CN115716528A - Bionic leading edge wing implementation device and bionic leading edge structure establishment method - Google Patents
Bionic leading edge wing implementation device and bionic leading edge structure establishment method Download PDFInfo
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- CN115716528A CN115716528A CN202310023861.0A CN202310023861A CN115716528A CN 115716528 A CN115716528 A CN 115716528A CN 202310023861 A CN202310023861 A CN 202310023861A CN 115716528 A CN115716528 A CN 115716528A
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Abstract
The invention discloses a bionic leading edge wing implementation device and a bionic leading edge structure building method, and belongs to the technical field of bionic flow control. The device comprises a controller, a high-voltage power supply, a voltage regulator, a function generator and a starting vortex generator set; the high-voltage power supply provides driving voltage for starting the vortex generator set through a gate circuit; the voltage regulator is used for regulating the amplitude and the frequency of the output voltage of the high-voltage power supply; the function generator can output a driving signal to control the unsteady work of the high-voltage power supply; the starting vortex generator set comprises a plurality of starting vortex generators, and the starting vortex generators are buried in the wing-shaped structure and are uniformly arranged on the front edge of the wing-shaped structure in the spanwise direction; the controller is electrically connected with the gate circuit, the function generator and the voltage regulator. The invention utilizes the plasma excitation principle to continuously induce and generate the starting vortex, and the starting vortex can form a pneumatic bionic wavy leading edge structure on the leading edge of the wing-shaped structure to play a role in inhibiting separation, thereby realizing the purposes of increasing lift, reducing drag and controlling noise.
Description
Technical Field
The invention relates to the technical field of bionic flow control, in particular to a bionic leading edge wing realizing device and a bionic leading edge structure establishing method.
Background
The aerodynamic wing section structures of aircraft wings, wind turbine blades, compressor cascades and the like all have serious flow separation phenomena under specific working conditions. For the wings of the aircraft, the phenomenon of 'stall' can be caused by flow separation in a large angle of attack, at the moment, the lift coefficient of the aircraft suddenly drops, the resistance rapidly rises, and the flight safety is seriously damaged; for a wind turbine, the working wind field environment is complex and changeable, the local flow condition of the blades is extremely unstable, the flow separation phenomenon is serious, the power generation efficiency is greatly influenced, and meanwhile, the unsteady gas pulsation generated by the flow separation can generate serious pneumatic noise pollution and the like. The flow separation phenomenon occurring on the above aerodynamic airfoil structure is very common, and how to effectively inhibit separation, thereby improving efficiency and reducing noise is always a research object of great concern.
The wavy leading edge is arranged on the fin of a large marine organism such as a whale, the structure can effectively improve the aerodynamic characteristics of the wing section under a large attack angle and inhibit the flow separation phenomenon, so that the lift force is improved, the resistance is reduced, and the noise is controlled, therefore, the bionic wavy leading edge structure is widely researched and applied in various fields such as aircrafts, wind power generation and the like as a passive flow control means.
The existing bionic wavy leading edge structure mostly adopts a mode of integrally changing the three-dimensional configuration of a model, the wavy structure is directly processed at the leading edge, the processing is complex, the cost is high, and in addition, the parameters of the processed leading edge structure are fixed, cannot be changed, and cannot adapt to the optimal requirements under different working conditions. Although effective in inhibiting separation under certain conditions, such as high angles of attack, operating conditions under other conditions are not ideal and additional induced drag is generated.
Disclosure of Invention
The invention provides a bionic leading edge wing realizing device, aiming at solving the problems that a bionic wavy leading edge structure realized by the prior art cannot adapt to the optimal requirements under different working conditions, can generate additional induced resistance and the like. The invention can generate starting vortex by continuously inducing the starting vortex generator set through the discharge excitation in the flow, thereby generating a wave-shaped front edge on aerodynamic wing section structures such as aircraft wings, wind turbine blades, air compressor blade grids and the like, and achieving the purposes of improving lift force, reducing resistance and controlling noise.
The invention is realized by the following technical scheme:
a biomimetic leading edge airfoil implementation apparatus comprising: the controller, the high-voltage power supply, the voltage regulator, the function generator and the starting vortex generator set are connected;
the high-voltage power supply provides driving voltage for the starting vortex generator group through a gate circuit;
the voltage regulator is electrically connected with the high-voltage power supply and is used for regulating the amplitude and the frequency of the output voltage of the high-voltage power supply;
the function generator is electrically connected with the driving module of the high-voltage power supply and can output a driving signal to control the unsteady work of the high-voltage power supply;
the starting vortex generator set comprises a plurality of starting vortex generators, and the starting vortex generators are embedded in the airfoil structure and are uniformly arranged on the front edge of the airfoil structure in the spanwise direction; the starting vortex generator adopts plasma induction to generate a starting vortex, and the starting vortex forms a bionic wavy leading edge structure on the leading edge of the airfoil structure;
the controller is used for controlling a gate circuit between the high-voltage power supply and the starting vortex generator set to work so as to control the working sequence of the starting vortex generator set;
the controller is also used for controlling the function generator and the voltage regulator to drive signals output by the high-voltage power supply.
As a preferred embodiment, the starting vortex generator comprises a high-voltage exposed electrode, a dielectric layer and a grounding buried electrode which are sequentially arranged from top to bottom; and the high-voltage exposed electrode is positioned outside the wing-shaped structure, and the grounding buried electrode is positioned inside the wing-shaped structure.
As a preferred embodiment, the high-voltage bare electrode and the grounding buried electrode are both made of copper foils;
the dielectric layer is made of an insulating material.
As a preferred embodiment, the controller of the present invention controls the voltage regulator to adjust the amplitude and frequency of the output voltage of the high voltage power supply, so as to adjust the height of the generated bionic wavy leading edge structure.
As a preferred embodiment, the controller of the present invention controls the operation sequence of the set of start vortex generators through a gate circuit to adjust the width of the generated bionic wavy leading edge structure.
As a preferred embodiment, the controller of the present invention controls the unsteady operation of the high voltage power supply by the function generator to form a stable vortex structure.
In a preferred embodiment, the high-voltage power supply of the present invention employs an ac power supply or a pulse power supply;
the working voltage of the high-voltage power supply is 5 to 20kV.
On the other hand, the invention provides a bionic leading edge structure building method based on the bionic leading edge wing realizing device, which comprises the following steps:
matching the optimal parameters of the front edge wave structure from the database according to the actual flow condition;
determining the working sequence of the starting vortex generator group according to the optimal parameters of the front edge wave-shaped structure, and controlling the gate circuit to adjust the number and the spacing of the starting vortex generators so as to realize the control of the width of the wave-shaped front edge structure;
outputting a signal to the voltage regulator, controlling the amplitude and frequency of the output voltage of the high-voltage power supply, and realizing the control of the height of the wavy structure;
and outputting a signal to the function generator to enable the starting vortex generator to generate abnormal plasma excitation discharge so as to generate a stable bionic wavy front edge structure.
As a preferred embodiment, the method of the present invention comprises: and controlling whether the bionic wavy leading edge structure is generated or not according to the actual flow condition.
As a preferred embodiment, the method for controlling whether to generate the bionic wavy leading edge structure according to the actual flow condition specifically comprises the following steps:
the device does not work under the flowing non-separation state, and a bionic wavy leading edge structure is not generated;
the bionic wave-shaped front edge structure is generated to inhibit separation when the bionic wave-shaped front edge structure works in a flow separation state.
The invention has the following advantages and beneficial effects:
the invention utilizes the plasma excitation principle to continuously induce and generate the starting vortex, and the starting vortex can form a pneumatic bionic wavy leading edge structure on the leading edge of the wing-shaped structure to play a role in inhibiting separation, thereby realizing the purposes of increasing lift, reducing resistance and controlling noise.
The invention adopts an electric driving mode for control, and can control whether to generate a wave structure according to actual needs, namely, the wave structure is not generated under the condition of no separation of flow, so that the wing-shaped structure can work in the optimal starting shape without increasing extra resistance; the flow separation state works to generate a wave-shaped front edge structure, separation is inhibited, high lift drag reduction or noise reduction is realized, and the optimal control effect is achieved by monitoring the working state in real time and adjusting the parameters of the wave-shaped front edge structure.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
fig. 1 is a schematic structural diagram of a bionic leading edge implementation device according to an embodiment of the invention.
Fig. 2 is a schematic diagram of generating a virtual bionic wavy leading edge structure according to an embodiment of the present invention.
Fig. 3 is a schematic diagram of the height of the wave structure for increasing voltage amplitude adjustment according to the embodiment of the invention.
FIG. 4 is a schematic diagram of adjusting the width of the wave-shaped structure by changing the combined working sequence of the start vortex generator according to the embodiment of the present invention.
Reference numbers and corresponding part names in the drawings:
1-controller, 2-gate circuit/switch assembly, 3-high voltage bare electrode, 4-dielectric layer, 5-ground buried electrode, 6-airfoil structure, 7-start vortex, 8-virtual bionic wavy leading edge structure A, 9-virtual bionic wavy leading edge structure B and 10-virtual bionic wavy leading edge structure C.
Detailed Description
Hereinafter, the term "comprising" or "may include" used in various embodiments of the present invention indicates the presence of the invented function, operation or element, and does not limit the addition of one or more functions, operations or elements. Furthermore, as used in various embodiments of the present invention, the terms "comprises," "comprising," "includes," "including," "has," "having" and their derivatives are intended to mean that the specified features, numbers, steps, operations, elements, components, or combinations of the foregoing, are only meant to indicate that a particular feature, number, step, operation, element, component, or combination of the foregoing, and should not be construed as first excluding the existence of, or adding to the possibility of, one or more other features, numbers, steps, operations, elements, components, or combinations of the foregoing.
In various embodiments of the invention, the expression "or" at least one of a or/and B "includes any or all combinations of the words listed simultaneously. For example, the expression "a or B" or "at least one of a or/and B" may include a, may include B, or may include both a and B.
Expressions (such as "first", "second", and the like) used in various embodiments of the present invention may modify various constituent elements in various embodiments, but may not limit the respective constituent elements. For example, the above description does not limit the order and/or importance of the elements described. The foregoing description is for the purpose of distinguishing one element from another. For example, the first user device and the second user device indicate different user devices, although both are user devices. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of various embodiments of the present invention.
It should be noted that: if it is described that one constituent element is "connected" to another constituent element, the first constituent element may be directly connected to the second constituent element, and a third constituent element may be "connected" between the first constituent element and the second constituent element. In contrast, when one constituent element is "directly connected" to another constituent element, it is understood that there is no third constituent element between the first constituent element and the second constituent element.
The terminology used in the various embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the various embodiments of the invention. As used herein, the singular forms are intended to include the plural forms as well, unless the context clearly indicates otherwise. Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which various embodiments of the present invention belong. The terms (such as terms defined in a commonly used dictionary) will be construed to have the same meaning as the contextual meaning in the related art and will not be construed to have an idealized or overly formal meaning unless expressly so defined in various embodiments of the present invention.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Examples
The traditional mode of integrally changing the three-dimensional configuration of the model is adopted, a wave-shaped front edge structure is directly processed at the front edge, the structural parameters are fixed and cannot be changed, the optimal requirements under different working conditions cannot be met, and meanwhile, extra induced resistance and the like can be generated. In view of the above, the embodiments of the present invention provide a device for realizing a bionic leading edge airfoil, which can continuously induce the generation of start vortexes by plasma discharge excitation in a flow process, thereby controlling whether to generate a wavy leading edge structure according to actual needs, adjusting the shape of the generated bionic wavy leading edge structure, and achieving the purposes of increasing lift force, reducing resistance, and controlling noise.
Specifically, as shown in fig. 1, the bionic leading edge wing implementation device of the embodiment of the invention mainly comprises a controller 1, a gate circuit/switch assembly 2, a high-voltage power supply, a voltage regulator, a function generator and a starting vortex generator set. Wherein the content of the first and second substances,
the high-voltage power supply can adopt an alternating current power supply or a pulse power supply, and the working voltage is 5-20kV. The high-voltage power supply provides driving voltage for the starting vortex generator set.
The voltage regulator is connected with the high-voltage power supply and can adjust the amplitude and frequency of the output voltage of the high-voltage power supply.
The function generator is connected with the driving module of the high-voltage power supply and can control the unsteady work of the high-voltage power supply by outputting a driving signal.
The starting vortex generator set comprises a plurality of starting vortex generators which are uniformly arranged near the leading edge of the airfoil structure 6 in an embedded mode along the spanwise direction (the spanwise direction is the direction from the wing root to the wing tip of the wing; and the chordwise direction is the direction from the leading edge to the trailing edge of the wing). The starting vortex generator mainly comprises a high-voltage exposed electrode 3, a dielectric layer 4 and a grounding buried electrode 5 which are sequentially arranged from top to bottom. The high-voltage exposed electrode 3 and the grounding buried electrode 5 are both made of copper foils, and the dielectric layer is made of insulating materials such as polyimide or epoxy resin.
The controller 1 is capable of controlling the operation of a gate/switch assembly 2 located between the power supply and the set of pneumatic vortex generators, thereby controlling the sequence of operations that initiate the set of vortex generators. The gate/switch assembly 2 of the embodiment of the present invention is, but not limited to, a MOS transistor or a transistor.
The controller 1 is also electrically connected with the function generator and the voltage regulator to control the driving signals generated by the function generator and the voltage regulator to the high-voltage power supply.
The working principle of the bionic leading edge wing realizing device provided by the embodiment of the invention is as follows:
by applying high voltage between the grounding buried electrode 5 and the high-voltage exposed electrode 3, air seen by the electrodes can be punctured to generate charged particles, and the particles can wrap the air to move directionally under the action of electric field force. At the moment of starting the vortex generator, a starting vortex is generated above the electrode, and the starting and closing processes of the vortex generator can be continuously and repeatedly started through the non-constant control of the high-voltage power supply, so that the starting vortex is continuously induced to be generated, and a stable vortex structure is formed macroscopically, as shown in fig. 2. The vortex structures can form pneumatic bionic wavy leading edges on the leading edges of the wing-shaped structures, and play a role in inhibiting separation, so that the aims of increasing lift, reducing drag and controlling noise are fulfilled.
In the embodiment of the invention, the controller 1 can control the voltage regulator to adjust the amplitude, the frequency and the like of the voltage output by the high-voltage power supply, so as to realize the control of the height of the wavy structure, as shown in fig. 3.
The embodiment of the invention can control the working sequence of the set of start vortex generators by the controller 1, thereby realizing the control of the width of the wave-shaped structure, as shown in fig. 4.
The embodiment of the invention can control the function generator through the controller 1 to form a stable bionic wavy leading edge structure.
By adopting the bionic leading edge wing realizing device provided by the embodiment of the invention, the bionic wavy leading edge structure can be generated according to actual conditions, the width, the height and the like of the bionic leading edge structure are controlled according to actual requirements, the controllability of the bionic leading edge structure is improved, and the purposes of improving the lift force, reducing the resistance, controlling the noise and the like are realized.
The embodiment of the invention adopts the bionic leading edge wing realizing device to realize the establishment of the bionic leading edge structure, and the specific process is as follows:
step 1, according to the actual flow situation, matching the optimal parameters of the leading edge wave structure from a database in the controller 1.
And 2, determining a working sequence of the starting vortex generator set according to the optimal front edge wave structure parameters, controlling a gate circuit/switch assembly 2 between the high-voltage power supply and the starting vortex generator set by the controller, and further adjusting the number and the interval of the starting vortices to realize the control of the width of the wave structure.
And 3, the controller 1 outputs signals to the voltage regulator to control the amplitude and frequency of the output voltage of the high-voltage power supply, so that the height of the corrugated structure is controlled.
And 4, outputting a signal to the function generator by the controller 1, starting the vortex generator to generate abnormal plasma excitation discharge (the abnormal discharge is an excitation discharge form which changes along with time), and further generating a stable bionic wavy front edge structure.
By adopting the bionic leading edge realizing device, whether a bionic wavy leading edge structure is generated or not can be controlled according to actual needs, namely the bionic wavy leading edge structure does not work under the flowing non-separation state, the wavy structure is not generated, the wing-shaped structure can be ensured to work in the well-designed optimal pneumatic shape, and additional resistance is not increased; the flow separation state is operated to generate a wavy leading edge structure, separation is inhibited, high lift drag reduction or noise reduction is realized, and the parameters of the wavy leading edge structure can be adjusted by monitoring the working state in real time (namely monitoring the surface pressure of the wing through a pressure sensor arranged on the wing so as to reflect the working state through pressure change), so that the optimal control effect is achieved.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only examples of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A biomimetic leading edge airfoil implementation apparatus, comprising: the controller, the high-voltage power supply, the voltage regulator, the function generator and the starting vortex generator set are connected;
the high-voltage power supply provides driving voltage for the starting vortex generator set through a gate circuit;
the voltage regulator is electrically connected with the high-voltage power supply and is used for regulating the amplitude and the frequency of the output voltage of the high-voltage power supply;
the function generator is electrically connected with the driving module of the high-voltage power supply and can output a driving signal to control the unsteady work of the high-voltage power supply;
the starting vortex generator set comprises a plurality of starting vortex generators, and the starting vortex generators are embedded in the airfoil structure and are uniformly arranged on the front edge of the airfoil structure in the spanwise direction; the starting vortex generator adopts plasma induction to generate a starting vortex, and the starting vortex forms a bionic wavy leading edge structure on the leading edge of the airfoil structure;
the controller is used for controlling a gate circuit between the high-voltage power supply and the starting vortex generator set to work so as to control the working sequence of the starting vortex generator set;
the controller is also used for controlling the function generator and the voltage regulator to drive signals output by the high-voltage power supply.
2. The bionic leading edge wing implementation device of claim 1, wherein the starting vortex generator comprises a high-voltage exposed electrode, a dielectric layer and a grounding buried electrode which are sequentially arranged from top to bottom; and the high-voltage exposed electrode is positioned outside the wing-shaped structure, and the grounding buried electrode is positioned inside the wing-shaped structure.
3. The bionic leading edge wing implementation device of claim 2, wherein the high-voltage bare electrode and the grounding buried electrode are both made of copper foil;
the dielectric layer is made of an insulating material.
4. The device of claim 1, wherein the controller controls the voltage regulator to adjust the amplitude and frequency of the output voltage of the high voltage power supply to adjust the height of the generated bionic wavy leading edge structure.
5. The bionic leading edge wing implementation device of claim 1, wherein the controller controls the operation sequence of the start vortex generator set through a gate circuit so as to adjust the width of the generated bionic wavy leading edge structure.
6. The bionic leading edge wing implementation device of claim 1, wherein the controller controls unsteady operation of the high-voltage power supply through the function generator to form a stable vortex structure.
7. The bionic leading edge wing implementation device of any one of claims 1-6, wherein the high-voltage power supply is an alternating current power supply or a pulse power supply;
the working voltage of the high-voltage power supply is 5-20kV.
8. The method for establishing the bionic leading edge structure of the bionic leading edge wing realization device according to any one of claims 1 to 7, is characterized by comprising the following steps:
matching the optimal parameters of the front edge wave structure from the database according to the actual flow condition;
determining the working sequence of the starting vortex generator group according to the optimal parameters of the front edge wave-shaped structure, and controlling the gate circuit to adjust the number and the spacing of the starting vortex generators so as to realize the control of the width of the wave-shaped front edge structure;
outputting a signal to the voltage regulator, controlling the amplitude and the frequency of the output voltage of the high-voltage power supply, and realizing the control of the height of the wavy structure;
and outputting a signal to the function generator to enable the starting vortex generator to generate abnormal plasma excitation discharge so as to generate a stable bionic wavy front edge structure.
9. The method of claim 8, wherein the method comprises: and controlling whether the bionic wavy leading edge structure is generated or not according to the actual flow condition.
10. The method for establishing a bionic leading edge structure according to claim 9, wherein whether the bionic wavy leading edge structure is generated or not is controlled according to actual flow conditions, and specifically:
the device does not work in a flowing non-separation state, and a bionic wavy front edge structure is not generated;
working in a flow separation state, a bionic wavy leading edge structure is generated, and separation is inhibited.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080145210A1 (en) * | 2006-12-15 | 2008-06-19 | General Electric Co. | Airfoil leading edge end wall vortex reducing plasma |
| CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
| 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 |
| CN109319169A (en) * | 2018-11-24 | 2019-02-12 | 中国人民解放军空军工程大学 | Rf (discharge) plasma excitation improves the device and method of aerofoil profile separation stall |
| US20190193843A1 (en) * | 2017-12-26 | 2019-06-27 | Subaru Corporation | Flow control apparatus, flow control method, and aircraft |
| CN112298535A (en) * | 2020-09-14 | 2021-02-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for inhibiting airfoil buffeting through pulsed arc plasma energy deposition |
-
2023
- 2023-01-09 CN CN202310023861.0A patent/CN115716528A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080145210A1 (en) * | 2006-12-15 | 2008-06-19 | General Electric Co. | Airfoil leading edge end wall vortex reducing plasma |
| CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
| 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 |
| US20190193843A1 (en) * | 2017-12-26 | 2019-06-27 | Subaru Corporation | Flow control apparatus, flow control method, and aircraft |
| CN109319169A (en) * | 2018-11-24 | 2019-02-12 | 中国人民解放军空军工程大学 | Rf (discharge) plasma excitation improves the device and method of aerofoil profile separation stall |
| CN112298535A (en) * | 2020-09-14 | 2021-02-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for inhibiting airfoil buffeting through pulsed arc plasma energy deposition |
Non-Patent Citations (2)
| Title |
|---|
| 吴霖鑫;李国强;杨永东;张鑫;陈磊: "旋翼翼型动态失速等离子体流动控制试验研究" * |
| 张仕栋;胡文蓉;: "仿生波状前缘机翼动态失速控制的数值研究" * |
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