CN206968982U - VTOL fixed-wing unmanned plane structure - Google Patents
VTOL fixed-wing unmanned plane structure Download PDFInfo
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- CN206968982U CN206968982U CN201720715358.1U CN201720715358U CN206968982U CN 206968982 U CN206968982 U CN 206968982U CN 201720715358 U CN201720715358 U CN 201720715358U CN 206968982 U CN206968982 U CN 206968982U
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Abstract
VTOL fixed-wing unmanned plane structure of the present utility model, technical purpose are to provide that a kind of air drag is small, and the VTOL fixed-wing unmanned plane structure of flying quality is lifted while improving power service efficiency.Include fuselage main body, the fuselage main body both sides are provided with port wing and starboard wing, and the fuselage main body is provided with main duct, and the main duct is provided with main rotor, and main rotor is driven by motor；Fuselage main body front end is provided with head rotor；The outside of the port wing is provided with the left-handed wing, and the outside of the starboard wing is provided with the dextrorotation wing.The utility model good appearance, the aerodynamic interference resistance between aircraft components is small, and lift-drag ratio is high, and aerodynamic characteristic is good.Simple in construction, in light weight, giving up, resistance is small, and low in energy consumption, flying quality is good.Suitable for plant protection, industry, police and military field.
Description
Technical field
A kind of unmanned plane structure is the utility model is related to, in particular, is related to a kind of VTOL fixed-wing unmanned plane
Structure.
Background technology
In the prior art, the VTOL fixed-wing unmanned plane of civil area is mainly combined type configuration, i.e., in fixation
Four rotors are directly superimposed on the wing, simple combined type configuration is exactly that more rotor structures are superimposed on the basis of fixed-wing, between part
Aerodynamic interference it is obvious, aerodynamic drag is larger, and pneumatic efficiency is low, influences flying quality.Four rotors are only in takeoff and landing
When just play a role, when unmanned plane is in airplane-mode, fourth officer rotor and its power transmission and executing agency etc. are into " taking
Weight ", so that unmanned plane air drag in airplane-mode becomes big, power consumption increase, flying quality reduces.
Utility model content
Technical purpose of the present utility model is to overcome in the prior art, the structure of unmanned plane there is resistance during flight is big,
The efficiency of actual of power is low, the bad technical problem of flying quality；It is small to provide a kind of air drag, improves power and uses effect
The VTOL fixed-wing unmanned plane structure of flying quality is lifted while rate.
VTOL fixed-wing unmanned plane structure, includes fuselage main body, the fuselage main body both sides be provided with port wing and
Starboard wing, the fuselage main body are provided with main duct, and the main duct is provided with main rotor, and main rotor is driven by motor；Fuselage
Body front end is provided with head rotor；The outside of the port wing is provided with the left-handed wing, and the outside of the starboard wing is provided with the dextrorotation wing.
Further, it is provided with nose-gear below the front end of fuselage main body.
Further, bearing pin is provided between the fuselage main body and port wing and starboard wing to connect.
Further, for the left-handed wing in the left duct on port wing, the dextrorotation wing is located at the right side of starboard wing
In duct.
Further, the port wing tail end is provided with left vertical tail, and the starboard wing tail end is provided with right vertical tail.
Further, the main duct is provided with the axle sleeve that verts, and tiliting axis, the main rotation are provided with the axle sleeve that verts
The wing is on tiliting axis.
Further, in unmanned plane VTOL, the left vertical tail and right vertical tail can be also used as rising and falling
Frame.
Further, the both ends thin-wall bearing of the tiliting axis.
Further, the rear side of the fuselage main body is provided with tailing axle, for connecting left and right wing, reduces vibration.
Further, the rear side of the fuselage main body is provided with tailing axle, for aiding in supporting fuselage duct.
Further, the port wing and starboard wing are respectively equipped with battery flat.
Further, the fuselage main body is provided with mission module, and task device is provided with mission module.
Further, the tailing axle is one to run through port wing and starboard wing screw mandrel, and being arranged with internal thread on screw mandrel adds
Weight copper pipe.
Advantageous effects of the present utility model are：Good appearance, the aerodynamic interference resistance between aircraft components is small, rises resistance
Than high, aerodynamic characteristic is good.Simple in construction, in light weight, giving up, resistance is small, and low in energy consumption, flying quality is good.Can greatly it reduce in military affairs
Radar area, Stealth Fighter are good.VTOL fixed-wing unmanned plane combines the excellent of fixed wing aircraft and rotor craft
Point, flying speed is high, voyage is remote, cruising time is long, can VTOL, can hover operation, maneuverability etc..Due to VTOL
Fixed-wing unmanned plane is without transmitting/recovery system, and required optional equipment is few, and operating personnel are few, therefore use cost expense is relatively low.
VTOL fixed-wing unmanned plane can be widely used for military, paramilitary and civil area.It is suitable for border patrol, anti-terrorism, again
Can the VTOL on ship deck, can quickly fly to target overhead, carry out spot hover scouting, islands and reefs patrol, marine anti-
Smuggling.Particularly after carry infrared viewing device, unmanned plane possesses the ability in night reconnaissance, patrol.Civilian aspect can be used for state
Native mapping, meteorological detection, environment monitoring, forest fire protection, police patrol etc..Specifically, can be multiple in industrial aspect, unmanned plane
Long-distance flight to desolate and uninhabited mining area is prospected under miscellaneous topographic features, or carries out 3D mappings to mining area, instructs exploitation to make
Industry；In addition, it may also be used for inspection to high-tension bus-bar and oil-gas pipeline etc..In terms of traffic, the real-time monitoring available for traffic
And tour of highway etc..Agriculturally, available for large stretch of farmland is maked an inspection tour, to assess crop growth situation and disease pest
Evil situation.In terms of animal husbandry, available for monitoring drove.In terms of the disaster relief, can earthquake or, fire or situations such as flood
Under, the very first time enters the region that people is unable to reach, and disaster area is assessed.
Brief description of the drawings
Fig. 1 is the structural representation of the utility model one embodiment.
Embodiment
With reference to Fig. 1, specific embodiment of the present utility model is described in detail, but claim is not limited in any way.This
The VTOL fixed-wing unmanned plane structure of utility model, includes fuselage main body 100, and the both sides of fuselage main body 100 are provided with
Port wing 201 and starboard wing 301, the fuselage main body 100 are provided with main duct 104, and the main duct 104 is provided with main rotor
500, main rotor 500 is driven by motor；The front end of fuselage main body 100 is provided with head rotor 101；The outside of the port wing 201 is set
There is the left-handed wing 102, the outside of the starboard wing 301 is provided with the dextrorotation wing 103.When implementing, set below the front end of fuselage main body 100
There is nose-gear.Bearing pin is provided between the fuselage main body 100 and port wing 201 and starboard wing 301 to connect.The left-handed wing
102 in the left duct on port wing 201, and the dextrorotation wing 103 is in the right duct of starboard wing 301.It is left when implementing
The tail end of wing 201 is provided with left vertical tail 200, and the tail end of starboard wing 301 is provided with right vertical tail 300.Set on the main duct 104
There is the axle sleeve that verts, tiliting axis 500 is provided with the axle sleeve that verts, when implementing, tiliting axis 500 can tilt as needed, described
Main rotor 502 is on tiliting axis 500.The both ends thin-wall bearing of the tiliting axis 500.The rear side of the fuselage main body 100 is set
There is tailing axle 501, for aiding in supporting main duct 104.The port wing 201 and starboard wing 301 are respectively equipped with battery flat.It is described
Fuselage main body is provided with mission module 400, when implementing, control circuit can be provided with mission module, it is each that control circuit includes connection
The MCU and resistance of individual motor switch.When implementing, tailing axle 501 is using port wing 201 and the screw mandrel of starboard wing 301 is run through, in screw mandrel
On be arranged with internal thread and aggravate copper pipe, the internal thread aggravates the 5%-30% that copper pipe is screw mandrel length, passes through and rotate spiral shell in regulation
Line aggravates the correspondence position of copper pipe and screw mandrel, it is possible to achieve the balance of port wing 201 and starboard wing 301 is debugged, this tune
Try smart structural design and it is easy to implement.
Dynamical system when unmanned plane VTOL or hovering is auxiliary by the main rotor 502 on a tiliting axis 500 and three
Rise control duct composition.By setting tiliting axis 500, when flying before unmanned plane turns from hovering, the Plane of rotation of main rotor 502 can be to
Before vert 90 °.When unmanned plane flies to be transitioned into floating state in the past, the Plane of rotation of main rotor 502 from can vert 90 ° backward.It is main
Rotor 502 uses carbon fiber blade so that unmanned plane is in VTOL or hovering with good stability.Three auxiliary ducts
It is distributed in isosceles triangle, the control moment on front and rear during VTOL and left and right directions can be increased, when being advantageous to VTOL
Control performance and stability.Unmanned plane uses blended wing-body totality pneumatic design technology, reduces air agitation during flight,
Flight resistance is reduced, increases flight efficiency, while handsome in appearance, manufacturing process is simple, with militarily can also greatly subtracting
Few radar area, there is preferable Stealth Fighter.Using left vertical tail 200 and right vertical tail 300, left vertical tail
200 and right vertical tail 300 may act as in VTOL undercarriage use, implement when, can use in left vertical tail 200
And the right lower section of vertical tail 300 is provided with race, and lifting wheel construction is provided with race, undercarriage after eliminating two, not only
Construction weight is alleviated, reduces aerodynamic drag during flight, reduces the complexity of structure, and reduce body center of gravity position
Put, add dynamic stability during unmanned plane VTOL.In addition, left vertical tail 200 and right vertical tail 300 are located at two
Wing both ends, the effect of winglet is served, restrained effectively the generation of tip vortex, reduce aerodynamic drag.Main culvert
The trailing edge of road 104 is directly punched and is fixedly connected with port wing 201 and starboard wing 301 with carbon fiber pipe, ensure that housing construction is strong
Flying weight is alleviated while spending.In a word, it blended wing-body aerodynamic arrangement, can greatly reduce resistance, increase in body
Free space, i.e., theoretical upper limb body sectional thickness larger part can arrange load, reduce the radar reflection characteristic of complete machine（It is military）,
Eliminate the interference between additional drag and wing and fuselage caused by the parts such as fuselage, so as to obtain at a lower rate compared with
High lift-drag ratio, improves flying quality.
Claims (10)
1. VTOL fixed-wing unmanned plane structure, it is characterized in that：Include fuselage main body, the fuselage main body both sides are provided with a left side
Wing and starboard wing, the fuselage main body are provided with main duct, and the main duct is provided with main rotor, and main rotor is driven by motor
It is dynamic；Fuselage main body front end is provided with head rotor；The outside of the port wing is provided with the left-handed wing, and the outside of the starboard wing is provided with the right side
Rotor.
2. VTOL fixed-wing unmanned plane structure according to claim 1, it is characterized in that：Below the front end of fuselage main body
Provided with nose-gear.
3. VTOL fixed-wing unmanned plane structure according to claim 1, it is characterized in that：The fuselage main body and left machine
Bearing pin is provided between the wing and starboard wing to connect.
4. VTOL fixed-wing unmanned plane structure according to claim 1, it is characterized in that：The left-handed wing is located at left machine
In left duct on the wing, the dextrorotation wing is in the right duct of starboard wing.
5. VTOL fixed-wing unmanned plane structure according to claim 1, it is characterized in that：The port wing tail end is provided with
Left vertical tail, the starboard wing tail end are provided with right vertical tail.
6. VTOL fixed-wing unmanned plane structure according to claim 1, it is characterized in that：The main duct, which is provided with, to incline
Rotating shaft set, tiliting axis is provided with the axle sleeve that verts, the main rotor is on tiliting axis.
7. VTOL fixed-wing unmanned plane structure according to claim 1, it is characterized in that：The rear side of the fuselage main body
Provided with tailing axle, for aiding in supporting fuselage duct.
8. VTOL fixed-wing unmanned plane structure according to claim 1, it is characterized in that：The port wing and starboard wing
It is respectively equipped with battery flat.
9. VTOL fixed-wing unmanned plane structure according to claim 1, it is characterized in that：The fuselage main body is provided with
Mission module, task device is provided with mission module.
10. VTOL fixed-wing unmanned plane structure according to claim 7, it is characterized in that：The tailing axle is one to run through
Port wing and starboard wing screw mandrel, internal thread is arranged with screw mandrel and aggravates copper pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720715358.1U CN206968982U (en) | 2017-06-20 | 2017-06-20 | VTOL fixed-wing unmanned plane structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720715358.1U CN206968982U (en) | 2017-06-20 | 2017-06-20 | VTOL fixed-wing unmanned plane structure |
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| Publication Number | Publication Date |
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| CN206968982U true CN206968982U (en) | 2018-02-06 |
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| CN201720715358.1U Active CN206968982U (en) | 2017-06-20 | 2017-06-20 | VTOL fixed-wing unmanned plane structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107399432A (en) * | 2017-06-20 | 2017-11-28 | 深圳高科新农技术有限公司 | VTOL fixed-wing unmanned plane structure |
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2017
- 2017-06-20 CN CN201720715358.1U patent/CN206968982U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107399432A (en) * | 2017-06-20 | 2017-11-28 | 深圳高科新农技术有限公司 | VTOL fixed-wing unmanned plane structure |
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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: 20221115 Address after: Room 606, Comprehensive Building, Huanghua Comprehensive Bonded Zone, Qishan Community, Huanghua Town, Changsha County, Hunan 410100 Patentee after: Wang Kuiguang Address before: 518000 North 801-805 unit, 8th floor, A building, 2, Guangdong, Shenzhen, Nanshan District. Patentee before: SHENZHEN HI-TECH NEW AGRICULTURE TECHNOLOGIES Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230104 Address after: 1008-09, Building 4, Guanming Business Center, No. 798, Zhongyi 1st Road, Dongjing Street, Yuhua District, Changsha City, 410000, Hunan Province Patentee after: Hunan Plant Protection UAV Technology Co.,Ltd. Address before: Room 606, Comprehensive Building, Huanghua Comprehensive Bonded Zone, Qishan Community, Huanghua Town, Changsha County, Hunan 410100 Patentee before: Wang Kuiguang |