| Document |
Document Title |
|
JP7097591B2 |
A flow control method according to one aspect of the present disclosure is a flow control method of controlling flow around a blade of a rotary wing, a plasma actuator being disposed at the blade. The flow control method includes: determ...
|
|
JP7096698B2 |
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 actuato...
|
|
JP7015585B2 |
The purpose of the present invention is to provide a paraglider with which it is possible to perform a rise-up without being aided by the force of wind, and generate an airflow from the front to the rear of the upper surface of a canopy ...
|
|
JP7012226B2 |
To freely perform both of reduction of a pressure resistance and reduction of friction resistance, and perform air flow control therefor in a state of having no penalty substantially.An air flow controller 4 comprises: a sensor 5 for det...
|
|
JP2021187328A |
To provide a lift variable mechanism which can vary a lift generated at a wing of an aircraft without moving a large member such as a movable wing piece of the aircraft, a rotor blade of a rotary wing aircraft or the like.A lift variable...
|
|
JP6964886B2 |
A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the co...
|
|
JP2021526094A |
The vehicle includes a main body and at least one wing coupled to the main body. The source of the compressed fluid is coupled to the main body. The vehicle further includes first and second thrusters, each said first and second thruster...
|
|
JP2021113608A |
To provide a method of reducing resistance or drag received by an object, for example, an aircraft by using staggered periodic riblets.First periodic riblets (110) are formed on a smooth surface (104) of a physical object (100), and then...
|
|
JP6910801B2 |
An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. A micro-lattice support structur...
|
|
JP6854088B2 |
Aerodynamic microstructures 300 having sub-microstructure are disclosed herein. One disclosed example apparatus includes an aerodynamic microstructure 300 defining an external surface of a vehicle 100, and a pattern of sub-microstructure...
|
|
JP6854089B2 |
Aerodynamic microstructures (312, 314, 316, 402, 708, 808, 1008) having sub-microstructure (312, 314, 316, 402, 708, 808, 1008) are disclosed herein. One disclosed example apparatus includes an aerodynamic microstructure on an external s...
|
|
JP2021032220A |
To provide a cross flow fan that can increase a wind pressure and an air volume without increasing a diameter.A cross flow fan 3 comprises: a plurality of vanes 15 arranged at predetermined intervals in a circumferential direction around...
|
|
JP2021011258A |
To provide a method of enhancing operation of an aircraft and a method of manufacturing a wing that are capable of improving aerodynamic efficiency by maintaining a laminar flow under cruise conditions while handling worst-case condition...
|
|
JP6826068B2 |
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 ...
|
|
JP6779624B2 |
In one aspect the present subject matter is directed to a gas-electric propulsion system (100) for an aircraft (10). The system may include a turbofan jet engine 1(02,104), an electric powered boundary layer ingestion fan (106) that is c...
|
|
JP6734762B2 |
An airfoil (400) includes a first side (410) and a second side opposite the first side, and an apparatus (450a) coupled to the first side (410) of the airfoil (400), the apparatus (450a) comprising a first edge having a first uneven edge...
|
|
JP6714925B2 |
[Object] To provide a riblet structure that further reduces drag, which is a sum of turbulent friction drag and pressure drag, and an object including such a riblet structure. [Solving Means] An object 1 such as an aircraft, plant, and p...
|
|
JP6707391B2 |
To provide a blade including an air flow generation device capable of sufficiently obtaining air flow control effect for a long term.The blade 10 including an air flow generation device includes a blade body 20 and an air flow generating...
|
|
JP6706235B2 |
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 t...
|
|
JP6689231B2 |
An intake designing method includes: setting a value of a design parameter related to a design target that is directed to a front fuselage, a bump, and an intake duct of an aircraft; setting a shape of the design target on the basis of t...
|
|
JP6681749B2 |
A structure for anti-adhesion of high-temperature air according to the present invention includes: a high-temperature air duct that is provided in an accessory of an aircraft and allows high-temperature air likely to be higher than a spe...
|
|
JP6675731B2 |
To provide an airflow generation device in which dielectric substrates and electrodes are strongly bonded by chemically crosslinking through chemical bonds, which efficiently and homogeneously generates an airflow by plasma discharge bet...
|
|
JP2020032938A |
To provide a flight body that establishes compatibility between safe landing and short field takeoff by a high lift coefficient and a reduction in induction resistance during high-speed navigation, by a simple structure.A flight body hav...
|
|
JP2019209736A |
To provide an unmanned flight body with improved thrust.In an unmanned flight body which obtains thrust by rotation of plural propellers 12 and flies, an electrode 20 is located on an upper surface part 12s of the propeller 12 along a fr...
|
|
JP2019189045A |
To provide a device that prevents reduction of a lift even when the angle of attack of a flap provided on a main wing or the like of an aircraft is increased.A wing structure 1 is for an aircraft, and includes a stationary wing 3, a flap...
|
|
JP6563645B2 |
A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to all...
|
|
JP6500002B2 |
A propulsion system for an aircraft (200) including a plurality of primary engines is provided. The plurality of primary engines includes at least a first primary engine (252) and a second primary engine (254), each configured for mounti...
|
|
JP6491981B2 |
To provide an air flow generator capable of suppressing electric field concentration near the top of both ends of columnar electrodes inside a dielectric.An air flow generator comprises: a dielectric; a first columnar electrode arranged ...
|
|
JP6453578B2 |
An aero-contouring apparatus is provided. The aero-contouring apparatus has a housing assembly and a motor assembly disposed therein. The motor assembly has a motor unit and a drive unit. The aero-contouring apparatus further has an enga...
|
|
JP6424042B2 |
An airfoil active bleed system and related method. A housing includes an induction wall (39), an exhaust wall (40a,b) having one or more exhaust ports (44), and a chamber (41) between the induction and exhaust walls. Zero-net-mass-flux a...
|
|
JP6401759B2 |
A propulsion system for an aircraft (10) is provided having an aft engine configured to be mounted to the aircraft (10) at an aft end of the aircraft (10). The aft engine includes a fan (304) rotatable about a central axis of the aft eng...
|
|
JP2018151059A |
To provide a turbulent flow friction resistance reduction device that eliminates the need for highly frequent maintenance and the need for a complicated control system.A turbulent flow friction resistance reduction device 10 has a wall s...
|
|
JP6387062B2 |
A propulsion system (100) for an aircraft (10) is provided having an aft engine configured to be mounted to the aircraft (10) at an aft end of the aircraft (10). The aft engine includes a fan (304) rotatable about a central axis of the a...
|
|
JP2018127151A |
To provide a working robot which can move on even an off-road and has high working efficiency.A hopper robot has: a ducted fan; a robot structure; radio communication equipment; an inertia measurement device; a ladder; a momentum wheel; ...
|
|
JP2018016239A |
To provide an aircraft that is suitable for slow flight with reduced air resistance relative to that a variety of tailless aircrafts having a triangular shape in plan view are disclosed but any of them are suitable for high speed flight....
|
|
JP2018004059A |
To provide an airflow control apparatus capable of producing sufficient airflow control effects even in a situation where a boundary layer of an airflow flowing through a surface of an object can become thicker.An airflow control apparat...
|
|
JP2017534808A |
The profile element used to generate the force comprises a material having an effective surface and a plurality of cavities arranged on the effective surface of the material. The plurality of cavities comprises pinholes, each pinhole hav...
|
|
JP6213985B2 |
When a target object is made of an insulating material, a conducting wire (3) and a conductive thin film (5) are attached to a surface of the target object so as to be opposed to each other, and a pulse voltage is applied between the con...
|
|
JP6133946B2 |
The invention relates to an air generation unit (1) for an aircraft (100), an air generation arrangement (10), an aircraft (100) and a method for operating an air generation unit (1) in an aircraft (100). The air generation unit (1) for ...
|
|
JP6128568B2 |
In an intake structure of an aircraft that takes in air from a front side of an airframe, a bump is provided on a surface of the airframe of the aircraft at a portion immediately before an intake. The bump is formed so as to smoothly pro...
|
|
JP6126299B2 |
An assembly includes a substrate, a film on the substrate, and a coating on the film. The film includes a material permeable to organic solvents, and the coating includes a material reactive with the film. Alternatively, the assembly may...
|
|
JP6105290B2 |
Air vehicles and associated aerodynamic structures are provided which include ridged solar panels to both reduce the drag and increase the solar energy harvested by the solar panel. The air vehicle may include an airframe and a solar pan...
|
|
JP6039714B2 |
A dual channel wing for an aircraft, comprising an inboard and an outboard portion, wherein each portion comprises a channel wing section. Each channel may include a propulsor and the propulsors of each of the channels may be offset rela...
|
|
JP6029068B2 |
The purpose of the present invention is to provide a surface flow control system, with which laminarization of the boundary layer can be controlled over a broad range from low velocity to high velocity regardless of the form of the movin...
|
|
JP5963673B2 |
An array of aerodynamic riblets is formed with a surface layer for adhering to an aerodynamic surface and a plurality of riblet tips having a parabolic cross section extending from the surface layer ( Fig. 1 ).
|
|
JP2016107958A |
To provide a boundary layer controller configured to correspond to the intake side inner peripheral surface shape of a propulsion engine in an aircraft.The boundary layer controller includes a venturi generator 10 configured such that wh...
|
|
JP5871508B2 |
To provide an impeller wheel airplane and an impeller wheel in which bird's wing-flapping motion is converted into parallel rotary motion.The impeller wheel 4 converts the bird's wing-flapping motion into rotary motion by periodically sw...
|
|
JP2016008040A |
To provide a boundary layer control device of an aircraft which suppresses boundary layer separation and, thereby, highly contributes to stable flight of the aircraft even upon landing and taking-off of the aircraft in which the separati...
|
|
JP5738772B2 |
A purging system for a laminar flow control system comprises an air scoop and a diffuser fluidly connected thereto. The air scoop is disposable into an external flow of an external atmosphere. The diffuser is configured to fluidly connec...
|
|
JP5700974B2 |
|
