8 results about "Plasma actuator" patented technology

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.

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.

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.

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 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).

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.