Subaru Corporation

Maki Kikuchi

Hiroki Kato

Kentaro Yoshida

Nobuyuki Nakazato

Akitoshi Sakaguchi

Mitsuru Kono

Yukinobu Tomonaga

Takayuki Oguri

Kohei Nakano

Tomofumi Iwamoto

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.

Rotor support device, rotor, gas turbine engine, and aircraft

An aircraft includes an airframe, a hollow member, and a plasma actuator. The hollow member has a body and an internal flow passage. The body extends from front of the airframe to rear of the airframe and has a hollow shape. The internal flow passage extends in the body from the front to the rear. The body has an introduction port configured to introduce a fluid into the internal flow passage, and a blow hole provided more toward the rear than the introduction port, and penetrating the body from an inner circumferential surface of the body to an outer circumferential surface of the body. The plasma actuator is provided at the outer circumferential surface of the body, and disposed on one or more sides, in a circumferential direction of the body, of the blow hole.

Aircraft

A flow control system includes a movable wing attachable to a wing of an aircraft, and a plasma actuator mountable on a surface of the movable wing. The flow control system is configured to control air flow around the wing by having the changing of the steering angle of the movable wing work in conjunction with the operation of the plasma actuator.

Flow control system, flow control method, and aircraft

A wing structure for an aircraft includes a stationary wing, a movable wing and at least one plasma actuator. The movable wing is configured to have a slot between the movable wing and the stationary wing. The at least one plasma actuator is configured to control air flow through the slot.

Wing structure for an aircraft including plasma actuators for controlling air flow through a slot, and method of controlling the same

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.

Growing community of inventors

Tokyo, Japan

Maki Kikuchi