A plasma excitation device

Abstract

The utility model discloses a kind of plasma excitation devices, and plasma excitation device includes wing and tilting slope, wing and tilting slope are equipped with plasma exciter;Rotating assembly is equipped between wing and tilting slope;Connecting rod mechanism is equipped beside tilting slope;Power device is equipped at the end of connecting rod mechanism;Aircraft flight stage, the angle between tilting slope and wing is changed by controlling connecting rod mechanism, so that plasma exciter generates different intensity jet, inhibits flow separation, improves flow field quality, while the whole device and moving part are buried in wing interior, and the structure of device has no influence on wing itself aerodynamic shape.

Description

Technical Field

[0001] This utility model relates to the field of exciter technology, and in particular to a plasma excitation device. Background Technology

[0002] When conventional aircraft fly at high angles of attack, boundary layer separation often occurs on the wing surface due to insufficient resistance to adverse pressure gradients. This leads to a significant loss of lift, a sharp increase in drag, and a deterioration of aerodynamic characteristics, potentially causing stall or even a crash. Therefore, flow separation on the wing surface is a critical issue limiting aircraft aerodynamic efficiency and flight safety. To address this problem, active flow control technology can be used to control flow separation on lifting surface components such as wings and tail fins, suppressing flow separation and thus improving the aircraft's aerodynamic performance at high angles of attack.

[0003] For suppressing flow separation in airfoils, active flow control technology applies a disturbance to the external flow field via an exciter. After coupling with the mainstream flow field, boundary layer separation and reattachment or a delayed separation point can be achieved, effectively improving the flow separation problem. In recent years, with the development of technology, surface dielectric barrier discharge plasma exciters have been widely used in the field of active flow control technology due to their advantages such as simple structure and low cost. When using plasma excitation to suppress flow separation in airfoils, the exciter can be placed on the leading edge of the airfoil, and an alternating or pulsed high-voltage current can be input to the plasma exciter. The exciter will release a surface jet to the outside. After the jet is injected into the mainstream flow field of the airfoil, it can promote the mixing of the boundary layer airflow, enhance the kinetic energy of the bottom airflow, thereby enhancing its resistance to pressure gradient and suppressing the separation phenomenon. Furthermore, conventional plasma exciters can be placed on a very thin plane, and when installed on the airfoil surface, they have little impact on the shape of the airfoil.

[0004] Currently, conventional plasma actuators perform well at low speeds, but their ability to control flow separation becomes significantly insufficient when the incoming flow velocity increases to above 30 m / s, resulting in minimal improvement in aircraft aerodynamic performance. This characteristic severely limits the application range of plasma excitation. As the flight Mach number and incoming flow Reynolds number increase, the kinetic energy of the external flow field on the wing increases. To achieve flow separation suppression, the actuator needs to generate a sufficiently strong jet intensity. However, the jet intensity generated by conventional planar dielectric barrier discharge plasma actuators exhibits a threshold effect with voltage amplitude; further increasing the voltage will not increase the excitation intensity but may instead damage the actuator.

[0005] Therefore, the main problem is how to increase the intensity of the jet generated by the plasma exciter and improve the airflow separation control effect of the wing under high-speed conditions without affecting the aerodynamic shape of the aircraft. Utility Model Content

[0006] The purpose of this invention is to solve the technical problems existing in the prior art and to provide a plasma excitation device.

[0007] To achieve the above objectives, the technical solution provided by this utility model is: a plasma excitation device, including a wing, a rotating assembly, and a linkage mechanism. A jet port is provided on the wing, and a tilting ramp is rotatably connected to the jet port through the rotating assembly. The linkage mechanism is connected to the rotating assembly to drive the rotating assembly to rotate. A plasma exciter is provided on the tilting ramp and the wing. The plasma exciter includes a buried electrode and an exposed electrode. The buried electrode is installed on the upper surface of the wing and is covered with an insulating material that extends to the surface of the tilting ramp. The exposed electrode is installed on the insulating material located on the surface of the tilting ramp. The buried electrode and the exposed electrode are aligned with each other and parallel to the edges.

[0008] Preferably, the linkage mechanism includes a limiting support fixed to the wing, a first link, a second link, and a third link. Limiting holes are provided on both the front and rear sides of the middle part of the limiting support, and the second link is slidably connected in the limiting holes. A servo motor is provided on the inner side of the right end of the limiting support. The output end of the servo motor is connected to a rotating shaft. The rotating shaft extends to the outside of the limiting support and is fixedly connected to a drive rod. The drive rod is hinged to the right side of the first link by a pin. The left side of the first link is hinged to the right side of the second link by a pin. The left side of the second link is hinged to the right side of the third link by a pin. A transmission shaft is fixedly provided on one side of the middle of the tilting slope and is hinged to the left side of the third link.

[0009] Preferably, the rotating assembly includes a pin and a mounting bracket fixedly mounted on the wing. The mounting bracket is rotatably connected to the tilting ramp via the pin. The mounting bracket and the tilting ramp are provided with coaxial holes that mate with the pin. The pin passes through the tilting ramp and is rotatably connected to the coaxial hole of the mounting bracket and the left end of the limiting bracket.

[0010] This utility model also discloses a control method for the aforementioned plasma excitation device. Specifically, the control method involves: first, powering on the servo motor and the plasma exciter; rotating the servo motor causes the first link to move, which in turn moves the second link forward or backward; subsequently, the position of the third link changes, causing the transmission shaft to move the tilting ramp upward or downward, thereby changing the angle between the wing and the tilting ramp and altering the jet intensity; wherein, under the same voltage, the smaller the angle between the wing and the tilting ramp, the stronger the jet intensity generated by the plasma exciter, and the stronger the ability to suppress flow separation, thus improving the flow field quality through the increased jet intensity generated by the plasma exciter.

[0011] The beneficial effects of this utility model are:

[0012] In this invention, when the aircraft is flying at a high angle of attack, the rotation of the servo motor is adjusted to drive the linkage mechanism to move, thereby changing the angle between the wing and the tilting plane. This alters the intensity of the jet flow generated by the plasma exciter, increasing the excitation intensity value and suppressing flow separation compared to conventional planar exciters. This improves the flow field quality and optimizes aerodynamic performance. Meanwhile, the entire device and moving parts are embedded inside the wing, so the structure of the device has virtually no impact on the aerodynamic shape of the wing itself. Attached Figure Description

[0013] The accompanying drawings, which are provided to further illustrate the present invention and constitute a part of the present invention, illustrate exemplary embodiments of the present invention and are used to explain the present invention, but do not constitute an undue limitation of the present invention.

[0014] Figure 1 This is a schematic diagram of the actuator being installed on the wing in this utility model;

[0015] Figure 2 This is a three-dimensional structural diagram of the exciter in this utility model;

[0016] Figure 3 This is a schematic diagram of the rotating component structure in this utility model;

[0017] Figure 4 This is a schematic diagram illustrating the working principle of the exciter in this utility model;

[0018] Figure 5 This is a schematic diagram of the transmission component structure in this utility model;

[0019] Figure 6 This is a schematic diagram of the transmission assembly installed on the wing in this utility model.

[0020] Attached image captions:

[0021] 1. Wing; 2. Jet nozzle; 3. Insulating material; 4. Buried electrode; 5. Exposed electrode; 6. Tilting ramp; 7. Pin; 8. Mounting bracket; 9. Servo; 10. Limiting bracket; 11. First link; 12. Second link; 13. Third link; 14. Drive shaft; 15. Power supply. Detailed Implementation

[0022] This section will describe in detail the specific embodiments of the present utility model. The preferred embodiments of the present utility model are shown in the accompanying drawings. The purpose of the drawings is to supplement the textual description with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the present utility model, but they should not be construed as limiting the scope of protection of the present utility model.

[0023] In the description of this utility model, it should be understood that the directional descriptions, such as up, down, front, back, left, right, etc., indicate the directional or positional relationship based on the directional or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0024] In the description of this utility model, "several" means one or more, "multiple" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. If "first" or "second" is used in the description, it is only for the purpose of distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0025] In the description of this utility model, unless otherwise explicitly defined, terms such as "setting," "installation," and "connection" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.

[0026] Reference Figures 1-5 In a preferred embodiment of this utility model, a plasma excitation device includes a wing 1, a rotating assembly, and a linkage mechanism. A jet port 2 is provided on the wing 1. A tilting ramp 6 is rotatably connected to the jet port 2 via the rotating assembly. The rotating assembly drives the tilting ramp 6 to rotate, changing the angle between the wing 1 and the tilting ramp 6, thus generating jets of varying intensities. The linkage mechanism is connected to the rotating assembly to drive its rotation. Plasma exciters are provided on the tilting ramp 6 and the wing 1. Each plasma exciter includes a buried electrode 4 and an exposed electrode 5. The buried electrode 4 is mounted on the upper surface of the wing 1 and covered with an elastic insulating material 3 extending to the surface of the tilting ramp 6. The exposed electrode 5 is mounted on the elastic insulating material 3 located on the surface of the tilting ramp 6. The buried electrode 4 and the exposed electrode 5 are aligned with each other and parallel to their edges.

[0027] Specifically, the direction of the induced velocity of the plasma exciter is from the exposed electrode 5 to the buried electrode 4. The direction of the induced velocity is consistent with the mainstream, which injects stronger energy into the flow field, significantly delays airflow separation, increases lift and reduces drag, and enables the aircraft to take off stably.

[0028] Preferably, the elastic insulating material 3 is made of thermoplastic polyurethane elastomer (TPU). When the tilting ramp 6 is tilted, the elastic insulating material will stretch and contract appropriately, and the amount of stretching and contraction is small. Therefore, the change in the angle of the tilting ramp 6 does not affect the use of the insulating material 3. The exposed electrode 5 is installed on the insulating material 3, connected to the positive terminal of the power supply 15, and exposed to the air.

[0029] Furthermore, both the buried electrode 4 and the exposed electrode 5 are copper foil electrodes.

[0030] In this embodiment, the linkage mechanism includes a limiting support 10 fixed on the wing 1, a first link 11, a second link 12, and a third link 13. Limiting holes are provided on the front and rear sides of the middle part of the limiting support 10, and the second link 12 is slidably connected in the limiting holes. A servo motor 9 is provided on the inner side of the right end of the limiting support 10. The output end of the servo motor 9 is connected to a rotating shaft. The rotating shaft extends to the outside of the limiting support 10 and is fixedly connected to a drive rod. The drive rod is hinged to the right side of the first link 11 by a pin. The left side of the first link 11 is hinged to the right side of the second link 12 by a pin. The left side of the second link 12 is hinged to the right side of the third link 13 by a pin. A transmission shaft 14 is fixedly provided on the front and rear sides of the tilting ramp 6. The transmission shaft 14 is hinged to the left side of the third link 13. The third link 13 is connected to the transmission shaft 14, thereby driving the tilting ramp 6 to rotate by an angle.

[0031] Specifically, the servo motor 9 is activated, and the first link 11 drives the second link 12 to move. The second link 12 moves forward or backward under the limitation of the limiting hole on the limiting support 10, thereby driving the position of the third link 13 to move, which in turn changes the angle of the tilting slope 6, and finally controls the angle between the tilting slope 6 and the wing 1, thereby adjusting the jet excitation intensity and suppressing flow separation.

[0032] Specifically, under the same voltage, the smaller the angle between the wing 1 and the tilting ramp 6, the stronger the excitation intensity generated by the plasma actuator and the stronger its ability to suppress flow separation.

[0033] More specifically, in this invention, the angle between the tilting inclined plane 6 and the wing 1 is changed. After the angle is changed, the jet intensity generated by the plasma exciter is stronger, and its impact on the flow field is greater, thus improving the plasma's effect on flow field quality. At the same time, the entire device and moving parts are embedded inside the wing 1, and the structure of the device will not have any additional impact on the flow field.

[0034] In this embodiment, the rotating assembly includes a pin 7 and a mounting bracket 8 fixedly mounted on the wing 1. The mounting bracket 8 is rotatably connected to the tilting ramp 6 via the pin 7. The mounting bracket 8 and the tilting ramp 6 are provided with coaxial holes that cooperate with the pin 7. The pin 7 passes through the tilting ramp 6 and is rotatably connected to the coaxial hole of the mounting bracket 8 and the left end of the limiting bracket 10.

[0035] This utility model also discloses a control method for the aforementioned plasma excitation device. The control method specifically involves: firstly, power is supplied to the servo motor 9 and the plasma exciter; the servo motor 9 rotates, causing the first connecting rod 11 to move, which in turn causes the second connecting rod 12 to move forward or backward; subsequently, the position of the third connecting rod 13 changes, causing the transmission shaft 14 to drive the tilting ramp 6 to move upward or downward, thereby changing the angle between the wing 1 and the tilting ramp 6 and altering the jet excitation intensity; wherein, under the same voltage, the smaller the angle between the wing 1 and the tilting ramp 6, the stronger the jet intensity generated by the plasma exciter, and the stronger the ability to suppress flow separation, thus improving the flow field quality by changing the jet intensity generated by the plasma exciter.

[0036] Without causing conflict, those skilled in the art can freely combine and use the above-mentioned additional technical features.

[0037] The above description is only a preferred embodiment of the present utility model. Any technical solution that achieves the purpose of the present utility model by essentially the same means shall fall within the protection scope of the present utility model.

Claims

1. A plasma excitation device, characterized in that: The device includes a wing (1), a rotating assembly, and a linkage mechanism. A jet port (2) is provided on the wing (1). A tilting ramp (6) is rotatably connected to the jet port (2) through the rotating assembly. The linkage mechanism is connected to the rotating assembly to drive the rotating assembly to rotate. Plasma exciters are provided on the tilting ramp (6) and the wing (1). The plasma exciter includes a buried electrode (4) and an exposed electrode (5). The buried electrode (4) is installed on the upper surface of the wing (1) and is covered with an elastic insulating material (3). The insulating material (3) extends to the surface of the tilting ramp (6). The exposed electrode (5) is installed on the insulating material (3) located on the surface of the tilting ramp (6). The buried electrode (4) and the exposed electrode (5) are aligned with each other and parallel to the edge.

2. The plasma excitation device according to claim 1, characterized in that: The linkage mechanism includes a limiting support (10) fixed on the wing (1), a first link (11), a second link (12) and a third link (13). Limiting holes are provided on the front and rear sides of the middle part of the limiting support (10), and the second link (12) is slidably connected in the limiting holes. A servo motor (9) is provided on the inner side of the right end of the limiting support (10). The output end of the servo motor (9) is connected to a rotating shaft. The rotating shaft extends to the outside of the limiting support (10) and is fixedly connected to a drive rod. The drive rod is hinged to the right side of the first connecting rod (11) by a pin. The left side of the first connecting rod (11) is hinged to the right side of the second connecting rod (12) by a pin. The left side of the second connecting rod (12) is hinged to the right side of the third connecting rod (13) by a pin. A transmission shaft (14) is fixedly provided on one side of the middle of the tilting slope (6). The transmission shaft (14) is hinged to the left side of the third connecting rod (13).

3. The plasma excitation device according to claim 2, characterized in that: The rotating assembly includes a pin (7) and a mounting bracket (8) fixedly mounted on the wing (1). The mounting bracket (8) is rotatably connected to the tilting ramp (6) via the pin (7). The mounting bracket (8) and the tilting ramp (6) are provided with coaxial holes that cooperate with the pin (7). The pin (7) passes through the tilting ramp (6) and is rotatably connected to the coaxial hole of the mounting bracket (8) and the left end of the limiting bracket (10).

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