Circulation Control Method for Wings

Abstract

The present invention provides a circulation control method suitable for a wing, wherein a plurality of blowing-suction separation port pairs consisting of a first jet injection port and a first fluid suction port are arranged in an array along a fluid flow direction on the upper surface of the wing starting from a position close to a leading edge of the wing; in each blowing-suction separation port pair, the first jet injection port is arranged upstream of the first fluid suction port; the first jet injection port continuously injects a jet outward, and the ejected high-energy jet flows downstream, continuously injecting energy into a low-energy boundary layer on the upper surface of the wing; the first fluid suction port continuously inhales surrounding fluid inward, continuously sucking away a low-energy boundary layer at a high-pressure area on the upper surface of the wing downstream of the first jet injection port, maintaining the energy of the boundary layer, and resisting flow separation of a local fluid; a blowing-suction relay control effect is formed between the plurality of blowing-suction separation port pairs arranged in an array along the fluid flow direction on the upper surface of the wing, thereby realizing flow separation control on the upper surface of the wing of the entire wing.

Description

Technical Field

[0001] The present invention relates to the technical field of active flow control, and in particular to a circulation control method suitable for a wing. Background Art

[0002] Flow control technology can be divided into passive flow control and active flow control (AFC). Passive control is to change the flow field environment through passive control devices. It is a pre-designed working condition and cannot be changed in real time. When the actual flow field deviates greatly from the designed working condition, passive flow control cannot achieve its optimal control effect. AFC directly injects energy into the flow field through external forces to generate disturbances in the flow field and couple with the flow pattern of the flow field itself, thereby achieving changes and control of the flow field. Compared with passive flow control, the advantage of AFC is that it can adjust the working condition so that it appears at the time and location where it is most needed. By injecting energy into the local flow field, it can obtain local or global flow environment changes, achieving the effect of "a little effort to achieve a great result".

[0003] As one of the most dynamic flow control methods, AFC technology has a wide range of applications in aircraft lift increase, drag reduction, noise reduction, attitude control, etc. Circulation Control technology, as one of the flow control methods, changes the circulation of the wing by blowing air at the trailing edge of the wing to form a Coanda effect, thereby achieving lift increase, drag reduction and attitude control of the aircraft. It has the advantages of being simple to use and easy to implement.

[0004] With the continuous development of synthetic jet technology in modern times, as a new type of AFC technology, synthetic jet has been widely used in wing circulation control and lift increase and drag reduction. The principle of traditional synthetic jet circulation control is as follows: Figure 1 As shown, as the diaphragm 1 reciprocates in the actuator cavity 2, a synthetic jet of periodic alternating blowing and suction is formed at the fluid inlet and outlet 3 of the synthetic jet actuator. When the synthetic jet is in the blowing range, the ejected jet flows along the outer wall surface of the arc-shaped Coanda trailing edge 6, forming a deflected fluid at the trailing edge, so that the airfoil has an aerodynamic curvature, increasing the circulation and overall lift of the wing; when the synthetic jet is in the suction range, the fluid inlet and outlet suck the low-speed fluid in the boundary layer from the vicinity of the wall surface, increasing the ability of the upper wall fluid to resist flow separation and inhibiting separation. For a traditional synthetic jet actuator, its jet outlet is the jet inlet, and the jet blowing and suction are performed at the same position. From the perspective of control mechanism, when the circulation is controlled at the trailing edge, the jet only blows but does not suck, which can further increase the circulation and obtain greater lift. When in the suction range, sucking the separation area behind the separation point in the middle section of the wing will achieve a better effect than sucking at the trailing edge, and the suppression of separation will be more obvious.

[0005] Compared with synthetic jet actuators, synthetic dual jet actuators can double the energy utilization efficiency, have advantages such as preventing ballast failure, and have greater application potential in circulation control. In order to solve the problems existing in traditional synthetic jet circulation control methods and the defects compared with synthetic dual jets, it is necessary to develop a new synthetic dual jet circulation control method. Summary of the invention

[0006] In view of the defects of traditional synthetic (dual) jet actuators, the purpose of the present invention is to provide a circulation control method suitable for wings. The present invention designs a blowing-suction separation synthetic dual jet actuator, replaces the synthetic jet actuator with the blowing-suction separation synthetic dual jet actuator, and divides its inlet and outlet into a jet outlet and a fluid inlet, wherein the fluid inlet can only allow fluid to enter, and the jet outlet can only allow fluid to be ejected. At the same time, the number, angle, position coordinates and other parameters of the fluid inlet and jet outlet can be flexibly adjusted to meet the use requirements. In controlling the flow of the wing, the fluid inlet can be set in the separation zone, and the jet outlet can be set at the trailing edge to achieve a better circulation control effect.

[0007] In order to achieve the above technical objectives, the technical solution adopted by the present invention is:

[0008] A circulation control method suitable for a wing, wherein a plurality of blow-suction separation port pairs consisting of a first jet injection port and a first fluid suction port are arranged in an array along the fluid flow direction of the upper surface of the airfoil of the wing starting from a position close to the leading edge of the wing;

[0009] Each blow-suction separation port is aligned, and the first jet injection port is arranged upstream of the first fluid suction port, that is, the first jet injection port is closer to the leading edge of the wing than the first fluid suction port; the first jet injection port continuously ejects jets outward, and the ejected high-energy jets flow downstream, continuously injecting energy into the low-energy boundary layer on the upper surface of the airfoil; the first fluid suction port continuously sucks in the surrounding fluid inward, continuously sucking away the low-energy boundary layer at the high-pressure area on the upper surface of the airfoil downstream of the first jet injection port, maintaining the energy of the boundary layer, and resisting the flow separation of the local fluid;

[0010] A plurality of blowing-suction separation port pairs are arranged in an array along the fluid flow direction of the upper surface of the airfoil to form a blowing-suction relay control effect, thereby realizing flow separation control on the upper surface of the airfoil of the entire wing.

[0011] Furthermore, in the present invention, the jet injection direction of the first jet injection port is consistent with the tangent direction of the wall surface where the first jet injection port is located, and the fluid suction direction of the first fluid suction port is consistent with the tangent direction of the wall surface where the first fluid suction port is located.

[0012] Furthermore, the wing airfoil of the present invention is an airfoil with a Coanda trailing edge, and a second main jet injection port, a second relay jet injection port and a second fluid suction port are arranged on the upper wall of the airfoil near the Coanda trailing edge. The second fluid suction port is arranged upstream of the second main jet injection port, and the second main jet injection port is closer to the Coanda trailing edge and is located at the starting point of the Coanda trailing edge. The second relay jet injection port is arranged at the Coanda trailing edge and is located at the separation point of the Coanda deflected airflow. The second fluid suction port continuously sucks in the low-energy boundary layer on the upper wall of the airfoil near the Coanda trailing edge to maintain the energy of the fluid on the upper wall and delay the flow separation on the upper wall; the second main jet injection port continuously injects jets onto the Coanda wall. Under the action of the Coanda trailing edge, the jet moves along the curved wall of the Coanda trailing edge to form a deflected fluid at the trailing edge of the airfoil. The deflected fluid will separate at a position at the Coanda trailing edge. The second relay jet injection port is set at the separation point of the deflected fluid to inject energy into the deflected fluid that is about to separate, causing it to undergo a secondary deflection, thereby giving the airfoil an aerodynamic curvature and increasing the circulation of the wing.

[0013] Furthermore, in the wing of the present invention, more than one first blowing-suction separation synthetic jet actuator is arranged, and each group of blowing-suction separation ports corresponds to a first blowing-suction separation synthetic dual jet actuator; the first blowing-suction separation synthetic jet actuator comprises an actuator cavity and a vibrating membrane arranged in the actuator cavity, the actuator cavity is provided with at least one fluid inlet and at least one fluid outlet, the fluid inlet is provided with a first one-way flow guide structure that restricts the fluid to only enter and not exit, the fluid outlet is provided with a second one-way flow guide structure that restricts the fluid to only exit and not enter, all fluid inlets of the first blowing-suction separation synthetic jet actuator are connected to the corresponding first fluid suction port, and all fluid outlets of the first blowing-suction separation synthetic jet actuator are connected to the corresponding first jet injection port. Through the above technical scheme, the location of each blowing-suction separation synthetic dual jet actuator in the present invention has the effect of resisting separation locally, playing the role of "micro-coordination". By arranging the array along the flow direction, the effect of relay control can be achieved, thereby realizing the flow separation control of the entire upper wing surface.

[0014] Furthermore, in the first blowing-suction separation synthetic jet actuator of the present invention, the vibration membrane separates the actuator cavity into two symmetrical cavities in the upper and lower parts, and the left side walls of the upper and lower cavities are provided with fluid outlets, and jets are alternately ejected from the fluid outlets of the upper and lower cavities, and the phases of the jets ejected from the fluid outlets of the upper and lower cavities differ by 180°, so the jet ejected from the first jet ejection port can be considered to be continuous; the right side walls of the upper and lower cavities are provided with fluid inlets, and the fluids are alternately sucked in through the fluid inlets of the upper and lower cavities, and the phases of the fluids sucked in by the fluid inlets of the upper and lower cavities differ by 180°, so the fluid sucked in from the outside through the first fluid suction port can be considered to be continuous.

[0015] Furthermore, the wing of the present invention is provided with more than one second blow-suction separation synthetic jet actuator, the second blow-suction separation synthetic jet actuator comprises an actuator cavity and a vibrating membrane arranged in the actuator cavity, the actuator cavity is provided with at least one fluid inlet and at least one fluid outlet, the fluid inlet is provided with a first one-way guide structure for restricting the fluid to enter but not exit, the fluid outlet is provided with a second one-way guide structure for restricting the fluid to exit but not enter, all the fluid inlets of the second blow-suction separation synthetic jet actuator are connected to the second fluid suction port, and among all the fluid outlets of the second blow-suction separation synthetic jet actuator, at least a part is connected to the second main jet injection port, and another part is connected to the second relay jet injection port.

[0016] Furthermore, the first one-way flow guide structure of the present invention is a Tesla one-way flow guide channel that restricts fluid from entering but not exiting, and the second one-way flow guide structure is a Tesla one-way flow guide channel that restricts fluid from exiting but not entering.

[0017] Furthermore, the first one-way flow guide structure of the present invention is a Tesla one-way valve installed at the fluid inlet and having a Tesla one-way flow guide channel that restricts the fluid to only enter but not exit, and the second one-way flow guide structure is a Tesla one-way valve installed at the fluid outlet and having a Tesla one-way flow guide channel that restricts the fluid to only exit but not enter.

[0018] Furthermore, the Tesla one-way flow guide channel described in the present invention includes a straight main flow channel and an arc-shaped return flow channel. Return flow channels connected to the direct flow channel are arranged on the left and right sides of the main flow channel, and the outlet direction of the return flow channel is the same as the flow direction of the fluid in the main flow channel.

[0019] Furthermore, the main flow channel of the present invention is a straight flow channel with a constant flow cross-section.

[0020] Furthermore, the inlet end or the outlet end of the main flow channel of the present invention adopts a flow cross-section contraction type structure or a flow cross-section expansion type structure.

[0021] Furthermore, the fluid inlet and fluid outlet of the present invention are arranged symmetrically or asymmetrically.

[0022] Furthermore, the fluid inlet and fluid outlet of the present invention are the same, or the number of the fluid inlet is greater than the number of the fluid outlet, or the number of the fluid inlet is less than the number of the fluid outlet. The distribution, arrangement, spacing, etc. of all fluid inlets are not limited, and the distribution, arrangement, spacing, etc. of all fluid outlets are not limited.

[0023] Furthermore, in the present invention, the structural parameters of the Tesla one-way flow guide channel in the first one-way flow guide structure and the Tesla one-way flow guide channel in the second one-way flow guide structure are the same or different, so as to adjust the different conduction capabilities of fluid suction and fluid ejection.

[0024] Through the above technical solution, the technical effects that the present invention can produce are:

[0025] 1. The circulation control method applicable to the wing provided by the present invention has the jet injection port and the fluid suction port at different positions, the jet injection port only sprays but does not suck, and the fluid suction port only sucks but does not spray. Furthermore, the first blowing-suction separation synthetic dual jet actuator is arranged in an array along the flow direction on the upper surface of the airfoil. The first jet injection port has the function of continuously spraying the jet outward, and the ejected high-energy jet flows downstream, continuously injecting energy into the low-energy boundary layer of the upper wall; at the same time, the first fluid suction port arranged not far downstream has the function of continuously sucking the surrounding fluid inward, and by continuously sucking away the low-energy boundary layer at the high-pressure area on the upper wall of the trailing edge of the airfoil, the energy of the boundary layer is maintained to resist the flow separation of the local fluid. Each synthetic dual jet actuator has the effect of resisting separation locally, playing the role of "micro-coordination". By arranging in an array along the flow direction, the effect of relay control can be achieved, thereby realizing the flow separation control of the entire upper wing surface. The present invention realizes the separation of blowing and suction of fluid, and solves the shortcomings of the traditional synthetic jet actuator, such as the common fluid inlet and outlet for fluid suction and injection, the complex flow field at the fluid inlet and outlet, and the mutual influence of blowing and suction (such as self-sufficient effect).

[0026] 2. The present invention provides a wing circulation control method located at the trailing edge, wherein a second main jet injection port, a second relay jet injection port and a second fluid suction port are arranged on the upper wall of the airfoil near the Coanda trailing edge, the second fluid suction port is arranged upstream of the second main jet injection port, the second main jet injection port is closer to the Coanda trailing edge, and the position is the starting point of the Coanda trailing edge, and the second relay jet injection port is arranged at the Coanda trailing edge, and the position is the separation point of the Coanda deflected airflow. The second fluid suction port continuously sucks in the low-energy boundary layer on the upper wall of the airfoil near the Coanda trailing edge to maintain the energy of the fluid on the upper wall, delaying the flow separation on the upper wall; the second main jet injection port continuously injects jets onto the Coanda wall, and the jet moves along the curved wall of the Coanda trailing edge under the action of the Coanda trailing edge, forming a deflected fluid at the trailing edge of the airfoil. The deflected fluid will separate at a certain position at the Coanda trailing edge, and the second relay jet injection port is set at the separation point of the deflected fluid, injecting energy into the deflected fluid that is about to separate again, causing it to undergo a secondary deflection, so that the airfoil has an aerodynamic curvature and increases the circulation of the wing.

[0027] 3. The present invention provides a blowing-suction separation synthetic double jet actuator. By designing a blowing-suction separation synthetic double jet actuator to achieve blowing-suction separation, the control efficiency of the synthetic double jet actuator can be fully utilized, and its environmental adaptability can be enhanced, so that the synthetic double jet actuator can work efficiently in more flow field environments.

[0028] 4. The Tesla unidirectional flow channel in the present invention has a simple structure and no movable mechanical parts. It can achieve a unidirectional control effect based on the flow principle. The traditional diaphragm type one-way valve control device, such as Figure 7 As shown in the figure, the one-way valve of its mechanical structure will have a certain blocking effect on the jet ejection, destroying the integrity of the flow field of the synthetic jet actuator, and when the frequency is high, its one-way effect will be greatly reduced or even cause fluid blockage. Tesla's one-way flow channel will not block the jet and can work at any frequency.

[0029] 5. The Tesla one-way valve in the present invention is a component that can be replaced as a whole. Figure 8 , 9 As shown in 10, the Tesla one-way valve configuration under different parameters can be pre-designed, and the entire valve can be replaced according to actual use and flow field conditions to improve efficiency and avoid repeated installation and disassembly of the entire actuator during use.

[0030] 6. The present invention can significantly increase the ability of the fluid on the upper surface of the two-dimensional airfoil to resist separation, and can achieve the effect of increasing lift by increasing the circulation. Compared with other cooperative jet technologies based on cooperative control principles, it also has the characteristics of low energy consumption, light structure weight, and easy miniaturization. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a schematic diagram of the principle of synthetic jet circulation control;

[0032] Figure 2 It is a structural schematic diagram of an embodiment of the present invention;

[0033] Figure 3 yes Figure 2 Schematic diagram of local control;

[0034] Figure 4 It is a structural schematic diagram of an embodiment of the present invention;

[0035] Figure 5 yes Figure 4 Control schematic diagram;

[0036] Figure 6 It is a schematic diagram of multiple Tesla one-way flow guide channels in series;

[0037] Figure 7 This is a schematic diagram of the flow field inside the Tesla unidirectional flow channel when the flow is positive;

[0038] Figure 8 This is a schematic diagram of the flow field inside the Tesla unidirectional flow channel when the flow is reverse;

[0039] Fig. 9 It is a structural diagram of a diaphragm type one-way valve;

[0040] Fig.10 1 is a schematic diagram of a replaceable Tesla one-way valve provided in an embodiment;

[0041] Fig.11 1 is a schematic diagram of a replaceable Tesla one-way valve provided in an embodiment;

[0042] Fig.12 1 is a schematic diagram of a replaceable Tesla one-way valve provided in an embodiment;

[0043] Fig.13 It is a structural schematic diagram of an embodiment of the present invention;

[0044] The symbols in the figure represent:

[0045] 1. Vibrating membrane; 2. Actuator cavity; 3. Jet inlet and outlet; 4. Fluid outlet; 5. Fluid inlet; 6. Coanda trailing edge; 7. First one-way guide structure; 8. Second one-way guide structure; 9. Main flow channel; 10. Return flow channel; 11. Diaphragm-type one-way valve; 12. First jet injection port; 13. First fluid suction port; 14. Second main jet injection port; 15. Second fluid suction port; 16. Second relay jet injection port.

[0046] The purpose, features and advantages of the present invention will be further described with reference to the accompanying drawings in conjunction with the embodiments. DETAILED DESCRIPTION

[0047] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0048] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0049] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0050] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0051] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0052] Reference Figure 2 In one embodiment, a circulation control method suitable for a wing is proposed, on the upper surface of the airfoil of the wing, a plurality of groups of blowing and suction separation port pairs consisting of a first jet injection port 12 and a first fluid suction port 13 are arranged in an array along the fluid flow direction of the upper surface of the airfoil starting from a position close to the leading edge of the wing;

[0053] Each blowing and suction separation port is aligned, and the first jet injection port 12 is arranged upstream of the first fluid suction port 13, that is, the first jet injection port 12 is closer to the leading edge of the wing than the first fluid suction port 13; the first jet injection port 12 continuously ejects a jet outward, and the ejected high-energy jet flows downstream, continuously injecting energy into the low-energy boundary layer on the upper surface of the airfoil; the first fluid suction port 13 continuously inhales the surrounding fluid inward, continuously sucks away the low-energy boundary layer at the high-pressure area on the upper surface of the airfoil downstream of the first jet injection port 12, maintains the energy of the boundary layer, and resists the flow separation of the local fluid;

[0054] A plurality of blowing-suction separation port pairs are arranged in an array along the fluid flow direction of the upper surface of the airfoil to form a blowing-suction relay control effect, thereby realizing flow separation control on the upper surface of the airfoil of the entire wing.

[0055] Reference Figure 3In this embodiment, a blowing-suction separation synthetic jet actuator is designed to realize the blowing-suction separation function of the blowing-suction separation port. More than one first blowing-suction separation synthetic jet actuator is arranged in the wing, and each group of blowing-suction separation ports corresponds to one first blowing-suction separation synthetic double jet actuator.

[0056] like Figure 3 As shown, the jet injection direction of the first jet injection port 12 is consistent with the tangent direction of the wall surface where the first jet injection port 12 is located, and the fluid suction direction of the first fluid suction port 13 is consistent with the tangent direction of the wall surface where the first fluid suction port 13 is located.

[0057] like Figure 3 As shown, the first blowing-suction separation synthetic jet actuator includes an actuator cavity 2 and a vibrating membrane 1 arranged in the actuator cavity 2, the actuator cavity 2 is provided with at least one fluid inlet 5 and at least one fluid outlet 4, the fluid inlet 5 is provided with a first one-way flow guide structure for restricting the fluid to enter but not exit, the fluid outlet 4 is provided with a second one-way flow guide structure for restricting the fluid to exit but not enter, all the fluid inlets 5 of the first blowing-suction separation synthetic jet actuator are connected to the corresponding first fluid suction port 12, and all the fluid outlets 5 of the first blowing-suction separation synthetic jet actuator are connected to the corresponding first jet injection port 13.

[0058] When the first blowing-suction separation synthetic double jet actuator is working, the fluid outlet 4 of the first blowing-suction separation synthetic double jet actuator is connected to the first jet injection port 12, and the jet is continuously ejected outward locally. The ejected high-energy jet flows downstream, and continuously injects energy into the local low-energy boundary layer. At the same time, the fluid inlet 5 of the first blowing-suction separation synthetic double jet actuator is connected to the first fluid suction port 13, and the fluid at the upper wall surface is continuously sucked away locally. The low-energy boundary layer at the first fluid suction port 13 is continuously sucked away, and the energy of the boundary layer is maintained to resist the flow separation of the local fluid at the location of the first fluid suction port 13, thereby increasing the circulation of the airfoil. In the present invention, each blowing-suction separation synthetic double jet actuator has the effect of resisting separation locally, and plays the role of "micro-coordination". At the same time, by arranging the first blowing-suction separation synthetic double jet actuator in an array along the flow direction, the local flow separation can be controlled separately by blowing and sucking step by step, and the effect of relay control can be achieved, thereby realizing the flow separation control of the entire upper wing surface.

[0059] Reference Figure 4An embodiment provides a circulation control method suitable for a wing, wherein the wing airfoil is an airfoil with a Coanda trailing edge, and a second main jet injection port 14, a second relay jet injection port 16 and a second fluid suction port 15 are arranged on the upper wall of the airfoil near the Coanda trailing edge, and the second fluid suction port 15 is arranged upstream of the second main jet injection port, and the second main jet injection port 14 is closer to the Coanda trailing edge and is located at the starting point of the Coanda trailing edge 6, and the second relay jet injection port 16 is arranged at the Coanda trailing edge and is located at the separation point of the Coanda deflected airflow. The second fluid suction port 15 continuously sucks in the low-energy boundary layer on the upper wall of the airfoil near the Coanda trailing edge to maintain the energy of the fluid on the upper wall and delay the flow separation on the upper wall; the second main jet injection port 14 continuously injects jets onto the Coanda wall. Under the action of the Coanda trailing edge, the jet moves along the curved wall of the Coanda trailing edge to form a deflected fluid at the trailing edge of the airfoil. The deflected fluid will separate at a position at the Coanda trailing edge. The second relay jet injection port 16 is arranged at the separation point of the deflected fluid to inject energy into the deflected fluid that is about to separate, so that it undergoes a secondary deflection, thereby giving the airfoil an aerodynamic curvature and increasing the circulation of the wing.

[0060] Reference Figure 5 In this embodiment, the blowing and suction separation synthetic jet actuator is designed to realize the blowing and suction separation function of the second main jet injection port 14, the second relay jet injection port 16 and the second fluid suction port 15. The wing airfoil is an airfoil with a Coanda trailing edge. There is more than one second blowing and suction separation synthetic jet actuator in the wing near the Coanda trailing edge, and the second blowing and suction separation synthetic jet actuator includes an actuator cavity 2 and a vibrating membrane 1 arranged in the actuator cavity 2. The actuator cavity 2 is provided with at least one fluid inlet 5 and at least one fluid outlet 4. The fluid inlet 5 is provided with a first one-way flow guide structure that restricts the fluid to only enter but not exit, and the fluid outlet 4 is provided with a second one-way flow guide structure that restricts the fluid to only exit but not enter. All fluid inlets 5 of the second blowing and suction separation synthetic jet actuator are connected to the second fluid suction port 15, and at least one part of all fluid outlets 4 of the second blowing and suction separation synthetic jet actuator is connected to the second main jet injection port 14, and the other part is connected to the second relay jet injection port 16.

[0061] Reference Figure 5The wing airfoil is an airfoil with a Coanda trailing edge, and a second blowing-suction separation synthetic double jet actuator is installed in the wing. The second blowing-suction separation synthetic double jet actuator has a fluid inlet 5 that only enters but does not exit, and a fluid outlet 4 that only exits but does not enter. The second fluid suction port 15 is arranged upstream of the second main jet injection port 14, and the second main jet injection port 14 is closer to the Coanda trailing edge and is located at the starting point of the Coanda trailing edge 6. The second relay jet injection port 16 is arranged at the Coanda trailing edge 6 and is located at the separation point of the Coanda deflected airflow. The second fluid suction port 15 is arranged on the upper wall of the airfoil near the Coanda trailing edge 6, the second main jet injection port 14 is arranged at the starting point of the Coanda trailing edge 6, and the second relay jet injection port 16 is arranged at the separation point of the Coanda deflected airflow ejected by the second main jet injection port 14. The second fluid suction port 15 is arranged upstream of the second main jet injection port 14, the second main jet injection port 14 is located at the starting point of the Coanda trailing edge, and the second relay jet injection port 16 is located at the separation point of the Coanda deflected airflow. The second main jet injection port 14 is connected to the fluid outlet 4 of the upper cavity of the second blowing-suction separation synthetic double jet actuator, the second relay jet injection port 16 is connected to the fluid outlet 4 of the lower cavity of the second blowing-suction separation synthetic double jet actuator, and the second fluid suction port 15 is connected to the fluid inlet 5 of the second blowing-suction separation synthetic double jet actuator. The fluid inlet 5 of the second blowing-suction separation synthetic double jet actuator continuously sucks in the low-energy boundary layer on the upper wall of the airfoil close to the Coanda trailing edge through the second fluid suction port 15 to maintain the energy of the fluid on the upper wall and delay the flow separation on the upper wall. The fluid outlet 4 of the second blowing-suction separation synthetic double jet actuator continuously ejects jets through the second main jet injection port 14. Under the action of the Coanda trailing edge, the jet moves along the curved wall surface of the Coanda trailing edge to form a deflected fluid at the trailing edge of the airfoil. The deflected fluid will separate at a certain position at the Coanda trailing edge. The second relay jet injection port 16 is set at the separation point of the deflected fluid to inject energy into the deflected fluid that is about to separate, so that it undergoes a second deflection, so that the airfoil has an aerodynamic curvature and the circulation of the wing is increased.

[0062] Reference Fig.13, this embodiment provides a circulation control method suitable for a wing, wherein the wing airfoil is an airfoil with a Coanda trailing edge. On the upper surface of the wing airfoil, a plurality of groups of blowing and suction separation port pairs consisting of a first jet injection port 12 and a first fluid suction port 13 are arranged in an array along the fluid flow direction of the upper surface of the airfoil starting from a position close to the leading edge of the wing; in each blowing and suction separation port pair, the first jet injection port 12 is arranged upstream of the first fluid suction port 13, that is, the first jet injection port 12 is closer to the leading edge of the wing than the first fluid suction port 13; the first jet injection port 12 continuously ejects a jet outward, and the ejected high-energy jet flows downstream, continuously injecting energy into the low-energy boundary layer on the upper surface of the airfoil; the first fluid suction port 13 continuously inhales the surrounding fluid inward, continuously sucking away the low-energy boundary layer at the high-pressure area on the upper surface of the airfoil downstream of the first jet injection port 12, maintaining the energy of the boundary layer, and resisting the flow separation of the local fluid. At the same time, a second main jet injection port 14, a second relay jet injection port 16 and a second fluid suction port 15 are arranged on the upper wall surface of the airfoil near the Coanda trailing edge. The second fluid suction port 15 is arranged upstream of the second main jet injection port. The second main jet injection port 14 is closer to the Coanda trailing edge and is located at the starting point of the Coanda trailing edge 6. The second relay jet injection port 16 is arranged at the Coanda trailing edge and is located at the separation point of the Coanda deflected airflow. The second fluid suction port 15 continuously sucks in the low-energy boundary layer on the upper wall of the airfoil near the Coanda trailing edge to maintain the energy of the fluid on the upper wall and delay the flow separation on the upper wall; the second main jet injection port 14 continuously injects jets onto the Coanda wall. Under the action of the Coanda trailing edge, the jet moves along the curved wall of the Coanda trailing edge to form a deflected fluid at the trailing edge of the airfoil. The deflected fluid will separate at a position at the Coanda trailing edge. The second relay jet injection port 16 is arranged at the separation point of the deflected fluid to inject energy into the deflected fluid that is about to separate, so that it undergoes a secondary deflection, thereby giving the airfoil an aerodynamic curvature and increasing the circulation of the wing.

[0063] Fig.13 The embodiment shown is Figure 2 The embodiments shown and Figure 4 The combination of the embodiments shown in the figure, the design, arrangement and principle of the first blowing-suction separation synthetic double jet actuator and the second blowing-suction separation synthetic double jet actuator are respectively Figure 2 The embodiments shown and Figure 4 The same as the illustrated embodiment, the first blow-suction separation synthetic double jet exciter and the second blow-suction separation synthetic double jet exciter are integrated into the interior of the wing at the same time.

[0064] Fig.13In the process, the fluid outlet 4 of the first blowing-suction separation synthetic dual jet actuator is connected to the first jet injection port 12, and the jet is continuously ejected outward locally. The ejected high-energy jet flows downstream, and continuously injects energy into the local low-energy boundary layer. At the same time, the fluid inlet 5 of the first blowing-suction separation synthetic dual jet actuator is connected to the first fluid suction port 13, and the fluid at the upper wall is continuously sucked away locally. The low-energy boundary layer at the first fluid suction port 13 is continuously sucked away, and the energy of the boundary layer is maintained to resist the flow separation of the local fluid at the location of the upper wall actuator, thereby increasing the circulation of the airfoil and achieving a "micro-synergy" effect. At the same time, by arranging the first blowing-suction separation synthetic dual jet actuator in an array along the flow direction, the local flow separation can be controlled separately by blowing and sucking step by step, thereby achieving a relay effect and better controlling the flow separation of the entire upper wall. Specifically, a plurality of first blow-suction separation synthetic double jet actuators are installed in an array along the flow direction inside the wing, the first blow-suction separation synthetic double jet actuator having a fluid inlet 5 for inflow only and a fluid outlet 4 for outflow only, a first jet injection port 12 is arranged near the leading edge of the airfoil at the local position of each actuator, and a first fluid suction port 13 is arranged near the trailing edge at the local position of each actuator, the first jet injection port 12 is connected to the fluid outlet 4 of the first blow-suction separation synthetic double jet actuator, and the first fluid suction port 13 is connected to the fluid inlet 5 of the first blow-suction separation synthetic double jet actuator.

[0065] at the same time Fig.13 In the illustrated embodiment, a second blowing-suction separation synthetic double jet actuator is installed in the wing near the Coanda trailing edge 6. The fluid inlet 5 of the second blowing-suction separation synthetic double jet actuator continuously sucks in the low-energy boundary layer near the Coanda trailing edge on the upper wall of the airfoil through the second fluid suction port 15 to maintain the energy of the fluid on the upper wall and delay the flow separation on the upper wall. The fluid outlet 4 of the second blowing-suction separation synthetic double jet actuator continuously ejects jets through the second jet injection port 14. Under the action of the Coanda trailing edge, the jet moves along the curved wall of the Coanda trailing edge to form a deflected fluid at the trailing edge of the airfoil. The deflected fluid will separate at a certain position at the Coanda trailing edge. The second relay jet injection port 16 is arranged at the separation point of the deflected fluid to inject energy into the deflected fluid that is about to separate, so that it undergoes a secondary deflection, so that the airfoil has an aerodynamic curvature and the circulation of the wing is increased. Specifically, the second fluid suction port 15 is arranged upstream of the second jet injection port 14, the second main jet injection port 14 is located at the starting point of the Coanda trailing edge, and the second relay jet injection port 16 is located at the separation point of the Coanda deflected airflow. The second main jet injection port 14 is connected to the fluid outlet 4 of the upper cavity of the second blowing-suction separation synthetic double jet actuator, the second relay jet injection port 16 is connected to the fluid outlet 4 of the lower cavity of the second blowing-suction separation synthetic double jet actuator, and the second fluid suction port 15 is connected to the fluid inlet 5 of the second blowing-suction separation synthetic double jet actuator.

[0066] In one embodiment, a blow-suction separation synthetic double jet actuator is provided, and the first blow-suction separation synthetic double jet actuator and the second blow-suction separation synthetic double jet actuator in the above embodiments can adopt this structure. Specifically, the blow-suction separation synthetic double jet actuator comprises an actuator cavity 2 and a vibrating membrane 1 arranged in the actuator cavity 2, and the actuator cavity 2 is provided with at least one fluid inlet 5 and at least one fluid outlet 4. The fluid inlet 5 is provided with a first one-way flow guide structure 7 that restricts the fluid to only enter and not exit, and the fluid outlet is provided with a second one-way flow guide structure 8 that restricts the fluid to only exit and not enter. The first one-way flow guide structure 7 is a Tesla one-way flow guide channel that restricts the fluid to only enter and not exit, and the second one-way flow guide structure 8 is a Tesla one-way flow guide channel that restricts the fluid to only exit and not enter. Compared with the traditional synthetic jet actuator, the blow-suction separation synthetic jet actuator based on the Tesla one-way flow guide channel can realize that only fluid is ejected from the fluid outlet 4, and only fluid is allowed to enter the fluid inlet 5.

[0067] like Figure 7 As shown, the Tesla unidirectional flow guide channel for only exiting but not entering provided in the fluid outlet 4 and the Tesla unidirectional flow guide channel for only entering but not exiting provided in the fluid inlet 5 can be an integrated structure with the actuator cavity 2. Those skilled in the art can customize the blowing-suction separation synthetic jet excitation according to the needs of the actual application scenario, and by pre-designing various structural parameters of the Tesla unidirectional flow guide channel for only exiting but not entering provided in the fluid outlet 4 and the Tesla unidirectional flow guide channel for only entering but not exiting provided in the fluid inlet 5, the manufactured blowing-suction separation synthetic jet actuator can meet the application requirements, and the manufactured blowing-suction separation synthetic jet actuator can have the conduction capacity required by the design for fluid suction and fluid ejection.

[0068] In the above embodiment, the interior of the fluid inlet 5 is processed into a Tesla one-way flow channel that can only enter but not exit, and the interior of the fluid outlet 4 is processed into a Tesla one-way flow channel that can only exit but not enter. Since the Tesla one-way flow channel has the characteristic of one-way conduction, it can limit the fluid to enter only from the fluid inlet 5 and flow out from the fluid outlet 4, so as to achieve the effect of controlling the one-way conduction of the inlet and outlet, and no additional energy is required to control its opening and closing. At the same time, compared with the diaphragm type one-way valve 11 (such as Fig. 9 As shown, the synthetic jet actuator body is provided with at least one fluid inlet 5 and at least one fluid outlet 4, the fluid inlet 5 is provided with a first one-way flow guide structure 7 that restricts the fluid from entering but not exiting, and the fluid outlet is provided with a second one-way flow guide structure 8 that restricts the fluid from exiting but not entering. The first one-way flow guide structure 7 and the second one-way flow guide structure 8 are both diaphragm-type one-way valves 11), which have almost no effect on the downstream flow field of the jet.

[0069] In one embodiment, the synthetic jet actuator body includes an actuator cavity 2 and a vibrating membrane 1 disposed in the actuator cavity 2, and the actuator cavity 2 is provided with at least one fluid inlet 5 and at least one fluid outlet 4. The first one-way flow guide structure 7 is a Tesla one-way valve installed at the fluid inlet 5 and having a Tesla one-way flow guide channel that restricts fluid from entering but not exiting, and the second one-way flow guide structure 7 is a Tesla one-way valve installed at the fluid outlet 4 and having a Tesla one-way flow guide channel that restricts fluid from entering but not exiting. The Tesla one-way valve is detachably installed at the fluid inlet and the fluid outlet, so that it is easy to disassemble and replace. When the application requirements change, the Tesla one-way valve with a suitable parameter structure can be replaced in real time, so that the blowing and suction separation synthetic jet actuator after the Tesla one-way valve is replaced meets the application requirements, and the manufactured blowing and suction separation synthetic jet actuator has the conduction capacity required by the design for fluid suction and fluid ejection.

[0070] The vibration membrane 1 in the present invention can be a piezoelectric ceramic sheet. The actuator cavity 2 can be a single cavity structure, that is, only one cavity, such as Figure 7 The actuator cavity 2 may also adopt a double-cavity structure, that is, the vibrating membrane divides the actuator cavity into two independent cavities on the left and right, such as Figure 3 , Figure 5 In the dual-cavity exciter cavity 2, the two cavities can be symmetrically arranged on the left and right sides of the vibration membrane, or can be asymmetrically distributed. Figure 3 The exciter cavity 2 of the double-cavity structure is symmetrically arranged on both sides of the vibration membrane.

[0071] In the present invention, the first one-way flow guide structure 7 may have only one Tesla one-way flow guide channel that restricts fluid from entering but not exiting, or may be formed by connecting multiple Tesla one-way flow guide channels that restrict fluid from entering but not exiting in series. Similarly, the second one-way flow guide structure 8 may have only one Tesla one-way flow guide channel that restricts fluid from exiting but not entering, or may be formed by connecting multiple Tesla one-way flow guide channels that restrict fluid from exiting but not entering in series. By increasing the number of Tesla one-way flow guide channels connected in series, the one-way conductivity can be increased, such as Figure 6 shown.

[0072] Reference Figure 7 , which is a schematic diagram of the flow field inside the Tesla unidirectional flow channel. The Tesla unidirectional flow channel includes a straight main flow channel 9 and an arc-shaped return flow channel 10. The return flow channels 10 connected to the main flow channel 9 are arranged on the left and right sides of the main flow channel 9. The outlet direction of the return flow channel 10 is the same as the flow direction of the fluid in the main flow channel. The return flow channel 10 includes an arc segment and an oblique line segment. The arc segment and the oblique line segment are connected as a whole to form a return channel. The ends of the arc segment and the ends of the oblique line segment are respectively connected to the upstream and downstream positions of the main flow channel.

[0073] The fluid can only enter the actuator cavity 2 from the fluid inlet 5, and the fluid ejected from the actuator cavity 2 can only be ejected from the actuator cavity 2 from the fluid outlet 4. When the fluid flows through the Tesla one-way flow channel, the forward flowing fluid is not blocked. Under the influence of the return flow channel 10, part of the main flow of the fluid will enter the return flow channels on both sides of the main flow channel. Under the guidance of the return flow channel, this part of the fluid will re-enter the main flow channel through the return flow channel outlet, avoiding the loss of jet energy. The Tesla one-way flow channel has a simple structure, no movable mechanical parts, and can achieve a one-way control effect based on the flow principle.

[0074] like Figure 8 As shown in the figure, a schematic diagram of the flow field inside the Tesla unidirectional flow channel under reverse flow conditions is shown. When the fluid flows through the Tesla unidirectional flow channel in reverse, the main flow of the fluid will expand to both sides when flowing through the oblique line segment of the return flow channel, and enter the return flow channels on both sides through the end of the oblique line segment. Under the guidance of the return flow channel, it flows out through the arc segment end of the return flow channel. However, at this time, the main flow velocity is opposite to the velocity of the fluid flowing out of the return flow channel. The fluid flowing out of the return flow channel will collide with the main flow here, thereby forming a stagnation, preventing the reverse flow from continuing to develop, and achieving the effect of unidirectional conduction. The unidirectional conductivity of the Tesla unidirectional flow channel is related to the ratio of its main flow channel width D and the return flow channel width d. When D / d>3, the main flow channel is wider than the return flow channel, the fluid entering the return flow channel becomes less, and the unidirectional conductivity becomes weaker. When the ratio increases to a certain extent, it can be understood that the return flow channel does not exist and has no effect on the main flow, that is, it loses unidirectional conductivity; when D / d<3, it can be considered that the unidirectional conductivity of the Tesla unidirectional flow channel is good. When the ratio becomes smaller and smaller, its unidirectional conductivity is better, but it will affect the flow rate of the main flow channel and the volume occupied by the entire Tesla unidirectional flow channel. Therefore, it is most appropriate for D / d to be between 1-3.

[0075] Furthermore, the Tesla unidirectional flow channel of the present invention can be flexibly designed to adjust the different conduction capabilities of fluid intake and fluid ejection. In some embodiments, the main flow channel of the Tesla unidirectional flow channel is a straight flow channel with a constant flow cross section, such as Figure 6 , Figure 7 and Fig.10 shown.

[0076] In some embodiments, the inlet or outlet of the main channel 9 of the Tesla one-way flow channel adopts a flow cross-section contraction type structure or a flow cross-section expansion type structure. Fig.11 As shown, the Tesla unidirectional flow channel is a Tesla unidirectional flow channel that restricts fluid from only flowing out but not flowing in. A flow cross-section contraction type structure is adopted at the outlet end of the main flow channel 9. Fig.11 The Tesla one-way guide flow channel shown can further compress and accelerate the ejected jet before ejection.

[0077] Furthermore, the structural parameters of the Tesla unidirectional flow channel in the first unidirectional flow guide structure of the present invention are the same or different from those of the Tesla unidirectional flow channel in the second unidirectional flow guide structure to adjust the different conduction capabilities of fluid suction and fluid ejection. The structural parameters of the Tesla unidirectional flow channel include the flow cross-sectional area of ​​the main channel, the flow cross-sectional area of ​​the return channel, the angle between the return channel and the main channel, the contraction ratio of the contraction section set at the outlet end of the main channel (i.e., the ratio of the flow cross-sectional areas at both ends of the contraction section), and the like.

[0078] Compare Fig.10 , Fig.11 and Fig.12 , Fig.10 The flow cross-sectional area of ​​the return flow channel is reduced, specifically, the flow cross-sectional area of ​​the return flow channel is reduced by reducing the width of the return flow channel. The flow cross-sectional area of ​​the main channel is about 3 times the flow cross-sectional area of ​​a single return flow channel. Fig.11 In the invention, a flow cross-section contraction structure is adopted at the outlet end of the main flow channel, so that the ejected jet can be further compressed and accelerated before being ejected. Fig.12 The angle between the return flow channel 10 and the main flow channel 9 is reduced. In practical applications, the Tesla one-way valve with suitable structural parameters of the Tesla one-way flow guide channel can be replaced at any time according to different flow field environment needs.

[0079] The blowing and suction separation synthetic jet actuator provided by the present invention has an unlimited number of fluid inlets and fluid outlets, an unlimited arrangement of the fluid inlets and fluid outlets, an unlimited position of the fluid inlets and fluid outlets on the actuator cavity, and an unlimited size and shape of the fluid inlets and fluid outlets. The fluid inlet and jet outlet are provided on the cavity wall of the actuator cavity, and the specific positions can be flexibly arranged to meet the placement requirements and use requirements of the actuator under different application scenarios. The fluid inlet and fluid outlet can be symmetrical positions or asymmetrical positions, and the number of fluid inlets and fluid outlets can be equal or unequal. For example, in some embodiments, the number of fluid inlets and fluid outlets is the same. In some embodiments, the number of fluid inlets is greater than the number of fluid outlets. In some embodiments, the number of fluid inlets is less than the number of fluid outlets. The shapes of the fluid inlet and fluid outlet can be the same or different, and can be any regular or irregular shape such as rectangle, circle, square, ellipse, etc. In addition, the shape of the exciter cavity in the present invention is not limited, and can be various regular or irregular three-dimensional shapes such as a cuboid, a cube, a sphere, a cylinder, an ellipsoid, etc. Similarly, the shape of the cavity wall on the exciter cavity where the fluid inlet and / or the fluid outlet is provided is not limited, and can be a plane, an arc surface or other curved surfaces and irregular surfaces, and can be freely designed according to the surface to be installed. Technical personnel in this field can make reasonable designs and selections according to actual needs.

[0080] The blowing and suction separation synthetic jet actuator provided by the present invention can flexibly adjust the number, distribution, position, angle, shape, etc. of the fluid inlet 5 and the fluid outlet 4 according to its application requirements, and can realize the generation of synthetic jets with multiple functions by controlling the opening and closing of the Tesla one-way valve and symmetrical or asymmetrical arrangement of the fluid inlet 5 and the fluid outlet 4. The biggest difference between the present invention and the traditional synthetic jet actuator is that the fluid inlet 5 and the fluid outlet 4 are independently arranged, rather than the same opening serving as the fluid inlet and outlet at the same time, and the present invention realizes the blowing and suction separation of the jet.

[0081] The above are only preferred embodiments of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should be regarded as the protection scope of the present invention.

Claims

1. A circulation control method for a wing, characterized in that: On the upper surface of the airfoil of the wing, a plurality of groups of blow-suction separation port pairs consisting of a first jet injection port and a first fluid suction port are arranged in an array along the fluid flow direction of the upper surface of the airfoil starting from a position close to the leading edge of the wing; Each blow-suction separation port is aligned, and the first jet injection port is arranged upstream of the first fluid suction port, that is, the first jet injection port is closer to the leading edge of the wing than the first fluid suction port; the first jet injection port continuously ejects jets outward, and the ejected high-energy jets flow downstream, continuously injecting energy into the low-energy boundary layer on the upper surface of the airfoil; the first fluid suction port continuously sucks in the surrounding fluid inward, continuously sucking away the low-energy boundary layer at the high-pressure area on the upper surface of the airfoil downstream of the first jet injection port, maintaining the energy of the boundary layer, and resisting the flow separation of the local fluid; A plurality of blowing and suction separation port pairs are arranged in an array along the fluid flow direction of the upper surface of the airfoil to form a blowing and suction relay control effect, thereby realizing flow separation control on the upper surface of the airfoil of the entire wing; The wing airfoil is an airfoil with a Coanda trailing edge, and a second main jet injection port, a second relay jet injection port, and a second fluid suction port are arranged on the upper wall of the airfoil near the Coanda trailing edge, the second fluid suction port is arranged upstream of the second main jet injection port, the second main jet injection port is closer to the Coanda trailing edge, and the position is the starting point of the Coanda trailing edge, and the second relay jet injection port is arranged at the Coanda trailing edge, and the position is the separation point of the Coanda deflected airflow; The second fluid suction port continuously sucks in the low-energy boundary layer on the upper wall of the airfoil near the Coanda trailing edge to maintain the energy of the fluid on the upper wall and delay the flow separation on the upper wall; the second main jet injection port continuously injects jets onto the Coanda wall. Under the action of the Coanda trailing edge, the jet moves along the curved wall of the Coanda trailing edge to form a deflected fluid at the trailing edge of the airfoil. The deflected fluid will separate at a position at the Coanda trailing edge. The second relay jet injection port is set at the separation point of the deflected fluid to inject energy into the deflected fluid that is about to separate, causing it to undergo a secondary deflection, thereby giving the airfoil an aerodynamic curvature and increasing the circulation of the wing.

2. The circulation control method applicable to a wing according to claim 1, characterized in that: The jet injection direction of the first jet injection port is consistent with the tangent direction of the wall surface where the first jet injection port is located, and the fluid suction direction of the first fluid suction port is consistent with the tangent direction of the wall surface where the first fluid suction port is located.

3. The circulation control method applicable to a wing according to claim 1 or 2, characterized in that: More than one first blow-suction separation synthetic jet actuator is arranged in the wing, and each group of blow-suction separation ports corresponds to a first blow-suction separation synthetic double jet actuator; the first blow-suction separation synthetic jet actuator includes an actuator cavity and a vibration membrane arranged in the actuator cavity, and the actuator cavity is provided with at least one fluid inlet and at least one fluid outlet, the fluid inlet is provided with a first one-way guide structure for limiting the fluid to only enter but not exit, and the fluid outlet is provided with a second one-way guide structure for limiting the fluid to only exit but not enter, all fluid inlets of the first blow-suction separation synthetic jet actuator are connected to the corresponding first fluid suction port, and all fluid outlets of the first blow-suction separation synthetic jet actuator are connected to the corresponding first jet injection port.

4. The circulation control method applicable to a wing according to claim 3, characterized in that: In the first blowing-suction separation synthetic jet actuator, the vibration membrane separates the actuator cavity into two symmetrical cavities in the upper and lower directions. The left side walls of the upper and lower cavities are provided with fluid outlets, and jets are alternately ejected from the fluid outlets of the upper and lower cavities, and the jets ejected from the fluid outlets of the upper and lower cavities differ in phase by 180°. The right side walls of the upper and lower cavities are provided with fluid inlets, and the fluids are alternately sucked in through the fluid inlets of the upper and lower cavities, and the fluids inhaled by the fluid inlets of the upper and lower cavities differ in phase by 180°.

5. The circulation control method applicable to a wing according to claim 1, characterized in that: There is more than one second blow-suction separation synthetic jet actuator arranged in the wing, and the second blow-suction separation synthetic jet actuator includes an actuator cavity and a vibrating membrane arranged in the actuator cavity, and the actuator cavity is provided with at least one fluid inlet and at least one fluid outlet, the fluid inlet is provided with a first one-way guide structure for restricting the fluid to enter but not exit, and the fluid outlet is provided with a second one-way guide structure for restricting the fluid to exit but not enter, all the fluid inlets of the second blow-suction separation synthetic jet actuator are connected to the second fluid suction port, and among all the fluid outlets of the second blow-suction separation synthetic jet actuator, at least a part is connected to the second main jet injection port, and another part is connected to the second relay jet injection port.

6. The circulation control method applicable to a wing according to claim 4 or 5, characterized in that: The first one-way flow guide structure is a Tesla one-way flow guide channel that restricts fluid from entering but not exiting, and the second one-way flow guide structure is a Tesla one-way flow guide channel that restricts fluid from exiting but not entering.

7. The circulation control method applicable to a wing according to claim 4 or 5, characterized in that: The first one-way flow guiding structure is a Tesla one-way valve installed at the fluid inlet and having a Tesla one-way flow guiding channel that restricts the fluid to only enter but not exit. The second one-way flow guiding structure is a Tesla one-way valve installed at the fluid outlet and having a Tesla one-way flow guiding channel that restricts the fluid to only exit but not enter.

8. The circulation control method applicable to a wing according to claim 6, characterized in that: The Tesla one-way flow guide channel includes a straight main flow channel and an arc-shaped return flow channel. Return flow channels connected to the direct flow channel are arranged on the left and right sides of the main flow channel, and the outlet direction of the return flow channel is the same as the flow direction of the fluid in the main flow channel.

9. The circulation control method applicable to a wing according to claim 8, characterized in that: The main flow channel is a straight flow channel with a constant flow cross section; or the inlet end or the outlet end of the main flow channel adopts a flow cross section contraction type structure or a flow cross section expansion type structure.

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