The present invention relates to an ice detection/protection and flow control system based on printing of dielectric barrier discharge sliding plasma actuators. This invention has advantages such as: reduced weight, low maintenance cost, no environmental impact, fully electric operation and combination of functionalities (ice detection, deicing, anti-icing and flow control).

The system comprises the following components: exposed AC electrode (1), dielectric layer (2), embedded electrode (3), sliding/nanosecond electrode (4), ground plane (5), AC power supply (6), DC power supply (7), nanosecond range pulse generator (8), monitoring capacitor (9), high voltage probe (10), control module (11), temperature sensor (12), control signal input module (13) and monitoring system (14). The system senses ice formation and generates extensive surface heating to prevent ice accumulation.

A flow control apparatus includes a plasma actuator, a storage device, and a control circuit. The plasma actuator causes discharge in a discharge area by applying an alternating-current (AC) voltage between electrodes to form an induced flow of gas. The electrodes are shifted relatively to each other with a dielectric disposed between them. The storage device stores a changing condition of an AC voltage waveform for changing a gas flow state formed in a flow control area of gas from a first state to a second state by adding the induced flow of gas. The control circuit refers to the changing condition of the AC voltage waveform and control the AC voltage waveform based on the changing condition of the AC voltage waveform, in a case of changing the gas flow state formed in the gas flow control area from the first flow state to the second flow state.

A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor.

In an embodiment of the invention there is a cyclotronic actuator. The actuator is defined by having a high-voltage plasma driver connected to a first electrode. The first electrode is surrounded by a dielectric material. A second electrode is grounded and placed away from the first electrode, such that a plasma arc is formed between the pair of electrodes when the high-voltage plasma driver is activated. A ring magnet surrounding the second electrode is configured to introduce a magnetic field locally to the plasma arc. The plasma arc will then discharge in a radial direction. The magnet creates a local magnetic field oriented vertically in a direction parallel to the axisymmetric orientation of the first and second electrodes to create a Lorentz Force. The force causes the plasma arc to move in a tangential direction and causes the plasma arc to discharge out in a circular pattern.

An aircraft control system includes a flow control device and a control circuit. The flow control device is configured to control a flow of air around an aircraft. The control circuit is configured to control the flow control device so that a pressure distribution loaded on a surface of a structure that constitutes the aircraft is equal to a control value of a pressure distribution calculated based on a physical quantity detected by a sensor provided in the aircraft. The physical quantity relates to the air.

A wing comprising a leading edge composed of a skin transparent to microwaves, magnetrons implanted under the skin and arranged in rows and in columns alongside one another, between two successive rows of magnetrons, a discharge row successively comprising an electrode and a ground electrode, where each electrode passes through the skin and where each ground electrode is under the skin.

A system includes a surface, an actuator, and processing circuitry. The surface includes one or more non-actuating zones and one or more actuatable zones. The actuator is configured to a flow property of a fluid that flows over the one or more actuatable zones of the surface. The processing circuitry is configured to obtain a value of a parameter of the fluid that flows over the surface, and operate the actuator to adjust the flow property of the fluid that flows over the one or more actuatable zones based on the value of the parameter of the fluid.

Systems, equipment, and methods to deposit energy to modify and control air flow, lift, and drag, in relation to air vehicles, and methods for seeding flow instabilities at the leading edges of control surfaces, primarily through shockwave generation through deposition of laser energy at a distance.

A method is provided for generating a region of plasma in a gaseous atmosphere that includes argon. A laser beam from a Ti:sapphire laser is directed into the gaseous atmosphere such that a portion of the argon along the laser beam is ionized. Microwave energy is directed into the ionized region of the laser beam to generate a plasma.

In an embodiment of the invention there is a cyclotronic actuator. The actuator is defined by having a high-voltage plasma driver connected to a first electrode. The first electrode is surrounded by a dielectric material. A second electrode is grounded and placed away from the first electrode, such that a plasma arc is formed between the pair of electrodes when the high-voltage plasma driver is activated. A ring magnet surrounding the second electrode is configured to introduce a magnetic field locally to the plasma arc. The plasma arc will then discharge in a radial direction. The magnet creates a local magnetic field oriented vertically in a direction parallel to the axisymmetric orientation of the first and second electrodes to create a Lorentz Force. The force causes the plasma arc to move in a tangential direction and causes the plasma arc to discharge out in a circular pattern.