CN206719551U - A kind of Three-wing-surface solar energy unmanned plane - Google Patents
A kind of Three-wing-surface solar energy unmanned plane Download PDFInfo
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- CN206719551U CN206719551U CN201720474277.7U CN201720474277U CN206719551U CN 206719551 U CN206719551 U CN 206719551U CN 201720474277 U CN201720474277 U CN 201720474277U CN 206719551 U CN206719551 U CN 206719551U
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- wing
- solar energy
- canard
- unmanned plane
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Abstract
The utility model is created and provides a kind of Three-wing-surface solar energy unmanned plane, including fuselage and the canard from head to tail, wing and the empennage that are set gradually from；Oar is installed in the head section before the canard and drives the motor of oar；Fuselage, which is provided with, is used to drive canard deflection with the adjustment mechanism in change of flight course；Wing includes spar and the rib set perpendicular to spar, and the wing is wrapped other positions in addition to top surface by covering；It is provided through at least two Kev bracing wires of the rib in wing, the solar energy piece for the consuming parts power supply on fuselage is respectively and fixedly provided with the Kev bracing wire between every two rib.Motor and oar in the utility model creation are arranged in before canard, in addition using the structure of complete dynamic canard, when canard deflects less angle, very big lift can be provided, greatly improve the ability of resistance of airplane nose-down pitching moment, the ability of the anti-nose-down pitching moment of solar energy unmanned plane is improved, improves the flying quality of aircraft.
Description
Technical field
The invention belongs to unmanned vehicle technical field, more particularly, to a kind of Three-wing-surface solar energy unmanned plane.
Background technology
At present, although normal arrangement solar energy unmanned air vehicle technique comparative maturity, there is U.S. AC such as and promoted company to carry
" Mecrator " solar energy unmanned plane that " SoLong " the solar energy unmanned plane that goes out, QinetiQ companies of Britain propose etc..But
Compared to three-surface configuration, normal arrangement solar powered aircraft still has many weak points.Because solar energy piece absorbs limited energy,
Must be big aircraft so to spread more solar energy pieces, and generally, aircraft is bigger, it spreads solar energy piece quantity
It is more, there is provided energy is bigger.But solar powered aircraft provides finite energy after all, the offer that no image of Buddha battery is the same to be stablized is big
Power electricity, and big aircraft horizontal stabilizer apart from motor and oar farther out, elevator operation is insensitive, when aircraft run into it is larger
Nose-down pitching moment when, it is likely that cause air crash accident.In addition, because solar energy unmanned plane belongs to big aircraft, wing is larger,
And it is often negative lift caused by conventional airplane horizontal stabilizer, wing can bear bigger structural loads, it is necessary to pole
Strong structural strength, weight increase therewith, but due to the finite energy that solar energy piece provides, its weight demands is extremely light, and this can not
The flying quality for causing great contradiction, influenceing solar powered aircraft avoided.
The content of the invention
In view of this, the invention is intended to overcome defect present in above-mentioned prior art, proposes a kind of Three-wing-surface too
Positive energy unmanned plane.
To reach above-mentioned purpose, what the technical scheme of the invention was realized in：
A kind of Three-wing-surface solar energy unmanned plane, including fuselage and set gradually from canard from head to tail, wing and
Empennage；Oar is installed in the head section before the canard and drives the motor of oar；The fuselage, which is provided with, to be used to drive
Dynamic canard deflection is with the adjustment mechanism in change of flight course；The wing includes spar and the rib set perpendicular to spar, and
The wing is wrapped other positions in addition to top surface by covering；At least two Gen Kaifula of the rib are provided through in wing
Line, the solar energy piece for the consuming parts power supply on fuselage is respectively and fixedly provided with the Kev bracing wire between every two rib.
Further, the rib is provided with the via for being used for wearing Kev bracing wire.
Further, the canard is fixed on is installed vertically on the carbon beam of the fuselage by bearing, the left and right two of canard
Partial symmetry is arranged on the both ends that the carbon beam stretches out fuselage.
Further, adjustment mechanism is included in the first rocking arm and carbon beam that are fixedly installed on steering wheel and steering wheel output shaft
Second rocking arm of portion's fixed setting；Connected between first rocking arm and the second rocking arm by iron wire.
Further, the solar energy piece does not protrude from wing top surface.
Further, the solar energy piece is fixed in Kev bracing wire by paper self-adhesive tape.
Further, the wing has the inclination angle to three degree of body upper.
Relative to prior art, the invention has the advantage that：
The invention is simple in construction, reasonable in design, and motor and oar are arranged in before canard, wind caused by the rotation of its high speed
Speed can be concentrated through canard, in addition using the structure of complete dynamic canard, when canard deflects less angle, you can provide very big
Lift, greatly improve the ability of resistance of airplane nose-down pitching moment, improve the ability of the anti-nose-down pitching moment of solar energy unmanned plane,
The structural loads of wing are reduced, reduce the weight of aircraft, improve the flying quality of aircraft.
Brief description of the drawings
The accompanying drawing for forming the part of the invention is used for providing further understanding the invention, present invention wound
The schematic description and description made is used to explain the invention, does not form the improper restriction to the invention.
In accompanying drawing：
Fig. 1 is the structural representation of the invention；
Fig. 2 is the structural representation of canard part in the invention；
Fig. 3 is the structural representation for the wing section that Kev bracing wire is provided with the invention；
Fig. 4 is the structural representation of wing section when solar energy piece is set in the invention；
Fig. 5 is the structural representation of adjustment mechanism part in the invention.
Description of reference numerals：
1- fuselages；2- canards；3- wings；4- empennages；5- oars；6- spars；7- ribs；8- Kev bracing wires；9- solar energy pieces；
10- RECTANGULAR WINGSs；11- tapered airfoils；12- vias；13- gaps；14- carbon beams；15- steering wheels；The rocking arms of 16- first；The rocking arms of 17- second；
18- iron wires.
Embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the invention can
To be mutually combined.
In the description of the invention, 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 invention and simplifies description, rather than instruction
Or imply that signified device or element must have specific orientation, with specific azimuth configuration and operation, therefore be not understood that
For the limitation to the invention.In addition, term " first ", " second " etc. are only used for describing purpose, and it is not intended that instruction
Or imply relative importance or the implicit quantity for indicating indicated technical characteristic.Thus, " first ", " second " etc. are defined
Feature can express or implicitly include one or more this feature.In the description of the invention, unless separately
It is described, " multiple " are meant that two or more.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in the description of the invention
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 joined directly together, can also be indirectly connected 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 invention.
Describe the invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
A kind of Three-wing-surface solar energy unmanned plane, as shown in Fig. 1 to 5, including fuselage 1 and set successively from head to tail
Canard 2, wing 3 and the empennage 4 put；Oar 5 is installed in the head section before the canard 2 and drives the motor of oar；
The fuselage, which is provided with, to be used to drive canard 2 to deflect with the adjustment mechanism in change of flight course；The wing 3 includes the He of spar 6
The rib 7 set perpendicular to spar, and the wing 3 is wrapped other positions in addition to top surface by covering 8；It is provided with wing 3
Through at least two Kev bracing wires 8 of the rib 7, it is respectively and fixedly provided with the Kev bracing wire 8 between every two rib 7 as on fuselage
The solar energy piece 9 of consuming parts power supply.Wing has the inclination angle to three degree of body upper.
It is pointed out that the motor of oar 5 and driving oar is arranged on before canard 2, caused wind speed can be quick
By canard 2, increase the pitch control power of unmanned plane, stability is more preferable.
In an optional embodiment, wing 3 uses the method that rectangular wing is combined with tapered wing, specifically, machine
The wing can include the RECTANGULAR WINGS 10 at wing root and the tapered airfoil 11 at wing tip.Tapered airfoil at wing tip can be used without mask knot
Structure, simple in construction, easily manufactured, by substantial amounts of it is demonstrated experimentally that in the case of without mask structure, wing tip can be born completely
The torsion of wing.In addition, tapered airfoil can also by drive mechanism, it is telescopic be arranged in RECTANGULAR WINGS, more enrich this
The performance of unmanned plane.
The invention provide unmanned plane use three-surface configuration, awing, by solar energy piece absorption solar energy
Electric energy is provided for consuming parts.In order to ensure the stabilization of power supply and improve endurance, in an optional embodiment,
The battery for being used to store electric energy being connected with each solar energy piece can be set on fuselage, connected by battery and each consuming parts
Connect, power supply supply is more stable, and cruising time is longer.
Solar energy piece can use commercially available solar battery sheet, and in the invention, each solar energy piece 9 is all cut
For 125mmX125mm fritter, solar energy piece is largely avoided by spar or the possibility of rib extrusion damage, and at utmost
Go to spread more solar energy pieces using wing area.It is pointed out that unmanned plane is in flight course, wing is bullied flow resistance
Power is influenceed, and certain deflection, and pitching adjustment or course adjustment each time, the deformation of wing are had relative to normality
Amount and deformation angle can change, therefore, the invention the corresponding spar in each side of each solar energy piece (or
Rib) between all leave gap 13, generally, gap is effectively prevented because wing deformation causes and solar energy piece in 1-2mm or so
The possibility of damage.
Above-mentioned rib is provided with the via 12 for being used for wearing Kev bracing wire, and via is adapted with Kev bracing wire diameter, avoided
Larger gap is produced, Kev bracing wire is effectively positioned, and just can guarantee that the stability of solar energy piece.As for selection by solar energy
Piece is fixed in Kev bracing wire by paper self-adhesive tape, rather than is directly anchored on wing, is exactly in order to ensure each solar energy piece
Can there is certain activity space on wing, also, each solar energy piece also still allows for certain change in displacement between each other.
Above-mentioned canard 2 is fixed on to be installed vertically on the carbon beam 14 of the fuselage by bearing, left and right two parts of canard 2
It is symmetricly set on the both ends that the carbon beam stretches out fuselage.Above-mentioned adjustment mechanism includes fixation on steering wheel 15 and steering wheel output shaft and set
Second rocking arm 17 of fixed setting in the middle part of the first rocking arm 16 and carbon beam put；By iron wire between first rocking arm and the second rocking arm
18 connections.
In flight course, power can be exported by steering wheel, the first rocking arm pulls iron wire, is applied to the effect of the second rocking arm
Power so that carbon beam flips an angle, and then realizes the upset of canard, because canard is using the structure design of complete dynamic canard, energy
Enough in the case where deflecting very little angle, there is provided bigger lift.
Above-mentioned solar energy piece does not protrude from wing top surface.Avoid in flight course, influenceed by air drag, such knot
Structure designs, and is embedded in spar, in rib institute clip space equivalent to solar energy piece, the influence of air-flow is not subject in flight course,
Effectively play while use function, it is ensured that the stability of unmanned plane entirety.
The invention is simple in construction, reasonable in design, and motor and oar are arranged in before canard, wind caused by the rotation of its high speed
Speed can be concentrated through canard, in addition using the structure of complete dynamic canard, when canard deflects less angle, you can provide very big
Lift, greatly improve the ability of resistance of airplane nose-down pitching moment, improve the ability of the anti-nose-down pitching moment of solar energy unmanned plane,
The structural loads of wing are reduced, reduce the weight of aircraft, improve the flying quality of aircraft.
The preferred embodiment of the invention is the foregoing is only, is not intended to limit the invention creation, it is all at this
Within the spirit and principle of innovation and creation, any modification, equivalent substitution and improvements made etc., the invention should be included in
Protection domain within.
Claims (7)
- A kind of 1. Three-wing-surface solar energy unmanned plane, it is characterised in that：The duck set gradually including fuselage and from head to tail The wing, wing and empennage；Oar is installed in the head section before the canard and drives the motor of oar；Set on the fuselage Have for driving canard deflection with the adjustment mechanism in change of flight course；The wing includes spar and perpendicular to spar setting Rib, and the wing is wrapped other positions in addition to top surface by covering；At least the two of the rib are provided through in wing Root Kev bracing wire, the solar energy piece for the consuming parts power supply on fuselage is respectively and fixedly provided with the Kev bracing wire between every two rib.
- A kind of 2. Three-wing-surface solar energy unmanned plane according to claim 1, it is characterised in that：The rib, which is provided with, to be used for Wear the via of Kev bracing wire.
- A kind of 3. Three-wing-surface solar energy unmanned plane according to claim 1, it is characterised in that：The canard, which is fixed on, to be passed through Bearing is installed vertically on the carbon beam of the fuselage, and left and right two parts of canard are symmetricly set on the carbon beam stretches out fuselage two End.
- A kind of 4. Three-wing-surface solar energy unmanned plane according to claim 3, it is characterised in that：The adjustment mechanism includes rudder Second rocking arm of fixed setting in the middle part of the first rocking arm and carbon beam being fixedly installed on machine and steering wheel output shaft；First rocking arm And second connected by iron wire between rocking arm.
- A kind of 5. Three-wing-surface solar energy unmanned plane according to claim 1, it is characterised in that：The solar energy piece does not protrude In wing top surface.
- A kind of 6. Three-wing-surface solar energy unmanned plane according to claim 1, it is characterised in that：The solar energy piece passes through paper Adhesive tape is fixed in Kev bracing wire.
- A kind of 7. Three-wing-surface solar energy unmanned plane according to claim 1, it is characterised in that：The wing has to fuselage The inclination angle that three degree of top.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720474277.7U CN206719551U (en) | 2017-04-28 | 2017-04-28 | A kind of Three-wing-surface solar energy unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720474277.7U CN206719551U (en) | 2017-04-28 | 2017-04-28 | A kind of Three-wing-surface solar energy unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206719551U true CN206719551U (en) | 2017-12-08 |
Family
ID=60508429
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720474277.7U Expired - Fee Related CN206719551U (en) | 2017-04-28 | 2017-04-28 | A kind of Three-wing-surface solar energy unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206719551U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108408023A (en) * | 2018-03-08 | 2018-08-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control method, flight control system based on canard and aircraft |
| CN113562160A (en) * | 2021-08-07 | 2021-10-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Front wing application method for improving pitching moment characteristic of airplane |
| KR20210148488A (en) * | 2020-05-28 | 2021-12-08 | 조남석 | Unmanned aerial vehicle |
-
2017
- 2017-04-28 CN CN201720474277.7U patent/CN206719551U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108408023A (en) * | 2018-03-08 | 2018-08-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control method, flight control system based on canard and aircraft |
| CN108408023B (en) * | 2018-03-08 | 2020-09-08 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control method and system based on canard wing and airplane |
| KR20210148488A (en) * | 2020-05-28 | 2021-12-08 | 조남석 | Unmanned aerial vehicle |
| KR102380247B1 (en) * | 2020-05-28 | 2022-03-30 | 조남석 | Unmanned aerial vehicle |
| CN113562160A (en) * | 2021-08-07 | 2021-10-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Front wing application method for improving pitching moment characteristic of airplane |
| CN113562160B (en) * | 2021-08-07 | 2024-01-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Front wing application method for improving pitching moment characteristics of airplane |
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| 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 |
Granted publication date: 20171208 Termination date: 20180428 |
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| CF01 | Termination of patent right due to non-payment of annual fee |