CN108116661A - A kind of active flow control devices and control method for rotor - Google Patents
A kind of active flow control devices and control method for rotor Download PDFInfo
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- CN108116661A CN108116661A CN201711190883.7A CN201711190883A CN108116661A CN 108116661 A CN108116661 A CN 108116661A CN 201711190883 A CN201711190883 A CN 201711190883A CN 108116661 A CN108116661 A CN 108116661A
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- driver
- mounting groove
- rotor
- cover board
- flow control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The embodiment of the invention discloses a kind of active flow control devices and control method for rotor, it is related to rotor craft technical field, performance and security of the rotor craft in flight course can be promoted in the case where not changing the aerodynamic configuration of rotor blade.The present invention includes：The upper surface of rotor blade (1) offers at least 1 bar shaped mounting groove, cover board (2) is mounted in the bar shaped mounting groove, the outer surface for completing the cover board (2) of installation is completely covered the bar shaped mounting groove, and the upper surface of rotor blade (1) is collectively formed with the unslotted part of rotor blade (1)；The inner surface of cover board (2) opens up mounting groove position, and the quantity of mounting groove position is identical with the quantity of driver, in each mounting groove position：Including a boss (21), boss (21) surrounding is higher by and intermediate low-lying formation circular groove (22), and the center of circular groove (22) opens up a gas outlet (23).
Description
Technical field
The present invention relates to rotor craft technical field more particularly to a kind of active flow control devices for rotor and
Control method.
Background technology
Rotor is the critical component of helicopter, and the unsteady vortex field that rotor movement generates is sufficiently complex, preceding sudden
The opposite speed of incoming flow in rotor wing rotation direction is superimposed on flow velocity degree, rotor blade is caused and is operated in serious asymmetrical air ring
In border.Such as：Row (along preceding winged direction of flow) blade is generally operational in the big angle of attack state of low speed after rotor, easily generates air-flow point
From so there is complicated dynamic stall phenomenon so that security of the rotor craft in flight course flies less than fixed-wing
Row device.
Therefore, it is necessary to optimize the dynamic stall performance in rotor movement.In existing scheme mainly using profile optimization and
Method in terms of the Optimum Aerodynamic Designs such as new blade tip passively adapts to certain actual specific rotor Airflow Environment.
But it is merely able to passive to meet some specific rotor Airflow Environments using profile optimization and new blade tip.And
In flight course, rotor Airflow Environment is in dynamic change, right only by profile optimization and the prioritization scheme of new blade tip
It is relatively limited in the promotion of security of the rotary-wing flight in flight course.
The content of the invention
The embodiment of the present invention provides a kind of active flow control devices and control method for rotor, can not change
In the case of the aerodynamic configuration for becoming rotor, security of the rotor craft in flight course is promoted.
In order to achieve the above objectives, the embodiment of the present invention adopts the following technical scheme that：
The active flow control devices are mounted on rotor blade (1), and the active flow control devices include：Cover board
(2) and installation driver group (3) on the cover board；
The upper surface of rotor blade (1) offers at least 1 bar shaped mounting groove, and cover board (2) is mounted on the bar shaped mounting groove
In, the outer surface for completing the cover board (2) of installation is completely covered the bar shaped mounting groove, and with the unslotted portion of rotor blade (1)
Divide the upper surface that rotor blade (1) is collectively formed；
The inner surface of cover board (2) opens up mounting groove position, and the quantity of mounting groove position is identical with the quantity of driver, in each peace
In tankage position：Including a boss (21), boss (21) surrounding is higher by and intermediate low-lying formation circular groove (22), circular groove
(22) center opens up a gas outlet (23)；
Driver group (3) includes at least two drivers, and connection mode in parallel, driver are used between each driver
Each driver in group (3)：The surrounding the raised area of driver front fitting boss (21) so that driver front and circle
Groove (22) forms cavity (24).
Wherein, in each mounting groove position：The gas outlet (23) that the center of circular groove (22) opens up is strip opening；
The gas outlet of all mounting groove positions is located in same horizontal line.
Alternatively, in each mounting groove position：The gas outlet (23) that the center of circular groove (22) opens up includes at least two
Stomata；The stomata of all mounting groove positions is all located in same horizontal line.
Even number mounting hole is offered around boss (21), the even number mounting hole is uniform around the circular groove
Distribution；Where each driver is mounted on each by screw or rivet on the mounting hole of mounting groove position.
Active flow control devices and control method provided in an embodiment of the present invention for rotor, and in particular to Yi Zhongke
To delay the separation of blade surface air-flow and attached, the active control device that lift is enable to recover of air-flow weight can be made.Do not changing
In the case of the external form for becoming blade, controller, cavity and cabling are reasonably arranged inside blade.So as to enhance in boundary layer
The blending of outer air-flow so that flow separation phenomenon is able to effectively weaken and inhibit；The tangential component of synthesizing jet-flow can be direct
The Implantation Energy into low-energy boundary layer air so as to alleviate the influence of adverse pressure gradient, further alleviates the segregation phenomenon of air-flow.Using
The rotor of this active control device is with obvious effects in terms of dynamic stall is improved, on the basis of synthesizing jet-flow control mechanism research
On, the adjusting of parameters when being designed to the synthesizing jet-flow active control device for being suitable for rotor, while considering to control.
The rotor after active control is added compared with original rotor, improves stalling angle, also improves paddle disk pulling force, so as to not change rotation
In the case of the aerodynamic configuration of wing blade, security of the rotor craft in flight course is promoted.
Description of the drawings
It to describe the technical solutions in the embodiments of the present invention more clearly, below will be to needed in the embodiment
Attached drawing is briefly described, it should be apparent that, the accompanying drawings in the following description is only some embodiments of the present invention, for ability
For the those of ordinary skill of domain, without creative efforts, it can also be obtained according to these attached drawings other attached
Figure.
Fig. 1 is the propeller-blade section schematic diagram of the active flow control devices provided in an embodiment of the present invention for rotor；
Fig. 2 a are the top view of (inner surface) inside cover board provided in an embodiment of the present invention；
Fig. 2 b are the close-up schematic view of a mounting groove position in cover board provided in an embodiment of the present invention；
Fig. 3 is the gas outlet schematic diagram of cover board upper surface provided in an embodiment of the present invention；
Fig. 4 is the close-up schematic view of alternatively possible mounting groove position provided in an embodiment of the present invention；
Fig. 5 is the top view of the inside (inner surface) of complete cover board provided in an embodiment of the present invention；
Fig. 6 is the top view of the inside (inner surface) of the cover board after driver provided in an embodiment of the present invention installation；
Fig. 7 is the partial enlarged view of the inside (inner surface) of the cover board after driver provided in an embodiment of the present invention installation；
Fig. 8 is principle schematic provided in an embodiment of the present invention；
Fig. 9 is parameter curve schematic diagram provided in an embodiment of the present invention.
Specific embodiment
For those skilled in the art is made to more fully understand technical scheme, below in conjunction with the accompanying drawings and specific embodiment party
Formula is described in further detail the present invention.Embodiments of the present invention are described in more detail below, the embodiment is shown
Example is shown in the drawings, wherein same or similar label represents same or similar element or with identical or class from beginning to end
Like the element of function.It is exemplary below with reference to the embodiment of attached drawing description, is only used for explaining the present invention, and cannot
It is construed to limitation of the present invention.Those skilled in the art of the present technique are appreciated that unless expressly stated, odd number shape used herein
Formula " one ", "one", " described " and "the" may also comprise plural form.It is to be further understood that the specification of the present invention
The middle wording " comprising " used refers to there are the feature, integer, step, operation, element and/or component, but it is not excluded that
Other one or more features of presence or addition, integer, step, operation, element, component and/or their group.It should be understood that
When we claim element to be " connected " or during " coupled " to another element, it can be directly connected or coupled to other elements or
There may also be intermediary elements.In addition, " connection " used herein or " coupling " can include wireless connection or coupling.Here make
Wording "and/or" includes any cell of one or more associated list items and all combines.The art
Technical staff is appreciated that unless otherwise defined all terms used herein have (including technical term and scientific terminology)
The meaning identical with the general understanding of the those of ordinary skill in fields of the present invention.It is it should also be understood that such as general
Those terms defined in dictionary, which should be understood that, to be had a meaning that is consistent with the meaning in the context of the prior art, and
Unless being defined as here, will not be explained with the meaning of idealization or overly formal.
The embodiment of the present invention provides a kind of active flow control devices for rotor, as shown in Figure 1, including：
The active flow control devices are mounted on rotor blade (1), and the active flow control devices include：Cover board
(2) and installation driver group (3) on the cover board.
The upper surface of rotor blade (1) offers at least 1 bar shaped mounting groove, and cover board (2) is mounted on the bar shaped mounting groove
In, the outer surface for completing the cover board (2) of installation is completely covered the bar shaped mounting groove, and with the unslotted portion of rotor blade (1)
Divide the upper surface that rotor blade (1) is collectively formed.
It should be noted that cover board is strip, cover board is the direction installation along rotor blade, i.e. cover board and rotor
Blade is in approximately parallel state.And a plurality of cover board can be installed on rotor blade, more large-scale especially at some
On rotor craft, the width of rotor blade installs the cover board that 2-5 items are mutually parallel enough, such as：It is shown in Fig. 1, rotor
2 cover boards being mutually parallel are mounted on blade, multiple drivers can be installed on each cover board, so as to improve driver
Group work efficiency.And the quantity for the bar shaped mounting groove that the upper surface of rotor blade offers, and the cover board quantity Matching installed,
And the bar shaped mounting groove at place is completely covered in the outer surface of all cover boards, so as to which the upper surface of rotor blade be collectively formed.
The inner surface of cover board (2) opens up mounting groove position, and the quantity of mounting groove position is identical with the quantity of driver, in each peace
In tankage position：Including a boss (21), boss (21) surrounding is higher by and intermediate low-lying formation circular groove (22), circular groove
(22) center opens up a gas outlet (23).
Driver group (3) includes at least two drivers, and connection mode in parallel, driver are used between each driver
Each driver in group (3)：The surrounding the raised area of driver front fitting boss (21) so that driver front and circle
Groove (22) forms cavity (24).
In the preferred embodiment of the present embodiment, the thickness that driver front forms cavity (24) with circular groove (22) is 3
Millimeter.
Driver is installed by screw to be needed to ensure to seal on the cover board, during installation, can be selected silica gel, be encouraged
Connection mode in parallel is used to ensure that the voltage that each driver is assigned under specified working condition is identical between device.Cover board and
Between blade the mode of screw can be taken to fix.It is bolted between blade and propeller hub, is set in blade in working condition
In the case of setting, by calculating stress at this time, suitable material and the size of bolt are selected.
In the present embodiment, the partial enlarged view of a kind of cover inner surface as shown in Fig. 2 a, Fig. 2 b, in each mounting groove
In position：The gas outlet (23) that the center of circular groove (22) opens up is strip opening (alternatively referred to as strip gap).Such as Fig. 3
Shown, the gas outlet of all mounting groove positions is located in same horizontal line.
Optionally, strip opening can be replaced by the stomata of continuity point, in stomata scheme, the leachy cross section of institute
The sum of product is more than or equal to 70% of the cross-sectional area of strip opening in strip opening scheme.Another lid as shown in Figure 4
The partial enlarged view of plate inner surface, in each mounting groove position：The gas outlet (23) that the center of circular groove (22) opens up includes
At least two stomata.The stomata of all mounting groove positions is all located in same horizontal line.
In the preferred embodiment of the present embodiment, the surface roughness Ra 1.6 of gas outlet (23).Surface operating mode substantially outlet
Discharge surface can't see cutter trade (such as due to burr, notch etc. caused by machining accuracy is not high).Gas outlet (23) ensures one
Fixed finish, to reduce the loss of outlet jet speed.
In the present embodiment, as shown in Figure 5, even number mounting hole, the even number are offered around boss (21)
Mounting hole is uniformly distributed around the circular groove.
Partial enlarged view after loading onto driver back shroud top view and driver as shown in Figure 7 installation as shown in Figure 6,
Where each driver is mounted on each by screw or rivet on the mounting hole of mounting groove position.Wherein, the particular type of driver
Number can be such as the B1S in Fig. 6,7,28-03608-101000.
Specifically, the size of circular groove is consistent with driver specification, slightly larger than the diaphragm of driver, it is slightly less than excitation
Device frontage dimension.Groove section can be changed according to the shape of driver.
After ensureing that installation is stablized, sectional area reduces boss as far as possible, to reduce cover board total weight, and provides driver
Control and the arrangement space of power circuit.
Specifically, driver front, which is bonded the gap formed with boss (21), passes through silica gel sealing.
Further, in order to ensure the air-tightness of device, the mounting means also taken includes：Before making to be screwed,
A circle silica gel first is applied in the surrounding of boss, is tightening screw afterwards；After installing, exported respectively for single driver
Wind speed is tested, and is compared with reference state, it is ensured that driver cavity has sealed.
In the present embodiment, cover board (2) is mounted on rotor blade (1) by swell fixture.
The gap formed after being installed between cover board (2) and rotor blade (1) is covered by gastight material.Such as：In order to protect
The aerodynamic configuration of blade is demonstrate,proved, it, can be by the gap adhesive tape or aviation glue between cover board and blade after installing cover board
Band wraps.
Synthesizing jet-flow technology is considered as one of current most potential rotor active Flow Control technology.After rotor
Row blade works under the big angle of attack, and synthesizing jet-flow can be such that separated air-flow is deflected to blade surface, and air-flow weight may be made attached,
Lift is recovered.Hassan et al. is had studied using the CFD approach of lift line theory combination full potentia1 equation, generalized potentia1 equation in blade for the first time
Leading edge nearby blown using normal direction/and the method for air-breathing carries out the active Flow Control of paddle-vortex interaction.Then, Di ndar, Hassan
Et al. numerical value has been carried out to the hovering rotor for being applied with steady jet control using Eu l er equations and non-structural adaptive mesh
Simulation.Above-mentioned limited research is all numerical simulation result, and analysis of experiments lacks always, main reason is that lacking a kind of be applicable in
In the synthesizing jet-flow active control device of rotor.
The utility model is related to a kind of active control devices of rotor blade, and in particular to one kind can delay blade surface
The separation of air-flow and can make air-flow weight attached, the active control device that lift is enable to recover.
To solve the problems, such as lifting airscrew retreating blade dynamic stall in the prior art, the utility model provides a kind of knot
Structure is small, light-weight, low energy consumption, response is fast into jet stream active control device.In the case where not changing the external form of blade, in paddle
Interlobar part reasonably arranges controller, cavity and cabling.
By CFD approach numerical simulation and experimental study, show that synthesizing jet-flow can be by the disturbance of normal direction by border
The high speed mainstream of layer outer layer is introduced in the boundary layer of low energy, so as to enhance the blending of air-flow inside and outside boundary layer so that air-flow point
It is able to effectively weaken and inhibit from phenomenon；The tangential component of synthesizing jet-flow can directly inject energy into low-energy boundary layer air
Amount so as to alleviate the influence of adverse pressure gradient, further alleviates the segregation phenomenon of air-flow.Existed using the rotor of this active control device
It is with obvious effects to improve dynamic stall aspect, on the basis of the research of synthesizing jet-flow control mechanism, the synthesis for being suitable for rotor is penetrated
The adjusting of parameters when flowing active control device to be designed, while considering to control.Add active control after rotor with
Original rotor is compared, and stalling angle can improve 2-3 °, and paddle disk pulling force improves about 10%.
The present invention also provides a kind of active Flow Control methods for rotor, apply in above-mentioned active flow control devices
On, i.e., include in device：Active flow control devices are mounted on rotor blade (1), the active flow control devices bag
It includes：The driver group (3) of cover board (2) and installation on the cover board；The upper surface of rotor blade (1) offers at least 1 bar shaped installation
Slot, cover board (2) are mounted in the bar shaped mounting groove, and the bar shaped peace is completely covered in the outer surface for completing the cover board (2) of installation
Tankage, and the upper surface of rotor blade (1) is collectively formed with the unslotted part of rotor blade (1)；The inner surface of cover board (2) is opened
If mounting groove position, the quantity of mounting groove position is identical with the quantity of driver, in each mounting groove position：Including a boss
(21), boss (21) surrounding is higher by and intermediate low-lying formation circular groove (22), and the center of circular groove (22) opens up one and goes out
Gas port (23)；Driver group (3) includes at least two drivers, and connection mode in parallel, excitation are used between each driver
Each driver in device group (3)：The surrounding the raised area of driver front fitting boss (21) so that driver front and circle
Connected in star (22) forms cavity (24).
The main of the control method includes：It determines current Airflow Environment, and jet stream is opened according to current Airflow Environment
Array.
Specifically, leading edge of the installation site away from rotor blade (1) of the first to the 5th driver be followed successively by 5%c, 15%c,
30%c, 45%c and 60%c, wherein c are the chord length of rotor blade section aerofoil profile, going out in the mounting groove position where each driver
The width of gas port (23) is 1%c.
Such as：On the rotor of OA213 aerofoil profiles, suction surface 5%c, 15%c, 30%c, 45%c and 60%c away from leading edge
It puts and jet-flow excitor (exit width is 1%c) is set respectively.
In the present embodiment, using OA213 aerofoil profiles as application, by the driving frequency F of synthesizing jet-flow+, momentum of impinging jet coefficient
Cμ, jet stream bias angle thetajetWith jet location etc. as aerofoil profile aerodynamic characteristic is improved in terms of adjusting parameter.Wherein, state choosing is calculated
Free stream Mach number M=0.4 (typical rotor retreating blade working condition) is taken, the Reynolds number based on aerofoil profile chord length is Re=8.5
×106。
First, synthesizing jet-flow excitor of the OA213 aerofoil profiles upper surface away from leading edge 5%c is opened, it is immeasurable to have carried out synthesizing jet-flow
Research of the guiding principle frequency to jet vectoring influential effect.The other parameter setting of synthesizing jet-flow is：Momentum of impinging jet coefficient Cμ=
0.0007, jet stream bias angle thetajet=25 °.As jet stream dimensionless frequency F+When=0.5, the increment of wing section lift coefficient is maximum.With
The increase of jet stream dimensionless frequency, synthesizing jet-flow are decreased obviously the improvement of wing section lift coefficient.Different, synthesis is penetrated
The improvement to profile drag coefficient and torque coefficient is flowed respectively in F+=2.0 and F+Reach optimum efficiency, synthesizing jet-flow when=1.0
Aerofoil profile lift resistance ratio under control is in F+Peak value there are one=2.0.Larger jet stream dimensionless frequency so that jet stream is pneumatic to aerofoil profile
The improvement of force coefficient declines rapidly.It follows that promote a certain aerodynamic force of aerofoil profile emphatically, it may be employed and penetrate accordingly
Stream frequency is driven driver.In general, the most effective immeasurable firm frequency of jet stream is improved to aerofoil profile entirety aerodynamic characteristic
In 0.5≤F+Between≤2.0.
The current Airflow Environment of the basis opens Jet stream array, specifically includes：
At least one driver is opened, the jet stream bias angle theta for the driver openedjetEqual 30 ° of value, momentum of impinging jet coefficient
CμEqual value 0.09, jet stream dimensionless frequency F+Value is more than or equal to 20 and less than or equal to 50；
The working frequency of each driver is 200Hz.
Such as：The operation principle of driver as shown in Figure 8, between driver speed and driving frequency and input voltage
Relation, from jet stream time averaged velocity shown in Fig. 9 with driving voltage and frequency variation curve can be seen that effluxvelocities with excitation
There is certain functional relation between frequency, with the raising of driving frequency, effluxvelocity first increases and then decreases, when excitation frequency
When rate is near 200Hz, driver muzzle velocity reaches maximum, therefore the fixation jet-flow excitor frequency 200Hz set.Its
In, to promote a certain aerodynamic force of aerofoil profile emphatically, corresponding jet stream frequency may be employed, driver is driven.For synthesis
Influence of the jet stream frequency to rotor-blade airfoil dynamic stall control effect is studied.It is separately turned on penetrating at 10%c and 60%c
Driver is flowed, aerofoil profile aerodynamic characteristic is controlled using different jet stream dimensionless frequencies, wherein, jet stream drift angle is taken as
θjet=30 °, momentum of impinging jet coefficient is Cμ=0.09, jet stream dimensionless frequency F+Take 20~50.
Specifically, when lift coefficient increment need to be promoted, first and second and five driver of unlatching；Alternatively, open first and four
Driver；
And when resistance coefficient reduction amount need to be promoted, first and second and four driver of unlatching；Alternatively, open first and five
Driver.
Situation is controlled compared to one-jet driver, the control of synthesizing jet-flow array can become apparent raising aerofoil profile and exist
The aerodynamic characteristic of stall conditions.For example, compared with the aerofoil profile aerodynamic coefficient increment under injection the flow control, (bag of Jet stream array 7
It includes：The combination of jet-flow excitor 1,2 and 5) can by lift coefficient increment improve about 26%, Jet stream array 6 (including：Jet stream swashs
Encourage the combination of device 1,2 and 4) resistance coefficient reduction amount can be improved about 13%.By reasonably setting synthesizing jet-flow array combination,
Control effect of the synthesizing jet-flow to the separation of airfoil surface air-flow and stall can be effectively improved, and then preferably improves the gas of aerofoil profile
Dynamic characteristic.
On the basis of more than numerical simulation result, the different drivers in Jet stream array are set with different jet parameters,
Further study influence of the synthesizing jet-flow array parameter to profile lift and drag characteristic control effect.The group of synthesizing jet-flow array
It is consistent shown in conjunction and table.
The number of 2 Jet stream array of table combination
Table then gives the synthesizing jet-flow parameter of the different jet driver in the present embodiment.As can be seen that compared with control
Situation one processed, the momentum of impinging jet coefficient of driver increase to Cμ=0.007, the jet stream drift angle of each driver is separately positioned on
Between 45 ° to 70 °.
The control parameter (control situation two) of 3 each jet-flow excitor of table
It follows that compared with the state of a control of single jet-flow excitor 1, Jet stream array is to wing section lift coefficient and resistance
The control effect of coefficient is more notable.Compared to injection flow control, Jet stream array 3 (combination of jet-flow excitor 1 and 4) is to lift
The control effect of coefficient improves nearly 100%, and Jet stream array 4 (combination of jet-flow excitor 1 and 5) is to profile drag coefficient
Control effect also improves nearly 26.5%.
In the preferred embodiment of the present embodiment, leading edge of the installation site away from aerofoil profile rotor blade (1) of the 6th driver
10%c, and jet stream drift angle is set as 20 °；5th driver sets jet stream drift angle as 40 °.
When the jet stream drift angle of driver is 20 ° at 10%c, array can improve the maximum lift coefficient of aerofoil profile well,
It is and more preferable when the control effect when flow angle of the driver at 60%c is 40 ° is than 60 °；Jet stream drift angle at 60%c
For 20 ° when, close to leading edge driver jet stream drift angle smaller when (40 °).Then, for the jet stream drift angle of synthesizing jet-flow array
The affecting laws of rotor-blade airfoil dynamic stall are studied in combination.The jet stream dimensionless frequency of driver is F at two+=
30, momentum coefficient is Cμ=0.01.It is drawn by experiment, when the jet stream drift angle of driver is 20 ° at 10%c, array can
Well improve aerofoil profile maximum lift coefficient, and the flow angle of driver 60%c at for 40 ° when control effect ratio
It is more preferable at 60 °；When jet stream drift angle at 60%c is 20 °, during close to the jet stream drift angle smaller of the driver of leading edge
(40 °), the control effect of array is more preferable.On the whole, when the drift angle of jet-flow excitor is smaller, the control effect of array
Fruit becomes apparent.
Active Flow Control method provided in an embodiment of the present invention for rotor, and in particular to one kind can delay blade
The separation of airflow on surface and can make air-flow weight attached, the active control device that lift is enable to recover.Do not changing the outer of blade
In the case of type, controller, cavity and cabling are reasonably arranged inside blade.So as to enhance mixing for air-flow inside and outside boundary layer
It is mixed so that flow separation phenomenon is able to effectively weaken and inhibit；The tangential component of synthesizing jet-flow can be directly to low energy side
Implantation Energy in interlayer so as to alleviate the influence of adverse pressure gradient, further alleviates the segregation phenomenon of air-flow.Using this active control
The rotor of device is with obvious effects in terms of dynamic stall is improved, on the basis of the research of synthesizing jet-flow control mechanism, to being suitable for
The synthesizing jet-flow active control device of rotor is designed, at the same consider control when parameters adjusting.Addition is actively controlled
Rotor after system improves stalling angle compared with original rotor, also improves paddle disk pulling force, so as to not change the pneumatic outer of rotor
In the case of shape, security of the rotor craft in flight course is promoted.
Each embodiment in this specification is described by the way of progressive, identical similar portion between each embodiment
Point just to refer each other, and the highlights of each of the examples are difference from other examples.It is real especially for equipment
For applying example, since it is substantially similar to embodiment of the method, so describing fairly simple, related part is referring to embodiment of the method
Part explanation.The above description is merely a specific embodiment, but protection scope of the present invention is not limited to
This, any one skilled in the art in the technical scope disclosed by the present invention, the variation that can readily occur in or replaces
It changes, should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of claim
Subject to enclosing.
Claims (10)
1. a kind of active flow control devices for rotor, which is characterized in that including：
The active flow control devices are mounted on rotor blade (1), and the active flow control devices include：Cover board (2)
With the driver group (3) of installation on the cover board；
The upper surface of rotor blade (1) offers at least 1 bar shaped mounting groove, and cover board (2) is mounted in the bar shaped mounting groove, complete
The bar shaped mounting groove is completely covered into the outer surface of the cover board (2) of installation, and it is common with the unslotted part of rotor blade (1)
Form the upper surface of rotor blade (1)；
The inner surface of cover board (2) opens up mounting groove position, and the quantity of mounting groove position is identical with the quantity of driver, in each mounting groove
In position：Including a boss (21), boss (21) surrounding is higher by and intermediate low-lying formation circular groove (22), circular groove (22)
Center open up a gas outlet (23)；
Driver group (3) includes at least two drivers, and connection mode in parallel, driver group are used between each driver
(3) each driver in：The surrounding the raised area of driver front fitting boss (21) so that driver front is recessed with circle
Slot (22) forms cavity (24).
2. the active flow control devices according to claim 1 for rotor, which is characterized in that in each mounting groove position
In：The gas outlet (23) that the center of circular groove (22) opens up is strip opening, and the gas outlet of all mounting groove positions is located at
In same horizontal line；
Alternatively, in each mounting groove position：The gas outlet (23) that the center of circular groove (22) opens up includes at least two gas
Hole, and the stomata of all mounting groove positions is all located in same horizontal line.
3. the active flow control devices according to claim 1 for rotor, which is characterized in that driver front and circle
The thickness that connected in star (22) forms cavity (24) is 3 millimeters；
The surface roughness Ra 1.6 of gas outlet (23).
4. the active flow control devices according to claim 1 for rotor, which is characterized in that
Even number mounting hole is offered around boss (21), the even number mounting hole uniformly divides around the circular groove
Cloth；
Where each driver is mounted on each by screw or rivet on the mounting hole of mounting groove position；
Cover board (2) is mounted on rotor blade (1) by swell fixture, and covers cover board (2) and rotor blade by gastight material
(1) gap formed after being installed between；
Driver front is bonded the gap formed with boss (21) and passes through silica gel sealing.
5. the active flow control devices for rotor according to any one in claim 1-5, which is characterized in that swash
It encourages leading edge of the installation site of device away from rotor blade (1) and is followed successively by 5%c, 15%c, 30%c, 45%c and 60%c, wherein c is
The chord length of rotor blade section aerofoil profile, the width of the gas outlet (23) in the mounting groove position where each driver is 1%c.
A kind of 6. active Flow Control method for rotor, which is characterized in that including：
Active flow control devices are mounted on rotor blade (1), and the active flow control devices include：Cover board (2) and peace
The driver group (3) of dress on the cover board；
The upper surface of rotor blade (1) offers at least 1 bar shaped mounting groove, and cover board (2) is mounted in the bar shaped mounting groove, complete
The bar shaped mounting groove is completely covered into the outer surface of the cover board (2) of installation, and it is common with the unslotted part of rotor blade (1)
Form the upper surface of rotor blade (1)；
The inner surface of cover board (2) opens up mounting groove position, and the quantity of mounting groove position is identical with the quantity of driver, in each mounting groove
In position：Including a boss (21), boss (21) surrounding is higher by and intermediate low-lying formation circular groove (22), circular groove (22)
Center open up a gas outlet (23)；
Driver group (3) includes at least two drivers, and connection mode in parallel, driver group are used between each driver
(3) each driver in：The surrounding the raised area of driver front fitting boss (21) so that driver front is recessed with circle
Slot (22) forms cavity (24)；
It determines current Airflow Environment, and Jet stream array is opened according to current Airflow Environment.
7. the active Flow Control method according to claim 6 for rotor, which is characterized in that the first to the 5th excitation
Leading edge of the installation site of device away from rotor blade (1) is followed successively by 5%c, 15%c, 30%c, 45%c and 60%c, and wherein c is rotation
The chord length of wing blade section aerofoil profile, the width of the gas outlet (23) in the mounting groove position where each driver is 1%c.
8. the active Flow Control method according to claim 7 for rotor, which is characterized in that the basis is current
Airflow Environment opens Jet stream array, including：
At least one driver is opened, the jet stream bias angle theta for the driver openedjetEqual 30 ° of value, momentum of impinging jet coefficient CμTake
Value 0.09, jet stream dimensionless frequency F+ values are more than or equal to 20 and less than or equal to 50；
The working frequency of each driver is 200Hz.
9. the active Flow Control method according to claim 8 for rotor, which is characterized in that including：
When lift coefficient increment need to be promoted, first and second and five driver of unlatching；Alternatively, the first and four driver of unlatching；
When resistance coefficient reduction amount need to be promoted, first and second and four driver of unlatching；Alternatively, the first and five driver of unlatching.
10. the active Flow Control method according to claim 9 for rotor, which is characterized in that
Leading edge 10%c of the installation site of 6th driver away from rotor blade (1), and jet stream drift angle is set as 20 °；
5th driver sets jet stream drift angle as 40 °.
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| CN201711190883.7A CN108116661A (en) | 2017-11-24 | 2017-11-24 | A kind of active flow control devices and control method for rotor |
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| CN201711190883.7A CN108116661A (en) | 2017-11-24 | 2017-11-24 | A kind of active flow control devices and control method for rotor |
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| CN114763196A (en) * | 2022-05-17 | 2022-07-19 | 吉林大学 | Small-sized fixed-wing aircraft stall control method based on nonlinear dimension reduction |
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