CN109178296A - Winglet and aerofoil system - Google Patents
Winglet and aerofoil system Download PDFInfo
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- CN109178296A CN109178296A CN201811244562.5A CN201811244562A CN109178296A CN 109178296 A CN109178296 A CN 109178296A CN 201811244562 A CN201811244562 A CN 201811244562A CN 109178296 A CN109178296 A CN 109178296A
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- winglet
- wing
- driving device
- girder
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- 230000007246 mechanism Effects 0.000 claims description 18
- 239000007787 solid Substances 0.000 claims 1
- 230000009467 reduction Effects 0.000 abstract description 9
- 230000000694 effects Effects 0.000 description 7
- 238000010586 diagram Methods 0.000 description 6
- 238000005452 bending Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000000919 ceramic Substances 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- 238000004146 energy storage Methods 0.000 description 3
- 230000036244 malformation Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011897 real-time detection Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000009193 crawling Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000407 epitaxy Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
- B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/30—Aircraft characterised by electric power plants
- B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
- B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of winglet and aerofoil systems.The winglet includes: winglet；Driving device, for controlling the rotation of the winglet；Pressure-detecting device, positioned at the root surface of the winglet, for detecting the target moment of flexure of the winglet root；Control device is connected with the driving device and the pressure-detecting device, for generating control signal based on the target moment of flexure, so that the driving device adjusts the inclination angle of the winglet according to the control signal.The technical solution can solve the aircraft drag reduction in entire voyage stage, while also ensure the economy of aircraft.
Description
Technical field
The present invention relates to technical field of aerospace more particularly to a kind of winglets and aerofoil system.
Background technique
With increasingly highlighting for energy problem, the energy-saving and emission-reduction problem that each energy consumption industry faces is on the rise.It is same with this
When, aviation industry is also increasingly the economy of emphasis aircraft.Based on this, as reduction aircraft oil consumption and economy is solved
The important channel of problem, aircraft drag reduction technology have received widespread attention.
For large aircraft, induced drag is one of the important component of resistance suffered by aircraft, in cruise rank
Section accounts for the 40% of drag overall, and is even up to the 50%~70% of drag overall in takeoff phase and ramp-up period, therefore lower and lure
Resistance is led to have great importance for aircraft drag reduction.The method for reducing induced drag more generally accepted at present is the wing in wing
Tip position increases winglet, and in the design parameter of winglet, inclination angle be influence drag-reduction effect principal element it
One.
But at present in the aircraft that Civil Aviation System is on active service, the geometric parameter of winglet only for cruising phase drag reduction into
Go optimization, and the drag-reduction effect in the off design points such as take off and climb is bad, for short distance course line, rises
Fly and climb account for total endurance specific gravity it is larger, therefore winglet bring economic benefits are not obvious, and can even be reduced sometimes
The economy of aircraft.
Summary of the invention
To overcome the problems in correlation technique, the embodiment of the invention provides a kind of winglet and wing systems
System.The technical solution is as follows:
According to a first aspect of the embodiments of the present invention, a kind of winglet is provided, comprising:
Winglet；
Driving device, for controlling the rotation of the winglet；
Pressure-detecting device, positioned at the root surface of the winglet, for detecting the target moment of flexure of the winglet root；
Control device is connected with the driving device and the pressure-detecting device, for being based on the target moment of flexure
Control signal is generated, so that the driving device adjusts the inclination angle of the winglet according to the control signal.
In one embodiment, the pressure-detecting device includes piezoelectric transducer.
In one embodiment, the piezoelectric transducer includes piezoelectric ceramics.
In one embodiment, the control device includes signal acquisition unit and flies to control plate；
The signal acquisition unit is for obtaining the corresponding electrical signal of the target moment of flexure and sending out the electrical signal
Give the winged control plate；
The winged control plate is used for raw according to the electrical signal of the electrical signal and previous acquisition currently obtained
At corresponding control signal and it is sent to the driving device.
According to a second aspect of the embodiments of the present invention, a kind of aerofoil system, including wing-body and first aspect are provided
Described in any item winglets；
Wherein, the wing-body includes the additional wing box positioned at tip location, and the winglet rotation is connected to institute
It states in additional wing box.
In one embodiment, the aerofoil system further includes rotating mechanism；
The winglet includes girder and the winglet ontology being fixedly connected with the girder, and the additional wing box includes web
And the lug by extending outside the web, the girder are connected with the lug by the rotating mechanism.
In one embodiment, the rotating mechanism includes shaft and link mechanism, and the girder is equipped with the first limit
Hole, the lug are equipped with the second limit hole, and the shaft passes through first limit hole and second limit hole and passes through
The link mechanism is connected to the driving device.
In one embodiment, groove is equipped in first limit hole, the surface of the shaft is equipped with protrusion, described convex
It rises and cooperates with the groove, with the relative position for limiting the girder Yu the shaft.
In one embodiment, the rotating mechanism further includes bearing, the outer surface of the bearing and first limit
The inner surface in hole is in contact, and the inner surface of the bearing is in contact with the outer surface of the shaft.
In one embodiment, the driving device includes steering engine, and the steering engine is fixed on the web of the additional wing box
On.
In one embodiment, the wing-body further includes multiple ribs, close wing tip direction in the multiple rib
Two ribs be ribs.
In one embodiment, solar panel is additionally provided on the wing-body.
The technical solution that the embodiment of the present invention provides can include the following benefits:
The technical solution by pressure-detecting device detect winglet root target moment of flexure, and by means of control device according to
The variation tendency of flight parameter is predicted in the variation of the target moment of flexure, to generate corresponding control signal, enables driving device
Enough inclination angles that winglet is adjusted according to the control signal, thus achieve the effect that reduce winglet root institute bending moment, it in this way can be true
The intensity of tip vortex can be weakened in real time by protecting winglet, the lift resistance ratio of wing be improved with this, to solve entire voyage
The aircraft drag reduction in stage, while also ensuring the economy of aircraft.
It should be understood that above general description and following detailed description be only it is exemplary and explanatory, not
It can the limitation present invention.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows and meets implementation of the invention
Example, and be used to explain the principle of the present invention together with specification.
Fig. 1 is the assembly structure diagram of winglet shown according to an exemplary embodiment；
Fig. 2 is the operational module schematic diagram of winglet shown according to an exemplary embodiment；
Fig. 3 is the connection relationship diagram of aerofoil system shown according to an exemplary embodiment；
Fig. 4 is the structural schematic diagram one of aerofoil system shown according to an exemplary embodiment；
Fig. 5 is the structural schematic diagram two of aerofoil system shown according to an exemplary embodiment.
Specific embodiment
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.Following description is related to
When attached drawing, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.Following exemplary embodiment
Described in embodiment do not represent all embodiments consistented with the present invention.On the contrary, they be only with it is such as appended
The example of device and method being described in detail in claims, some aspects of the invention are consistent.
Technical solution provided by the embodiment of the present invention is related to a kind of winglet, can be used for solving in the entire voyage stage
Aircraft drag reduction.Fig. 1 diagrammatically illustrates the assembly structure diagram of the winglet 10.As can be seen from FIG. 1, the wingtip
Winglet 10 is installed on the wing tip direction of wing-body 20, specifically may include winglet 101, driving device 102, pressure-detecting device
103 and control device 104.Wherein, driving device 102 is connected with winglet 101, for controlling the rotation of winglet 101；Pressure
Force checking device 103 is located at the root surface of winglet 101, for detecting the target moment of flexure of 101 root of winglet receiving；Control device
104 are connected with driving device 102 and pressure-detecting device 103, for generating control signal according to target moment of flexure, so that driving
Device 102 adjusts the inclination angle of winglet 101 according to the control signal.It should be understood that the inclination angle of winglet 101 refers to winglet 101
It, specifically can be by being adjusted around chordwise rotation relative to the angle between 20 place plane of wing-body.
Based on this, in entire voyage the stage especially takeoff phase and crawling phase of aircraft, since flight parameter is (main
Be presented as aircraft angle of attack and flying speed) continuous variation, the intensity of tip vortex also changes accordingly, the three-dimensional flow of distortion
Have in along wing open up to component, which acts on winglet 10 variation that will be presented as its root bending moment.
The technical program detects the target moment of flexure of 101 root of winglet by pressure-detecting device 103, and by means of control device 104
The variation tendency of flight parameter is predicted according to the variation of the target moment of flexure, to generate corresponding control signal, so that driving device
102 can adjust the inclination angle of winglet 101 according to the control signal, thus achieve the effect that reduce 101 root institute bending moment of winglet,
It can ensure that winglet 10 can weaken the intensity of tip vortex in real time in this way, the lift resistance ratio of wing improved with this, thus
The aircraft drag reduction in entire voyage stage is solved, while also ensuring the economy of aircraft.
In this example embodiment, the pressure-detecting device 103 may include pressure detecting instrument or piezoelectric transducer
Deng, and be not limited.In view of piezoelectric transducer sensitivity with higher and lighter weight, therefore the present embodiment can
To use piezoelectric transducer as pressure-detecting device 103.Wherein, piezoelectric transducer can be using the pressure with high tension electricity coefficient
Electroceramics, such as d31 type piezo ceramic element, specifically can be set on the root surface of winglet 101, i.e., close to wing-body
At 20 position.Due in the ternary flow field of distortion along wing open up to component will lead to its root when acting on winglet 10
The variation of portion's moment of flexure, therefore piezoelectric ceramics can be arranged in the present embodiment here, in order to the moment of flexure at the real-time detection position, and will
The moment of flexure detected is converted to electrical signal, enables control device 104 to generate corresponding control according to moment of flexure variation and believes
Number, to control the inclination angle that driving device 102 adjusts winglet 101.In the present embodiment, control device 104 can be set in fuselage
Portion, the data line of piezoelectric transducer can be hidden in inside wing and be pierced by from airfoil root and be connected with control device 104
It connects.The present embodiment can also reinforce the root structure of winglet 10, to guarantee the intensity and rigidity in malformation.
In this example embodiment, control device 104 has both data processing function and control function.Refering to what is shown in Fig. 2, control
The concrete composition module of device 104 processed includes signal acquisition unit 1041, flies control plate 1042 and power supply 1043.Wherein, signal
Acquisition unit 1041 is connected with pressure-detecting device 103, for obtaining the corresponding electrical signal of target moment of flexure and believing the electricity
It number is sent to and to fly control plate 1042, fly control plate 1042 and be connected with driving device 102, the electrical signal currently obtained for basis is with before
The electrical signal of secondary acquisition generates corresponding control signal and the control signal is sent to driving device 102, so that driving dress
102 are set according to the inclination angle of the control Signal Regulation winglet 101, power supply 1043 can be used for providing electric power to control device 104.
Exemplary, for aircraft when being in ramp-up period, flight parameter (is mainly reflected in aircraft angle of attack and flying speed)
Continuous variation, the intensity of tip vortex also change accordingly, the ternary flow field distorted at this time have along wing open up to point
Amount, the component act on winglet 10 variation that can be then presented as its root bending moment.Based on this, pressure-detecting device 103
Such as the target moment of flexure that piezoelectric transducer can be born with 101 root of real-time detection winglet, and the target moment of flexure is converted into phase
The electrical signal answered is sent to the signal acquisition unit 1041 of control device 104, and signal acquisition unit 1041 can will receive
Data pass to fly control plate 1042 again, flying control plate 1042 at this time can will be currently received when data are passed to according to sample frequency
Electrical signal is compared with previous received electrical signal, so that the variation trends to tip vortex determine, from
And generate corresponding control signal and be applied to driving device 102, driving device 102 will adjust winglet according to the control signal
101 inclination angle, so that its root bending moment changes towards reduced trend, to guarantee that winglet 10 can weaken wing tip in real time
The intensity of vortex, to improve the lift resistance ratio of wing.
Technical solution provided by the embodiment of the present invention further relates to a kind of aerofoil system, refering to what is shown in Fig. 3, it includes wing
Ontology 20 and above-mentioned winglet 10.Wherein, wing-body 20 includes additional wing box 201, which is located at machine
The tip location of wing ontology 20, the rotation of winglet 10 are connected in additional wing box 201, are specifically attached to additional wing box 201
Epitaxial membrane on.
Based on this, the present embodiment is connected in the additional wing box 201 of wing-body 20 by rotating winglet 10, and
It is rotated according to control signal relative to wing-body 20, to realize the tilt adjustment of winglet 101, can ensure that in this way
Aerofoil system can weaken the intensity of tip vortex in real time, improve the lift resistance ratio of wing, to solve flying for entire voyage stage
Machine drag reduction.
Optionally, refering to what is shown in Fig. 4, winglet 101 includes girder 1011 and the winglet sheet being fixedly connected with girder 1011
Body 1012.Wherein, girder 1011 has the epitaxial part for protruding from winglet ontology 1012, which can be used as connecting component
It is connected with wing-body 20.
Optionally, refering to what is shown in Fig. 5, additional wing box 201 is including two webs 2011 and by two 2011 extensions of web
Two lugs 2012 stretched out, driving device 102 is fixed on the web 2011 of additional wing box 201, and the control of driving device 102
Line processed can be hidden in inside wing and be pierced by from airfoil root to be connected to control device 104.Wherein, web 2011 and lug
It with rib 202 is boundary between 2012, web 2011 is located at the inside of rib 202, and lug 2012 is located at the outside of rib 202, this
Lug 2012 can be connected as connecting component with winglet 10 by sample.
Based on above structure, in conjunction with Fig. 1 it is found that the epitaxial part of girder 1011 and two lugs 2012 can pass through rotation
Mechanism 30 is connected, and is rotated with playing the role of supporting winglet 10 and controlling winglet 10 around chordwise.
Specifically, rotating mechanism 30 may include shaft 301 and link mechanism 302, the epitaxy part of girder 1011 sets up separately
Have the first limit hole 100, lug 2012 is equipped with the second limit hole 200, girder 1011 be correspondingly arranged at two lugs 2012 it
Between gap location, and the difference between the thickness of girder 1011 and the spacing of two lugs 2012 be less than threshold limit value, make winner
Beam 1011 is inserted between two lugs 2012 just.Wherein, coordinate contact surface between girder 1011 and lug 2012
Smoothness should be able to ensure that the frictional force that coupling part is subject in rotation of winglet 101 is sufficiently small.Based on this, shaft 301 can
It is connected to driving device 102 across the first limit hole 100 and the second limit hole 200, and by link mechanism 302, the connecting rod machine
Structure 302 may include multiple connecting rods, by taking two connecting rods as an example, a connecting rod can be connected with driving device 102, another connecting rod can with turn
Axis 301 is connected, hinged between two connecting rods, can control the rotation of shaft 301 by driving device 102 in this way, in turn
Achieve the effect that controlling winglet 10 rotates.It should be understood that rotating mechanism 30 can also use its in addition to connecting rod
Its mode realizes that the present embodiment is not construed as limiting this.
In view of girder 1011 is driven by shaft 301, in order to guarantee between girder 1011 and shaft 301
Relative stability, the present embodiment can also be arranged groove in the inside of the first limit hole 100, protrusion are arranged on the surface of shaft 301,
By protrusion and the mutual cooperation of groove, the relatively fixed of girder 1011 and shaft 301 can be limited.
In this example embodiment, driving device 102 may include steering engine, which can be according to the winglet of different size
Depending on 101, selection principle be guarantee winglet 101 near by wing tip when ternary Distorted Flow Field active force can gram
Take along wing open up to component and around the tangential rotation of wing, herein under the premise of should consider light-weight and small in size rudder as far as possible
Machine.
Specifically, steering engine is located at the inside of wing-body 20, it can be disposed adjacent with additional wing box 201, such as fixed
On the web 2011 of additional wing box 201, therefore the present embodiment also needs to reinforce the last one wing box of wing tip, with
Convenient for guaranteeing the strength and stiffness during malformation, enable the active force from winglet 10 along wing
Force path is transmitted to airfoil root.Wherein, the last one wing box of wing tip refers to close to last the two of wing tip direction
Region defined by between a rib 202.Based on this, the reinforcement mode of wing box is as follows: on the one hand, wing-body 20 includes multiple
Rib 202, two ribs in multiple rib close to wing tip direction can be set to ribs, it may be assumed that outermost in wing tip direction
Two ribs 202 of side are ribs；On the other hand, rotating mechanism 30 can also include bearing, which is set to the first limit
In hole 100 and it is used to support shaft 301, the outer surface of bearing is in contact with the inner surface of the first limit hole 100, the interior table of bearing
Face is in contact with the outer surface of shaft 301.In this way, the last one wing box of wing tip is just enhanced, so as to
Guarantee the strength and stiffness during malformation.
In this example embodiment, solar panel can also be set on the surface of wing-body 20, the solar-electricity
Pond plate is subjected to illumination to convert light energy into electric energy；Wherein, which can also further pass through charge and discharge control
Device is connected with energy-storage battery, by power storage in energy-storage battery.In this way, which the electrical equipment inside aerofoil system is equal
It can be connected to energy-storage battery by charging-discharging controller, electricity can be provided in this way for aerofoil system.
Based on above structure it is found that in aerofoil system provided by the present embodiment, in order to realize the inclination angle of winglet 10
It is adjustable, it increased in structure compared to existing aerofoil system, such as additional wing box 201 and shaft 301 etc., therefore
Need to guarantee in implementation process wing load path have enough stiffness and strength, and herein under the premise of select lighter machine
The wing, in order to guarantee the economy of aircraft after installation variant winglet.In addition, being applied to wing in structures such as ripple coverings
When, it also should ensure that the smoothness on surface while wrapping up variant winglet, to achieve the effect that reducing friction resistance, from
And guarantee the drag-reduction effect of aircraft.
Those skilled in the art are considering specification and after practicing disclosure disclosed herein, will readily occur to of the invention its
Its embodiment.This application is intended to cover any variations, uses, or adaptations of the invention, these modifications, purposes or
Person's adaptive change follows general principle of the invention and including the undocumented common knowledge in the art of the present invention
Or conventional techniques.The description and examples are only to be considered as illustrative, and true scope and spirit of the invention are by following
Claim is pointed out.
It should be understood that the present invention is not limited to the precise structure already described above and shown in the accompanying drawings, and
And various modifications and changes may be made without departing from the scope thereof.The scope of the present invention is limited only by the attached claims.
Claims (10)
1. a kind of winglet characterized by comprising
Winglet；
Driving device, for controlling the rotation of the winglet；
Pressure-detecting device, positioned at the root surface of the winglet, for detecting the target moment of flexure of the winglet root；
Control device is connected with the driving device and the pressure-detecting device, for being generated based on the target moment of flexure
Signal is controlled, so that the driving device adjusts the inclination angle of the winglet according to the control signal.
2. winglet according to claim 1, which is characterized in that the control device includes signal acquisition unit and flies
Control plate；
The signal acquisition unit is for obtaining the corresponding electrical signal of the target moment of flexure and being sent to the electrical signal
The winged control plate；
The winged control plate is used to generate phase according to the electrical signal of the electrical signal and previous acquisition currently obtained
The control signal answered simultaneously is sent to the driving device.
3. a kind of aerofoil system, which is characterized in that including wing-body and winglet of any of claims 1 or 2；
Wherein, the wing-body includes the additional wing box positioned at tip location, and the winglet rotation is connected to described attached
Add in wing box.
4. aerofoil system according to claim 3, which is characterized in that the aerofoil system further includes rotating mechanism；
The winglet includes girder and the winglet ontology being fixedly connected with the girder, the additional wing box include web and
By the lug extended outside the web, the girder is connected with the lug by the rotating mechanism.
5. aerofoil system according to claim 4, which is characterized in that the rotating mechanism includes shaft and link mechanism,
The girder is equipped with the first limit hole, and the lug is equipped with the second limit hole, and the shaft passes through first limit hole
With second limit hole and the driving device is connected to by the link mechanism.
6. aerofoil system according to claim 5, which is characterized in that it is equipped with groove in first limit hole, described turn
The surface of axis is equipped with protrusion, and the protrusion cooperates with the groove, with the phase for limiting the girder with the shaft
To position.
7. aerofoil system according to claim 5, which is characterized in that the rotating mechanism further includes bearing, the bearing
Outer surface be in contact with the inner surface of first limit hole, the inner surface of the bearing connects with the outer surface of the shaft
Touching.
8. aerofoil system according to claim 3, which is characterized in that the driving device includes steering engine, and the steering engine is solid
It is scheduled on the web of the additional wing box.
9. aerofoil system according to claim 3, which is characterized in that the wing-body further includes multiple ribs, described
Two ribs in multiple ribs close to wing tip direction are ribs.
10. aerofoil system according to claim 3, which is characterized in that be additionally provided with solar battery on the wing-body
Plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811244562.5A CN109178296A (en) | 2018-10-24 | 2018-10-24 | Winglet and aerofoil system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811244562.5A CN109178296A (en) | 2018-10-24 | 2018-10-24 | Winglet and aerofoil system |
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| Publication Number | Publication Date |
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| CN109178296A true CN109178296A (en) | 2019-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811244562.5A Pending CN109178296A (en) | 2018-10-24 | 2018-10-24 | Winglet and aerofoil system |
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| CN (1) | CN109178296A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110525632A (en) * | 2019-10-10 | 2019-12-03 | 中国科学院工程热物理研究所 | The structure combined in the air for aircraft and the aircraft using it |
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| CN209506073U (en) * | 2018-10-24 | 2019-10-18 | 东汉太阳能无人机技术有限公司 | Winglet and aerofoil system |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525632A (en) * | 2019-10-10 | 2019-12-03 | 中国科学院工程热物理研究所 | The structure combined in the air for aircraft and the aircraft using it |
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