181. High-lift generating device, wing, and noise-reduction device for high-lift generating device

申请号: JP2009164869

申请日: 2009-07-13

公开（公告）号: JP2011020476A

公开（公告）日: 2011-02-03

发明人: HIRAI MAKOTO; TAKENAKA KEIZO; IMAMURA TARO; YAMAMOTO KAZUOMI; YOKOGAWA YUZURU

<P>PROBLEM TO BE SOLVED: To provide a high-lift generating device which reduces noises caused when flaps are deployed and suppresses the degradation of aerodynamic characteristics when the flaps are retracted, and moreover, suppresses an increase in weight, and to provide a wing and a noise-reduction device of the high-lift generating device. <P>SOLUTION: The high-lift generator includes a flap 5 arranged in a deployable/retractable manner to a main wing, and a protrusion 6A-1 protruded smoothly in a direction away from the flap 5 in the vicinity of at least one end in the positive pressure surface PS of the flap 5. <P>COPYRIGHT: (C)2011,JPO&INPIT

182. A SHIP'S HULL AND A SHIP INCLUDING SUCH A HULL

申请号: PCT/NO2011/000267

申请日: 2011-09-21

公开（公告）号: WO2012087146A1

公开（公告）日: 2012-06-28

发明人: LADE, Terje

A ship's hull is provided where a substantial portion of the ship's hull, above its waterline, is designed essentially as a section of an aerofoil of the NACA foil type which is symmetrical to the centre line (S) of the ship's hull and where the leading edge (3) of the aerofoil section (2) is facing in the direction of the front of the ship (1), in order, with relative wind, to generate an aerodynamic lift that produces propulsion for the ship (1) within an angular sector of the ship's (1) course or direction of propulsion, the aerodynamic lift being balanced out by a hydrodynamic lift generated below the waterline. Also provided is a ship (1) including the aforementioned ship's hull.

183. Control force generator

申请号: US678347

申请日: 1984-12-05

公开（公告）号: US4682746A

公开（公告）日: 1987-07-28

发明人: Andrew S. W. Thomas

A control force generator for an aircraft using circulation control to a selectively produce lift on an otherwise non-lift surface. The generator employs a novel, double-slot single Coanda surface arrangement for selectively generating the aerodynamic lift.

184. Vortex left platform

申请号: US12660903

申请日: 2010-03-08

公开（公告）号: US20110215191A1

公开（公告）日: 2011-09-08

发明人: William D. Gramling

Apparatus and method of using a generated vortex contained in a cylindrical enclosure to generate aerodynamic lift.

185. AERODYNAMIC LIFT ENHANCING SYSTEM FOR A FLYING AUTOMOTIVE VEHICLE

申请号: US14744858

申请日: 2015-06-19

公开（公告）号: US20160368339A1

公开（公告）日: 2016-12-22

发明人: Taewoo Nam

An aerodynamic lift enhancing system for increasing aerodynamic lift generated by a body of an automotive flying vehicle is disclosed. The automotive flying vehicle includes a vehicle body enclosing a passenger compartment and having an upper surface at least partially defined by a hood, a roof extending over the passenger compartment, and a front windshield disposed between the hood and roof. The front windshield includes a leading edge positioned proximate a trailing edge of the hood and a trailing edge positioned adjacent the roof. The automotive flying vehicle includes wings extending laterally outward from the vehicle body. The aerodynamic lift enhancing system includes an air discharge nozzle located upstream from the leading edge of the front windshield, the air discharge nozzle operable to discharge a stream of air over the upper surface of the vehicle.

186. Wind-turbine blade, wind power generator equipped with the same, and design method for the same

申请号: JP2010238038

申请日: 2010-10-22

公开（公告）号: JP2012092657A

公开（公告）日: 2012-05-17

发明人: FUKAMI KOJI

PROBLEM TO BE SOLVED: To provide a wind-turbine blade which achieves desired aerodynamic characteristics under condition that the upper-limit value of the chord length on the blade-root side is restricted.SOLUTION: The wind-turbine blade includes a blade body 3 in which the chord length is increased from the blade tip 1b side to the blade root 1a side. The blade body 3 has: a blade tip region 1c provided on the tip side of the blade body and in which the chord length is gradually increased toward the blade root 1a side while having a substantially constant first design lift coefficient; a maximum chord length position 1d located at a position that becomes the maximum chord length on the blade root 1a side and having a second design lift coefficient larger than the first design lift coefficient; and a transition region 1e located between the blade tip region 1c and the maximum chord length position 1d. The design lift coefficient of the transition region 1e is gradually increased from the first design lift coefficient to the second design lift coefficient in a direction from the blade tip 1b side toward the blade root 1a side.

187. Method for easily evaluating drag of model receiving aerodynamic lift in magnetic suspension and balance system

申请号: JP2007092049

申请日: 2007-03-30

公开（公告）号: JP2008249527A

公开（公告）日: 2008-10-16

发明人: SAWADA HIDEO

PROBLEM TO BE SOLVED: To provide a technique capable of rationally evaluating aerodynamic forces by substantially improving the efficiency of wind tunnel test and simultaneously eliminating such waste that both a model suspension device and a mechanical balance device, which should not have been required for a wind tunnel provided with a magnetic suspension and balance system, should be separately provided. SOLUTION: In a method for easily evaluating drag of a model receiving aerodynamic lift in a magnetic suspension and balance system, a known external force in a horizontal direction is provided for the model in a state on which lift is not acting to determine the relation of a drag coil current balancing the horizontal external force. A rate of change (B) of the drag coil current to changes in the horizontal external force is quantitatively evaluated on the basis of the relation. The relation between the drag coil current (I _drag) and attitude angles (θ) when the attitude angle of the model is changed without providing any external force except gravity is determined. Drag (D) when lift (L) is acting is evaluated on the basis of gravity (mg) acting on the model on the basis of a proposed equation. COPYRIGHT: (C)2009,JPO&INPIT

188. Dynamic lift adjustment structure of current collector

申请号: JP2012138787

申请日: 2012-06-20

公开（公告）号: JP2014003847A

公开（公告）日: 2014-01-09

发明人: MITSUMOJI TAKESHI; SATO YUICHI; IKEDA MITSURU

PROBLEM TO BE SOLVED: To provide a dynamic lift adjustment structure of a current collector, which can easily adjust dynamic lift acting on the current collector by reducing aerodynamic force acting on the frame of the current collector with a simple structure.SOLUTION: A turbulent flow transition part 10 allows a laminar flow boundary layer formed on a frame surface 6e by a flow F on the frame surface 6e of a current collector 3 to make a transition to a turbulent flow boundary layer. When there is the turbulent flow transition part 10 on the frame surface 6e, the laminar flow boundary layer on the frame surface 6e makes a transition to the turbulent flow boundary layer, and the flow F is disturbed by the turbulent flow transition part 10, causing active momentum exchange. Thus, the flow F is hardly separated from the frame surface 6e, and the separation of the flow F from the frame surface 6e is retarded. As a result, a separation point of the flow F is moved backward to the downstream side so that Karman vortices generated behind a frame 6 are weakened, and aerodynamic force Lacting on the frame 6 is reduced. Thereby, dynamic lift Lacting on the current collector 3 is adjusted.

189. HYBRID AIRSHIP

申请号: US12429542

申请日: 2009-04-24

公开（公告）号: US20100270424A1

公开（公告）日: 2010-10-28

发明人: James D. DeLaurier

A hybrid airship comprises a non-rigid body having a delta-wing shape and an airfoil cross-section. The body is shaped for generating aerodynamic lift during forward flight, and contains a gas for generating buoyancy lift. At least one splitter plate is pivotally connected along a trailing edge of the body. The splitter plate is configured to be controllably pivoted for controlling the airship.

190. SPLITTER PLATE FOR HYBRID AIRSHIP CONTROL

申请号: PCT/CA2010/000631

申请日: 2010-04-23

公开（公告）号: WO2010121384A1

公开（公告）日: 2010-10-28

发明人: DELAURIER, James D.

A hybrid airship comprises a non-rigid body having a delta-wing shape and an airfoil cross-section. The body is shaped for generating aerodynamic lift during forward flight, and contains a gas for generating buoyancy lift. At least one splitter plate is pivotally connected along a trailing edge of the body. The splitter plate is configured to be controllably pivoted for controlling the airship.

191. Gliding ring

申请号: US3992

申请日: 1979-01-16

公开（公告）号: US4456265A

公开（公告）日: 1984-06-26

发明人: Alan J. Adler

A gliding ring toy comprised of an annular airfoil angled in order to compensate for air downwash effects and to balance the aerodynamic lift, fore and aft, in gliding flight.

192. DEVICE AND METHOD FOR INCREASING THE AERODYNAMIC LIFT OF AN AIRCRAFT

申请号: EP11767986.0

申请日: 2011-10-05

公开（公告）号: EP2625096A1

公开（公告）日: 2013-08-14

发明人: WEBER, Carsten; FISCHER, Markus; GROTE, Arne; RADESPIEL, Rolf; DREYER, Martin

A lift arrangement for an aircraft (2) comprises an aircraft fuselage section with an outside (3), an aerodynamic lift body (6, 8)attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies (12)arranged upstream of a leading edge (14) of the aerodynamic lift body (6, 8). The add-on bodies(12) comprise an aerodynamically effective surface and are equipped with incoming airflow to generate vortices (18) that impinge on the aerodynamic lift body (6, 8), thus leading to an increase inlift on the aerodynamic lift body (6, 8). Consequently it becomes possible with simple means to effectively influence lift generation on a lift body (6, 8), in particular to compensate for loss of lift as a result of icing. Preferably, the add-on bodies are moveable, and, when operational conditions do not require the use of said add-on bodies, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.

193. Marine Propulsion Multihull Ship

申请号: US15111896

申请日: 2015-01-15

公开（公告）号: US20160332700A1

公开（公告）日: 2016-11-17

发明人: Lionel Huetz; Gianluca Guelfi; Matthieu Kerhuel; Hubert Thomas

A ship having a length to width ratio smaller than two and including a superstructure and at least two hulls, the superstructure forming a wing able to generate an aerodynamic lift comprised between 20 and 90% of the weight of the ship at a cruising speed thereof, the wing including curved ends connected to each of the hulls and having a developed surface of an extrados of the wing substantially equal to the product of the length by the width of the ship, wherein a point for application of the aerodynamic lift generated by the superstructure is situated behind the center of gravity for application of the gravitational forces on the ship, and a point for application of the resultant of the hydrodynamic forces generated by the hulls is situated in front of the center of gravity.

194. Negative lift measurement device for automobile

申请号: JP2004253559

申请日: 2004-08-04

公开（公告）号: JP2006044623A

公开（公告）日: 2006-02-16

发明人: TANAKA YUJI

PROBLEM TO BE SOLVED: To measure intensity of negative lift of an automobile gradually varied at traveling of the automobile and to inform a driver of intensity of the negative pressure at the present time. SOLUTION: In the negative lift measurement device 9 for the automobile, a (screw type) load sensor 7 is provided between a trunk lid 2 of the automobile 1 and an aerodynamic power device (wing) 3, an input part for converting a signal of the load sensor to a numerical value and an operation part for calculating the numerical value from the input part are provided and a numerical value display part for receiving the signal from the operation part and displaying the negative lift. COPYRIGHT: (C)2006,JPO&NCIPI

195. DEVICE AND METHOD FOR INCREASING THE AERODYNAMIC LIFT OF AN AIRCRAFT

申请号: EP11767986.0

申请日: 2011-10-05

公开（公告）号: EP2625096B1

公开（公告）日: 2017-07-19

发明人: WEBER, Carsten; FISCHER, Markus; GROTE, Arne; RADESPIEL, Rolf; DREYER, Martin

196. High lift force-generating device, wing and slat

申请号: JP2010030075

申请日: 2010-02-15

公开（公告）号: JP2011162154A

公开（公告）日: 2011-08-25

发明人: HAYASHI KENSUKE; ISHIHARA KENYA; YAHATA YUSAKU; HIRAI MAKOTO

PROBLEM TO BE SOLVED: To provide a high lift force-generating device and a wing, which can suppress generation of aerodynamic noise while suppressing increase in body weight. SOLUTION: A recess and projection part 20 is formed in a bottom plate 7 extending rearward in a lower surface of a slat 3, so that a position in which air flow flowing along the surface of the slat 3 is exfoliated from the bottom plate 7 to generate a vortex is made uneven in the air flow direction. Thereby, the vortex generated in a recess 20A and the vortex generated in a projection 20B are short in correlation with each other, and the vortices are hardly connected to each other, and becomes the independent vortexes, so that the generated vortex is weak in strength, which can reduce the pressure fluctuation on a body surface, and suppress generation of the aerodynamic sound. COPYRIGHT: (C)2011,JPO&INPIT

197. Low aerodynamic noise type current collection equipment

申请号: EP94305343.9

申请日: 1994-07-20

公开（公告）号: EP0635392A1

公开（公告）日: 1995-01-25

发明人: Hidaka, Hideto; Iwamoyto, Kengo; Noguchi, Yasuhiro; Miyamura, Motohiro; Yazima, Seiichi; Sakai, Inao

A low aerodynamic noise type current collection equipment is provided for reducing variation in aerodynamic force applied to a current collector during the train operation. A central region (2a) of a current collector (1) having a collector head (2) with a top surface in which a contact strip (3) is embedded is rectangular in cross-section, and each side region is shaped in cross-section convex in the front and rear directions, such as an elliptical shape. The rectangular shape has characteristics such that the magnitude of the aerodynamic lift force would be kept substantially constant even if the inclination angle against the aerial flow would be changed. Accordingly, the cross-sectional shape of the central region (2a) of the current collector (1) which is liable to receive the turbulent aerial flow by the support portion (4) in the current collector (1), whereby it is possible to suppress the variation in aerodynamic lift force generated in the current collector even if the angle of the aerial flow that would collide against the current collector (1) would be unstable. The cross-sectional shape of each side region (2b) is made convex in the front and rear directions such as an elliptical shape to thereby reduce the aerodynamic noise.

198. Ground effect craft with divergent channel

申请号: US3726246D

申请日: 1971-04-07

公开（公告）号: US3726246A

公开（公告）日: 1973-04-10

发明人: WUKOWITZ E

This invention relates to an advanced marine ground effect design concept achieving aerodynamic lift with thrust contributing forces by fluid flow through a divergent channel in the bottom of the craft. The invention is illustrated as applied to a motor boat hull having catamaran sections on both sides of the divergent channel. Velocity head of air is converted into pressure head in the channel to develop lift and forward thrust.