CN206598982U - A kind of VUAV - Google Patents
A kind of VUAV Download PDFInfo
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- CN206598982U CN206598982U CN201720180853.7U CN201720180853U CN206598982U CN 206598982 U CN206598982 U CN 206598982U CN 201720180853 U CN201720180853 U CN 201720180853U CN 206598982 U CN206598982 U CN 206598982U
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- propeller
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- poppet
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- unmanned plane
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Abstract
The utility model proposes a kind of VUAV, the body of unmanned plane uses high lift-drag ratio class all-wing aircraft aerodynamic arrangement, and is provided with four motors and propeller in the way of " ten " font is arranged on fuselage.The thrust difference that can be produced using propeller above and below fuselage forms pitch control torque, the thrust difference produced using fuselage left-and-right spiral oar forms driftage control moment, and utilize the rolling control moment of four propeller different rotating speeds formation, the gesture stability of unmanned plane body is carried out, VTOL of the unmanned plane in narrow and small region and the spot hover in flight course at an arbitrary position is realized.The unmanned plane is transformed into after flat winged state, and class Flying-wing body can produce larger cruise lift-drag ratio, greatly improve the payload level and flying distance of unmanned plane.It during the unmanned plane horizontal flight, can only be promoted, compared with low velocity flight, can also simultaneously be promoted using four propellers simultaneously, carry out rapid flight using left and right horizontal propeller.
Description
Technical field
The present invention relates to unmanned aerial vehicle technical field, more particularly to a kind of VUAV.
Background technology
VUAV is because small to takeoff and landing site requirements, with huge application prospect.It is existing nobody
Machine realizes VTOL mainly by following several forms：One is to realize vertical rise using many rotors (such as four rotor wing unmanned aerial vehicles)
Drop, it is low to there is aircraft pneumatic efficiency in this mode, and it is small to carry flight load, the problems such as flight time is short；Two be straight using rotor
The mode of the machine of liter realizes VTOL, and this mode needs the larger main rotor system of power, the moment of torsion produced for balance rotor,
Need specially to design tail-rotor or coaxial rotor system, complicated integral structure, the body free degree is more, flight control is difficult；Three are
VTOL is realized using tilting rotor (such as U.S. V-22 aircrafts), this mode needs the complicated inclining rotary mechanism of design, transmission
System architecture is complicated, there is larger structure deadweight, and conversion and control of verting process is complicated, and reliability is relatively low.
In addition, having occurred in that some new vertical landing unmanned planes at present, typically there is culvert type unmanned plane (such as Buddhist nun suddenly
Wei Er T-Hawk unmanned planes), many rotors and fixed-wing Combined unmanned machine (such as " roc " unmanned plane of Chengdu company in length and breadth), adopt
Unmanned plane (such as 611 VD200 unmanned planes of Air China) of VTOL etc. is controlled with propellerslip.These new vertical landings without
It is man-machine there is also some technical problems, such as culvert type unmanned plane is influenceed substantially, to vibrate during VTOL by ground effect
Strongly, and during horizontal flight lift and the thrust advanced are provided by duct engine completely, flying speed is relatively low；Many rotors are with consolidating
Determine wing Combined unmanned machine and usually rely on the pulling force that four rotors of fixed installation produce to lift unmanned plane and realize VTOL, but
In horizontal flight, four rotors can not provide onward impulse, and unmanned plane must install propulsion motor and propeller, add machine
Body structure deadweight, and four rotors and mounting structure are added significantly to aerodynamic drag, the overall pneumatic efficiency of unmanned plane is relatively low；And
The unmanned plane controlled using propellerslip is in VTOL, because flying speed is low, relies primarily on the spiral of wing nose
The slip-stream increase rudder face control efficiency that oar is provided, carries out the gesture stability of unmanned plane, this requires unmanned plane must be installed larger
The propeller of diameter and the engine of relatively high power.In addition, the slip-stream that propeller is provided is by environmental condition (such as fitful wind) and body
The influence of surface projection part is obvious, causes slip-stream unstable, brings difficulty to flight control, easily cause aircraft accident.Due to
Upper technical problem is difficult to solve, cause existing VUAV flight stability and navigability, payload mass,
The Key Performance Indicators such as horizontal flight speed, maximum flying distance are all extremely restricted, and have impact on its actual engineer applied.
Therefore, the technology restriction of existing VUAV is broken through, the new unmanned plane that innovation and development is suitable for VTOL is pneumatic
Layout is to realize that unmanned plane VTOL technology obtains the key broken through.
The content of the invention
In order to overcome, the pneumatic efficiency of generally existing in existing VUAV technology is low, inclining rotary mechanism is complicated, winged
The problems such as row time is short, flying speed is low, mode conversion is complicated, present invention firstly provides a kind of new ideas tailstock formula VTOL
Unmanned plane.
The body of the unmanned plane uses high lift-drag ratio class all-wing aircraft aerodynamic arrangement, and the side arranged on fuselage with " ten " font
Formula is provided with four motors and propeller.The thrust difference that the unmanned plane can be produced using propeller above and below fuselage forms pitching control
Torque processed, the thrust difference produced using fuselage left-and-right spiral oar forms driftage control moment, and utilizes four propeller differences
The rolling control moment of rotating speed formation, carries out the gesture stability of unmanned plane body, realizes that unmanned plane is vertical in narrow and small region
Landing and the spot hover in flight course at an arbitrary position.The unmanned plane is transformed into after flat winged state, class Flying-wing
Body can produce larger cruise lift-drag ratio, greatly improve the payload level and flying distance of unmanned plane.The unmanned plane
It during horizontal flight, can only be promoted using left and right horizontal propeller, carry out, compared with low velocity flight, four can also being used simultaneously
Individual propeller is promoted simultaneously, carries out rapid flight.
The technical scheme is that：
A kind of VUAV, including middle machine body 1, port wing 17, starboard wing 3, left motor and spiral
Oar 18, right motor and propeller 2, the left motor and propeller 18 are arranged on the front end of port wing 17, right motor and spiral shell
Revolve oar 2 and be arranged on the front end of starboard wing 3；It is characterized in that：Also include upper motor and propeller 8, lower motor and propeller 19；
Upper motor and propeller 8 are arranged on the upper front end of after-poppet 9, and lower motor and propeller 19 are arranged on the lower front end of after-poppet 12,
Upper after-poppet 9 is arranged on the top of middle machine body 1 by upper bracket 10, and lower after-poppet 12 is arranged on middle machine body by lower carriage 20
1 bottom；Left motor and propeller 18, right motor and propeller 2, upper motor and propeller 8, lower motor and propeller
19 arrange relative to middle machine body longitudinal center axis in " ten " font；The rear portion of port wing 17 is provided with left back support 14, right machine
The rear portion of the wing 3 is provided with right after-poppet 6, and left back support 14, right after-poppet 6, upper after-poppet 9 and lower after-poppet 12 are relative to middle machine
Body longitudinal center axis is arranged in " ten " font, and rear end is concordant.
Further preferred scheme, a kind of VUAV, it is characterised in that：Install left in the outer end of port wing 17
Winglet 16, left direction rudder 15 is arranged on the left rear portion of winglet 16, and right winglet 4, right direction are installed in the outer end of starboard wing 3
Rudder 5 is arranged on the right rear portion of winglet 4；Port aileron 13 is arranged on the rear portion of port wing 17, and starboard aileron 7 is arranged on the rear portion of starboard wing 3；
Elevator 11 is arranged on the rear portion of middle machine body 1.
Further preferred scheme, a kind of VUAV, it is characterised in that：Middle machine body 1 employs class
Lifting body aerodynamic arrangement；Upper bracket 10 and the cross section of lower carriage 20 use symmetrical airfoil.
Further preferred scheme, a kind of VUAV, it is characterised in that：Port wing 17, starboard wing 3,
Upper bracket 10, lower carriage 20, upper after-poppet 9, lower after-poppet 12, left back support 14 and right after-poppet 6 are the module that can be dismantled
Change structure.
Beneficial effect
VUAV proposed by the present invention is using installation " ten " font arrangement on high lift-drag ratio body
Motor and propeller, by adjusting the thrust size of four propellers of body, produce pitching, rolling and yawing and carry out nobody
The gesture stability of machine, realizes the VTOL of unmanned plane, efficiently solves conventional vertical landing unmanned plane and verts or rotor system
Complicated, mode conversion control is complicated, the low defect of pneumatic efficiency.The VUAV, it is possible to achieve in narrow and small region
VTOL, spot hover and level efficiently fly.The VUAV, housing construction can be torn open with fast and easy
Unload and assemble, carry after difference in functionality load, can apply to power-line patrolling, resources observation, environmental protection, logistics delivery etc. many
Plant civil and military field.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Brief description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become from description of the accompanying drawings below to embodiment is combined
Substantially and be readily appreciated that, wherein：
Fig. 1 is a kind of VUAV layout schematic side view of the invention；
Fig. 2 is a kind of VUAV layout front-view schematic diagram of the invention；
Fig. 3 is a kind of VUAV layout schematic top plan view of the invention；
Fig. 4 is the decomposing schematic representation shown in a kind of VUAV；
The mark of each part is as follows in accompanying drawing：1st, middle machine body；2nd, right motor and propeller；3rd, starboard wing；4th, right flank
Tip winglet；5th, right direction rudder；6th, right after-poppet；7th, starboard aileron；8th, upper motor and propeller；9th, upper after-poppet；10th, upper branch
Frame；11st, elevator；12nd, lower after-poppet；13rd, port aileron；14th, left back support；15th, left direction rudder；16th, left winglet；17、
Port wing；19th, lower motor and propeller；18th, left motor and propeller；20th, lower carriage.
Fig. 5 is the VTOL process schematic shown in a kind of VUAV.
Embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning to end
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and be not considered as limiting the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " are, based on orientation shown in the drawings or position relationship, to be for only for ease of
The description present invention and simplified description, rather than indicate or imply that the device or element of meaning must have specific orientation, Yi Te
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
As shown in figures 1-4, the VUAV in the present embodiment includes middle machine body 1, port wing 17, starboard wing
3rd, left motor and propeller 18, right motor and propeller 2, the left motor and propeller 18 are arranged on before port wing 17
End, right motor and propeller 2 are arranged on the front end of starboard wing 3, and left motor and propeller 18 exist with right motor and propeller 2
It is symmetrical in organism level face.
Also include upper motor and propeller 8, lower motor and propeller 19；Upper motor and propeller 8 are arranged on upper
The front end of after-poppet 9, lower motor and propeller 19 are arranged on the lower front end of after-poppet 12, and upper after-poppet 9 is installed by upper bracket 10
On the top of middle machine body 1, lower after-poppet 12 is arranged on the bottom of middle machine body 1 by lower carriage 20, upper motor and propeller 8 with
Lower motor and propeller 19 are symmetrical above and below in body vertical plane.Left motor and propeller 18, right motor and spiral
Oar 2, upper motor and propeller 8, lower motor and propeller 19 are in " ten " font relative to middle machine body longitudinal center axis
Arrangement, it is possible to achieve the control during VTOL.
The rear portion of port wing 17 is provided with left back support 14, and the rear portion of starboard wing 3 is provided with right after-poppet 6, left back support 14, the right side
After-poppet 6, upper after-poppet 9 and lower after-poppet 12 are arranged relative to middle machine body longitudinal center axis in " ten " font, and rear end
Concordantly, ground can be stood in the form of " tail seat " on ground.
Left winglet 16 is installed in the outer end of port wing 17, and left direction rudder 15 is arranged on the left rear portion of winglet 16, starboard wing 3
Right winglet 4 is installed in outer end, and right direction rudder 5 is arranged on the right rear portion of winglet 4, and left direction rudder 15 and right direction rudder 5 can be with
Deflection carries out Heading control during unmanned plane horizontal flight；Port aileron 13 is arranged on the rear portion of port wing 17, and starboard aileron 7 is installed
At the rear portion of starboard wing 3, rolling when port aileron 13 can carry out unmanned plane horizontal flight with starboard aileron 7 with differential deflection is controlled；Rise
Drop rudder 11 and be arranged on the rear portion of middle machine body 1, elevator 11 can deflect pitch control when carrying out unmanned plane horizontal flight up and down.
Middle machine body 1 in the present embodiment employs liftbody type aerodynamic arrangement, middle machine body 1, port wing 13 and right machine
The main body that the wing 3 is constituted employs the aerodynamic arrangement of class all-wing aircraft, and fuselage and Airfoil Sections use airfoil with high ratio of lift over drag, and left wing's tip is small
The wing 16 and right winglet 4 can reduce induced drag during cruising flight, and fuselage upper bracket 10 and lower carriage 20 use low-resistance
Symmetrical airfoil, reduces aerodynamic drag during unmanned plane horizontal flight, and whole unmanned plane body pneumatic efficiency is high, lift-drag ratio of cruising
More than 10.
VUAV in the present embodiment uses modularized design, port wing 17, starboard wing 3, upper bracket 10, under
Support 20, upper after-poppet 9, lower after-poppet 12, left back support 14 and right after-poppet 6 can realize quick disassembly and assembly, electricity
Machine and support are coupled using standard flange, convenient to carry out quick-replaceable according to different task load.
The control mode of above-mentioned VUAV is：
Before the VUAV takes off, by being propped up behind upper after-poppet 9, lower after-poppet 12, left back support 14 and the right side
Frame 6 vertically stands on ground in tailstock form；When taking off, by the pulling force of four propellers by body band from the ground, when body from
After ground certain distance, by adjusting the rotating speed of the upper and lower propeller of body, (rotating speed of upper motor and propeller 8 is more than bottom electricity
The rotating speed of machine and propeller 19) pitching moment that thrust difference generation is bowed is formed, realize aircraft from vertically to the mould of horizontal flight
State is changed, and horizontal flight is realized after certain speed when aircraft reaches.
During landing, by adjusting the rotating speed of the upper and lower propeller of body, (rotating speed of lower motor and propeller 19 is more than top
The rotating speed of motor and propeller 8) form thrust difference and produce the pitching moment come back, realize aircraft from horizontal flight to vertical landing
Mode conversion, after horizontal flight speed is zero, by adjust four propellers pulling force gradually reduce aircraft altitude, pass through
Vertical landing is on the ground in the form of tail is sat for four after-poppets.
During VTOL, left and right propeller direction of rotation is identical, and upper and lower propeller direction of rotation is identical, left and right spiral
Oar direction of rotation is opposite with upper and lower propeller direction of rotation.Left and right revolution speed of propeller is adjusted simultaneously, produces rolling control moment,
The anti-twisted torque of the upper and lower propeller generation of balance body and the rolling control for carrying out body；Left and right propeller is adjusted respectively to turn
Speed, forms left and right thrust difference and produces driftage control moment, carries out the driftage control of body.
In VTOL, the control moment of the pitching, rolling and three passages of going off course that are produced by four propellers is larger,
And being influenceed smaller by factors such as fitful wind, body surface structures, the maneuverability of unmanned plane is preferable, strong antijamming capability, Ke Yishi
The existing spot hover of unmanned plane at an arbitrary position.
And in horizontal flight, pitch control control is realized by the deflection of elevator 11 of After-Body, by wing
The differential deflection of port aileron 13 and starboard aileron 7 produces rolling control moment, realizes that the rolling to unmanned plane is controlled, small by wingtip
The collaboration deflection of the left direction rudder 15 and right direction rudder 5 at wing rear portion produces driftage control moment, realizes the driftage control to unmanned plane
System., can be different from the rotating speed of right motor and propeller 2 by adjusting left motor and propeller 18 in larger crosswind,
The pulling force formed on course is poor, produces larger yawing, realizes that the driftage to unmanned plane is controlled.
In addition, having high speed and two kinds of state of flights of low speed when in horizontal flight：During low-speed condition, only with left side electricity
Machine and propeller 18 and right motor and propeller 2 work, to save energy, realize unmanned plane flying for long time；High-speed flight
During state, left motor and propeller 18, right motor and propeller 2, upper motor and propeller 8, lower motor and spiral
Oar 19 works simultaneously, produces compared with high thrust, realizes the rapid flight of unmanned plane.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from the principle and objective of the present invention
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (4)
1. a kind of VUAV, including middle machine body（1）, port wing（17）, starboard wing（3）, left motor and spiral
Oar（18）, right motor and propeller（2）, the left motor and propeller（18）Installed in port wing（17）Front end, right side
Motor and propeller（2）Installed in starboard wing（3）Front end；It is characterized in that：Also include upper motor and propeller（8）, bottom
Motor and propeller（19）；Upper motor and propeller（8）Installed in upper after-poppet（9）Front end, lower motor and propeller
（19）Installed in lower after-poppet（12）Front end, upper after-poppet（9）Pass through upper bracket（10）Installed in middle machine body（1）Top, under
After-poppet（12）Pass through lower carriage（20）Installed in middle machine body（1）Bottom；Left motor and propeller（18）, right motor and
Propeller（2）, upper motor and propeller（8）, lower motor and propeller（19）Relative to middle machine body longitudinal center axis
Arranged in " ten " font；Port wing（17）Rear portion is provided with left back support（14）, starboard wing（3）Rear portion is provided with right after-poppet
（6）, left back support（14）, right after-poppet（6）, upper after-poppet（9）With lower after-poppet（12）Relative to middle machine body longitudinal center
Axis is arranged in " ten " font, and rear end is concordant.
2. a kind of VUAV according to claim 1, it is characterised in that：Port wing（17）Outer end is installed by left wing's tip
Winglet（16）, left direction rudder（15）Installed in left winglet（16）Rear portion, starboard wing（3）Outer end is installed by right winglet（4）,
Right direction rudder（5）Installed in right winglet（4）Rear portion；Port aileron（13）Installed in port wing（17）Rear portion, starboard aileron（7）Peace
Mounted in starboard wing（3）Rear portion；Elevator（11）Installed in middle machine body（1）Rear portion.
3. a kind of VUAV according to claim 1 or claim 2, it is characterised in that：Middle machine body（1）Employ class liter
Li Ti aerodynamic arrangements；Upper bracket（10）And lower carriage（20）Cross section uses symmetrical airfoil.
4. a kind of VUAV according to claim 3, it is characterised in that：Port wing（17）, starboard wing（3）, on
Support（10）, lower carriage（20）, upper after-poppet（9）, lower after-poppet（12）, left back support（14）With right after-poppet（6）For can
The modular construction of dismounting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720180853.7U CN206598982U (en) | 2017-02-28 | 2017-02-28 | A kind of VUAV |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720180853.7U CN206598982U (en) | 2017-02-28 | 2017-02-28 | A kind of VUAV |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206598982U true CN206598982U (en) | 2017-10-31 |
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ID=60147944
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720180853.7U Expired - Fee Related CN206598982U (en) | 2017-02-28 | 2017-02-28 | A kind of VUAV |
Country Status (1)
| Country | Link |
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| CN (1) | CN206598982U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892102A (en) * | 2017-02-28 | 2017-06-27 | 王文正 | A kind of VUAV and its control method |
| CN113734425A (en) * | 2021-11-05 | 2021-12-03 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned helicopter and control system thereof |
-
2017
- 2017-02-28 CN CN201720180853.7U patent/CN206598982U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892102A (en) * | 2017-02-28 | 2017-06-27 | 王文正 | A kind of VUAV and its control method |
| CN113734425A (en) * | 2021-11-05 | 2021-12-03 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned helicopter and control system thereof |
| CN113734425B (en) * | 2021-11-05 | 2022-02-08 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned helicopter and control system thereof |
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Legal Events
| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171031 Termination date: 20210228 |