A kind of VUAV - Google Patents
A kind of VUAV Download PDFInfo
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- CN206358361U CN206358361U CN201720019359.2U CN201720019359U CN206358361U CN 206358361 U CN206358361 U CN 206358361U CN 201720019359 U CN201720019359 U CN 201720019359U CN 206358361 U CN206358361 U CN 206358361U
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Abstract
The utility model proposes a kind of VUAV, including fuselage (1), fuselage (1) the front end both sides are symmetrical arranged canard (2) and rotor power group (5), fuselage (1) the rear end both sides are symmetrical arranged main wing (3) and rotor power group (5), and the afterbody of the fuselage (1) sets fixed-wing power packages (4).The utility model proposes a kind of VUAV, combine advantage of both fixed-wing unmanned plane and VUAV, the fixed wing aircraft for choosing canard blended wing-body is main body, rotor and the common primary load bearing part of fixed wing aircraft are used as using canard and aircraft main wing girder, complete the installation of four rotors, it is final realize with more excellent aerodynamic arrangement can VTOL a unmanned plane, its VTOL function makes aircraft be taken off without runway, and the Fixed Wing AirVehicle of canard configuration also possesses longer endurance than common rotor.
Description
Technical field
The utility model belongs to technical grade unmanned air vehicle technique field, especially a kind of VUAV.
Background technology
In the fixed wing aircraft that aviation field is common, due to producing lift balance airplane weight, dynamical system mainly by wing
System is mainly used to overcome aircraft flight resistance, therefore can just allow the liftoff liter of fixed wing aircraft much smaller than the power of aircraft weight
Sky, its flying speed is than comparatively fast, voyage and cruise time are also longer, but landing distance, it is desirable to high-quality runway, serious shadow
Ring and hamper fixed wing aircraft in the remote application without special machine Performance Area.
In the heligyro that aviation field is common, it can solve the problem of narrow and small place VTOL.Known
In rotor craft, in addition to common single-rotor helicopter, also many oar helicopters, many oar helicopters are generally by change
The rotating speed of oar carrys out change of flight posture, such as 4 oar heligyroes, and 4 oars are placed relative to Central Symmetry, wherein there is 2 oars
It is to turn clockwise, also 2 oars are counterclockwise rotates.When aircraft is needed toward a directional steering, increase as long as changing
Plus the rotating speed of wherein 2 clockwise/counterclockwise oars, boat can just be changed by reducing the rotating speed of other 2 counterclockwise/oars clockwise
To.When needing to tilt aircraft, as long as reducing the rotating speed of the oar on heading, increase the rotating speed of oar of symmetric position with regard to that can pass through
Lift difference is flown to specified direction.
But the rotor efficiency being directly connected with dynamical system can not show a candle to the wing of fixed wing aircraft, therefore power consumption is big.And because
The component that its pace is produced mainly by rotor disk by the inclination of pitch is provided, while the resistance of helicopter forward flight
Power is also much bigger compared with fixed wing aircraft.Therefore its flying speed, distance and cruising time are all not so good as fixed wing aircraft, are researched and developed for this
It is a set of that to have the aircraft of fixed wing aircraft and helicopter a little concurrently extremely urgent.
Utility model content
In order to solve the above problems, the utility model provides a kind of VUAV.
Concrete technical scheme is as follows：
A kind of VUAV, including fuselage (1), fuselage (1) the front end both sides are symmetrical arranged canard (2) and rotation
Wing power packages (5), fuselage (1) the rear end both sides are symmetrical arranged main wing (3) and rotor power group (5), the tail of the fuselage (1)
Portion sets fixed-wing power packages (4).
Preferably, the fixed-wing power packages (4) include electro-motor, wooden oar and reduction gearing.
Preferably, the rotor power group (5) includes connector, electro-motor and rotor carbon oar.
Preferably, aircraft control system, fuel tank and circuit built in the fuselage (1).
Preferably, aircraft control system, battery and circuit built in the fuselage (1).
Preferably, aircraft control system, battery, fuel tank and circuit built in the fuselage (1).
Preferably, the one end of the main wing (3) away from fuselage (1) sets vertical winglet.
Relative to prior art, a kind of VUAV described in the utility model has the advantage that：
The utility model proposes a kind of VUAV, combine fixed-wing unmanned plane and VUAV
Both sides advantage, the fixed wing aircraft for choosing canard blended wing-body is main body, and rotor is used as using canard and aircraft main wing girder
With the common primary load bearing part of fixed wing aircraft, complete the installation of four rotors, it is final realize with more excellent aerodynamic arrangement can be vertical
A unmanned plane of landing, its VTOL function makes aircraft be taken off without runway, the Fixed Wing AirVehicle of canard configuration
Also longer endurance is possessed than common rotor.
Brief description of the drawings
Fig. 1 be the utility model proposes a kind of VUAV stereogram.
Description of reference numerals：
The rotor power group of 1 fuselage, 2 canard, 3 main wing, 4 fixed-wing power packages 5
Embodiment
The technical solution of the utility model is further described below in conjunction with embodiment.It should be appreciated that herein
The embodiment of description only to explain the utility model, is not used to limit the utility model.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " on ", " under ",
The orientation or position relationship of the instruction such as "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " are
Based on orientation shown in the drawings or position relationship, it is for only for ease of description the utility model and simplifies description, rather than indicate
Or imply that the device or element of meaning must have specific side, with specific azimuth configuration and operation, therefore it is not intended that
To limitation of the present utility model.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in description of the present utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can be mechanical connection or electrical connection；Can be directly connected to, can also be indirectly connected to by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, on being understood by concrete condition
State concrete meaning of the term in the utility model.
Describe the utility model in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Fig. 1 be the utility model proposes a kind of VUAV stereogram, including：Fuselage (1), the fuselage
(1) aircraft control system, fuel tank and circuit built in, either aircraft control system, battery and circuit or aircraft control system,
Fuel tank, battery and circuit, can be mixed according to actual conditions selection using electronic, oily dynamic or oil electricity.Fuselage (1) front end two
Side is symmetrical arranged canard (2) and rotor power group (5), and the canard (2) is symmetricly set on the both sides of fuselage (1) front end, described
Rotor power group (5) is arranged on one end of canard (2), and the position that two groups of rotor power groups (5) being connected with canard (2) are set is closed
In fuselage (1) symmetrically, the rotor power group (5) includes connector, electro-motor and rotor carbon oar, fuselage (1) rear end
Both sides are symmetrical arranged main wing (3) and rotor power group (5), and the main wing (3) is symmetricly set on the both sides of fuselage (1) rear end,
One end of main wing (3) is provided with rotor power group (5), and two groups of rotor power groups (5) being connected with main wing (3) are on fuselage (1)
Symmetrically, the afterbody of the fuselage (1) sets fixed-wing power packages (4), and the fixed-wing power packages (4) include electro-motor, wood
Oar and reduction gearing, set vertical winglet, the winglet can increase in the one end of main wing (3) away from fuselage (1)
Plus the lateral stability of aircraft, induced drag can also be reduced.
The fixed wing aircraft for choosing canard blended wing-body is main body, and rotor and fixation are used as using canard and aircraft main wing girder
The common primary load bearing part of wing aircraft, completes the installation of four rotors.It is final realize with more excellent aerodynamic arrangement can VTOL work(
The so a innovative unmanned plane of energy.The maximum advantage of this unmanned plane is fixed-wing and the two forward positions of VTOL
Function preferably combine.The VTOL function of unmanned plane makes aircraft be taken off without runway；And canard configuration is consolidated
Determine the advantage that rotor aircraft also possesses longer endurance than common rotor.
It is main body that the unmanned plane, which chooses canard blended wing-body airplane, is mainly in view of the following aspects.With routine
Layout fixed wing aircraft is compared, and canard configuration can realize that the liter higher than normal arrangement hinders by the pneumatic coupling of the front and rear wing
Than；And the combination of hung down mast and fixed-wing girder causes the same normal arrangement with function of having hung down of aircraft ratio to fly
The resistance that device is produced is smaller, and weightening is less.In configuration aspects, this layout causes aircraft greatly to eliminate vertical of addition
The weight gain problem that functional bands are come is dropped, and effectively combines both primary load bearing parts, the combination of wing and rotor is eliminated greatly
The carbon pipe of amount, loss of weight, drag-reduction effect are obvious.
According to the instruction of earth station, unmanned plane starts work of taking off, aircraft control system control rotor power group (5) rotation
Turn, produce upward lift, after reaching a certain height, aircraft control system control fixed-wing power packages (4) and rotor power group
(5) cooperate, the thrust that fixed-wing power packages (4) are provided forward produces speed forward, canard (2) and main wing (3) are produced
Lift, and the lift that progressively substitution rotor power group (5) is produced, unmanned plane is from rotor flying State Transferring to fixed-wing flight shape
State, meanwhile, canard (2) and elevator and the posture of aileron control unmanned plane on main wing (3) reach the mesh of aircraft smooth flight
's.
In summary, the utility model proposes a kind of VUAV, combine fixed-wing unmanned plane and vertical
Advantage of both landing unmanned plane, the fixed wing aircraft for choosing canard blended wing-body is main body, with canard and aircraft main wing master
Beam completes the installation of four rotors as rotor and the common primary load bearing part of fixed wing aircraft, and final realize has more excellent pneumatic cloth
Office can VTOL a unmanned plane, its VTOL function makes aircraft be taken off without runway, and canard configuration is consolidated
Determine rotor aircraft and also possess longer endurance than common rotor.
Embodiment above is preferred embodiment of the present utility model, not thereby limits of the present utility model special
Sharp protection domain.Those skilled in the art belonging to any the utility model, it is disclosed in the utility model not departing from
The equivalent structure and the conversion of equivalent step done on the premise of spirit and scope to content of the present utility model each falls within this reality
Within new claimed the scope of the claims.
Claims (7)
1. a kind of VUAV, including fuselage (1), it is characterised in that fuselage (1) the front end both sides are symmetrical arranged duck
The wing (2) and rotor power group (5), fuselage (1) the rear end both sides are symmetrical arranged main wing (3) and rotor power group (5), the machine
The afterbody of body (1) sets fixed-wing power packages (4).
2. a kind of VUAV according to claim 1, it is characterised in that fixed-wing power packages (4) bag
Include electro-motor, wooden oar and reduction gearing.
3. a kind of VUAV according to claim 1, it is characterised in that the rotor power group (5) includes
Connector, electro-motor and rotor carbon oar.
4. a kind of VUAV according to claim 1, it is characterised in that aircraft control built in the fuselage (1)
System processed, fuel tank and circuit.
5. a kind of VUAV according to claim 1, it is characterised in that aircraft control built in the fuselage (1)
System processed, battery and circuit.
6. a kind of VUAV according to claim 1, it is characterised in that aircraft control built in the fuselage (1)
System processed, battery, fuel tank and circuit.
7. a kind of VUAV according to claim 1, it is characterised in that the main wing (3) is away from fuselage (1)
One end vertical winglet is set.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720019359.2U CN206358361U (en) | 2017-01-09 | 2017-01-09 | A kind of VUAV |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720019359.2U CN206358361U (en) | 2017-01-09 | 2017-01-09 | A kind of VUAV |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206358361U true CN206358361U (en) | 2017-07-28 |
Family
ID=59380346
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720019359.2U Active CN206358361U (en) | 2017-01-09 | 2017-01-09 | A kind of VUAV |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206358361U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828913A (en) * | 2017-01-09 | 2017-06-13 | 北京猎鹰无人机科技有限公司 | A kind of VUAV |
| CN112960100A (en) * | 2021-03-03 | 2021-06-15 | 北京博鹰通航科技有限公司 | Aircraft and control method thereof |
-
2017
- 2017-01-09 CN CN201720019359.2U patent/CN206358361U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828913A (en) * | 2017-01-09 | 2017-06-13 | 北京猎鹰无人机科技有限公司 | A kind of VUAV |
| CN112960100A (en) * | 2021-03-03 | 2021-06-15 | 北京博鹰通航科技有限公司 | Aircraft and control method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200820 Address after: No.4 factory building, Fuyang industrial square, Fuyuan Road, Chengyang street, Xiangcheng economic and Technological Development Zone, Suzhou City, Jiangsu Province Patentee after: Aerospace Zhongxing (Jiangsu) Technology Co., Ltd Address before: Room 1003-1, building 7, No. 98, lianshihu West Road, Mentougou District, Beijing 100039 Patentee before: BEIJING FALCON UAV TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211227 Address after: 102407 466, block D, Beijing fund town building, Fangshan District, Beijing Patentee after: Aerospace Zhongxing (Beijing) Technology Co.,Ltd. Address before: 215137 plant 4, Fuyang industrial square, Fuyuan Road, Chengyang street, Xiangcheng economic and Technological Development Zone, Suzhou City, Jiangsu Province Patentee before: Aerospace Zhongxing (Jiangsu) Technology Co., Ltd |