29 results about "Plasma actuator" patented technology

There is provided an apparatus for processing a substrate, comprising: a substrate holder disposed in a processing chamber and configured to hold the substrate; a processing gas supplying part configured to supply a processing gas into the processing chamber; a surrounding member disposed to surround a peripheral portion of the substrate held by the substrate holder and having an annular wall portion made of a dielectric; a plasma actuator disposed at the wall portion and configured to plasmarize the processing gas supplied by the processing gas supply part and form flow of plasma of the processing gas along the wall portion in a preset direction; and an injection mechanism configured to inject the plasma formed by the plasma actuator and flowing along the wall portion toward the peripheral portion of the substrate held by the substrate holder to perform processing using the plasma.

The invention discloses a complex wind field simulation method suitable for a small and medium-sized unmanned aerial vehicle wind resistance test, and relates to the technical field of intelligent wind control, and the method comprises the steps: based on a plasma exciter control instruction set, generating a directional micro vortex group in a wind tunnel through a plasma exciter array, meanwhile, the spatial distribution of the directional micro vortex group is regulated and controlled by adopting an ultrasonic interference method, and a three-dimensional turbulent flow field is generated; an unmanned aerial vehicle anti-risk test is executed, anti-wind performance data is collected and combined with PIV to verify the stability of the nest ring structure, and dynamic adjustment is carried out through a fuzzy PID control algorithm; and constructing a judgment matrix based on the adjusted wind resistance test data, calculating a wind resistance performance index of the unmanned aerial vehicle by adopting a dynamic time warping algorithm, and generating a performance evaluation report. According to the invention, through vortex ring stability feature extraction and fuzzy PID dynamic adjustment based on the deep space-time convolutional network, closed-loop stability control in a complex wind field environment is realized.

Provided are sterilization devices and the like that exhibit superior sterilization performance, superior to that achieved with ozone or ultraviolet light. The sterilization devices and the like are equipped with a plasma generator and an ultraviolet light source. The plasma generator is a plasma actuator having a first electrode and a second electrode disposed so as to sandwich a dielectric. In the plasma actuator, an induced flow including ozone is generated by applying a voltage between the two electrodes. The ultraviolet light source is arranged so as to irradiate the surface of a sterilization target, and the plasma actuator is arranged so as to supply the induced flow to the surface.

A cooling device is provided with a heat sink having a plurality of fins, and a plasma actuator. Flow paths are formed between adjacent ones of the fins. The plasma actuator is provided away from the fins where the flow paths are formed. The plasma actuator has electrodes that are arranged offset in the flow path direction. The plasma actuator generates an induced air flow flowing in a direction of the flow path in the central region between adjacent fins.

Provided is an electrification device equipped with a plasma actuator, wherein the plasma actuator: comprises a dielectric body, a first electrode provided on a first surface of the dielectric body, and a second electrode disposed across the dielectric body from the first electrode; by applying alternating-current voltage between the first electrode and the second electrode, generates an induced flow along an exposed portion not covered with the first electrode of the first surface of the dielectric body from an edge portion of the first electrode; and is disposed such that the induced flow is directly supplied to the surface of the body to be electrified, and applies direct-current voltage between the first electrode and the body to be electrified.

To provide a cooling device which can significantly obtain an improved effect in cooling efficiency enabled by adding a plasma actuator.SOLUTION: A cooling device comprises: a heat sink which has a base plate with a plurality of fins erected thereon, and which is provided with a flow path formed between the fins; a fan for flowing a main air current in the flow path; a plasma actuator which discharges electricity between electrodes separated by a dielectric so as to generate an induction flow in a flow direction of the main air current; and an additional fin. The additional fin and the plasma actuator are disposed upstream the heat sink in the flow direction of the main air current in the flow path. The additional fin and the plasma actuator face each other so as to form an extension flow path. A generation surface of the induction flow is flush with main surfaces of the fins. The additional fin is thicker than the fins. The extension flow path is narrower than the flow path. With such a configuration, it becomes possible to provide the cooling device which has a significantly great improvement effect in cooling efficiency enabled by adding a plasma actuator.SELECTED DRAWING: Figure 2

An aircraft includes a first leading edge defining a forward edge of a left aircraft wing, a second leading edge defining a forward edge of a right aircraft wing, a plurality of plasma actuators disposed along the first and second leading edges, a control processing unit communicatively coupled to each plasma actuator, and at least one flight stability sensor communicatively coupled to the control processing unit. The control processing unit commands the at least one plasma actuator to generate the plasma in response to a signal from the flight stability sensor.

This application relates to an open fan component of an open rotor engine, an open rotor engine, and a noise reduction method. The open fan component includes a stator with stator blades; a rotor with rotor blades, the stator blades being located downstream of the rotor blades; the rotor blades are provided with a plasma actuator array, the plasma actuator array having multiple plasma actuators; the open fan component has a standby state, a first operating state, a second operating state, and a third operating state.

The application discloses a dielectric barrier discharge plasma exciter model establishing method considering uncertainty, relates to the technical field of computational fluid dynamics, flow control and aeroacoustics, and comprises the following steps: firstly, time-averaged velocity fields under different excitation voltages are obtained through a static ion wind experiment, and volume force distribution and key evaluation indexes are inversed based on momentum balance; then, a parameterized linear plasma equivalent model is constructed, and charge density and an action region boundary are identified as uncertainty design variables; high-fidelity simulation and a proxy model are combined, interval multi-objective optimization is carried out in the initial range of variables, and interval midpoints and radii of peak velocity and volume force error are simultaneously minimized; finally, a corrected model with consideration of both accuracy and robustness is obtained, and is embedded into a CFD solver for flow control simulation. The application effectively overcomes the influence of parameter uncertainty, and significantly improves model prediction accuracy and engineering applicability.

A comb-shaped plasma actuator device and application for improving film cooling performance, belonging to the technical field of film cooling of gas turbine turbine blades; it includes a low-temperature plasma power supply, an exposed electrode, a buried electrode and an insulating medium; the low-temperature plasma power supply is connected to the exposed electrode and the buried electrode; the exposed electrode is in a comb shape, including a comb root and a comb tip, and is arranged on the upper surface of the first insulating medium, and there are film holes on the first insulating medium; the buried electrode is in a strip shape and is arranged on the lower surface of the first insulating medium; the exposed electrode and the buried electrode are asymmetrically arranged, and the distance along the flow direction is S; the bottom surface of the buried electrode is covered by the second insulating medium. The exposed electrode increases the distribution of the plasma in the spanwise direction, and the disturbance of the comb-shaped plasma to the flow field in the flow direction and the spanwise direction destroys the thermal boundary layer and the flow boundary layer of the wall surface, thereby strengthening the convective heat transfer performance of the wall surface.

An electrophotographic image-forming apparatus comprising an electrophotographic photoreceptor that serves as a member to be charged, a cleaning member that is in contact with a surface of the electrophotographic photoreceptor, and a plasma actuator. The plasma actuator is provided with a dielectric, a first electrode that is provided to a first surface of the dielectric, and a second electrode that is provided to the first electrode with the dielectric interposed therebetween. The plasma actuator generates an induced current from an edge of the first electrode along an exposed part of the first surface of the dielectric, the exposed part not being covered by the first electrode. The plasma actuator is disposed so as to be capable of directly supplying the induced current to the surface of the electrophotographic photoreceptor. The plasma actuator controls the electric potential of transfer residual toner on the surface of the electrophotographic photoreceptor.

A method for cleaning an enclosed space, the method comprising providing a reservoir of cleaning liquid; generating a very dry mist comprising the cleaning liquid, the mist containing aerosol droplets, where the mist passes through a non-thermal plasma actuator to form plasma active ion particles carried by the aerosol droplets of the mist, where the plasma active ion particles are hydroxyl ions; wherein the flow meter monitors mist flow of mist entering the closed space through the self-cleaning nozzle, and the flow speed of the mist passing through the self-cleaning nozzle is not larger than 2 ml / min; wherein the air pressure in the closed space is kept neutral; wherein there is no cavity within the self-cleaning nozzle, except for the cavity through which the very dry mist flows, and wherein the generated very dry mist is used to clean the enclosed space.

The present disclosure presents systems, apparatuses, and methods of active flow controls for dissipating tip vortices. In this regard, a method comprises positioning one or more fan-shaped plasma actuators on an end surface of a tip of one or more airfoils of an aircraft, wherein the fan-shaped plasma actuators are surface compliant with the surface of the tip of the one or more airfoils; and activating the one or more fan-shaped plasma actuators during a flight of the aircraft, wherein at least one tip vortex generated by a flight of the aircraft is reduced by an introduction of one or more vortices generated by the one or more fan-shaped plasma actuators on the end surface of the tip of the one or more airfoils of the aircraft. Other systems, apparatuses, and methods are also presented.

A cooling device is provided with a heat sink having a plurality of fins, and a plasma actuator. Flow paths are formed between adjacent ones of the fins. The plasma actuator is provided away from the fins where the flow paths are formed. The plasma actuator has electrodes that are arranged offset in the flow path direction. The plasma actuator generates an induced air flow flowing in a direction of the flow path in the central region between adjacent fins.

An unmanned aerial vehicle (UAV) powered using electric propulsion is provided. The unmanned aerial vehicle (UAV) includes a main frame and a plurality of thrust rings. The plurality of thrust rings is arranged in a first spatial configuration around the main frame and is rotatably coupled to at least one actuator in the main frame along a pivot axis. The unmanned aerial vehicle (UAV) further includes a plurality of plasma actuators disposed on at least one of the plurality of thrust rings. Further, in an actuated state, the plurality of plasma actuators actuates to generate a plasma thrust that causes the unmanned aerial vehicle (UAV) to orient along a particular axis or move in a specific direction.

A gas-powered device and a method for controlling the flow field in the tip region of the gas-powered device are disclosed. The gas-powered device is an axial-flow based transonic fan or compressor, and includes: a casing, a DBD plasma actuator, a rotor blade, a first insulating medium, an AC power supply, and a second insulating medium; a first insulating medium is provided on the inner wall of the casing to form an annular insulating medium, the positive electrode of the DBD plasma actuator is arranged in the first insulating medium to form an annular positive electrode, and the annular positive electrode is isolated from the inner wall of the casing by the first insulating medium, and the annular positive electrode is located upstream of the shock wave; the rotor blade is used as the negative electrode, and a second insulating medium is provided at the tip of the rotor blade to isolate the positive electrode and the negative electrode, and the AC power supply is respectively connected to the positive electrode and the negative electrode of the DBD plasma actuator to cause the DBD plasma actuator to generate plasma. The technical solution provided by the present disclosure is beneficial to improving the working performance of the gas-powered device under all working conditions.

A plasma-combined trailing edge suction flow control device for rotor blades is provided, comprising a plurality of blades (1), a nanosecond pulse dielectric barrier discharge plasma actuator (2) mounted at the leading edge of the blades and covering the entire blade extension; an air suction device (3) is mounted at the tail end of the blades, and the center of the air suction port is located at a position A%c from the leading edge. The tail end suction device (3) comprises a tail end suction port (3-1), a low-pressure air chamber (3-2) and a connecting pipe (3-3). When the dynamic stall of the rotor airfoil is controlled, a high-frequency nanosecond pulse power supply (4) is used to power the nanosecond pulse dielectric barrier discharge plasma actuator (2). A plasma-combined trailing edge suction flow control method for rotor blades is also provided. The present invention can effectively interfere with the flow field structure on the upper surface of the airfoil by combining plasma excitation with trailing edge suction, reduce the degree of flow separation, and thereby increase the average lift of the rotor blades, thereby improving the performance of the rotor blades.

Motor vehicle body with a plasma actuator, wherein the motor vehicle body (7) has a roof (8) and a movable tailgate (9), wherein the tailgate (9) is formed opposite a rear edge (11) of the roof (8), which is formed facing away from a front of the motor vehicle body (7), and wherein a first distance (13) and a second distance (14) are formed between the rear edge (11) and a flap edge (12) of the tailgate (9) opposite the rear edge (11) of the motor vehicle body (7), at least in the direction of a vertical axis (Z) of the motor vehicle body (7), and wherein the plasma actuator (1) has at least a first electrode (2) and a second electrode (3) which are connected to a power source (21), characterized in that the plasma actuator (1) is used to form a plasma (5) in a transition area (16) between the roof (8),at least the trailing edge (11), and the tailgate (9), at least the flap edge (12), comprising a movement gap (15), wherein the movement gap (15) between the trailing edge (11) and the flap edge (12) extends along a transverse body axis (Y) of the vehicle body (7), and wherein the first electrode (2) is arranged at or at least near the trailing edge (11) and the second electrode (3) is arranged at or at least near the flap edge (12).

To provide a cooling device which can improve cooling efficiency by causing an induction flow to reach the downstream of a flow path even if a heat sink has a long flow path length.SOLUTION: A cooling device comprises: a heat sink which has a flow path 23 formed between fins 21; a fan 4 for flowing a main air current 41 in the flow path 23; a plasma actuator which discharges electricity between electrodes 11 and 12 separated by a dielectric 13 so as to generate an induction flow 15 in a flow direction of the main air current 41; and an additional fin 3. The additional fin 3 and the plasma actuator are disposed upstream the heat sink in the flow direction of the main air current 41 in the flow path 23. The additional fin and the plasma actuator face each other so as to form an extension flow path 31. The plasma actuator is configured such that: the dielectric 13 is thicker than the fins 21; and a generation surface of the induction flow 15 is further offset to the center side in the width direction of the flow path 23 than main surfaces of the fins 21. The extension flow path 31 is narrower than the flow path 23.SELECTED DRAWING: Figure 2

The invention provides a composite air blowing and sucking device applying a dielectric barrier discharge plasma exciter. The composite air blowing and sucking device comprises a flow channel, the plasma exciter, an air blowing port and an air sucking port. The flow channel is located in the wing body, and the air blowing port and the air suction port are formed in the upper surface and the lower surface of the wing respectively and close to the rear edge of the wing. The air blowing port is communicated with the air suction port through the flow channel; the plasma exciter is arranged on the inner wall of the flow channel and can excite and generate plasma when the aircraft is in a transonic speed state, so that the airflow speed in the flow channel is increased, and shock wave buffeting is restrained. The shock wave buffeting suppression device is simple in structure, and the shock wave buffeting suppression effect is still remarkable in the large attack angle state.

The invention provides an automatic stall wing control method based on deep reinforcement learning, relates to the field of flow state control, and solves the problems that a static stall control method cannot cope with unsteady airflow changes, and an existing closed-loop control algorithm is limited in response in a complex and high-dimensional flow environment and lacks real-time intelligent adjustment capability. The system is suitable for aircrafts and the like, the wing flow field state and global parameters are collected in real time through the sensor, control actions are output through the DQN intelligent body, the dielectric barrier discharge plasma actuator is driven, and wing stall delay, lift force lifting and pneumatic vibration suppression are achieved. The problem of dynamic stall control failure is solved, limitation of a traditional method is overcome, full-working-condition intelligent self-adaptive control is achieved, the application threshold is lowered, the maneuvering flight safety boundary and control stability of the aircraft are improved, and the advanced control requirement of the high-maneuvering aircraft is met.

The present disclosure presents systems, apparatuses, and methods of active flow controls for dissipating tip vortices. In this regard, a method comprises positioning one or more serpentine plasma actuators on a top or bottom surface of one or more airfoils near a tip of an airfoil of an aircraft; and activating the one or more serpentine plasma actuators during a flight of the aircraft, wherein at least one tip vortex generated by the flight of the aircraft is reduced by an introduction of one or more airflows generated by one or more serpentine plasma actuators on the top or bottom surface of the one or more airfoils of the aircraft. Other systems, apparatuses, and methods are also presented.

A large-scale pulsed arc plasma exciter matrix with real-time variable formation is described. Based on a pulsed surface arc plasma exciter, individual arc plasma exciters are expanded in both row and column directions to form an arc plasma exciter matrix. A power supply circuit is provided, with each exciter having its own independent power supply unit. A method for achieving real-time variable control of the exciter matrix formation using a shift register is also provided. This invention facilitates expansion of the number of discharge circuits, with no electrical connections between the exciters, resulting in no interference and strong robustness. The discharge circuit eliminates reliance on a high-voltage trigger power supply, enabling dozens or hundreds of pulsed arc discharge plasma excitations. By introducing a shift register circuit, this matrix achieves real-time variable excitation formation, significantly improving the arc plasma exciter matrix's adaptability to complex and changing flight conditions and potentially achieving higher flow control efficiency.

A virtual variable pit plasma turbulent friction drag reduction device includes a pit flat plate (1) and a virtual pit plasma actuator (2). The pits on the pit flat plate (1) are arranged in a staggered pattern or a matrix pattern. The virtual pit plasma actuator (2) is arranged on the pit flat plate (1) and is a dielectric barrier discharge plasma actuator, including a high-voltage electrode (21), a dielectric layer (22), and a low-voltage electrode (23). There is also provided a virtual variable pit plasma turbulent friction drag reduction method, as well as a rapid preparation method of a flexible plasma actuator based on mask spraying. The present invention combines the plasma actuator active flow control technology with the pit passive flow control technology, and uses the virtual pit surface formed by the plasma actuator to improve the perturbation intensity of the pit on the flow field and enhance the drag reduction effect. In addition, the intensity of the variable pit plasma aerodynamic actuator can be adjusted according to the oncoming flow conditions. The method of the present invention is easy to be combined with sensors to form a closed-loop adaptive turbulent friction drag reduction device.

This application relates to a sliding arc plasma actuator for high-pressure environments, relating to the fields of plasma chemistry and plasma ignition and combustion. The sliding arc plasma actuator for high-pressure environments includes an electrode core stage and an actuator injection section. The electrode core stage includes a high-voltage electrode, which comprises a high-voltage electrode head and a high-voltage electrode rod arranged along its length. One end of the actuator injection section forms a gradually narrowing and widening throat, and this end is connected to an actuator outlet section. An air inlet pipe is arranged inside the outer wall of the actuator injection section, and an oil injection hole is opened in the flared portion of the throat. The high-voltage electrode rod is located in the actuator injection section, and the high-voltage electrode head extends into the flared portion of the throat. The high-voltage electrode is made of a metallic material capable of generating alpha or beta rays. This sliding arc plasma actuator for high-pressure environments has the performance of being suitable for high-pressure environments without changing the power supply breakdown voltage and cable insulation strength.

The invention relates to a device for cleaning solar panels (1), the principle of which is based on an ionic wind combined with an electrostatic force which are applied simultaneously to the dust particles. The device consists of a plasma actuator attached to a wheeled vehicle (9) on the surface of the panel (1). The plasma actuator comprises three electrodes: an ionising electrode (2), an earthed electrode (3) and a static electrode (4). Both the ionising electrode (2) and the static electrode (4) are supplied with the same electric voltage of about twenty kilovolts. The static electrode (4) is a cylindrical tube that applies an electric field so as to detach the dust particles from the surface of the panel (1) by means of an electric attractive force. The assembly made up of the ionising electrode (2) and the earthed electrode (3) produces an ionic wind that easily cleans the dust particles previously lifted by the static electrode (4).

An aircraft includes a combustion engine including a fuel injector, a plurality of plasma actuators disposed in the combustion engine downstream of the fuel injector, a control processing unit communicatively coupled to each plasma actuator of the plurality of plasma actuators, and at least one sensor communicatively coupled to the control processing unit, wherein the control processing unit commands the fuel injector and at least one plasma actuator of the plurality of plasma actuators to generate plasma in response to a signal from the at least one sensor.

To provide a high-durability plasma actuator capable of generating a strong induction flow.SOLUTION: A plasma actuator comprises a tabular dielectric, an upstream-side electrode which is disposed on one face of the dielectric, and a downstream-side electrode which is disposed on the other face or inside of the dielectric. The upstream-side electrode and the downstream-side electrode are offset-disposed, the upstream-side electrode includes a projection which protrudes to the side of the downstream-side electrode in an in-plane direction of the dielectric, the dielectric is formed from two kinds of dielectric materials of a first dielectric material and a second dielectric material having a higher dielectric constant and higher plasma resistance than the first dielectric material and includes a location including the second dielectric material and a location of the first dielectric material only in a planar view and a location overlapped with a tip end of the projection is the location including the second dielectric material, thereby providing a plasma actuator by which plasma moves forward and straight in a direction of the dielectric material having higher plasma resistance and which makes generation of a strong induction flow compatible with high durability.SELECTED DRAWING: Figure 4

This invention provides a plasma device and method for de-icing swept wings, including a plasma power supply and a plasma actuator. The plasma actuator is a surface dielectric barrier discharge plasma actuator, comprising an insulating dielectric layer, exposed electrodes, and buried electrodes. This invention uses a high-voltage AC surface dielectric barrier discharge plasma actuator for de-icing, which has advantages such as small size, light weight, low power consumption, fast response, no mechanical parts, and high heating efficiency. Furthermore, by utilizing the aerodynamic effect of the plasma actuator, energy can be injected into the airfoil boundary layer, delaying surface flow separation and improving the aerodynamic performance of the wing.