CN112849397A - Structure, wing and aircraft for enhancing vortex surfing - Google Patents
Structure, wing and aircraft for enhancing vortex surfing Download PDFInfo
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- CN112849397A CN112849397A CN202110271032.5A CN202110271032A CN112849397A CN 112849397 A CN112849397 A CN 112849397A CN 202110271032 A CN202110271032 A CN 202110271032A CN 112849397 A CN112849397 A CN 112849397A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
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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
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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
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Abstract
本发明涉及飞行领域，特别是一种加强涡流冲浪的结构、机翼及飞机。一种加强涡流冲浪的结构，包括射流装置，所述射流装置包括喷孔，所述喷孔设置在翼尖上，所述射流装置能够启闭所述喷孔，所述喷孔用于喷射气流。采用本发明所述加强涡流冲浪的结构，通过将射流装置的喷孔设置在翼尖上，通过射流装置来主动控制位于翼尖上的喷孔喷射气流，来主动控制前机的涡环量，进而增加对后机的附加升力，减少后机油耗，以此来减少编队飞机的整体油耗。
The invention relates to the field of flight, in particular to a structure, a wing and an aircraft for enhancing vortex surfing. A structure for enhancing vortex surfing, comprising a jet device, the jet device includes a jet hole, the jet hole is arranged on the wing tip, the jet device can open and close the jet hole, and the jet hole is used for jetting airflow . By adopting the structure for enhancing vortex surfing of the present invention, the nozzle holes of the jet device are arranged on the wingtip, and the jet stream device is used to actively control the jet flow of the nozzle holes located on the wingtip, so as to actively control the vortex ring volume of the front aircraft, In turn, the additional lift to the rear aircraft is increased, and the rear fuel consumption is reduced, thereby reducing the overall fuel consumption of the formation aircraft.
Description
Technical Field
The invention relates to the technical field of flight instruments, in particular to a structure, a wing and an airplane for 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.
Disclosure of Invention
The invention aims to: 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 achieve the purpose, the invention adopts the technical scheme that:
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.
By adopting the structure for enhancing the vortex surfing, the jet holes of the jet device are arranged on the wing tip, and the jet holes on the wing tip are opened and closed through the jet device, so that the jet holes on the wing tip can be actively controlled to jet airflow or stop jetting the airflow. 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. According to the structure for enhancing vortex surfing, the jet device is used for actively controlling the jet holes on the wing tip 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.
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.
By adopting the wing for enhancing vortex surfing, the jet holes of the jet device are arranged on the wing tip of the wing, and the jet holes on the wing tip can jet airflow under the control of the jet device, so that the vortex ring amount of the vortex of the wing tip is increased, the additional lift force provided for a rear engine is increased, and further the oil consumption of the rear engine is reduced.
An aircraft for enhancing vortex surfing comprises the wing for enhancing vortex surfing.
By adopting the aircraft for enhancing the vortex surfing, the jet holes of the jet device are arranged on the wing tips of the wings of the aircraft, and the jet holes on the wing tips can jet airflow under the control of the jet device, so that the vortex ring amount of the vortex of the wing tips is increased, the additional lift force provided for the rear aircraft is increased, and further the oil consumption of the rear aircraft is reduced.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. according to the structure for enhancing vortex surfing, the jet holes of the jet device are arranged on the wing tip of the wing of the airplane, and the jet holes on the wing tip are actively controlled to jet airflow through the jet device, so that the vortex ring amount of the front airplane is actively controlled, the additional lift force on the rear airplane is increased, the oil consumption of the rear airplane is reduced, and the overall oil consumption of the formation airplane is reduced.
2. According to the structure for enhancing vortex surfing, the spray holes are formed in the outer side face of the wing tip, the axis of each spray hole is perpendicular to the outer side face of the wing tip, so that the spray holes are conveniently formed in the outer side face of the wing tip, airflow sprayed by the spray holes can directly act on the wing tip vortex, the vortex amount of the wing tip vortex can be effectively increased by the airflow sprayed by the spray holes, more additional lift force is provided for a rear aircraft, and more oil consumption is reduced for the rear aircraft.
3. The jet device comprises a pipeline, and the jet device can introduce waste gas generated by a jet engine of the front aircraft through the pipeline on the basis of not increasing extra oil consumption for the front aircraft, and jet airflow from the nozzle at the wing tip to form annular airflow, so that the vortex amount 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.
4. According to the structure for enhancing vortex surfing, when an airplane cruises after taking off and carries out multi-airplane formation flying, waste gas of an engine nacelle of a front airplane flows to the spray holes at the wing tips of the front airplane through the pipeline and is sprayed out of the spray holes by the regulation of the jet regulator, airflow sprayed out of the spray holes increases the vortex flow of the wing tip vortexes of the front airplane, and is transmitted backwards in an atmospheric wind field to provide additional lift force for a rear airplane so as to reduce 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.
5. The wing for enhancing vortex surfing is used on an airplane, the jet holes of the jet device are arranged on the wing tip of the wing for enhancing vortex surfing of the airplane, and the jet holes on the wing tip are actively controlled by the jet device to jet airflow so as to actively control the vortex ring amount of a front airplane, further increase the additional lift force on a rear airplane and reduce the oil consumption of the rear airplane, thereby reducing the overall oil consumption of the formation airplane.
6. According to the aircraft for enhancing vortex surfing, the jet holes of the jet device are arranged on the wing tips of the wings of the aircraft for enhancing vortex surfing, and the jet holes on the wing tips are actively controlled by the jet device to jet airflow so as to actively control the vortex ring amount of the front aircraft, further increase the additional lift force on the rear aircraft and reduce the oil consumption of the rear aircraft, so that the overall oil consumption of the formation aircraft is reduced.
Drawings
FIG. 1 is a first schematic view of a structure for enhancing vortex surfing in accordance with the present invention;
figure 2 is a front view of a structure for enhancing vortex surfing in accordance with the present invention;
figure 3 is a top view of a 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 below with reference to the accompanying drawings.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention 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 arranged on a 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 fluidic device further comprises a pipe 102 and a jet regulator, wherein one end of the pipe 102 is connected with the jet hole 103, and the other end of the pipe is connected with the connecting hole 101, the jet regulator is connected with the pipe 102, the jet hole 103 or the engine nacelle, and the jet regulator is used for regulating the speed of the jet flow of the jet hole 103 to be 0-50 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.
The jet holes 103 of the jet device are arranged on the wing tip 11 of the wing of the airplane, and 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, thereby reducing the overall oil consumption of the formation airplane.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle 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 said jet stream ejected from 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.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110271032.5A CN112849397B (en) | 2021-03-09 | 2021-03-09 | Structure, wing and aircraft for strengthening vortex surfing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110271032.5A CN112849397B (en) | 2021-03-09 | 2021-03-09 | Structure, wing and aircraft for strengthening vortex surfing |
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| CN112849397A true CN112849397A (en) | 2021-05-28 |
| CN112849397B CN112849397B (en) | 2024-07-12 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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