CN106564585A - High-performance deep-stall wing structure and aircraft - Google Patents
High-performance deep-stall wing structure and aircraft Download PDFInfo
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- CN106564585A CN106564585A CN201610968343.6A CN201610968343A CN106564585A CN 106564585 A CN106564585 A CN 106564585A CN 201610968343 A CN201610968343 A CN 201610968343A CN 106564585 A CN106564585 A CN 106564585A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
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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
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/146—Aerofoil profile comprising leading edges of particular shape
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Plasma Technology (AREA)
Abstract
The invention provides a high-performance deep-stall wing structure and an aircraft, and belongs to the technical field of aeronautical facilities. The high-performance deep-stall wing structure comprises a wing body and a plasma exciter, the plasma exciter is attached to the back edge of the wing body, and the shape of the wing body is a preset waveform. By means of the high-performance deep-stall wing structure and the aircraft, the aerodynamic performance of the aircraft in the full attack angle scope is improved.
Description
Technical field
The present invention relates to air equipment technical field, more particularly to a kind of high-performance depth stalled wing structure and aircraft.
Background technology
In aviation field, the aeroperformance for improving aircraft is always emphasis of concern.Wherein, wing-body is big
Separation and stall under the angle of attack can affect the aeroperformance of aircraft, so as to jeopardize the safety of passenger.
In prior art, in order to solve the problems, such as separation and stall of the wing-body under the big angle of attack, a kind of conceptual design side
Case is to transform the leading edge that original wing-body is smoothed as rough leading edge so that when air-flow flows through wing-body leading edge
When, a whirlpool can be rolled from depression to projection, the whirlpool is elongated and downstream extended by the air-flow on flow direction, while with
Flow direction is axis rotation, the higher turbulent flow of flowing blending degree is gradually formed, so as to will be far from the height on wing-body surface
Speed flowing is involved in the low speeds flow on wing-body surface so that the kinetic energy near the air-flow on wing-body surface increases,
So as to improve the ability that flow separation is resisted in boundary region, to eliminate the phenomenon of wing-body separation and stall.
But, although eliminate wing-body by the rough leading edge of wing-body in prior art dividing under the big angle of attack
From the phenomenon with stall, aeroperformance of the aircraft under the big angle of attack is improve, but wing-body can be caused using which
Maximum lift and middle Low Angle Of Attack under lift reduce, so as to cause aeroperformance of the aircraft under middle Low Angle Of Attack poor.
The content of the invention
The present invention provides a kind of high-performance depth stalled wing structure and aircraft, to improve aircraft in full range of angles of attack
Aeroperformance.
The embodiment of the present invention provides a kind of high-performance depth stalled wing structure, including：
Wing-body and Plasma Actuator, the Plasma Actuator is attached at the wing-body trailing edge,
The wing-body leading edge is shaped as predetermined waveform.
In an embodiment of the present invention, the pre- ripple is shaped as triangular waveform, sinusoidal wave form or cosine waveform.
In an embodiment of the present invention, the Plasma Actuator includes covering electrode, dielectric and bare electrode.
In an embodiment of the present invention, the covering electrode and bare electrode is asymmetric is attached to the dielectric
Both sides, the covering electrode is attached at the wing-body trailing edge, and the first end for covering electrode with it is described
Lower surface at wing-body trailing edge is concordant, and the first end of the bare electrode is put down with the upper surface at the wing-body trailing edge
Together.
In an embodiment of the present invention, the second end of the second end place straight line and the bare electrode for covering electrode
The distance of place straight line is M millimeters, and M is more than or equal to 0 and less than or equal to 1.5.
In an embodiment of the present invention, the equal length of the length and the bare electrode for covering electrode, and be less than
Equal to the length of the wing-body spanwise direction, the length of the dielectric is more than the length for covering electrode；It is described
The width for covering electrode and the bare electrode is respectively less than equal to N microns, and the width of the dielectric is less than or equal to S microns,
The height of the covering electrode and the bare electrode is T times of the wing-body mean aerodynamic chord, and the insulation is situated between
The height of matter more than or equal to it is described covering electrode height, the height of the bare electrode and the covering electrode the second end with
Second end of the bare electrode apart from sum；Wherein, N more than or equal to 0 and less than or equal to 15, S more than or equal to 0 and less than etc.
In 250, T more than or equal to 0.3% and less than or equal to 1%, the height of the plane at the wing-body trailing edge is more than or equal to described
The height of dielectric.
In an embodiment of the present invention, the wave amplitude of the preset shape is P times of the wing-body mean aerodynamic chord,
The wavelength of the preset shape is Q times of the wing-body mean aerodynamic chord, wherein, the P is more than or equal to 0.03 and little
It is more than or equal to 0.11 and less than or equal to 0.43 in 0.11, Q is equal to.
In an embodiment of the present invention, the covering electrode and the bare electrode are metal material.
The embodiment of the present invention also provides a kind of aircraft, including：
High-performance depth stalled wing structure described in body and any of the above-described embodiment.
High-performance depth stalled wing structure provided in an embodiment of the present invention and aircraft, the high-performance depth stalled wing structure
Including：Wing-body and Plasma Actuator, Plasma Actuator is attached at wing-body trailing edge, wing-body leading edge
Be shaped as predetermined waveform.As can be seen here, in embodiments of the present invention, swashed by adhering to plasma at wing-body trailing edge
Encourage device so that under the driving of high voltagehigh frequency alternating current power supply, Plasma Actuator surface can be periodically produced from exposed electricity
Pole is to covering electrode direction, and washes away recirculating zone, Neng Gouti downwards to the wall jet in bare electrode direction from electrode is covered
The lift of wing-body is risen, so as to improve aeroperformance of the aircraft under middle Low Angle Of Attack, additionally, by by before wing-body
The kinetic energy increase for being shaped as predetermined waveform, the air-flow near wing-body surface being caused of edge, so as to improve boundary region
The ability of opposing flow separation, and then improve aeroperformance of the aircraft under the big angle of attack, i.e., carried by the embodiment of the present invention
For high-performance depth stalled wing structure, improve aeroperformance of the aircraft in full range of angles of attack.
Description of the drawings
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description does one and simply introduces, it should be apparent that, drawings in the following description are these
Some bright embodiments, for those of ordinary skill in the art, without having to pay creative labor, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is a kind of structural representation of high-performance depth stalled wing structure provided in an embodiment of the present invention；
Fig. 2 is a kind of top view of wing-body leading edge provided in an embodiment of the present invention；
Fig. 3 is the structural representation of another kind of high-performance depth stalled wing structure provided in an embodiment of the present invention；
Fig. 4 is a kind of structural representation of Plasma Actuator provided in an embodiment of the present invention；
Fig. 5 is that a kind of high voltagehigh frequency sinusoidal ac signal provided in an embodiment of the present invention shows in the electronics flow direction of negative half-cycle
It is intended to；
Fig. 6 is that a kind of high voltagehigh frequency sinusoidal ac signal provided in an embodiment of the present invention shows in the electronics flow direction of positive half period
It is intended to；
Fig. 7 is the graph of a relation of a kind of angle of attack provided in an embodiment of the present invention and lift coefficient；
Fig. 8 is a kind of structural representation of aircraft provided in an embodiment of the present invention.
Specific embodiment
To make purpose, technical scheme and the advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
The a part of embodiment of the present invention, rather than the embodiment of whole.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
Term " first ", " second ", " the 3rd " in description and claims of this specification and above-mentioned accompanying drawing, "
Four " etc. (if present) is the object for distinguishing similar, without for describing specific order or precedence.Should manage
The data that solution is so used can be exchanged in the appropriate case, so as to embodiments of the invention described herein, for example can be with
Order in addition to those for illustrating here or describing is implemented.Additionally, term " comprising " and " having " and they appoint
What deforms, it is intended that cover it is non-exclusive includes, for example, contain the process of series of steps or unit, method, system,
Product or equipment are not necessarily limited to those steps clearly listed or unit, but may include clearly not list or for
Other intrinsic steps of these processes, method, product or equipment or unit.
It should be noted that below these specific embodiments can be combined with each other, for same or analogous concept
Or process may be repeated no more in certain embodiments.
Fig. 1 is a kind of structural representation of high-performance depth stalled wing structure 10 provided in an embodiment of the present invention, is referred to
Shown in Fig. 1, certainly, the embodiment of the present invention is simply illustrated by taking Fig. 1 as an example, but do not represent present invention is limited only by this.Should
High-performance depth stalled wing structure 10 includes：
Wing-body 101 and Plasma Actuator 103, Plasma Actuator 103 is attached to the trailing edge of wing-body 101
Place, wing-body 101 leading edge is shaped as predetermined waveform 102.
Wherein, the big angle of attack typically refers to the angle of attack of the angle more than or equal to 12 degree, and middle Low Angle Of Attack refers to that angle is less than 12 degree
The angle of attack, certainly, specifically can be divided according to actual needs, and the present invention is simply illustrated as a example by 12 degree, but not generation
Table present invention is limited only by this.
Example, the leading edge of wing-body 101 is shaped as predetermined waveform 102, and the predetermined waveform 102 refers to its shape tool
There are wavelength and wave amplitude, shown in Figure 2, Fig. 2 is a kind of vertical view of the leading edge of wing-body 101 provided in an embodiment of the present invention
Scheme, certainly, the embodiment of the present invention is simply illustrated by taking Fig. 2 as an example, but do not represent the embodiment of the present invention to be limited only to this.
In embodiments of the present invention, by adhering to Plasma Actuator 103 at the trailing edge of wing-body 101 so that when
When the Plasma Actuator 103 is opened, under the driving of high voltagehigh frequency alternating current power supply, the surface meeting of Plasma Actuator 103
Periodically produce from bare electrode 1033 to covering electrode 1031 direction, and from covering electrode 1031 to bare electrode 1033
The wall jet in direction washes away downwards recirculating zone, so as to produce a kind of effect of drawn downstream in the upper surface of wing-body 101
Should, this swabbing effect further increases the ability of its opposing flow separation.Importantly, this swabbing effect causes machine
The flow velocity of the air-flow downstream of the upper surface of wing body 101 increases, and so as to improve the circular rector of wing-body 101, and then makes
Obtaining lift increases.Meanwhile, strike speed on wall jet from origin stream in the lower surface of wing-body 101 and slow down, therefore,
The lower surface of wing-body 101 forms a little low speed heavy pressure recirculating zone, increased the pressure of lower surface, it is also possible to lift wing
The lift of body 101, so as to improve aeroperformance of the aircraft under middle Low Angle Of Attack.
Further, in embodiments of the present invention, by the way that the leading edge of wing-body 101 is shaped as into predetermined waveform 102, when
When air-flow flows through 101 leading edge of wing-body, a whirlpool can be rolled to projection from depression, the whirlpool is by the air-flow on flow direction
Elongate and downstream extend, while the whirlpool rotates by axis of flow direction, and stream is gradually formed in development downstream
The higher turbulent flow of dynamic confusion degree.The volume energy-absorbing power of whirlpool and the mixing capacity of turbulent flow can will be far from the surface of wing-body 101
Flow at high speed be involved in the low speeds flow near the surface of wing-body 101 so that near the air-flow on the surface of wing-body 101
Kinetic energy increases, and so as to improve the ability that flow separation is resisted in boundary region, and then it is pneumatic under the big angle of attack to improve aircraft
Performance.
High-performance depth stalled wing structure 10 provided in an embodiment of the present invention, the high-performance depth stalled wing structure 10 is wrapped
Include：Wing-body 101 and Plasma Actuator 103, Plasma Actuator 103 is attached at the trailing edge of wing-body 101, machine
Wing body 101 leading edge is shaped as predetermined waveform 102.As can be seen here, in embodiments of the present invention, by wing-body 101
Adhere to Plasma Actuator 103 at trailing edge so that under the driving of high voltagehigh frequency alternating current power supply, Plasma Actuator 103
Surface can be periodically produced from bare electrode 1033 to covering electrode 1031 direction, and from covering electrode 1031 to exposed electricity
The wall jet in the direction of pole 1033 washes away downwards recirculating zone, can lift the lift of wing-body 101, so as to improve aircraft
Aeroperformance under middle Low Angle Of Attack, additionally, by the way that the leading edge of wing-body 101 is shaped as into predetermined waveform 102, can cause
Kinetic energy near the air-flow on the surface of wing-body 101 increases, so as to improve the ability that flow separation is resisted in boundary region, Jin Erti
High aeroperformance of the aircraft under the big angle of attack, i.e., by high-performance provided in an embodiment of the present invention depth stalled wing structure
10, improve aeroperformance of the aircraft in full range of angles of attack.
Based on the corresponding embodiments of Fig. 1, on the basis of the corresponding embodiments of Fig. 1, further, the embodiment of the present invention is also
Shown in Figure 3 there is provided another kind of high-performance depth stalled wing structure 10, Fig. 3 is provided in an embodiment of the present invention another
The structural representation of high-performance depth stalled wing structure 10 is planted, certainly, the embodiment of the present invention is simply illustrated by taking Fig. 2 as an example,
But not represent present invention is limited only by this.The high-performance depth stalled wing structure 10 also includes：
Optionally, Plasma Actuator 103 includes covering electrode 1031, dielectric 1032 and bare electrode 1033.
Example, shown in Figure 4, Fig. 4 is a kind of knot of Plasma Actuator 103 provided in an embodiment of the present invention
Structure schematic diagram, certainly, the present invention is simply illustrated by taking Fig. 3 as an example, but do not represent present invention is limited only by this.Cover electrode
1031 and the asymmetric both sides for being attached to dielectric 1032 of bare electrode 1033, cover electrode 1031 and be attached to wing-body
At 101 trailing edges, and the first end of covering electrode 1031 is concordant with the lower surface at the trailing edge of wing-body 101, bare electrode
1033 first end is concordant with the upper surface at the trailing edge of wing-body 101.
Wherein, the dielectric 1032 between the bare electrode 1033 of Plasma Actuator 103 and covering electrode 1031
Play a part of to stop high voltagehigh frequency electric discharge.Bare electrode 1033 and covering electrode 1031 connect respectively the two of high voltagehigh frequency power supply
Individual outfan, covers electrode 1031 as reference potential.
Optionally, cover the second end place straight line and the bare electrode 1033 of electrode 1031 the second end place straight line away from
From for M millimeters, M is more than or equal to 0 and less than or equal to 1.5.
Wherein, the second end place straight line of electrode 1031 and the distance of the second end place straight line of bare electrode 1033 are covered
Refer to the vertical dimension between the second end place straight line and the second end place straight line of bare electrode 1033 that cover electrode 1031.
Preferably, in embodiments of the present invention, the second end institute of the second end place straight line with bare electrode 1033 of electrode 1031 is covered
It is 0 in the distance value M of straight line, that is, the one end for covering electrode 1031 overlaps with one end of bare electrode 1033, to improve plasma
The discharge performance of body activator 103.
Further, for Plasma Actuator 103, it covers the length and bare electrode 1033 of electrode 1031
Equal length, and less than or equal to the length of the spanwise direction of wing-body 101, the length of dielectric 1032 is more than covering electrode
1031 length, to be completely covered by covering electrode 1031；The width for covering electrode 1031 and bare electrode 1033 is respectively less than etc.
In N microns, the width of dielectric 1032 is less than or equal to S microns, and the height for covering electrode 1031 and bare electrode 1033 is
T times of the mean aerodynamic chord of wing-body 101, the height of dielectric 1032 is more than or equal to covering the height of electrode 1031, naked
The height of dew electrode 1033 and the second end of covering electrode 1031 are with the second end of bare electrode 1033 apart from sum；Wherein, N
It is more than or equal to 0.3% and less than or equal to 1% more than or equal to 0 and less than or equal to 250, T more than or equal to 0 and less than or equal to 15, S, machine
The height of the plane at the trailing edge of wing body 101 is more than or equal to bare electrode 1033, covering electrode 1031 and pole gap height
With.
Example, in embodiments of the present invention, for convenience the installation of Plasma Actuator 103 with use, generally need
Sharp process should be cut to the trailing edge of wing-body 101.Will circular or sharp trailing edge be modified to plane, and revised plane
Bare electrode 1033, covering electrode 1031 and pole gap height sum highly not less than Plasma Actuator 103, so as to
The Plasma Actuator 103 is allowd preferably to be attached to the trailing edge of wing-body 101.
In addition, it is generally the case that the height of dielectric 1032 is more than or equal to height, the bare electrode for covering electrode 1031
1033 height and cover the second end of electrode 1031 and the second end of bare electrode 1033 apart from sum, and dielectric
1032 are at least covering 1 millimeter to 2 millimeters of the outboard end of electrode 1031 extension, to avoid bare electrode 1033 and cover electrode 1031
Between by the end face of dielectric 1032 discharge, so as to improve the high voltage performance of Plasma Actuator 103.
Further, by the way that the thickness of bare electrode 1033 and covering electrode 1031 is set to less than 15 microns, absolutely
The thickness of edge medium 1032 is less than 250 microns, so Plasma Actuator 103 can be attached directly to wing-body
At 101 trailing edges, due to Plasma Actuator 103 thickness relative to local flow boundary layer thickness very little so that this etc.
What gas ions activator 103 was subject to can ignore come raw disturbance of originally miscarrying.In embodiments of the present invention, by by plasma
Body is attached directly at the trailing edge of wing-body 101, rather than with the integrated machine-shaping of wing-body 101, the letter of its implementation
Folk prescription just, with higher feasibility.Further, since the action effect of Plasma Actuator 103 can pass through regulation power supply
Signal realization, therefore, pilot can adjust control effect, the flight optimal so as to realize aircraft according to practical flight demand
State.
In actual application, illustrate so that the waveform of high voltage high frequency voltage is as sine wave-shaped signal as an example.For
Power supply signal requires its voltage peak in 2kV～24kV, and frequency is in 1kHz～15kHz.The wherein convection current of Plasma Actuator 103
Dynamic control effect is raised with the increase of voltage and frequency, meanwhile, it is the requirement for considering airborne equipment, equipment should not be operated in
Under too high energy consumption, therefore the voltage and frequency of power supply signal can not be too high.Example, shown in Figure 5, Fig. 5 is this
A kind of high voltagehigh frequency sinusoidal ac signal that bright embodiment is provided flows to schematic diagram in the electronics of negative half-cycle.When high voltagehigh frequency just
When string AC signal is in negative half-cycle, that is, bare electrode 1033 is relative when covering electrode 1031 and being in low potential, and high pressure is high
Frequency effect causes the air ionization near bare electrode 1033 to form electronics, and under electric field force effect, electronics is in dielectric
1032 apparent motions, form by bare electrode 1033 to the electron stream for covering the direction of electrode 1031, and course of discharge is from bare electrode
1033 point to covering electrode 1031 direction.Due to the barrier effect of dielectric 1032, small part electronics can be situated between through insulation
The top layer of matter 1032, but most of electronics cannot pass through dielectric 1032 and arrive at covering electrode 1031, therefore, most of electronics
Aggregation rests on the surface of dielectric 1032 for covering the outside of electrode 1031.The discharge process is continued for, high voltagehigh frequency electric discharge
The electronics of generation endlessly moves to the dielectric 1032 for covering the surface of electrode 1031 from bare electrode 1033, until naked
Till the potential of dew electrode 1033 is higher than the potential for covering electrode 1031.While electron motion, due to air viscosity effect,
Air around driving is moved together, is covered so as to produce a kind of pointing to from bare electrode 1033 for the surface of dielectric 1032
The wall jet in the direction of electrode 1031.
In the same manner, shown in Figure 6, Fig. 6 exists for a kind of high voltagehigh frequency sinusoidal ac signal provided in an embodiment of the present invention
The electronics of positive half period flows to schematic diagram.When high voltagehigh frequency AC signal is in positive half period, electrode 1031 is covered relatively naked
When dew electrode 1033 is in low potential, high voltagehigh frequency is acted on and causes the air ionization covered near electrode 1031 to form electronics.By
In the barrier effect of dielectric 1032, the electronics produced by covering electrode 1031 itself can not through dielectric 1032 to
Up to bare electrode 1033, but be collected on covering the electronics near the dielectric 1032 in the outside of electrode 1031, then can be in electricity
Field force moves to bare electrode 1033 under driving, formed by covering electrode 1031 to the electron stream in the direction of bare electrode 1033, puts
The direction of bare electrode 1033 is pointed to from electrode 1031 is covered in electric direction.The discharge process is continued for, and is gathered in covering electrode
The electronics on 1031 surfaces endlessly flows to the direction of bare electrode 1033 from covering electrode 1031 direction, until covering electrode
Till 1031 potential is higher than the potential of bare electrode 1033.While electron motion, due to air viscosity effect, week is driven
The air for enclosing is moved together, so as to can produce a kind of surface of dielectric 1032 from cover electrode 1031 point to bare electrode
The wall jet in 1033 directions.
After above-mentioned positive half period and negative half-cycle form wall jet, the high speed wall jet washes away downwards backflow
Area, so that the tail end recirculating zone of script low speed heavy pressure becomes high velocity, low pressure area, so as to produce in the upper surface of wing-body 101
A kind of effect of drawn downstream of life, this swabbing action further increases the ability of its opposing flow separation.It is prior
It is that this swabbing effect causes the flow velocity of the air-flow downstream of the upper surface of wing-body 101 to increase, so as to improve wing
The circular rector of body 101, and then lift is increased.Meanwhile, strike wall from origin stream in the lower surface of wing-body 101 and penetrate
Speed slows down on stream, therefore, a little low speed heavy pressure recirculating zone is formed in the lower surface of wing-body 101, increased lower surface
Pressure, it is also possible to the lift of wing-body 101 is lifted, so as to improve aeroperformance of the aircraft under middle Low Angle Of Attack.
Optionally, cover electrode 1031 and bare electrode 1033 is metal material.
Example, in embodiments of the present invention, bare electrode 1033 and covering electrode 1031 are using with electric conductivity
Metal material make, such as Copper Foil etc..Additionally, dielectric 1032 is sub- using epoxy resin, quartz glass, ceramics, polyamides
Amine thin film, mylar etc. have high impedance, the insulant of good insulation preformance.Particularly, Plasma Actuator 103 is exhausted
Edge medium 1032 can adopt flexible mylar, make and form flexible Plasma Actuator 103, such that it is able to attach
In the surface for having camber.
Optionally, pre- ripple is shaped as triangular waveform, sinusoidal wave form or cosine waveform.Further, the wave amplitude of preset shape
For P times of the mean aerodynamic chord of wing-body 101, the wavelength of preset shape is Q times of the mean aerodynamic chord of wing-body 101,
Wherein, P is more than or equal to 0.11 and less than or equal to 0.43 more than or equal to 0.03 and less than or equal to 0.11, Q.
Wherein, the distance between crest and trough of the sine wave of wave amplitude representative definition leading edge shape, and wavelengths representative
The distance between the distance between sine wave crest and crest of definition leading edge shape (or trough and trough).If wave amplitude is excessive,
The significant loss of lift of comparison and resistance can be then caused to increase；If wave amplitude is too small, can weaken weaken under the big angle of attack separation and disappear
Except stall ability.If wavelength is excessive, can damage under its big angle of attack and weaken the ability for separating and eliminating stall.
In embodiments of the present invention, by by the leading edge of wing-body 101 be shaped to triangular waveform, sinusoidal wave form or
Cosine waveform.When air-flow flows through 101 leading edge of wing-body, a whirlpool can be rolled to projection from depression, the whirlpool is flowed
Air-flow on direction is elongated and downstream extended, while the whirlpool rotates by axis of flow direction, and in development downstream
In gradually form the flowing higher turbulent flow of confusion degree.The volume energy-absorbing power of whirlpool and the mixing capacity of turbulent flow can will be far from wing
The flow at high speed on the surface of body 101 is involved in the low speeds flow on the surface of wing-body 101 so that near wing-body 101
The kinetic energy of the air-flow on surface increases, and so as to improve boundary region the ability of flow separation is resisted, and then improves aircraft big
Aeroperformance under the angle of attack.
In application process, using Plasma Actuator 103 lift coefficient of wing-body 101 can be increased, so as to
Improve the lift of wing-body 101.Shown in Figure 7, Fig. 7 is a kind of angle of attack provided in an embodiment of the present invention and lift coefficient
Graph of a relation.Wherein, abscissa represents angle of attack, and vertical coordinate represents lift coefficient CL.Example, the Plasma Actuator 103
Frequency be 3kHz, voltage peak-to-peak value be 4kV.Can be seen by Fig. 7, compared to the situation that Plasma Actuator 103 is closed
(solid black line), open Plasma Actuator 103 after (white hollow line), under middle low angle of attack, lift coefficient curve to
Upper translation, the overall lift of wing-body 101 is improved.And under the big angle of attack, although the lift-rising ability of middle low angle of attack
Substantially weaken, but Plasma Actuator 103 also can further improve the lift-rising ability under the big angle of attack.Therefore, in the present invention
It is attached at the trailing edge of wing-body 101 by by the leading edge of wing-body 101 while being shaped as predetermined waveform 102 in embodiment
Plasma Actuator 103, lift coefficient of the wing-body 101 in full range of angles of attack can be improved, it is winged so as to improve
Aeroperformance of the row device in full range of angles of attack.
Fig. 8 is a kind of structural representation of aircraft 80 provided in an embodiment of the present invention, example, and the aircraft 80 can be with
For aircraft, shown in Figure 8, the aircraft 80 can include：
High-performance depth stalled wing structure 10 shown in body 801 and any of the above-described embodiment.
Aircraft 80 shown in the embodiment of the present invention, can perform the technical scheme shown in any of the above-described embodiment, in fact
Existing principle and beneficial effect are similar, are no longer repeated herein.
Finally it should be noted that：Various embodiments above only to illustrate technical scheme, rather than a limitation；To the greatest extent
Pipe has been described in detail with reference to foregoing embodiments to the present invention, it will be understood by those within the art that：Its according to
So the technical scheme described in foregoing embodiments can be modified, either which part or all technical characteristic are entered
Row equivalent；And these modifications or replacement, do not make the essence disengaging various embodiments of the present invention technology of appropriate technical solution
The scope of scheme.
Claims (9)
1. a kind of high-performance depth stalled wing structure, it is characterised in that include：
Wing-body and Plasma Actuator, the Plasma Actuator is attached at the wing-body trailing edge, described
Wing-body leading edge is shaped as predetermined waveform.
2. structure according to claim 1, it is characterised in that
The pre- ripple is shaped as triangular waveform, sinusoidal wave form or cosine waveform.
3. structure according to claim 1, it is characterised in that
The Plasma Actuator includes covering electrode, dielectric and bare electrode.
4. structure according to claim 3, it is characterised in that
The covering electrode and the asymmetric both sides for being attached to the dielectric of the bare electrode, the covering electrode attachment
At the wing-body trailing edge, and the first end for covering electrode is put down with the lower surface at the wing-body trailing edge
Together, the first end of the bare electrode is concordant with the upper surface at the wing-body trailing edge.
5. structure according to claim 4, it is characterised in that
The distance of the second end place straight line and the second end place straight line of the bare electrode for covering electrode is M millimeters, M
More than or equal to 0 and less than or equal to 1.5.
6. structure according to claim 5, it is characterised in that
The equal length of the length and the bare electrode for covering electrode, and less than or equal to the wing-body spanwise direction
Length, the length of the length of the dielectric more than the covering electrode；Electrode and the bare electrode of covering
Width is respectively less than equal to N microns, and the width of the dielectric is less than or equal to S microns, the covering electrode and the exposed electricity
The height of pole is T times of the wing-body mean aerodynamic chord, and the height of the dielectric is more than or equal to the covering
Second end of the height of electrode, the height of the bare electrode and the covering electrode and the second end of the bare electrode away from
From sum；Wherein, N is more than or equal to 0 and more than or equal to 0 and more than or equal to 0.3% and little less than or equal to 250, T less than or equal to 15, S
In equal to 1%, the height of the plane at the wing-body trailing edge is more than or equal to the height of the dielectric.
7. the structure according to any one of claim 1-6, it is characterised in that
The wave amplitude of the preset shape is P times of the wing-body mean aerodynamic chord, and the wavelength of the preset shape is institute
State wing-body mean aerodynamic chord Q times, wherein, the P is more than or equal to more than or equal to 0.03 and less than or equal to 0.11, Q
0.11 and less than or equal to 0.43.
8. structure according to claim 7, it is characterised in that
The covering electrode and the bare electrode are metal material.
9. a kind of aircraft, it is characterised in that include：
High-performance depth stalled wing structure described in body and any one of the claims 1-8.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107037824A (en) * | 2017-06-09 | 2017-08-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of all-wing aircraft model transverse control device and control method |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4208751A1 (en) * | 1992-02-27 | 1993-11-11 | Fritz Karl Hausser | Reducing resistance to aerofoil or hydrofoil passing through medium e.g. air or water - uses array of teeth formed on leading and/or trailing edge of aerofoil or hydrofoil section |
| US20060060721A1 (en) * | 2004-03-30 | 2006-03-23 | Phillip Watts | Scalloped leading edge advancements |
| CN101332871A (en) * | 2007-05-25 | 2008-12-31 | 波音公司 | Airfoil trailing edge plasma flow control apparatus and method |
| CN102756803A (en) * | 2012-07-04 | 2012-10-31 | 北京航空航天大学 | Pneumatic gurney flap based on plasma wall surface jet flow |
| CN102887223A (en) * | 2012-09-24 | 2013-01-23 | 北京航空航天大学 | Method of controlling plasma circular rector for wing with sharp trailing edge |
| CN103057691A (en) * | 2011-09-06 | 2013-04-24 | 空中客车西班牙运营有限责任公司 | Aircraft tail surface with leading edge section of undulated shape |
| CN105307931A (en) * | 2013-01-25 | 2016-02-03 | 彼得·艾瑞兰德 | Energy efficiency improvements for turbomachinery |
-
2016
- 2016-10-26 CN CN201610968343.6A patent/CN106564585B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4208751A1 (en) * | 1992-02-27 | 1993-11-11 | Fritz Karl Hausser | Reducing resistance to aerofoil or hydrofoil passing through medium e.g. air or water - uses array of teeth formed on leading and/or trailing edge of aerofoil or hydrofoil section |
| US20060060721A1 (en) * | 2004-03-30 | 2006-03-23 | Phillip Watts | Scalloped leading edge advancements |
| CN101332871A (en) * | 2007-05-25 | 2008-12-31 | 波音公司 | Airfoil trailing edge plasma flow control apparatus and method |
| CN103057691A (en) * | 2011-09-06 | 2013-04-24 | 空中客车西班牙运营有限责任公司 | Aircraft tail surface with leading edge section of undulated shape |
| CN102756803A (en) * | 2012-07-04 | 2012-10-31 | 北京航空航天大学 | Pneumatic gurney flap based on plasma wall surface jet flow |
| CN102887223A (en) * | 2012-09-24 | 2013-01-23 | 北京航空航天大学 | Method of controlling plasma circular rector for wing with sharp trailing edge |
| CN105307931A (en) * | 2013-01-25 | 2016-02-03 | 彼得·艾瑞兰德 | Energy efficiency improvements for turbomachinery |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107037824A (en) * | 2017-06-09 | 2017-08-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of all-wing aircraft model transverse control device and control method |
| CN107037824B (en) * | 2017-06-09 | 2023-10-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Transverse control device and control method for flying wing model |
| CN107914865A (en) * | 2017-11-27 | 2018-04-17 | 西北工业大学 | The virtual dynamic bionic apparatus and method of plasma for the leading edge of a wing |
| CN107914865B (en) * | 2017-11-27 | 2020-09-25 | 西北工业大学 | Plasma virtual dynamic bionic device and method for wing leading edge |
| CN109050876A (en) * | 2018-07-13 | 2018-12-21 | 北京航空航天大学 | A kind of new micro unmanned plane using bionical wing |
| CN109305326A (en) * | 2018-09-21 | 2019-02-05 | 北京航空航天大学 | Wing and aircraft |
| CN112373673A (en) * | 2020-09-25 | 2021-02-19 | 哈尔滨工业大学 | Leading edge double-convex structure for improving performance of double-convex wing section and flow control method thereof |
| CN112373673B (en) * | 2020-09-25 | 2023-09-26 | 哈尔滨工业大学 | Flow control method of leading edge biconvex structure for improving performance of biconvex wing section |
| CN112298549A (en) * | 2020-10-30 | 2021-02-02 | 北京航空航天大学 | Tilt rotor with bionic wavy leading edge and tilt rotor aircraft |
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