Multi-cavity vector plasma synthetic jet exciter

Abstract

The invention relates to the technical field of exciters, in particular to a multi-cavity vector plasma synthetic jet exciter which comprises a shell, a discharge control assembly and a vector regulation and control mechanism. A plurality of excitation cavities which are mutually independent and are spatially distributed are arranged in the shell; a plurality of jet flow outlets are formed in the same wall surface of the shell; the plurality of jet outlets are communicated with the plurality of excitation cavities in a one-to-one correspondence manner; the discharge control assembly comprises a cathode electrode, an anode electrode and a high-voltage pulse power supply corresponding to each excitation cavity; the tip of the cathode electrode and the tip of the anode electrode form an opposite discharge structure in the excitation cavity; the high-voltage pulse power supply is correspondingly and electrically connected with the cathode electrode and the anode electrode; the vector regulation and control mechanism enables momentum gradient distribution or a space-time coupling effect to be formed between the mutually-associated excitation cavities by adjusting discharge characteristic parameters of the excitation cavities or fluid dynamic parameters of the jet flow outlets, and therefore flow track deflection is generated in a synthetic jet flow intersection area.

Description

Technical Field

[0001] The present invention relates to the technical field of actuators, and in particular to a multi-cavity vector plasma synthetic jet actuator. Background Art

[0002] Modern air combat places higher demands on the comprehensive performance of combat aircraft, requiring both excellent maneuverability and agility while also taking into account stealth characteristics. Fluid thrust vectoring (FTV) technology controls the direction of the engine's main jet through secondary flow, avoiding the complex actuation mechanism, additional weight load, and exposed high-temperature components of traditional mechanical thrust vectoring (MTV) technology. It has significant advantages in improving aircraft maneuverability and reducing radar / infrared signatures. Since von Karman proposed the concept of thrust vectoring in the 1950s, FTV technology has undergone many iterations: shock vectoring (SVC), throat deflection, and counterflow vectoring laid the early technical foundation, and the co-directional secondary flow collaborative control scheme proposed by the University of Manchester in the early 21st century further promoted the development of efficient vector control. Research has shown that jet position and exit angle are the core parameters for optimizing vector efficiency, providing direction for subsequent technological innovation.

[0003] Plasma synthetic jet (PSJ) is a new flow control technology that generates transient high-speed jets (peak velocity of 500m / s) through high-energy pulse discharge. It has the advantages of millisecond response and no mechanical components, and shows the potential to replace traditional gas sources in FTV systems. Studies have confirmed that PSJ can adjust the thrust vector angle (accuracy ±2.5°) through secondary flow linearity under low-speed conditions. However, the jet direction of the existing PSJ actuator is limited by the fixed outlet configuration, resulting in a small thrust vector angle adjusted by secondary flow linearity, which is difficult to adapt to the demand for active vector control in a wide-speed flight environment. This passive characteristic has become a key bottleneck restricting its engineering application, and there is an urgent need to break through the technical barriers to dynamic adjustment of the jet direction. Summary of the Invention

[0004] (1) Technical issues to be resolved

[0005] In view of the above-mentioned shortcomings and deficiencies of the prior art, the present invention provides a multi-cavity vector plasma synthetic jet actuator, which solves the technical problem that the jet direction of the existing PSJ actuator is limited by the fixed outlet configuration, resulting in a small thrust vector angle for linear adjustment of the secondary flow.

[0006] (2) Technical solution

[0007] In order to achieve the above object, the multi-cavity vector plasma synthetic jet actuator of the present invention comprises:

[0008] The shell has a plurality of excitation cavities disposed therein that are independent of each other and spatially distributed; a plurality of jet outlets are provided on the same wall surface of the shell; the plurality of jet outlets are connected to the plurality of excitation cavities in a one-to-one correspondence;

[0009] The discharge control assembly includes a cathode electrode, an anode electrode, and a high-voltage pulse power supply corresponding to each excitation cavity; the tips of the cathode electrode and the anode electrode form a facing discharge structure in the excitation cavity; and the high-voltage pulse power supply is electrically connected to the cathode electrode and the anode electrode respectively;

[0010] The vector control mechanism forms a momentum gradient distribution or a time-space coupling effect between the interconnected excitation cavities by adjusting the discharge characteristic parameters of each excitation cavity or the fluid dynamic parameters of the jet outlet, thereby causing flow trajectory deflection in the synthetic jet intersection area.

[0011] Optionally, the vector control mechanism includes:

[0012] High-speed electronic switch module, which adjusts the discharge timing of each excitation cavity by controlling the instantaneous on and off of the high-voltage pulse power supply, with a minimum on-off control time of 1μs;

[0013] The voltage regulation unit is integrated into the high-voltage pulse power supply and adjusts the voltage amplitude between the cathode electrode and the anode electrode in real time according to the preset vector control parameters. The adjustment range is 1kV to 15kV.

[0014] The switchable energy storage capacitor array is composed of multiple energy storage capacitors with different capacitance values ​​and a relay group. The capacitance value of the energy storage capacitor connected to the circuit of the excitation cavity is dynamically selected through the relay group. The optional capacitance value range is 0.5μF to 100μF.

[0015] Optionally, the vector control mechanism realizes active control of the jet vector by at least one of the following methods:

[0016] By independently controlling the on / off states of high-speed electronic switches connecting each excitation cavity and adjusting the discharge timing phase difference between adjacent excitation cavities, a multi-channel discharge excitation with time series differences is constructed, where the phase difference Δt between the discharge moments of adjacent excitation cavities satisfies 1τ≤Δt≤9τ, where τ is the time period from the start of arc breakdown to the current returning to zero.

[0017] By configuring energy storage capacitors of different capacitance values ​​in each discharge circuit, a vortex pair system is constructed. The interaction between the main jet with dominant momentum characteristics generated by the high-energy cavity and the auxiliary perturbation jet entrainment vortex generated by the low-energy excitation cavity is utilized to deflect the main jet toward the perturbation jet, forming a directional flow trajectory.

[0018] The adjustable aperture mechanism set at the jet outlet is used to adjust the equivalent aperture size difference of the jet outlet, and a momentum gradient generation system with asymmetric energy distribution is constructed. The momentum gradient generation system with asymmetric energy distribution is used to control adjacent excitation cavities to generate a main jet with dominant momentum and a secondary jet with auxiliary disturbance, respectively, inducing a momentum transfer effect between jets to achieve jet vector synthesis.

[0019] Optionally, the adjustable aperture mechanism includes an aperture adjustment slider and a guide rod;

[0020] One end of the guide rod is located outside the shell, and the other end penetrates the wall of the shell and is connected to the aperture adjustment slider;

[0021] The aperture adjustment slider is connected to the jet outlet in an axial sliding manner along the guide rod; pushing and pulling the guide rod can enable the aperture adjustment slider to open or close the jet outlet to adjust the equivalent aperture size of the jet outlet.

[0022] Optionally, the distance between adjacent jet outlets is 2-6 mm.

[0023] Optionally, the diameter of each jet outlet is 1-4 mm;

[0024] When the diameters of the jet outlets are different, the difference in diameters between adjacent jet outlets is no more than 3 mm.

[0025] Optionally, the synthetic jet can be deflected in a two-dimensional plane or in three-dimensional space.

[0026] Optionally, N≥2 mutually unconnected excitation cavities are provided in the shell, and the excitation cavities are arrayed or ringed in the shell;

[0027] If N is an even number, a plurality of excitation cavity arrays are disposed inside the housing;

[0028] If N is an odd number, the main flow excitation cavity is arranged at the center of the shell; and the remaining multiple branch flow excitation cavities are arranged around the main flow excitation cavity.

[0029] Optionally, the housing has a plurality of partitions built into it;

[0030] The multiple excitation cavities are separated by multiple partitions;

[0031] The partition is made of insulating and heat-insulating materials; the shell is made of insulating and high thermal conductivity materials.

[0032] Optionally, the tip of the cathode electrode and the tip of the anode electrode are coaxially arranged inside the excitation cavity; the other end of the cathode electrode and the other end of the anode electrode respectively penetrate the shell and are electrically connected to the high-voltage pulse power supply;

[0033] Heat-resistant silicone is applied between the cathode electrode and the anode electrode and the shell.

[0034] (3) Beneficial effects

[0035] The beneficial effects of the present invention are:

[0036] The discharge control assembly controls the individual electrodes to operate independently, enabling arc discharge in each excitation cavity sequentially, i.e., arc discharge through the electrode tips. Arc discharge generates Joule heat, causing temperature and pressure disturbances in the flow field within the excitation cavity. The temperature and pressure within the excitation cavity rapidly rise, creating a pressure differential with the external flow field, causing gas to rapidly eject from the jet outlet, forming a jet. Two or more jets alternately draw into and out of the excitation cavity, creating a low-pressure zone and a pressure differential across the jet, which in turn causes the jet to deflect, thereby achieving vectorial control of the jet and forming a spatiotemporal coupling effect between the interconnected excitation cavities.

[0037] The vector control mechanism can adjust the discharge parameters (discharge energy) of each excitation cavity, such as the instantaneous on-off time of the high-voltage pulse power supply, the voltage amplitude of the anode and cathode electrodes, and the parallel dynamic energy storage capacitor, to create a momentum gradient distribution within the jet. The vector control mechanism can also adjust the fluid dynamics parameters of each excitation cavity's jet outlet, specifically the size of the jet outlet, to adjust the jet's momentum, similarly creating a momentum gradient distribution and ultimately regulating the deflection of the synthetic jet's flow trajectory.

[0038] Compared to traditional counter- or co-directional jet thrust vectoring devices, the present invention proposes a jet thrust vectoring device with vector control and a relatively simple structure. This device utilizes timing control, dynamic adjustment of discharge energy, and modification of the jet outlet aperture to achieve vector control of the jet. This device overcomes the limitations of traditional jet thrust vectoring actuators, which are limited by the fixed outlet direction, and addresses the small mainstream deflection angle and high thrust loss associated with traditional jet thrust vectoring technology, thus offering promising application prospects. Furthermore, this device retains the advantages of plasma synthetic jet actuators, such as small size, light weight, simple structure, rapid response, and the absence of a complex external gas supply. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 2 is a schematic structural diagram of a multi-cavity vector plasma synthetic jet actuator according to a first embodiment of the present invention;

[0040] Figure 2 2 is a schematic structural diagram of a multi-cavity vector plasma synthetic jet actuator according to a second embodiment of the present invention;

[0041] Figure 3 2. It is a schematic structural diagram of a multi-cavity vector plasma synthetic jet actuator according to a third embodiment of the present invention;

[0042] Figure 4Schematic diagram of the internal structure of a multi-cavity vector plasma synthetic jet actuator in a third embodiment of the present invention;

[0043] Figure 5 Schematic diagram of the exploded rectangular parallelepiped housing (N=2) of the present invention;

[0044] Figure 6 Schematic diagram of the exploded cylindrical shell (N=5) of the present invention;

[0045] Figure 7 Schematic diagram of the flow field of the traditional fixed outlet plasma synthetic jet thrust vector;

[0046] Figure 8 Schematic diagram of the flow field of the multi-cavity vector plasma synthetic jet thrust vector of the present invention.

[0047] [Description of Reference Numerals]

[0048] 1: housing; 101: excitation chamber; 102: jet outlet; 103: bottom shell; 104: cover plate;

[0049] 201: cathode electrode; 202: anode electrode; 203: high-voltage pulse power supply; 204: high-speed electronic switch module; 205: switchable energy storage capacitor array;

[0050] 3: Aperture adjustment mechanism; 301: Slider; 302: Guide rod; 303: Guide rail;

[0051] 4: Plasma synthetic jet; 401: Main jet; 402: Disturbed jet;

[0052] 5: High-speed nozzle;

[0053] 6: Thrust mainstream. DETAILED DESCRIPTION

[0054] In order to better explain the present invention and facilitate understanding, the present invention is described in detail below through specific implementation methods in conjunction with the accompanying drawings.

[0055] 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 various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0056] In addition, the terms "first," "second," and so on, used in this disclosure are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referenced. Thus, a feature specified as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of this disclosure, "plurality" means at least two, such as two or three, unless otherwise specifically defined.

[0057] In the present invention, unless otherwise specified or limited, the terms "connect," "fix," etc. should be understood in a broad sense. For example, "fix" can mean fixed connection, detachable connection, or integration; "connection" can mean mechanical connection or electrical connection; it can mean direct connection or indirect connection through an intermediate medium; it can mean internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0058] See also Figures 1 to 4 The present invention provides a multi-cavity vector plasma synthetic jet exciter, which includes a shell 1, a discharge control component and a vector control mechanism; the shell 1 is provided with a plurality of excitation cavities 101 that are independent of each other and distributed in space; a plurality of jet outlets 102 are opened on the same wall of the shell 1; the plurality of jet outlets 102 are connected to the plurality of excitation cavities 101 in a one-to-one correspondence; the discharge control component includes a cathode electrode 201, an anode electrode 202 and a high-voltage pulse power supply 203 corresponding to each excitation cavity 101; the tip of the cathode electrode 201 and the tip of the anode electrode 202 form a counter-discharge structure in the excitation cavity 101; the high-voltage pulse power supply 203 is electrically connected to the cathode electrode 201 and the anode electrode 202; the vector control mechanism adjusts the discharge characteristic parameters of each excitation cavity 101 or the fluid dynamic parameters of the jet outlet 102 to form a momentum gradient distribution or a spatiotemporal coupling effect between the mutually related excitation cavities 101, thereby causing flow trajectory deflection in the synthetic jet intersection area.

[0059] The discharge control assembly has independent control ports that can control each electrode to operate independently, enabling each excitation cavity 101 to perform arc discharge in sequence, that is, arc discharge is performed through the tip of the electrode. The arc discharge generates Joule heat, causing temperature and pressure disturbances in the flow field within the excitation cavity 101. The temperature and pressure within the excitation cavity 101 rise rapidly, creating a pressure difference with the external flow field, causing the gas to be rapidly ejected from the jet outlet 102, forming a jet with a maximum speed exceeding 500m / s. After the first jet is generated in the excitation cavity 101 on one side, after a certain phase difference, the excitation cavity 101 on the other side is controlled to generate the second jet, and so on. Two or more jets are alternately drawn into and ejected from the excitation cavity 101, forming a low-pressure area, resulting in a pressure difference on both sides of the jet, which in turn causes the jet to be deflected, thereby achieving vector control of the jet. In other words, the characteristic parameters of the discharge are adjusted, and a spatiotemporal coupling effect is formed between the interconnected excitation cavities 101.

[0060] The vector control mechanism can adjust the discharge characteristic parameters of each excitation cavity 101, such as the instantaneous on / off time of the high-voltage pulse power supply 203, the voltage amplitude of the cathode and anode electrodes, and the parallel dynamic energy storage capacitor. By adjusting the discharge parameters (discharge energy), the momentum gradient distribution of the jet is formed. The vector control mechanism can also adjust the fluid dynamic parameters of the jet outlet 102 of each excitation cavity 101, that is, the aperture size of the jet outlet 102, to adjust the momentum of the jet, similarly forming a momentum gradient distribution, ultimately achieving regulation of the synthetic jet flow trajectory.

[0061] Compared to traditional counter- or co-directional jet thrust vectoring devices, the present invention proposes a jet thrust vectoring device with vector control and a relatively simple structure. This device utilizes techniques such as timing control, dynamic adjustment of discharge energy, and modification of the jet outlet aperture to achieve vector control of the jet. This device overcomes the limitations of traditional jet thrust vectoring actuators, which often require fixed outlet directions, and addresses the small mainstream deflection angle and high thrust loss associated with traditional jet thrust vectoring technology, thus offering promising application prospects. Furthermore, this device retains the advantages of plasma synthetic jet actuators, such as small size, light weight, simple structure, rapid response, and the absence of complex external gas supply devices.

[0062] Furthermore, the vector control mechanism includes a high-speed electronic switch module 204, a voltage regulation unit and a switchable energy storage capacitor array 205; the high-speed electronic switch module 204 adjusts the discharge timing of each excitation cavity 101 by controlling the instantaneous on and off of the high-voltage pulse power supply 203, and the minimum on-off control time is 1μs; the voltage regulation unit is integrated in the high-voltage pulse power supply 203, and adjusts the voltage amplitude between the cathode electrode 201 and the anode electrode 202 in real time according to the preset vector control parameters, and the adjustment range is 1kV to 15kV; the switchable energy storage capacitor array 205 is composed of multiple energy storage capacitors with different capacitances and a relay group, and the capacitance of the energy storage capacitor connected to the circuit of the excitation cavity 101 is dynamically selected through the relay group, and the optional capacitance range is 0.5μF to 100μF.

[0063] Specifically, the high-speed electronic switch module 204 includes a high-speed electronic switch that can switch the circuit on and off in microseconds. The high-speed electronic switch can regulate the discharge moment of the electrodes in each excitation cavity 101. After the exciter cavity 101 on one side generates a jet, after a certain phase difference, the excitation cavity 101 on the other side is controlled to generate a jet, thereby realizing jet vector control. The voltage regulating unit adjusts the voltage across the electrodes in real time according to the preset vector control parameters. The switchable energy storage capacitor array 205 is connected in parallel with the energy storage capacitors 204 of different capacitance values. According to the capacitor energy storage formula Where C is the capacitance of the energy storage capacitor, and U is the breakdown voltage of the air in the excitation cavity 101. And according to Baschen's law, U b =f(dP), where U b is the breakdown voltage of the air in the excitation chamber 101, f can be determined by referring to the Baschen curve for a specific gas or by looking up a table, P is the pressure in the excitation chamber 101, and d is the distance between the tips of the anode electrode 202 and the cathode electrode 201. Therefore, it can be seen that the breakdown voltage is only related to P and d. Under the same external environment, the distance between the tips of the anode electrode 202 and the cathode electrode 201 in the two excitation chambers 101 is fixed, and the discharge energy of the excitation chamber 101 can be controlled by connecting energy storage capacitors of different capacitances in parallel. The combined control of the high-speed electronic switch module 204, the voltage regulation unit, and the switchable energy storage capacitor array 205 achieves the vector control requirement for the discharge energy of the excitation chamber 101.

[0064] The vector control mechanism of the present invention realizes active control of the jet vector through at least one of the following embodiments:

[0065] First embodiment:

[0066] like Figure 1As shown, by independently controlling the on / off state of the high-speed electronic switches connecting each excitation cavity 101 and adjusting the phase difference in the discharge timing between adjacent excitation cavities 101, a multi-channel discharge excitation system with time series differences is constructed. The phase difference Δt between the discharge moments of adjacent excitation cavities satisfies 1τ≤Δt≤9τ, where τ is the time period from the onset of arc breakdown to the return of current to zero. A phase difference of 2τ can cause the plasma synthetic jet 4 to deflect approximately 25° toward the phase-lagging jet. The opening and closing times of the high-speed electronic switch 204 can be adjusted in real time according to actual needs.

[0067] Second embodiment:

[0068] like Figure 2 As shown, by configuring energy storage capacitors of different capacitance values ​​in each discharge circuit, a vortex pair system is constructed, and the interaction between the main jet 401 with dominant momentum characteristics generated by the high-energy cavity and the auxiliary vortex 402 generated by the low-energy excitation cavity is utilized to deflect the main jet 401 toward the vortex 402, forming a directional flow trajectory.

[0069] During the synthetic jet coupling process, the reverse entrainment vortices generated by the main jet 401 and the disturbance jet 402 interact with each other, making the entrainment vortex outside the main jet 401 dominant, forming a strong low-pressure area, and its flow trajectory continuously deflected toward the disturbance jet 402 side.

[0070] It should be noted that when the discharge energy is too small, the speed of the main jet 401 and the disturbance jet 402 is too low, and the two cannot generate a vortex, resulting in a small deflection of the jet or even no deflection. Therefore, it is necessary to maintain the jet speed to meet the inverse of Strouhal's in, represents the time scale required for the fluid to pass through the characteristic length D0, f represents the period of vortex shedding or vibration, and the constant K depends on the geometric parameters of the cavity, such as the shape of the orifice / slot, or the radius of curvature and the aspect ratio of the slot.

[0071] Third embodiment:

[0072] like Figure 3 As shown, the adjustable aperture mechanism 3 provided at the jet outlet is used to adjust the difference in equivalent aperture size of the jet outlet, and a momentum gradient generation system with asymmetric energy distribution is constructed. The momentum gradient generation system with asymmetric energy distribution is used to control adjacent excitation cavities 101 to respectively generate a main jet with dominant momentum and a secondary jet with auxiliary disturbance, thereby inducing momentum transfer between jets to achieve jet vector synthesis.

[0073] To ensure baseline consistency in the discharge energy of each excitation cavity 101, a momentum gradient generation system is constructed by setting differences in the geometric dimensions of each jet outlet 102. Smaller jet outlets produce an acceleration effect due to the reduction in flow cross-sectional area, forming a high-momentum main jet 401. Larger jet outlets, on the other hand, generate low-momentum auxiliary disturbance jets 402 by reducing flow resistance. During operation, the main jet 401 and the disturbance jet 402 form an asymmetric momentum distribution. Based on the inter-jets momentum transfer mechanism, the main jet 401 is affected by the lateral pressure differential induced by the disturbance jet 402, causing the trajectory of the main jet 401 to shift directionally toward the disturbance jet 402.

[0074] The first and second embodiments achieve a spatiotemporal coupling effect by adjusting the discharge characteristic parameters of each excitation cavity 101; the third embodiment achieves a momentum gradient distribution by adjusting the fluid dynamic parameters of each jet outlet 102. These three embodiments can be used individually or in combination to create a momentum gradient distribution or spatiotemporal coupling effect between interconnected excitation cavities 101, thereby causing flow trajectory deflection at the synthetic jet intersection region. Alternatively, none of these three embodiments can be used to simply generate a non-vectorial plasma synthetic jet 4.

[0075] See also Figure 4 The adjustable aperture mechanism 3 includes an aperture adjustment slider 301 and a guide rod 302; one end of the guide rod 302 is located on the outside of the shell 1, and the other end penetrates the wall of the shell 1 and is connected to the aperture adjustment slider 301; the aperture adjustment slider 301 is connected to the jet outlet 102 in an axial sliding manner along the guide rod 302; pushing and pulling the guide rod 302 can enable the aperture adjustment slider 301 to open or close the jet outlet 102 to adjust the equivalent aperture size of the jet outlet 102. In this embodiment, the upper and lower ends of the shell 1 are correspondingly provided with a cover plate 104 and a bottom shell 103. The size of the slider 301 is the same as the shape of the hollowed-out volume of the cover plate 104, and the hollowed-out height is not less than 1 / 2 of the height of the cover plate 104. Grooves are correspondingly provided on the front and rear sides of the slider 301, and a pair of guide rails 303 are correspondingly provided on the cover plate 104. The grooves are connected to the guide rails 303 in an axial sliding manner along the guide rod 302. By pushing and pulling the guide rod 302 to move axially, the equivalent aperture of the jet outlet 102 can be reduced or increased. The front-to-back width of the slider 301 is consistent with the front-to-back width of the jet outlet 102, and the width is limited to 1-4 mm. The difference in the equivalent apertures of adjacent jet outlets 102 can be limited to 3 mm, where the aperture of the jet outlet on one side is 1.5 mm and the aperture of the jet outlet on the other side is 2.5 mm, which can cause the plasma synthetic jet 4 to deflect by about 10°. As for the specific telescopic position of the slider 301, it can be adjusted according to actual needs. The aperture adjustment mechanism 3 is not limited to the use of a slider structure, and an aperture adjustment mechanism of the aperture type can also be used. The appropriate aperture adjustment mechanism 3 can be selected according to actual needs, as long as it can adjust the equivalent aperture size of the jet outlet 102.

[0076] Additionally, the distance between adjacent jet outlets 102 is 2-6 mm. Multiple jet outlets 102 are centrally located on a single plate within the housing 1, and the distance between adjacent jet outlets 102 is relatively small, allowing the secondary jets to better influence the primary jet and more easily form a synthetic jet. The distance between adjacent jet outlets 102 should not be too large to prevent excessive dissipation of the disturbance jet 402 during downstream propagation, potentially rendering the vector control of the plasma synthetic jet 4 ineffective.

[0077] See also Figure 5 In one embodiment, the housing 1 is a rectangular parallelepiped; multiple excitation cavities 101 are arrayed within the housing 1; and multiple jet outlets 102 are correspondingly arrayed on the outer wall of the housing 1. Through technical means such as timing control, dynamic adjustment of discharge energy, and / or changes in jet outlet aperture, the plasma synthetic jet 4 can be deflected within a two-dimensional plane, for example, forward or backward, effectively increasing the adjustable range of the thrust vector angle.

[0078] See also Figure 6 In another embodiment, the housing 1 is cylindrical or a sector-shaped ring segment; one excitation chamber 101 (mainstream excitation chamber) is located at the center of the housing 1; the remaining excitation chambers 101 (tributary excitation chambers) surround the mainstream excitation chamber; and multiple jet outlets 102 are correspondingly disposed on the outer wall of the housing 1. Through timing control, dynamic adjustment of discharge energy, and / or variation of jet outlet aperture, the plasma synthetic jet 4 can be deflected in three dimensions, for example, forward and to the left, further increasing the adjustable range of the thrust vector angle.

[0079] The number of excitation cavities 101 is increased or decreased according to actual application requirements. Multiple excitation cavities 101 can expand the vector deflection of the jet from two dimensions to three dimensions, realizing jet vector control in the front, back, left, and right directions.

[0080] Furthermore, the housing 1 incorporates multiple partitions, separating the multiple excitation cavities 101. These partitions are made of insulating and heat-insulating materials, while the housing 1 is constructed from a material with high thermal conductivity. In this embodiment, the partitions are at least 2 mm thick to isolate the heat from the excitation cavities 101. The housing 1 is constructed from alumina, a material with high thermal conductivity and a thickness of less than 2 mm, to rapidly dissipate the energy of the gas discharge.

[0081] Secondly, the tip of the cathode electrode 201 and the tip of the anode electrode 202 are coaxially arranged inside the excitation cavity 101; the other end of the cathode electrode 201 and the other end of the anode electrode 202 are correspondingly passed through the shell 1 and electrically connected to the high-voltage pulse power supply 203; heat-resistant silicone is applied between the cathode electrode 201 and the anode electrode 202 and the shell 1. Specifically, the jet is more stable and has lower losses when the electrode tips are coaxially arranged. The heat-resistant silicone can effectively prevent heat from being lost through the gap between the electrode and the shell 1, effectively ensuring the temperature and pressure disturbances in the excitation cavity 101, so that the temperature and pressure rise rapidly to form a pressure difference with the external flow field.

[0082] like Figure 7 As shown, a multi-cavity vectored plasma synthetic jet actuator is mounted vertically on the wall at the exit of the high-speed nozzle 5, enabling thrust vectoring of the main thrust stream 6. For existing fixed-exit, non-vectored plasma synthetic jet actuators, the generated plasma synthetic jet 4 acts perpendicularly to the axis of the high-speed nozzle 5 on the main thrust stream 6. At an NPR of 18.46 and an SPR of 0.6, the main thrust stream can be deflected by α = 2.47°. Due to the fixed placement and geometric configuration of conventional plasma synthetic jet actuators, linear control of the main thrust stream 6 by varying the jet incidence angle is difficult.

[0083] See also Figure 8 The present invention uses technical means such as timing control, dynamic adjustment of discharge energy, and / or change of jet outlet aperture to generate a vector plasma synthetic jet 4. When the direction of the plasma synthetic jet 4 is deflected θ=40° in the opposite direction to the thrust main stream 6, the thrust main stream 6 can increase α to 6.61° under the same working conditions, an increase of up to 167%, and a significant gain.

[0084] The multi-cavity vector plasma synthetic jet actuator of the present invention can be improved on the basis of the existing jet thrust vector actuator, has a high degree of compatibility with the existing jet thrust vector actuator, retains the advantages of the existing jet thrust vector actuator, and can increase the thrust vector angle of the existing jet thrust vector actuator, meeting the needs of active vector control in a wide speed range flight environment.

[0085] It should be understood that the above description of the specific embodiments of the present invention is merely for the purpose of illustrating the technical approach and features of the present invention. Its purpose is to enable those skilled in the art to understand the contents of the present invention and implement them accordingly. However, the present invention is not limited to the above-described specific embodiments. Any changes or modifications made within the scope of the claims of the present invention are intended to be covered by the scope of protection of the present invention.

Claims

1. A multi-cavity vector plasma synthetic jet actuator, characterized in that: include: A shell (1), wherein a plurality of excitation cavities (101) are provided inside the shell (1) and are independent of each other and spatially distributed; a plurality of jet outlets (102) are provided on the same wall surface of the shell (1); the plurality of jet outlets (102) are connected to the plurality of excitation cavities (101) in a one-to-one correspondence; A discharge control component comprises a cathode electrode (201), an anode electrode (202) and a high-voltage pulse power supply (203) corresponding to each excitation cavity (101); the tip of the cathode electrode (201) and the tip of the anode electrode (202) form a facing discharge structure in the excitation cavity (101); and the high-voltage pulse power supply (203) is electrically connected to the cathode electrode (201) and the anode electrode (202) respectively. The vector control mechanism forms a momentum gradient distribution or a time-space coupling effect between the mutually related excitation cavities (101) by adjusting the discharge characteristic parameters of each excitation cavity (101) or the fluid dynamics parameters of the jet outlet (102), thereby generating a flow trajectory deflection in the synthetic jet intersection area.

2. The multi-cavity vector plasma synthetic jet actuator according to claim 1, characterized in that: Vector control mechanisms include: A high-speed electronic switch module (204) adjusts the discharge timing of each excitation cavity (101) by controlling the instantaneous on-off of the high-voltage pulse power supply (203), with a minimum on-off control time of 1 μs; A voltage regulating unit, integrated in the high-voltage pulse power supply (203), adjusts the voltage amplitude between the cathode electrode (201) and the anode electrode (202) in real time according to preset vector control parameters, with an adjustment range of 1 kV to 15 kV; The switchable energy storage capacitor array (205) is composed of a plurality of energy storage capacitors with different capacitance values ​​and a relay group. The capacitance value of the energy storage capacitor connected to the circuit of the excitation cavity (101) is dynamically selected by the relay group, and the capacitance value can be selected in the range of 0.5 μF to 100 μF.

3. The multi-cavity vector plasma synthetic jet actuator according to claim 1, characterized in that: The vector control mechanism realizes active control of the jet vector by at least one of the following methods: By independently controlling the on-off state of a high-speed electronic switch connected to each excitation cavity (101), the discharge timing phase difference between adjacent excitation cavities (101) is adjusted to construct a multi-channel discharge excitation with time series difference, wherein the phase difference Δt at the discharge moment of adjacent excitation cavities satisfies 1τ≤Δt≤9τ, where τ is the time period from the start of arc breakdown to the current returning to zero; By configuring energy storage capacitors of different capacitance values ​​in each discharge circuit, a vortex pair system is constructed, and the interaction between the main jet (401) with dominant momentum characteristics generated by the high-energy cavity and the auxiliary turbulent jet (402) vortex generated by the low-energy excitation cavity is utilized to deflect the main jet (401) toward the turbulent jet (402), thereby forming a directional flow trajectory; An adjustable aperture mechanism (3) provided at a jet outlet is used to adjust the difference in equivalent aperture size of the jet outlet, thereby constructing a momentum gradient generation system with asymmetric energy distribution. The momentum gradient generation system with asymmetric energy distribution is used to control adjacent excitation cavities (101) to respectively generate a primary jet with dominant momentum and a secondary jet with auxiliary disturbance, thereby inducing momentum transfer between the jets to achieve jet vector synthesis.

4. The multi-cavity vector plasma synthetic jet actuator according to claim 3, characterized in that: The adjustable aperture mechanism (3) comprises an aperture adjustment slider (301) and a guide rod (302); One end of the guide rod (302) is located outside the housing (1), and the other end penetrates the wall of the housing (1) and is connected to the aperture adjustment slider (301); The aperture adjustment slider (301) is slidably connected to the jet outlet (102) along the axial direction of the guide rod (302); pushing and pulling the guide rod (302) can enable the aperture adjustment slider (301) to open or close the jet outlet (102) to adjust the equivalent aperture size of the jet outlet (102).

5. The multi-cavity vector plasma synthetic jet actuator according to any one of claims 1 to 4, characterized in that: The distance between adjacent jet outlets (102) is 2-6 mm.

6. The multi-cavity vector plasma synthetic jet actuator according to any one of claims 1 to 4, characterized in that: The diameter of each jet outlet (102) is 1-4 mm; When the diameters of the jet outlets (102) are different, the difference in diameters between adjacent jet outlets (102) is no greater than 3 mm.

7. The multi-cavity vector plasma synthetic jet actuator according to any one of claims 1 to 4, characterized in that: Synthetic jets can be deflected in a two-dimensional plane or in three-dimensional space.

8. The multi-cavity vector plasma synthetic jet actuator according to any one of claims 1 to 4, characterized in that: N≥2 mutually unconnected excitation cavities (101) are provided in the housing (1), and the excitation cavities (101) are arranged in an array or in a ring in the housing (1); If N is an even number, a plurality of excitation cavities (101) are arrayed inside the housing (1); If N is an odd number, the main flow excitation cavity is arranged at the center of the housing (1); and the remaining plurality of branch flow excitation cavities are arranged around the main flow excitation cavity. An excitation cavity (101) is arranged at the geometric center of the shell (1); the remaining excitation cavities (101) are arranged around the excitation cavity (101) at the geometric center; and a plurality of jet outlets (102) are correspondingly arranged on the outer wall of the shell (1).

9. The multi-cavity vector plasma synthetic jet actuator according to any one of claims 1 to 4, characterized in that: The housing (1) has a plurality of partitions built in; The plurality of excitation cavities (101) are separated by a plurality of partitions; The partition is made of insulating and heat-insulating material; the shell (1) is made of insulating and high-thermal-conductivity material.

10. The multi-cavity vector plasma synthetic jet actuator according to any one of claims 1 to 4, characterized in that: The tip of the cathode electrode (201) and the tip of the anode electrode (202) are coaxially arranged inside the excitation cavity (101); the other end of the cathode electrode (201) and the other end of the anode electrode (202) respectively penetrate the shell (1) and are electrically connected to the high-voltage pulse power supply (203); Heat-resistant silica gel is applied between the cathode electrode (201) and the anode electrode (202) and the shell (1).

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