CN115716529B - Wing leading edge drooping dynamic stall control device and method - Google Patents
Wing leading edge drooping dynamic stall control device and method Download PDFInfo
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- CN115716529B CN115716529B CN202310030922.6A CN202310030922A CN115716529B CN 115716529 B CN115716529 B CN 115716529B CN 202310030922 A CN202310030922 A CN 202310030922A CN 115716529 B CN115716529 B CN 115716529B
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Abstract
The invention discloses a device and a method for controlling dynamic stall of leading edge sagging of a wing, which relate to the technical field of power control, wherein the device comprises a main control module, a plasma exciter, a power supply and a signal generator; the main control module is used for controlling the output of the signal generator according to the wing surface separation state; the signal generator modulates the power supply output waveform by outputting different waveform signals, so as to control the discharge state of the plasma exciter; the power supply provides a driving voltage for the plasma exciter; the plasma exciter is arranged on the front edge of the wing in the spanwise direction, and can generate an unsteady induced vortex structure, and the unsteady induced vortex structure interacts with main vortex of the front edge of the wing, so that a virtual front edge sagging structure is formed. The invention adopts a plasma unsteady excitation mode to continuously induce a vortex structure at the front edge of the wing, and the vortex structure interacts with main flow to generate a virtual front edge sagging structure at the front edge of the wing, thereby meeting the requirement of dynamic stall control.
Description
Technical Field
The invention relates to the technical field of power control, in particular to a device and a method for controlling trailing edge sagging dynamic stall.
Background
The helicopter is easy to dynamically stall when flying forwards and the trailing side blades are easy to dynamically stall, so that the flying speed of the helicopter is limited, meanwhile, the problems of lift force sudden drop and the like are caused in the vortex generation and falling process of the upper surfaces of the blades after stall, the flying safety is seriously endangered, the front edge sagging technology can be used for inhibiting the generation of separated vortex, the lift force coefficient of a rotor wing is improved, and the torque coefficient is reduced. In addition, the present large civil aircraft needs to use a wing high lift device in the take-off and landing process, and the existing high lift device comprises a front edge slat, a rear edge flap, a front edge drooping flap and the like, wherein the failure probability of the front edge drooping flap is relatively low, and the present large civil aircraft has become the main research direction of the present international advanced civil aircraft high lift device, as shown in fig. 1. The existing front edge sagging structure is driven through a mechanical structure, the mechanical action is long in time consumption and slow in response, the mechanical action can also cause adverse effects such as blade vibration, meanwhile, due to the fact that the weight of mechanical parts is large, the structure is complex, the aircraft design can be restrained, and a series of problems such as maintenance and inspection difficulties exist.
Disclosure of Invention
The invention provides a dynamic stall control device for leading edge sagging of a wing, which aims to solve the problems that the existing leading edge sagging structure driving technology is long in time consumption and slow in response, and can cause adverse effects such as blade vibration and the like. The invention utilizes the plasma exciter to continuously induce the vortex structure, and the vortex structure and the main flow interact to generate a virtual front edge sagging structure at the front edge of the wing, so as to meet the control requirement of dynamic stall.
The invention is realized by the following technical scheme:
a wing leading edge drooping dynamic stall control device comprises a main control module, a plasma exciter, a power supply and a signal generator;
the main control module is used for controlling the output of the signal generator according to the wing surface separation state;
the signal generator modulates the power supply output waveform by outputting different waveform signals, so as to control the discharge state of the plasma exciter;
the power supply provides a driving voltage for the plasma exciter;
the plasma exciter is arranged at a position close to the front edge of the wing along the direction from the wing root to the wing tip, and can generate an unsteady induced vortex structure, and the unsteady induced vortex structure interacts with the main stream vortex of the front edge of the wing, so that a virtual front edge sagging structure is formed.
Compared with the traditional mechanical front edge sagging structure, the invention has simple structure, even load distribution at the front edge of the wing, smaller influence on the appearance of the wing structure, high response speed and no adverse influence on the rotor wing in high-speed movement in the action process by combining an electric driving mode.
As a preferred embodiment, the plasma actuator of the present invention includes a high voltage electrode, an insulating dielectric layer, and a low voltage electrode;
the high-voltage electrode and the high-voltage electrode are respectively positioned at two sides of the insulating medium layer, the high-voltage electrode is arranged outside the wing, and the low-voltage electrode and the insulating medium layer are buried inside the wing.
As a preferred embodiment, the high-voltage electrode and the low-voltage electrode have no gap between each other, and the butt joint position is close to the front edge of the wing.
As a preferred embodiment, the high-voltage electrode and the low-voltage electrode of the invention are made of metal materials with conductive performance meeting the requirement;
the insulating medium layer is made of insulating materials.
As a preferred embodiment, the high voltage electrode and the low voltage electrode of the present invention use copper foil;
the insulating medium layer adopts polyimide.
As a preferred embodiment, the power supply of the present invention employs an ac discharge power supply;
the power supply high-voltage output end is connected with the high-voltage electrode, and the power supply low-voltage end is connected with the low-voltage electrode and grounded.
As a preferred embodiment, the signal generator of the present invention modulates the power supply output waveform by outputting different waveform signals, thereby controlling the on-off state of the plasma exciter, and outputting amplitude, frequency, duty cycle and phase parameters of the voltage.
As a preferred embodiment, the wing of the present invention is a helicopter rotor, a fixed wing airfoil or a two-dimensional airfoil.
On the other hand, the invention provides a control method based on the wing leading edge sagging dynamic stall control device, which comprises the following steps:
selecting optimal wing leading edge sagging shape parameters according to wing surface separation conditions;
setting waveform parameters of a signal generator according to the optimal wing leading edge sagging shape parameters, and controlling output voltage parameters of a plasma exciter so as to control the leading edge sagging parameters;
and starting a plasma exciter, and inducing a start vortex at the front edge of the wing through unsteady discharge, so as to generate a virtual front edge sagging structure.
As a preferred embodiment, the method of the present invention further comprises:
by installing a plasma exciter on the surface of a helicopter rotor, starting the plasma exciter when the blade moves to the backward side so as to form a virtual front edge sagging structure on the surface of the blade, thereby inhibiting the generation and development of surface separation vortex when the blade of the helicopter moves to the backward side;
turning off the plasma actuator when the blade is moved to the forward side maintains the original airfoil shape without a virtual leading edge sagging structure.
The invention has the following advantages and beneficial effects:
according to the invention, a virtual sagging structure is formed on the front edge of the wing by using plasma unsteady excitation, a complex mechanical actuating mechanism is not needed, and the weight of the wing in the sagging configuration of the front edge is reduced; because the electric driving mode is adopted, the control is easy, the response speed is high, and the rotor wing in high-speed movement cannot be influenced in the action process.
The plasma exciter is arranged on the surface of the wing, so that the maintenance is convenient.
The virtual front edge sagging structure generated by the invention can inhibit the generation and development of surface separation vortex when the blades of the helicopter move to the backward side when applied to the helicopter, and improves the lift coefficient and the normal force coefficient, and reduces the torque coefficient, thereby improving the equivalent lift-drag ratio of the rotor wing; when the device is applied to a fixed wing aircraft, the take-off and landing performance can be improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention. In the drawings:
FIG. 1 is a schematic block diagram of a dynamic stall control apparatus according to an embodiment of the present invention.
Fig. 2 is a schematic working diagram of a control device according to an embodiment of the present invention.
Fig. 3 is a schematic view of a plasma actuator according to an embodiment of the present invention.
FIG. 4 is a schematic diagram illustrating the generation of a virtual leading edge sagging vortex structure according to an embodiment of the present invention.
Fig. 5 is a schematic view of the leading edge droop configuration of a helicopter rotor according to an embodiment of the present invention.
In the drawings, the reference numerals and corresponding part names:
the device comprises a 1-wing, a 2-plasma exciter, a 21-high voltage electrode, a 22-insulating medium layer, a 23-low voltage electrode, a 3-virtual front edge sagging structure, a 4-main flow vortex, a 5-unsteady induced vortex, a 6-trailing side A, a 7-virtual front edge sagging structure A, an 8-trailing side B, a 9-virtual front edge sagging structure B and a 10-leading side.
Detailed Description
Hereinafter, the terms "comprises" or "comprising" as may be used in various embodiments of the present invention indicate the presence of inventive functions, operations or elements, and are not limiting of the addition of one or more functions, operations or elements. Furthermore, as used in various embodiments of the invention, the terms "comprises," "comprising," and their cognate terms are intended to refer to a particular feature, number, step, operation, element, component, or combination of the foregoing, and should not be interpreted as first excluding the existence of or increasing likelihood 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", etc.) used in the various embodiments of the invention may modify various constituent elements in the various embodiments, but the respective constituent elements may not be limited. For example, the above description does not limit the order and/or importance of the elements. The above description is only intended to distinguish one element from another element. 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 to "connect" one component element to another component element, a first component element may be directly connected to a second component element, and a third component element may be "connected" between the first and second component elements. Conversely, 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 is intended to include the plural 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 invention belong. The terms (such as those defined in commonly used dictionaries) will be interpreted as having a meaning that is the same as the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein in connection with the various embodiments of the invention.
For the purpose of making apparent the objects, technical solutions and advantages of the present invention, the present invention will be further described in detail with reference to the following examples and the accompanying drawings, wherein the exemplary embodiments of the present invention and the descriptions thereof are for illustrating the present invention only and are not to be construed as limiting the present invention.
Examples
The traditional mechanical front edge sagging structure can restrict the design of an aircraft due to the large weight and the complex structure of mechanical parts, has the problems of difficult maintenance and inspection and the like, and meanwhile, the mechanical actuation consumes long time and has slower response, and the mechanical actuation can also cause adverse effects such as blade vibration and the like. Based on the above, the embodiment of the invention provides a device for controlling the trailing edge sagging dynamic stall, and the embodiment of the invention adopts a plasma unsteady excitation mode to continuously induce a vortex structure on the trailing edge, and the vortex structure interacts with main flow to generate a virtual trailing edge sagging structure on the trailing edge, thereby meeting the requirement of dynamic stall control.
Specifically, as shown in fig. 1, the control device in the embodiment of the invention comprises a main control module, a plasma exciter 2 arranged near the front edge of the wing 1, a power supply, a signal generator and the like. The main control module is in communication connection with a signal generator, which is in communication connection with a control module of a power supply, which provides a driving voltage for the plasma exciter, the plasma exciter 2 being adapted to generate an induced vortex structure at the leading edge of the wing, which interacts with the main vortex structure so as to generate a virtual leading edge sagging structure 3 at the leading edge of the wing, as shown in fig. 2.
The main control module is used for judging the separation condition of the surface of the wing according to the detection equipment of the wing, so that the optimal front edge sagging shape parameters, such as sagging angle, length and the like, are obtained. The main control module can be a functional module unit integrated in a controller of the aircraft, or can be an independent controller module unit.
The main control module sends the waveform parameters corresponding to the optimal front edge sagging shape parameters to the signal generator, and the signal generator controls parameters such as the output voltage amplitude, frequency, duty ratio, phase and the like of the plasma exciter through the control module of the power supply, thereby controlling parameters such as the front edge sagging angle, the sagging occurrence phase and the like.
In the embodiment of the invention, the main control module judges the separation condition of the wing surface according to the wing pressure sensor, so that the optimal front edge sagging shape parameter can be obtained.
As shown in fig. 3, the plasma exciter 2 is installed near the front edge of the wing 1 in the spanwise direction (the spanwise direction is the direction from the wing root to the wing tip; the chordwise direction is the direction from the front edge to the rear edge), and mainly comprises a high-voltage electrode 21, an insulating medium layer 22 and a low-voltage electrode 23. The high-voltage electrode 21 and the high-voltage electrode 23 are respectively positioned at two sides of the insulating medium layer 22, the high-voltage electrode 21 is exposed in the air, namely, the high-voltage electrode 21 is arranged outside the wing 1, and the low-voltage electrode 23 and the insulating medium layer 22 are buried in the wing 1, so that the influence of an exciter on the appearance of the wing is reduced.
It should be noted that the wing according to the embodiment of the present invention may be, but is not limited to, a helicopter rotor, a fixed wing airfoil, or a two-dimensional airfoil.
There is no gap between the high voltage electrode 21 and the low voltage electrode 23, and the butt joint position 24 of the high voltage electrode 21 and the low voltage electrode 23 is close to the front edge of the wing. The abutment 24 is perpendicular to the airfoil and indicates that there is no gap between the high voltage electrode 21 and the low voltage electrode 23 when both ends are in the abutment.
The high-voltage electrode 21 and the low-voltage electrode 23 can be made of any metal material with excellent conductivity, preferably copper foil; the dielectric insulating layer 22 is made of an insulating material, and polyimide is preferably used in terms of dielectric constant and weight.
The power source may be, but is not limited to, an ac discharge power source, a high voltage output terminal of the power source is connected to the high voltage electrode 21, and a low voltage terminal of the power source is connected to the low voltage electrode 23 and grounded.
The signal generator is connected with the control module of the power supply, and modulates the output waveform of the power supply by outputting signals with different waveforms, so as to control the discharge state of the plasma exciter, including the switching state, and parameters such as amplitude, frequency, duty ratio and phase of the output voltage.
The working principle of the control device provided by the embodiment of the invention is as follows:
by applying a high voltage electric field between the high voltage electrode 21 and the low voltage electrode 23 of the plasma exciter 2, whereby the breakdown air generates a plasma which, under the influence of the electric field, entrains air to generate a directional movement directed from the high voltage electrode 21 towards the low voltage electrode 23. The plasma exciter 2 generates a start vortex at the moment of starting, and a stable vortex structure can be formed by using an unsteady excitation mode. By arranging the exciters in the spanwise direction in the vicinity of the wing leading edge, whereby in operation a vortex is generated which is distributed in the spanwise direction, the vortex (unsteady induced vortex 5) interacts with the main flow (main flow vortex 4, including separation and shedding vortices) to form a virtual leading edge sagging structure 3, as shown in fig. 4.
The working process of the control device provided by the embodiment of the invention specifically comprises the following steps:
And 2, setting waveform parameters of a signal generator according to the sagging shape parameters of the front edge, and controlling parameters such as amplitude, frequency, duty ratio, phase and the like of the output voltage of the exciter, thereby controlling parameters such as sagging angle of the front edge, phase and the like of sagging.
And 3, starting the plasma exciter 2, and inducing a start vortex at the front edge of the wing through unsteady discharge, so as to generate a virtual front edge sagging structure 3.
According to the embodiment of the invention, the virtual front edge sagging structure 3 is generated by utilizing the characteristic of the unsteady excitation induced vortex structure of the plasma exciter 2 which is arranged in the spanwise direction near the front edge of the wing (rotor wing); by controlling the output of the signal generator, leading edge sagging structures of different angles and lengths can be formed, thereby controlling for dynamic stall under different flight conditions.
For the helicopter rotor, by controlling the generation phase of the virtual front edge, the virtual front edge sagging structure A7 is formed only when the blade moves to the trailing side A6, the virtual front edge sagging structure B9 is formed when the blade moves to the trailing side B8, and the virtual front edge sagging structure is not formed when the blade moves to the leading side 10, as shown in fig. 5, the blade moves to the trailing side to open the exciter so as to form the virtual front edge sagging structure on the surface of the blade, so that the generation and development of surface separation vortex can be restrained when the blade of the helicopter moves to the trailing side, the lift coefficient and the normal force coefficient are improved, the torque coefficient is reduced, and the equivalent lift-drag ratio of the rotor is improved.
The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the invention, and is not meant to limit the scope of the invention, but to limit the invention to the particular embodiments, and any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (7)
1. The method is realized based on a stall control device, and the stall control device comprises a main control module, a plasma exciter, a power supply and a signal generator;
the main control module is used for controlling the output of the signal generator according to the wing surface separation state;
the signal generator modulates the power supply output waveform by outputting different waveform signals, so as to control the discharge state of the plasma exciter;
the power supply provides a driving voltage for the plasma exciter;
the plasma exciter is arranged at a position close to the front edge of the wing along the direction from the wing root to the wing tip, and can generate an unsteady induced vortex structure, and the unsteady induced vortex structure interacts with the main vortex of the front edge of the wing, so that a virtual front edge sagging structure is formed;
the plasma exciter comprises a high-voltage electrode, an insulating medium layer and a low-voltage electrode;
the high-voltage electrode and the high-voltage electrode are respectively positioned at two sides of the insulating medium layer, the high-voltage electrode is arranged outside the wing, and the low-voltage electrode and the insulating medium layer are buried in the wing; the high-voltage electrode is positioned on the upper airfoil surface of the wing, and the high-voltage electrode is positioned on the lower airfoil surface of the wing;
the method comprises the following steps:
selecting optimal wing leading edge sagging shape parameters according to wing surface separation conditions;
setting waveform parameters of a signal generator according to the optimal wing leading edge sagging shape parameters, and controlling output voltage parameters of a plasma exciter so as to control the leading edge sagging parameters;
starting a plasma exciter, and inducing a start vortex at the front edge of the wing through unsteady discharge, so as to generate a virtual front edge sagging structure;
the method comprises the steps that a plasma exciter is arranged on the surface of a rotor wing of the helicopter, and the plasma exciter is started when a blade moves to the backward side, so that a virtual front edge sagging structure is formed on the surface of the blade, and generation and development of surface separation vortex are restrained when the blade of the helicopter moves to the backward side;
turning off the plasma actuator when the blade is moved to the forward side maintains the original airfoil shape without a virtual leading edge sagging structure.
2. A method of dynamic stall control for leading edge droop of a wing according to claim 1, wherein the high voltage electrode is in abutting contact with the leading edge of the wing without gaps between the high voltage electrode and the low voltage electrode.
3. The method for controlling the trailing edge sagging dynamic stall of claim 1, wherein the high-voltage electrode and the low-voltage electrode are made of metal materials with conductive properties meeting requirements;
the insulating medium layer is made of insulating materials.
4. A method of controlling dynamic stall in leading edge droop of a wing according to claim 3, wherein the high voltage electrode and the low voltage electrode are copper foil;
the insulating medium layer adopts polyimide.
5. A method of controlling dynamic stall in leading edge droop in a wing as set forth in claim 1, wherein said power source is an ac discharge power source;
the power supply high-voltage output end is connected with the high-voltage electrode, and the power supply low-voltage end is connected with the low-voltage electrode and grounded.
6. A method of controlling dynamic stall control for leading edge droop in a wing as claimed in claim 1, wherein the signal generator modulates the power supply output waveform by outputting different waveform signals to control the on-off state of the plasma exciter, amplitude, frequency, duty cycle and phase parameters of the output voltage.
7. A method of dynamic stall control as claimed in any of claims 1 to 6 wherein the wing is a helicopter rotor, a fixed wing or a two-dimensional airfoil.
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