Composite air blowing and sucking device applying dielectric barrier discharge plasma exciter
By setting a composite blowing and suction device of a dielectric barrier discharge plasma exciter in the wing of the aircraft, the plasma exciter is used to strengthen the airflow velocity, solving the complexity of shock wave vibration control in transsonic flight and the poor suppression effect under large angle of attack states, and effectively suppressing shock vibration vibration is achieved.
Patent Information
- Application Number
- CN202510447452.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-10
- Publication Date
- 2025-07-08
AI Technical Summary
The shock wave vibration control method of existing aircraft during transonic flight speed is complex and has poor suppression effect under large angle of attack. The traditional blown and inhaled flow path is difficult to cope with the rapid changes in the flow field, resulting in structural fatigue acceleration and safety threats.
A composite blowing and suction device using a dielectric barrier discharge plasma exciter includes a flow channel, a plasma exciter, a blowing port and a suction port. The plasma exciter excites plasma on the inner wall of the flow channel to enhance the airflow velocity and suppress shock wave vibration.
The shock wave jitter can be significantly suppressed in both small angle of attack and large angle of attack, maintaining the stable aerodynamic performance of the aircraft, simple structure and flexible layout, and is suitable for a variety of flow channel positions.
Smart Images
Figure CN120270487A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of aerospace shock buffet control, and particularly relates to a composite blowing and suction device applying a dielectric barrier discharge plasma actuator. Background Art
[0002] When an aircraft flies at transonic speed, the interaction between the shock wave and the boundary layer will trigger low-frequency and large-amplitude shock oscillations, generating significant unsteady aerodynamic loads. This transonic shock buffet has an adverse impact on the actual flight of the aircraft. In addition to affecting the maneuverability of the aircraft, the periodic aerodynamic loads will also accelerate the fatigue damage of the aircraft structure, resulting in a significant shortening of the service life, increasing the use cost, and seriously threatening flight safety.
[0003] Currently, the main shock buffet control methods mainly include three main directions: shock control, boundary layer control, and trailing edge flow control. Shock control suppresses buffet by changing the shock root structure and reducing the total pressure loss. For example, arranging three-dimensional control bumps can improve transonic flow, but the control effect of the convex wall is very sensitive to the position of the shock wave. Under off-design conditions, a huge drag penalty will be paid. Boundary layer control changes the characteristics of the near-wall flow upstream of the shock-wave boundary layer interference to suppress or weaken the shock-induced separation. For example, using vortex generators to transport high-energy fluid from the outside of the boundary layer to the near-wall region. However, a large amount of energy is consumed to weaken the shock intensity by this method. Trailing edge flow control effectively controls the shock buffet by adjusting the flow field characteristics around the trailing edge of the wing. For example, using a trailing edge deflector (TED) to control buffet. TED is a deflector installed on the lower surface of the trailing edge of the wing. However, to ensure that TED can deflect appropriately when the wing is in different states to achieve a significant shock buffet control effect, further design is required to achieve the closed-loop active control of TED, and the design process of the control law is relatively complex.
[0004] In addition, shock buffet can be eliminated or weakened by arranging blowing and suction air channels downstream of the shock wave on the wing. This method is a passive flow control. It can better suppress shock buffet in the small angle of attack state. However, in complex flow states, especially when the angle of attack increases to more than 4.25°, the shock intensity increases significantly, and the range of the high turbulent kinetic energy region expands significantly. The extension of the high turbulent kinetic energy region indicates that the shock-induced flow separation is more serious. The traditionally arranged blowing and suction air channels are difficult to effectively cope with the rapid change of the flow field, and the shock buffet suppression effect is significantly insufficient. Summary of the Invention
[0005] The object of the present invention is to solve the problems existing in the shock wave suppression method adopted by existing aircraft during transonic flight, namely, the complex suppression process and the poor suppression effect under large angle of attack conditions, and to provide a composite blowing and suction device applying a dielectric barrier discharge plasma actuator.
[0006] To achieve the above object, the technical solution provided by the present invention is as follows:
[0007] A composite blowing and suction device applying a dielectric barrier discharge plasma actuator according to the present invention includes a flow channel, a plasma actuator, a blowing port and a suction port;
[0008] The flow channel is located inside the wing body;
[0009] The blowing port and the suction port are respectively arranged on the upper surface and the lower surface of the wing and are close to the trailing edge of the wing; the blowing port and the suction port are communicated through the flow channel;
[0010] The plasma actuator is arranged on the inner wall of the flow channel and is used for generating plasma when the aircraft is in a transonic state to enhance the air flow velocity in the flow channel and suppress shock wave buffet.
[0011] Further, the distance from the front end of the blowing port to the leading edge of the wing is 0.74 - 0.9 times the wing chord length, and the dimension of the blowing port along the wing chord direction is 0.005 times the wing chord length;
[0012] The distance between the front end of the blowing port and the front end of the suction port along the wing chord direction is 0.03 times the wing chord length, and the dimension of the suction port along the wing chord direction is 0.004 times the wing chord length.
[0013] Further, the distance from the front end of the blowing port to the leading edge of the wing is 0.82 times the wing chord length.
[0014] Further, the plasma actuator includes an actuator power supply, an upper electrode, a wire, a lower electrode and an insulating layer; the upper electrode and the lower electrode are respectively fixed on both side surfaces of the insulating layer and are arranged in a staggered manner; a plurality of the upper electrodes are connected in parallel and are connected to the positive electrode of the actuator power supply through a wire; a plurality of the lower electrodes are connected in parallel and are connected to the negative electrode of the actuator power supply through a wire.
[0015] Further, the insulating layer is formed by pasting polyimide tapes layer by layer; the materials of the upper electrode and the lower electrode are copper foils.
[0016] Further, the number of layers of the polyimide tape is not less than four.
[0017] Further, both the upper electrode and the lower electrode are rectangular.
[0018] The present invention also provides a wing, which includes the above-mentioned composite blowing and suction device.
[0019] The present invention also provides an aircraft, which includes the above-mentioned wing.
[0020] The advantages of the present invention are as follows:
[0021] 1. A composite blowing and suction device applying a dielectric barrier discharge plasma actuator of the present invention includes a flow channel, a plasma actuator, a blowing port and a suction port; the flow channel is located inside the wing body, the blowing port and the suction port are respectively arranged on the upper surface and the lower surface of the wing and are close to the trailing edge of the wing; the blowing port and the suction port are communicated through the flow channel; the plasma actuator is arranged on the inner wall of the flow channel and can generate plasma when the aircraft is in a transonic state to enhance the air flow velocity in the flow channel, and the shock buffet suppression effect is remarkable.
[0022] 2. The present invention is not only applicable to the shock buffet suppression in the small angle of attack state, but also has a remarkable suppression effect on the shock buffet when the angle of attack is greater than 4.25°, maintaining the stability of the aerodynamic performance of the aircraft.
[0023] 3. The device of the present invention has a simple, light and small structure, and the layout position is flexible. It can be arranged at any position in the flow channel, and can achieve a good shock buffet suppression effect.
[0024] The additional aspects and advantages of the present invention will be partly given in the following description, partly will become obvious from the following description, or will be understood through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS
[0025] The above and / or additional aspects and advantages of the present invention will become obvious and easy to understand from the description of the embodiments in conjunction with the following drawings, wherein:
[0026] Figure 1 is a cross-sectional schematic view of the wing along the fuselage direction, showing the position of the composite blowing and suction device on the wing;
[0027] Figure 2 is Figure 1 a partial enlarged view of
[0028] Figure 3 is a schematic diagram of the pasting position of the plasma actuator in the flow channel of the present invention;
[0029] Figure 4 is Figure 3 a composition diagram of the plasma actuator in
[0030] Figure 5It is a comparison chart of the change in the amplitude of the lift coefficient oscillation under no air flow control and under the control of the traditional blowing and suction air flow channels. The angle of attack in Figure 5a is 3.5°, the angle of attack in Figure 5b is 4.25°, and the angle of attack in Figure 5c is 5°;
[0031] Figure 6 It is a comparison chart of the change in the amplitude of the lift coefficient oscillation under no air flow control, under the control of the traditional blowing and suction air flow channels, and under the control of the composite blowing and suction air flow channels of the present invention. The angle of attack in Figure 6a is 4.25°, and the angle of attack in Figure 6b is 5°.
[0032] Explanation of reference numerals: 1 - wing, 2 - composite blowing and suction device, 3 - flow channel, 4 - suction port, 5 - blowing port, 6 - plasma actuator, 601 - actuator power supply, 602 - upper electrode, 603 - lower electrode, 604 - insulating layer. Detailed implementation manners
[0033] The embodiments of the present invention will be described in detail below. The embodiments are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.
[0034] Referring to Figures 1-2 , this embodiment provides a composite blowing and suction device 2 applying a dielectric barrier discharge plasma actuator, including a flow channel 3, a suction port 4, a blowing port 5, and a plasma actuator 6. The flow channel 2 is located inside the wing 1. The plasma actuator 6 is fixed on the inner wall of the flow channel 3. The suction port 4 and the blowing port 5 are respectively opened on the lower surface and the upper surface of the wing and are close to the trailing edge of the wing; the suction port 4 and the blowing port 5 are communicated through the flow channel 3. The distance from the front end of the blowing port to the leading edge of the wing is 0.74 times to 0.9 times the chord length of the wing. In this embodiment, the distance from the front end of the blowing port to the leading edge of the wing is 0.82 times the chord length of the wing; the distance between the front end of the suction port and the front end of the blowing port along the chord direction of the wing is 0.03 times the chord length of the wing; the dimension of the blowing port along the chord direction of the wing is 0.005 times the chord length of the wing, and the dimension of the suction port along the chord direction of the wing is 0.004 times the chord length of the wing.
[0035] Referring to Figure 3 and Figure 4 , an arrangement method of the plasma actuator is exemplified. The number of plasma actuators is one, and it can be set at any position on the inner wall of the flow channel. The plasma actuator 6 can be set at any position on the inner wall of the flow channel. The plasma actuator 6 includes an actuator power supply 601, an upper electrode 602, a lower electrode 603, and an insulating layer 604. The upper electrode 602 and the lower electrode 603 are respectively pasted and fixed on both side surfaces of the insulating layer 604. There are multiple upper electrodes 602 and multiple lower electrodes 603, which are arranged in a staggered manner. Multiple upper electrodes 602 are connected in parallel and then connected to the positive pole of the actuator power supply 601 through a wire; multiple lower electrodes 603 are connected in parallel and then connected to the negative pole of the actuator power supply 601 through a wire.
[0036] To further enhance the thickness of the jet flow in the flow channel and increase the area of the flow control effect, this embodiment also shows another layout method of the plasma actuator: the number of plasma actuators is multiple, and they are arranged symmetrically on both sides of the inner wall of the flow channel in a staggered manner.
[0037] Specifically, the materials of the upper electrode 602 and the lower electrode 603 are copper foils. The insulating layer 604 is formed by stacking and bonding polyimide tapes layer by layer, and the number of stacked layers is not less than 4 layers to ensure that the insulating layer is not broken down. The polyimide tapes are bonded layer by layer using an insulating adhesive. During the manufacturing process of the plasma actuator 6, the upper electrode and the lower electrode are respectively bonded to both side surfaces of the insulating layer. During the bonding process, there must be no air bubbles between the insulating layer and the lower electrode to ensure that the flow channel is not blocked; then the upper electrodes 602 are connected in parallel and then connected to the positive pole of the plasma power supply through wires, and the lower electrodes 603 are connected in parallel and then connected to the negative pole of the plasma power supply through wires.
[0038] This embodiment only describes the example of the SC(2)-0714 airfoil, which is not a limitation to the solution of the present invention. The composite blowing and suction device designed by the present invention can be extended to any airfoil.
[0039] This embodiment also provides a composite blowing and suction control method for transonic shock buffet control. The specific process is as follows:
[0040] First, set the above-mentioned composite blowing and suction device at a set position on the trailing edge of the wing. When the aircraft has shock buffet during transonic flight, turn on the plasma power supply switch, and the upper electrode starts to discharge, generating a plasma region around; keep the plasma power supply in the on state to strengthen the blowing and suction intensity in the flow channel and suppress the shock buffet. When the aircraft exits the shock buffet state, turn off the plasma power supply.
[0041] To illustrate the shock buffet suppression effect of the composite blowing and suction device based on the plasma actuator of the present invention, Figure 5 and 6 respectively provide the oscillation amplitude change diagrams of the lift coefficient of the traditional blowing and suction flow channel and the composite blowing and suction flow channel of the present invention at the incoming flow Mach number Ma = 0.75 and the angles of attack of 3.5° and 4.25°. Among them, Figure 5 shows the oscillation amplitude change result of the lift coefficient controlled by the traditional blowing and suction flow channel; at the incoming flow Mach number Ma = 0.75 and the angle of attack of 3.5°, the air flow velocity in the flow channel is about 260 m / s, and the oscillation amplitude almost completely disappears, indicating that the traditional blowing and suction flow channel can achieve a good suppression effect on shock buffet at a small angle of attack; however, at the angles of attack of 4.25° and 5°, the oscillation amplitude of the lift coefficient is about 0.75 - 0.85, and only a certain degree of suppression is achieved on the shock buffet, and the suppression effect is not ideal. Figure 6The variation results of the oscillation amplitude of the lift coefficient under the control of the composite blowing and suction air flow channel of the present invention are shown: in the same shock buffet environment, the plasma actuator is started, and the power discharge waveform of the driving actuator is not modulated, only steady excitation is carried out, plasma is generated by discharging near the upper electrode, which plays a role in continuously accelerating the air flow in the channel. When the flow Mach number Ma = 0.75 and the angle of attack is 4.25°, the air flow velocity in the channel can reach 270 m / s, and the oscillation amplitude almost completely disappears, the shock buffet is significantly suppressed, and the aerodynamic coefficient tends to be stable; when the angle of attack is 5°, the oscillation amplitude is only 0.02, and the shock buffet suppression effect is still significant.
[0042] It can be seen from the above comprehensive analysis that the composite blowing and suction device of the present invention has a good suppression effect on shock buffet and is applicable to the large angle of attack state.
[0043] As described above, it is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of various equivalent modifications or substitutions, and these modifications or substitutions should be covered within the protection scope of the present invention.
Claims
1. A composite blowing and suction device applying a dielectric barrier discharge plasma actuator, characterized in that, It includes a flow channel, a plasma actuator, a blowing port, and a suction port; The flow channel is located inside the wing body; The blowing port and the suction port are respectively arranged on the upper surface and the lower surface of the wing and are close to the trailing edge of the wing; the blowing port and the suction port are communicated through the flow channel; The plasma actuator is arranged on the inner wall of the flow channel and is used to generate plasma when the aircraft is in a transonic state so as to enhance the air flow velocity in the flow channel and suppress shock buffet.
2. The composite air blowing and suction device according to claim 1, wherein The distance from the front end of the blowing port to the leading edge of the wing is 0.74 - 0.9 times the wing chord length, and the dimension of the blowing port along the wing chord direction is 0.005 times the wing chord length; The distance between the front end of the blowing port and the front end of the suction port along the wing chord direction is 0.03 times the wing chord length, and the dimension of the suction port along the wing chord direction is 0.004 times the wing chord length.
3. The composite air blowing and suction device according to claim 2, characterized in that, The distance from the front end of the blowing port to the leading edge of the wing is 0.82 times the wing chord length.
4. The composite air blowing and suction device according to claim 1, wherein The plasma actuator includes an actuator power supply, an upper electrode, a wire, a lower electrode, and an insulating layer; The upper electrode and the lower electrode are respectively fixed on both side surfaces of the insulating layer and are arranged in a staggered manner; Multiple upper electrodes are connected in parallel and are connected to the positive electrode of the actuator power supply through a wire; Multiple lower electrodes are connected in parallel and are connected to the negative electrode of the actuator power supply through a wire.
5. The composite air blowing and suction device according to claim 4, wherein, The insulating layer is formed by pasting polyimide tapes layer by layer; The materials of the upper electrode and the lower electrode are copper foils.
6. The composite air blowing and suction device according to claim 5, wherein, The number of layers of the polyimide tape is not less than four.
7. The composite air blowing and suction device according to claim 6, wherein Both the upper electrode and the lower electrode are rectangular.
8. An airfoil, characterized in that, It includes the composite blowing and suction device according to any one of claims 1 - 7.
9. An aircraft, characterized in that, It includes the wing according to claim 8 of the claims.