CN214451802U - Structure, wing and aircraft for enhancing vortex surfing - Google Patents
Structure, wing and aircraft for enhancing vortex surfing Download PDFInfo
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- CN214451802U CN214451802U CN202120513704.4U CN202120513704U CN214451802U CN 214451802 U CN214451802 U CN 214451802U CN 202120513704 U CN202120513704 U CN 202120513704U CN 214451802 U CN214451802 U CN 214451802U
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- 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
Abstract
The utility model relates to a flight field, especially a structure, wing and aircraft of strengthening vortex surfing. A structure for enhancing vortex surfing comprising a fluidic device, said fluidic device comprising a nozzle orifice, said nozzle orifice being disposed on a wing tip, said fluidic device being capable of opening and closing said nozzle orifice, said nozzle orifice being for ejecting a stream of gas. Adopt strengthen the structure of vortex surfing, through setting up fluidic device's orifice on the wingtip, come the active control through fluidic device and lie in the orifice jet stream on the wingtip, come the vortex ring volume of the preceding machine of active control, and then increase the additional lift to the back machine, reduce back machine oil consumption to this reduces the whole oil consumption of formation aircraft.
Description
Technical Field
The utility model relates to a flight apparatus technical field, especially a structure, wing and aircraft of strengthening vortex surfing.
Background
The wing tip vortex is a great hazard to air traffic, and when an airplane sails in the air, if the airplane encounters the front wing tip vortex, the airplane can be violently overturned or suddenly dropped, and the influence is more serious particularly in the takeoff and landing stage. But the wing tip vortex is reasonably utilized, so that additional lift can be provided for the rear aircraft. Therefore, a great deal of theoretical research is carried out on the basis of the existing vortex surfing technology, and the principle and the technology of vortex surfing are considered to be introduced into the field of civil aviation.
The wing tip vortex is generated because: the pressure of the lower surface of the wing is larger than that of the upper surface of the wing, lift force is generated, wing tip vortex is generated at the wing tip from the lower part to the upper part, and the wing tip vortex is propagated backwards along with an atmospheric wind field to influence the rear-mounted aircraft. As the wing tip vortex is a ring volume, the washing phenomenon of the wake vortex airflow can be observed by horizontally observing the outer side of the wing tip vortex. The air flow washing can provide additional lifting force for the rear machine, so that the oil consumption of the rear machine is reduced, and the voyage is increased. The existing vortex surfing technical scheme is mainly based on the existing wing structure of an airplane, but cannot actively control the vortex ring amount to increase the additional lift force of an after-machine.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a: aiming at the problem that the vortex surfing technical scheme in the prior art is mainly based on the existing wing structure of an airplane and the additional lift force to an after-plane cannot be increased by actively controlling the vortex ring amount, the structure, the wing and the airplane for strengthening the vortex surfing are provided.
In order to realize the purpose, the utility model discloses a technical scheme be:
a structure for enhancing vortex surfing comprising a fluidic device, said fluidic device comprising a nozzle orifice, said nozzle orifice being disposed on a wing tip, said fluidic device being capable of opening and closing said nozzle orifice, said nozzle orifice being for ejecting a stream of gas.
Adopt strengthen the structure of vortex surfing, through setting up fluidic device's orifice on the wingtip, open and close the orifice that is located on the wingtip through fluidic device, can the orifice on the active control wingtip spout and establish the air current or stop spraying the air current. The airplane cruises after taking off and when a plurality of machines are grouped and fly, the vortex ring amount of the wing tip vortex can be increased by controlling the spray holes on the wing tip to spray air flow, the additional lift force provided for the rear machine is increased, and the oil consumption of the rear machine is further reduced; when the airplane flies and approaches, the jet holes on the wing tips are controlled to stop jetting airflow, so that the vortex ring amount of the front wing tip vortex is reduced, the influence of the vortex ring amount of the front wing tip vortex on the takeoff and approach of the rear airplane is reduced, and the flying interval is reduced. Strengthen the structure of vortex surfing, come the active control through fluidic device and lie in the orifice jet stream on the wingtip, come the vortex ring volume of the preceding machine of active control, and then increase the additional lift to the back machine, reduce back machine oil consumption to this reduces the whole oil consumption of formation aircraft.
Preferably, the nozzle hole is formed in the outer side surface of the wing tip.
By adopting the structure, the airflow jetted by the jet holes can directly act on the wing tip vortex, the jetted airflow can effectively increase the vortex flow of the wing tip vortex, provide more additional lift force for the rear aircraft and reduce more oil consumption for the rear aircraft.
Preferably, the nozzle holes are arranged obliquely upward.
The vortex of wing tip upwards flows in the form of ring outside, through setting up the orifice upwards to one side, makes the orifice jet stream have more to the wing tip vortex be forward increment, and then can more effective increase the vortex volume of wing tip vortex, provides more additional lift for the back aircraft, reduces more oil consumptions for the back aircraft.
Preferably, the axis of the nozzle hole is perpendicular to the outer side surface of the wing tip, so that the nozzle hole is conveniently arranged on the outer side surface of the wing tip on the premise of effectively increasing the vortex flow of the vortex of the wing tip, and the influence of the nozzle hole arrangement on the structural stability of the wing tip is reduced.
Further preferably, the nozzle hole is formed in the middle of the outer side face of the wing tip, so that the nozzle hole is further convenient to arrange.
Preferably, the jet device further comprises a pipeline, one end of the pipeline is connected with the jet hole, and the other end of the pipeline is connected with the engine nacelle.
By using the jet device, on the basis of not increasing extra oil consumption for the front aircraft, the front aircraft introduces waste gas generated by a jet engine of the front aircraft through a pipeline, and jets airflow through the jet holes at the wing tip to form circular airflow, increase the vortex flow of the wing tip vortex, provide more additional lift for the rear aircraft, and further reduce the oil consumption of the rear aircraft. And the jet flow perforation device has extremely simple structure, very convenient manufacture and extremely good effect.
It is further preferred that the jet device further comprises a jet regulator connected to the pipe, the nozzle holes or the engine nacelle, the jet regulator being adapted to regulate the velocity of the jet stream of the nozzle holes to 0-50 m/s.
The jet flow regulator is connected with the pipeline, the jet holes or the engine nacelle, so that the jet flow speed of the jet holes can be regulated according to actual conditions, and the jet flow regulator is further used for controlling increment of the jet flow device on the wing tip vortex ring quantity, and is higher in applicability. The speed of the jet flow of the jet hole is 0-50m/s, the normal use of the existing airplane can be met, and when the speed of the jet flow of the jet hole is controlled to be 0, the jet hole stops jetting the jet flow. By adopting the structure, when the airplane cruises after taking off and carries out multi-airplane formation flying, the waste gas of the engine nacelle of the front airplane flows to the spray holes at the wing tips of the front airplane through the pipelines and is sprayed out of the spray holes by the regulation of the jet regulator, the airflow sprayed out of the spray holes increases the vortex flow of the wing tip vortex of the front airplane, and the airflow is spread backwards in an atmospheric wind field to provide additional lift force for the rear airplane and reduce the oil consumption for the rear airplane. When the airplane flies and approaches, the vortex ring quantity of the front wing tip vortex is reduced through the adjustment of the jet regulator, the influence of the vortex ring quantity of the front wing tip vortex on the takeoff and approach of the rear airplane is reduced, and the flying interval is shortened.
Further preferably, the duct includes a communication hole through which the duct communicates with the engine nacelle;
the jet regulator comprises a controller, two guide rails and a baffle, wherein the two guide rails are connected with the engine nacelle, the baffle is connected with the two guide rails in a sliding mode, the controller is used for controlling the baffle to slide along the guide rails, and the baffle is used for shielding the communication hole.
By adopting the jet regulator, the controller controls the baffle to move along the guide rail, so that the baffle covers the communicating hole of the pipeline, and further controls the size of the communicating hole communicated with the engine nacelle to control the speed of jet flow of the jet orifice.
A wing for enhancing vortex surfing, comprising a wing body, wherein the wing body comprises a wing tip, and further comprising a structure for enhancing vortex surfing as described in any one of the above.
Adopt strengthen the wing of vortex surfing, through setting up fluidic device's orifice on the wingtip of wing, under fluidic device's control, the orifice on the wingtip can jet stream, increases the vortex ring volume of wingtip vortex, increases the additional lift that provides for the back aircraft, and then reduces back machine oil consumption.
An aircraft for enhancing vortex surfing comprises the wing for enhancing vortex surfing.
Adopt strengthen the aircraft of vortex surfing, through setting up fluidic device's orifice on the wingtip of the wing of aircraft, under fluidic device's control, orifice on the wingtip can jet stream, increases the vortex ring volume of wingtip vortex, increases the additional lift that provides for the back aircraft, and then reduces back engine oil consumption.
To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that:
1. strengthen structure of vortex surfing, set up on the wingtip of the wing of aircraft through the orifice with fluidic device to come the active control through fluidic device and lie in the orifice jet stream on the wingtip, come the vortex ring volume of active control front plane, and then increase the additional lift to the rear plane, reduce the rear plane oil consumption, reduce the whole oil consumption of formation aircraft with this.
2. Strengthen structure of vortex surfing, through locating the orifice the lateral surface of wingtip, and the axis perpendicular to of orifice the lateral surface of wingtip is convenient for set up the orifice the lateral surface of wingtip, and then be favorable to the air current of orifice injection can direct action in the wingtip vortex, the vortex volume that its air current of injection can more effectual increase wingtip vortex provides more additional lift for the back aircraft, reduces more oil consumptions for the back aircraft.
3. Strengthen structure of vortex surfing, fluidic device includes the pipeline, uses this fluidic device can be on the basis of not increasing extra oil consumption for the front aircraft, the front aircraft quotes the waste gas that its jet engine produced through the pipeline to at the orifice jet stream of wing point department, form the circulation air current, increase the vortex volume of wing point vortex, for the back aircraft provides more additional lift, further reduces the oil consumption of back aircraft. And the jet flow perforation device has extremely simple structure, very convenient manufacture and extremely good effect.
4. Strengthen structure of vortex surfing, the aircraft cruises after taking off, when carrying out multimachine formation flight, through the jet regulator is adjusted, makes the waste gas of the engine nacelle of preceding machine flow the orifice to the wing point department of preceding machine through the pipeline to by the orifice blowout, the vortex flow of the wing point vortex of preceding machine is increased to orifice spun air current, provides additional lift for the back machine at atmosphere wind field backward propagation, reduces the oil consumption for the back machine. When the airplane flies and approaches, the vortex ring quantity of the front wing tip vortex is reduced through the adjustment of the jet regulator, the influence of the vortex ring quantity of the front wing tip vortex on the takeoff and approach of the rear airplane is reduced, and the flying interval is shortened.
5. Strengthen wing of vortex surfing for on the aircraft, through setting up fluidic device's orifice at the aircraft strengthen on the wingtip of wing of vortex surfing, and come the orifice jet stream that active control is located on the wingtip through fluidic device, come the vortex ring volume of active control front plane, and then increase the additional lift to the back plane, reduce back machine oil consumption, reduce the whole oil consumption of formation aircraft with this.
6. Strengthen the aircraft of vortex surfing, through setting up the orifice of fluidic device at the aircraft strengthen on the wingtip of the wing of vortex surfing to come the active control through fluidic device and lie in the orifice jet stream on the wingtip, come the vortex ring volume of active control front engine, and then increase the additional lift to the back engine, reduce back engine oil consumption, reduce the whole oil consumption of formation aircraft with this.
Drawings
Fig. 1 is a first schematic view of the structure for enhancing vortex surfing according to the present invention;
figure 2 is a front view of the structure for enhancing vortex surfing of the present invention;
figure 3 is a top view of the structure for enhancing vortex surfing in accordance with the present invention;
FIG. 4 is a schematic view of the jet regulator configuration;
FIG. 5a is a y-direction velocity contour plot at the tip of a vane where no orifices are provided;
FIG. 5b is a y-direction velocity contour plot at the tip of the airfoil where the orifices are located;
FIG. 6a is a view showing a swirl amount distribution at 10m from the wing tip of a wing without nozzle holes;
FIG. 6b is a graph of the swirl distribution at 10m from the tip of the wing provided with the nozzle holes;
FIG. 7a is a Z-direction velocity profile of airflow at the rear 50m of an airfoil without orifices;
FIG. 7b is a Z-direction velocity profile of airflow at the rear 50m of an airfoil without orifices;
FIG. 8a is a Z-direction velocity profile of airflow at the rear 100m of an airfoil without orifices;
FIG. 8b is a Z-direction velocity profile of the airflow at the rear 100m of the airfoil provided with the nozzle holes;
FIG. 9a is a Z-direction velocity profile of airflow at the rear 200m of an airfoil without orifices;
FIG. 9b is a Z-direction velocity profile of airflow at 200m aft of the airfoil in which the nozzle holes are located.
Icon: 1-a wing body; 11-wingtip; 101-a communication hole; 102-a pipeline; 103-spraying holes; 201-a guide rail; 202-a baffle; 301-controller.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.
Example 1
Referring to fig. 1-9b, the structure for enhancing vortex surfing of the present invention comprises a jet device, wherein the jet device comprises a jet hole 103, the jet hole 103 is disposed on the wing tip 11, the jet device can open and close the jet hole 103, and the jet hole 103 is used for jetting airflow.
The wingtip 11 refers to a winglet at the tip of a wing of an aircraft. The fluidic device may be an existing jet, such as a small jet engine, and can provide jet flow to the nozzle 103 on the wing tip 11. The number and the size of the spray holes 103 are determined according to actual conditions. By adopting the structure for enhancing the vortex surfing, which is described in the embodiment, the jet holes 103 of the jet device are arranged on the wing tip 11, and the jet holes 103 on the wing tip 11 are opened and closed through the jet device, so that the jet holes 103 on the wing tip 11 can be actively controlled to jet air flow or stop jetting air flow. The airplane cruises after taking off and when a plurality of airplanes form a flying, the air flow is sprayed through the spray holes 103 on the wing tip 11, so that the vortex ring amount of the wing tip vortex can be increased, the additional lift force provided for the rear airplane is increased, and the oil consumption of the rear airplane is further reduced; when the airplane flies and approaches, the jet holes 103 on the wing tip 11 are controlled to stop jetting airflow, so that the vortex ring amount of the front wing tip vortex is reduced, the influence of the vortex ring amount of the front wing tip vortex on the takeoff and approach of the rear airplane is reduced, and the flying interval is reduced.
According to the structure for enhancing vortex surfing, the jet device is used for actively controlling the jet holes 103 on the wing tip 11 to jet airflow so as to actively control the vortex ring amount of the front airplane, further increase the additional lift force on the rear airplane and reduce the oil consumption of the rear airplane, so that the overall oil consumption of the formation airplane is reduced. Existing research has shown that use of a reasonable multi-aircraft tight formation vortex surfing technique can reduce fuel consumption by 40% for afteraircraft in long-distance transoceanic flight.
As shown in fig. 2, the injection hole 103 is provided on the outer side surface of the tip 11, and the outer side surface of the tip 11 is the left side surface in fig. 2. By adopting the structure, the airflow jetted by the jet holes 103 can directly act on the wing tip vortex, the jetted airflow can effectively increase the vortex flow of the wing tip vortex, provide more additional lift force for the rear aircraft and reduce more oil consumption for the rear aircraft.
Preferably, the nozzle holes 103 are arranged obliquely upward. The vortex of the wing tip 11 flows upwards in a ring shape on the outer side, and the jet holes 103 are arranged in the inclined direction, so that the jet airflow of the jet holes 103 has more positive increment on the wing tip vortex, the vortex quantity of the wing tip vortex can be effectively increased, more additional lift force is provided for a rear aircraft, and more oil consumption is reduced for the rear aircraft.
As another preferred mode, the axis of the nozzle hole 103 is perpendicular to the outer side surface of the wing tip 11, so that the nozzle hole 103 can be conveniently arranged on the outer side surface of the wing tip 11 on the premise of effectively increasing the vortex flow of the wing tip vortex, and the influence of the arrangement of the nozzle hole 103 on the structural stability of the wing tip 11 is reduced. And the spray hole 103 is arranged in the middle of the outer side surface of the wing tip 11, so that the spray hole 103 is further convenient to arrange.
As shown in fig. 2 to 4, the jet device further includes a pipe 102, one end of the pipe 102 is connected to the nozzle hole 103, and the communication hole 101 at the other end is connected to the engine pod, and a jet regulator, which is connected to the pipe 102, the nozzle hole 103, or the engine pod, and is used for regulating the velocity of the jet flow of the nozzle hole 103 to 0 to 50 m/s.
In this embodiment, in order to facilitate the arrangement of the jet regulator and reduce the influence of the jet regulator on the wing, the jet regulator is connected between the pipe 102 and the engine nacelle, so that the jet regulator can adjust the speed of the jet flow of the jet holes 103 according to actual conditions, and further is used for controlling the increment of the amount of the tip vortex ring of the jet device, and the jet regulator is higher in applicability. The speed of the jet flow of the jet hole 103 is 0-50m/s, which can meet the normal use of the existing airplane, and when the speed of the jet flow of the jet hole 103 is controlled to be 0, the jet flow of the jet hole 103 stops. By using the jet device, on the basis of not increasing extra oil consumption for the front aircraft, the front aircraft introduces waste gas generated by a jet engine of the front aircraft through a pipeline 102, and jets airflow through a jet hole 103 at the wing tip 11 to form circular airflow, so that the vortex quantity of the wing tip vortex is increased, more additional lift force is provided for the rear aircraft, and the oil consumption of the rear aircraft is further reduced. And the jet flow perforation device has extremely simple structure, very convenient manufacture and extremely good effect.
And the airplane cruises after taking off and when a plurality of airplanes are grouped and flying, the waste gas of the engine nacelle of the front airplane flows to the jet holes 103 at the wing tips 11 of the front airplane through the pipeline 102 and is sprayed out from the jet holes 103 by adjusting through the jet regulator, the airflow sprayed out from the jet holes 103 increases the vortex flow of the wing tip vortex of the front airplane, and the airflow is spread backwards in an atmospheric wind field to provide additional lift force for the rear airplane and reduce the oil consumption for the rear airplane. When the airplane flies and approaches, the vortex ring quantity of the front wing tip vortex is reduced through the adjustment of the jet regulator, the influence of the vortex ring quantity of the front wing tip vortex on the takeoff and approach of the rear airplane is reduced, and the flying interval is shortened.
In this embodiment, as shown in fig. 4, the jet regulator includes a controller 301, two guide rails 201, and a baffle 202, the two guide rails 201 connect the engine nacelle, the baffle 202 slidably connects the two guide rails 201, the controller 301 controls the baffle 202 to slide along the guide rails 201, and the baffle 202 shields the communication hole 101. And the controller 301 is controlled by electric signals, such as: the baffle 202 is provided with sliding teeth along the guide rail 201, and the controller 301 comprises a motor and driving teeth, wherein the driving teeth are engaged with the sliding teeth. Under the action of an electric signal, the motor rotates to drive the driving teeth to rotate, the driving teeth act on the sliding teeth to enable the baffle 202 to slide along the rail, the baffle 202 covers the communication hole 101 of the pipeline 102, and then the size of the communication hole 101 communicated with an engine nacelle is controlled to control the speed of airflow sprayed by the spray holes 103.
As shown in fig. 5a-5b, are y-direction velocity contour plots of a cross section at the orifice 103 of the tip 11. The wing tip 11 of fig. 5a is not provided with the nozzle hole 103, and the y-direction speed curves at the wing tip 11 are smoothly connected; the wing tip 11 of figure 5b is provided with an orifice 103 and the jet of the orifice 103 is 20m/s, and another sudden change in velocity can be observed outside the wing tip 11 at the wing tip. And the change of the constant velocity value, 5b is larger than 5a, and the eddy current amount at the same position 5b is larger.
6a-6b, are graphs of the vortex ring volume over a range of 0-10m on the wing near the tip 11. The wing tip 11 of fig. 6a is not provided with the nozzle holes 103, and the wing tip 11 of fig. 6b is provided with the nozzle holes 103, it can be observed that the vortex ring amount of the wing tip vortex in fig. 6b is significantly increased at the core, actually by about 20%, compared to the vortex ring amount of the wing tip vortex in fig. 6 a.
The airflow velocity ejected from orifices 103 in fig. 7a-9b is uniform.
7a-7b, the Z-direction velocity profile at the rear 50m of the airfoil. Since the front aircraft provides additional lift force for the rear aircraft by changing the distribution of the flow field to increase the speed in the Z direction, when the speed distribution in the Z direction at 50m behind the wing is observed, the wing tip 11 of fig. 7a is not provided with the jet holes 103, and the wing tip 11 of fig. 7b is provided with the jet holes 103, it can be observed that the flow field of fig. 7b after using the jet holes 103 to jet airflow is increased by about 60% in the speed peak value in the Z direction of the core region of the vortex core compared with the flow field of fig. 7 a.
As shown in fig. 8a-8b, the Z-direction velocity profile at the rear 100m of the wing. The wing tip 11 of fig. 8a is not provided with the injection holes 103, and the wing tip 11 of fig. 8b is provided with the injection holes 103, and it can be observed that the flow field of fig. 8b after the gas flow is injected by using the injection holes 103 has about 60% increased speed peak value in the Z direction of the vortex core region compared with the flow field of fig. 8 a.
9a-9b, the Z-direction velocity profile at the rear 200m of the airfoil. The wing tip 11 of fig. 9a is not provided with the injection holes 103, and the wing tip 11 of fig. 9b is provided with the injection holes 103, and it can be observed that the flow field of fig. 9b after the gas flow is injected by using the injection holes 103 has about 60% increased speed peak value in the Z direction of the vortex core region compared with the flow field of fig. 9 a.
From the above, by providing the nozzle 103 on the wing tip 11 and injecting the airflow through the nozzle 103, the Z-direction velocity of the core region can be maintained in the subsequent flow field, and good power is provided for the post-aircraft to use the vortex surfing technology.
Example 2
The embodiment provides a wing for enhancing vortex surfing, which comprises a wing body 1, wherein the wing body 1 comprises a wing tip 11, and further comprises the structure for enhancing vortex surfing, which is disclosed in the embodiment 1.
The wing for enhancing the vortex surfing is used for an airplane, the jet holes 103 of the jet device are arranged on the wing tip 11 of the wing for enhancing the vortex surfing of the airplane, and the jet holes 103 on the wing tip 11 are actively controlled to jet airflow through the jet device, so that the vortex ring amount of a front airplane is actively controlled, the additional lift force on a rear airplane is increased, the oil consumption of the rear airplane is reduced, and the overall oil consumption of the formation airplane is reduced.
Example 3
This embodiment provides a vortex surfing enhancing aircraft comprising a vortex surfing enhancing wing according to embodiment 2. In general, the wings for enhancing vortex surfing described in example 2 are provided in pairs on an airplane.
Adopt strengthen the aircraft of vortex surfing, set up on the wingtip 11 of the wing of aircraft through the orifice 103 with fluidic device to come the active control through fluidic device and lie in the orifice 103 jet stream on the wingtip 11, come the vortex ring volume of active control front engine, and then increase the additional lift to the back engine, reduce back engine oil consumption, reduce the whole oil consumption of formation aircraft with this.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A structure for enhancing vortex surfing, comprising a jet device, said jet device comprising a jet orifice (103), said jet orifice (103) being provided on a wing tip (11), said jet device being capable of opening and closing said jet orifice (103), said jet orifice (103) being adapted to emit a gas stream.
2. A structure for enhancing vortex surfing as claimed in claim 1 wherein said nozzle (103) is provided on an outer side of said wing tip (11).
3. A structure for enhancing vortex surfing as claimed in claim 2 wherein said nozzle holes (103) are arranged obliquely upwards.
4. A structure for enhancing vortex surfing as claimed in claim 2 wherein said nozzle (103) has an axis perpendicular to the outer side of said wing tip (11).
5. A structure for enhancing vortex surfing as claimed in claim 4 wherein said nozzle (103) is provided in the middle of the outer side of said wing tip (11).
6. A structure for enhancing vortex surfing as claimed in any one of claims 1-5 wherein said fluidic device further comprises a duct (102), said duct (102) being connected to said nozzle (103) at one end and to an engine nacelle at the other end.
7. A structure to enhance vortex surfing as claimed in claim 6 wherein said jet means further comprises a jet regulator connected to said duct (102), said jet holes (103) or said engine nacelle for regulating the velocity of the jet stream of said jet holes (103) to 0-50 m/s.
8. A structure for enhancing vortex surfing as claimed in claim 7 wherein said duct (102) comprises a communication aperture (101), said duct (102) communicating with said engine nacelle through said communication aperture (101);
the jet regulator comprises a controller (301), two guide rails (201) and a baffle (202), wherein the two guide rails (201) are connected with the engine nacelle, the baffle (202) is connected with the two guide rails (201) in a sliding mode, the controller (301) is used for controlling the baffle (202) to slide along the guide rails (201), and the baffle (202) is used for shielding the communication hole (101).
9. A wing for enhancing vortex surfing, comprising a wing body (1), said wing body (1) comprising a wing tip (11), characterized in that it further comprises a structure for enhancing vortex surfing as claimed in any one of claims 1-8.
10. An aircraft for enhancing vortex surfing comprising the wing for enhancing vortex surfing as claimed in claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120513704.4U CN214451802U (en) | 2021-03-09 | 2021-03-09 | Structure, wing and aircraft for enhancing vortex surfing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120513704.4U CN214451802U (en) | 2021-03-09 | 2021-03-09 | Structure, wing and aircraft for enhancing vortex surfing |
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| Publication Number | Publication Date |
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| CN214451802U true CN214451802U (en) | 2021-10-22 |
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| CN202120513704.4U Active CN214451802U (en) | 2021-03-09 | 2021-03-09 | Structure, wing and aircraft for enhancing vortex surfing |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112849397A (en) * | 2021-03-09 | 2021-05-28 | 中国民用航空飞行学院 | Structure, wing and aircraft for enhancing vortex surfing |
| CN115583349A (en) * | 2022-12-13 | 2023-01-10 | 中国民用航空飞行学院 | Aircraft self-adaptation emergency system based on meteorological big data |
-
2021
- 2021-03-09 CN CN202120513704.4U patent/CN214451802U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112849397A (en) * | 2021-03-09 | 2021-05-28 | 中国民用航空飞行学院 | Structure, wing and aircraft for enhancing vortex surfing |
| CN115583349A (en) * | 2022-12-13 | 2023-01-10 | 中国民用航空飞行学院 | Aircraft self-adaptation emergency system based on meteorological big data |
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