| Document |
Document Title |
|
JP2014046912A |
To enhance fuel efficiency improving performance of a rotor ship and downsize a rotor of the rotor ship by devising the surface shape of the rotor to improve a lift generating function of the rotor.In the rotor of a rotor ship, grooves a...
|
|
JP5431728B2 |
An aircraft including: a fuselage and two wings to which engine nacelles are attached and that are each connected laterally to the fuselage, one on each side thereof, by a central fairing. The central fairing includes, facing each wing, ...
|
|
JP2014009796A |
To provide a plasma actuator that has a structure capable of increasing kinetic energy of a fluid to be induced.The plasma actuator 1 includes a front face side electrode plate 3 and a rear face side electrode plate 4 while interposing a...
|
|
JP5361893B2 |
Wingtip feathers, including paired, fixed features, and associated systems and methods are disclosed. A method for designing an aircraft wing in accordance with a particular embodiment includes providing a geometry for a wing having an u...
|
|
JP2013236995A |
To provide an air current generating device which can accelerate a flow rate of a generated induced flow while suppressing a voltage to be applied to a pair of electrodes which generates dielectric barrier discharge.An air current genera...
|
|
JP5314198B1 |
To move the center of gravity of a conventional vertical take-off and landing transport aircraft forward due to the influence of a tail wind received by a vertical take-off and landing transport aircraft during low-speed flight, and the ...
|
|
JP5313884B2 |
An aircraft including a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pylon. At least one profiled ...
|
|
JP5308349B2 |
An airborne mobile platform generally includes a plurality of rotating rotor blades operating in an airflow that forms a boundary layer on each of the rotor blades. At least one of the rotor blades includes a section that encounters the ...
|
|
JP5302215B2 |
The fuselage has a central fuselage (4) comprising zones (10, 12, 14) on a side of a front fuselage (2). The width of the zone (10) measured along a tangent axis increases until a maximal width from the front towards rear of an aircraft....
|
|
JP5265519B2 |
Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the en...
|
|
JP5231770B2 |
Active systems and methods for controlling aircraft vortices are disclosed. An apparatus (50) in accordance with one embodiment is directed to an aircraft system that includes an airfoil (14) having first and second oppositely facing flo...
|
|
JP5205284B2 |
Apparatuses and methods for the controlled trailing wake flows. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. ...
|
|
JP5185784B2 |
|
|
JP5185871B2 |
|
|
JP5160098B2 |
|
|
JP5129232B2 |
The arrangement (1) has a wing (2) including proximal and distal ends, and a hooking pylon (4) of an engine (6) e.g. turbojet engine, suspended under the wing. The wing has a front zone (8) e.g. aerodynamic zone, situated toward the fron...
|
|
JP5126609B2 |
An aircraft includes a wing having a positive dihedral, the wing having a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than ...
|
|
JP5060163B2 |
|
|
JP5057374B2 |
|
|
JP5053263B2 |
A method for modeling the acoustic signature produced by an aircraft of interest flying at a particular supersonic Mach number/altitude operating point of interest. The method includes operating a sub-scale aircraft that is a sub-scale v...
|
|
JP5046115B2 |
To provide a noise reduction device composed by a simple mechanism capable of appropriately reducing a noise generated between a steering wing and a body wing without deteriorating an aerodynamic performance of an aircraft in taking off ...
|
|
JP5032486B2 |
The device has a control unit (8) provided in the form of a triangular tip in side and top views. The unit (8) is arranged on a fixation unit (11) of an oblong element (5) e.g. jet engine, and an aircraft carrier surface (4) such that a ...
|
|
JP4940434B2 |
A smart vortex generator including a main body, disposed on a body surface, such as a main wing of aircraft, making a boundary to a flow of fluid, and at least a part of which includes a shape memory alloy. A form of the main body, depen...
|
|
JP4882089B2 |
The system has a component (2) attached at an outer end of an aerofoil of an aircraft and comprising a fixed unit and two swiveling aerofoil units (7, 8) that are arranged downstream of the fixed unit and hinged relative to one another i...
|
|
JP4831337B2 |
To provide a vortex generator constituted of a simple mechanism capable of suppressing separation of the air flow flowing on an upper surface of a flap when the deflection angle of the flap is large, and suppressing increase of the air r...
|
|
JP4820878B2 |
A rudder of a commercial aircraft is provided that is divided along its longitudinal direction in at least one region and the parts of the rudder can be spread against the air flow surrounding the aircraft by means of an actuator in orde...
|
|
JP4800638B2 |
A helicopter (1) having a fuselage (2); and two rear wings (6) located on opposite sides of the fuselage (2) and having winglets (7), each projecting transversely from a free end of the relative wing (6).
|
|
JP2011522739A |
A device for the generation of aerodynamic vortices to be arranged on the spanwise side edge of a wing, or a regulating flap adjustably arranged on the latter, which in each case have a chordwise direction and a spanwise direction, where...
|
|
JP2011520687A |
An airfoil comprising a high pressure surface; a low pressure surface; a leading edge where the high and low pressure surfaces meet at the front of the airfoil; and a trailing edge where the high and low pressure surfaces meet at the bac...
|
|
JP4713160B2 |
An aerofoil has a body (14), and at least one flow control device, the flow control device including a passage (22) within the body (14) of the aerofoil, and a passage outlet (21) at an upper aerofoil surface (18) of the aerofoil, whereb...
|
|
JP4709777B2 |
A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and th...
|
|
JP2011513114A |
An aerodynamic structure (1) comprising a series of shock bumps (3a, 3b, 3c) extending from its surface. The shock bumps are distributed along a line (7) with a smaller mean angle of sweep than an unperturbed shock (4) which would form a...
|
|
JP4583562B2 |
To provide such a device for improving an aerodynamic characteristic that a nonlinear aerodynamic characteristic caused by a peeling off of border layer is not generated. In an airframe shape having a large contraction toward a rear side...
|
|
JP2010241406A |
To solve a problem that a helicopter and a space shuttle have complicated structures. A structure is vertically vibrated. When an actuator is elongated and contracted, the whole structure is vibrated and lift is generated.
|
|
JP2010120420A |
To provide a missile using a Coanda effect capable of efficiently generating lift.This missile 1 is a missile 1 using the Coanda effect and includes a blasting means 4 to blast an air current directed to the side of an upper surface 2a f...
|
|
JP4405685B2 |
An acoustic jet disposed within an aerodynamic surface, such as a wing or a blade, has a resilient wall supporting a mass. Vibrations of the blade cause oscillatory pressure waves within the acoustic jet, the nozzle of which directs flui...
|
|
JP4399191B2 |
A helicopter (1) having: a flow control device (8) provided at one of a lower portion of a side surface (2a) of a fuselage (2) and a portion on a lower surface (2a) of the fuselage (2) near the side surface (2a) and extending downward.
|
|
JP2009292451A |
To provide a blade having favorable characteristics, preventing vortexes of fluid such as a vortex easily generated at a distal end of the blade due to separation of the fluid and a trailing vortex.A body, a lateral face 12, a guide face...
|
|
JP2009527405A |
A high-lift flap of an aircraft is provided having a device for influencing the flap vortex as well as a device for influencing the flap vortex at the lateral edge of the aerodynamic high-lift flap, which can be achieved effectively and ...
|
|
JP2009515750A |
Described is a brake flap for an aircraft, which brake flap, for the purpose of delaying the aircraft, can be set at an angle relative to the airstream flowing around it, wherein the flap (20) comprises a free edge (21) which when set at...
|
|
JP2009511360A |
An aircraft includes a surface over which an airflow passes. A plasma actuator (1) is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of...
|
|
JP4237981B2 |
A main wing structure comprises at least a leading edge structure (11) and a wing central structure (12) coupled to each other, and has a particular laminar-flow airfoil. The laminar-flow airfoil includes an upper wing surface (Su), a lo...
|
|
JP2009029400A |
To provide a flying unit capable of increasing a lift force by a Coanda effect.This flying unit comprises a fluid supplying segment 20 for supplying fluid, a lift force generating segment 80 having an outer surface 12 inclined downward w...
|
|
JP4220393B2 |
|
|
JP2009501304A |
This invention relates to an element (11) for generating a fluid dynamic force, the element (11) comprising first (13) and second (15) surfaces extending in opposite directions from a leading edge (17) of the element (11) and meeting at ...
|
|
JP2008544921A |
A flow control device is disclosed including a flow control surface over which fluid is designed to flow in a predetermined direction. Vortex generators are associated with the flow control surface. Each respective vortex generator has a...
|
|
JP2008110678A |
To provide a deceleration method which is applicable to a flying object having a conical nose cone on its fore end and flying at high speed, or a moving object navigating in water, and utilizing the fluid resistance operable by a compact...
|
|
JP2008106619A |
To attain improvement of dynamic lift of a wind power generator and an aircraft by developing a wing shape capable of generating the dynamic lift over low to high wind speed areas since in a conventional fixed wing, the dynamic lift is l...
|
|
JP4070215B2 |
|
|
JP3980775B2 |
It is an object of the present invention to reduce the wave resistance by disposing a fluid element such as an engine nacelle in a predetermined position on the upper surface of the main wing, and positively superposing the air flow gene...
|
