261. TRAILING-EDGE FLAP SYSTEM

申请号: EP10776950.7

申请日: 2010-11-10

公开（公告）号: EP2499043A2

公开（公告）日: 2012-09-19

发明人: DOSTMANN, Tom; SCHLIPF, Bernhard; EICHHORN, Jochen

Trailing-edge flap system comprising a trailing-edge flap and a movement means, the movement means comprising at least a translatory mover for the translation of the trailing-edge flap and at least a rotational mover for the rotation of the trailing-edge flap.

262. WIND TURBINE BLADE CONTROL

申请号: PCT/GB2010000486

申请日: 2010-03-18

公开（公告）号: WO2010106322A3

公开（公告）日: 2011-04-21

发明人: WESTERFAARD CARSTEN HEIN; OLESEN NIELS ANKAR; SPRUCE CHRIS

A wind turbine variable is controlled by detecting air flow conditions in front of the leading edge of the blade. One or more Laser Doppler Anemometers are mounted on or incorporated into the blade to determine air flow velocity in the region in front of the leading edge of the blade. The measured flow conditions may be used to control the position of a control surface such as a trailing edge flap or the rotor speed. The LDAs may comprise lasers of different frequencies to enable more than one component of flow velocity to be measured.

263. ROTOR BLADE PITCH CONTROL ASSEMBLY

申请号: US10728270

申请日: 2003-12-04

公开（公告）号: US20050123400A1

公开（公告）日: 2005-06-09

发明人: Ashish Bagai

A rotor blade assembly provides a pitch control assembly to pitch the rotor blade about a rotor blade pitch axis. The pitch control assembly includes a trailing edge flap and a trailing edge servo flap that extend from the trailing edge of the rotor blade. The trailing edge flap is offset in the span wise direction relative to the trailing edge flap. The trailing edge servo flap is located upon a trailing edge servo flap arm linked to the trailing edge flap. To pitch the rotor blade, the trailing edge servo flap is pitched in a direction opposite the desired pitch direction of the trailing edge flap.

264. Aerodynamic prediction using semiempirical prediction techniques and methods therefor

申请号: US10036482

申请日: 2002-01-07

公开（公告）号: US06721682B1

公开（公告）日: 2004-04-13

发明人: Frankie G. Moore; Thomas C. Hymer

An improved aeroprediction code (APC) allows aerodynamics to be predicted for Mach numbers up to 20 for configurations with flares. Moreover, the improved APC advantageously extends the static aerodynamic predictions for Mach numbers less than 1.2, improves the body alone pitch damping for Mach numbers above 2.0, and develops a new capability for pitch damping of flared configurations at Mach numbers up to 20. The improved APC also permits determination of aerodynamic effects associated with power-on events and trailing edge flaps. Corresponding methods are also described.

265. RETRACTABLE BLADE STRUCTURE WITH A SPLIT TRAILING EDGE

申请号: PCT/IB2009/000118

申请日: 2009-01-23

公开（公告）号: WO2009095758A2

公开（公告）日: 2009-08-06

发明人: DEHLSEN, James, G., P.

This invention relates to blades, such as airfoils or rotor blades, in the field of aviation, or to blades of electric power-generating devices or fluid pumping devices, and more particularly to a structural support for a blade which has an outer aerodynamic module with a telescoping feature which, when extended out, increases the airfoil or blade diameter or length. The inventive extendible blade structure comprises an extender blade module (2) and a base blade module (8), the extender blade module (2) comprising a carrier airfoil shell (10) housing an extender blade (11), and an adjusting device for positioning the extender blade (11) between a retracted position within the carrier airfoil shell (10) and an extended position. The extender blade (11) is provided with trailing edge flaps (26, 28) and a support structure (34b) between the trailing edge flaps (26, 28), the flaps (26, 28) being urged together to form a trailing edge in the extended position, the carrier airfoil shell (10) is provided with a carrier airfoil shell support structure (24) and slots (56, 58) formed at upper and lower sides of the carrier airfoil shell support structure (24), each slot (56, 58) being adapted to accommodate one of the flaps (26, 28), the flaps (26, 28) being forced apart and guided into the slots (56, 58) by the carrier airfoil shell support structure (24) in the retracted position of the extender blade (11), and the carrier airfoil shell support structure (24) and the support structure (34b) of the extender blade (11) rest against each other between the flaps (26, 28).

266. Procédé et système de volet déporteur pour assurer la continuité aerodynamique à l'extrados d'une aile d'aéronef

申请号: EP04292116.3

申请日: 2004-09-02

公开（公告）号: EP1516813A1

公开（公告）日: 2005-03-23

发明人: Milliere, Jérôme

Selon l'invention, le volet déporteur (7) présente une corde (C) de longueur réglable et des moyens (16,19,20) sont prévus pour agir sur la longueur de ladite corde lorsque ledit volet déporteur (7) est en position rétractée.

267. Wing flap aerodynamic noise suppression

申请号: EP89313316.5

申请日: 1989-12-19

公开（公告）号: EP0375382A2

公开（公告）日: 1990-06-27

发明人: Whitehouse, Ian Roy; Chu, James K. British Aerospace

An arrangement for suppressing aerodynamic noise generated by cavity effect interaction between a wing flap shroud (18, 19) and one or more partially deployed trailing edge flaps (22). Noise suppression vanes (27) are so positioned with respect to the lower shroud (18) trailing edge (24) and the leading edge of the wing flaps at partial deployment that eddies and vortices (26) resulting from airflow separation at the lower shroud surface are diverted sufficiently by the noise suppression vanes (27) to avoid significant noise inducing impingement of the separated flow on the flap leading edge.

268. AIRCRAFT

申请号: EP16166183.0

申请日: 2016-04-20

公开（公告）号: EP3093235A1

公开（公告）日: 2016-11-16

发明人: Moxon, Matthew

An aircraft (10) comprises trailing edge flaps (17), a wing mounted propulsor (26) positioned such that the flaps (17) are located in a slipstream of the first propulsor in use when deployed. The aircraft (10) further comprises a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor comprises a ducted fan (30) configurable between a first mode, in which the fan (30) provides net forward thrust to the aircraft (10), and a second mode in which the fan (30) provides net drag to the aircraft. (10). The fan (30) is positioned to ingest a boundary layer airflow in use when operating in the first mode.

269. WIND TURBINE BLADE CONTROL

申请号: EP10710605

申请日: 2010-03-18

公开（公告）号: EP2409028B1

公开（公告）日: 2017-05-03

发明人: WESTERGAARD CARSTEN HEIN; OLESEN NIELS ANKER; SPRUCE CHRIS

270. FUSELAGE-MOUNTED LANDING GEAR ASSEMBLY FOR USE WITH A LOW WING AIRCRAFT

申请号: US14021301

申请日: 2013-09-09

公开（公告）号: US20150069178A1

公开（公告）日: 2015-03-12

发明人: Stephen T. Brown; Michael Lane Drake; Christopher R. Holtorf; Justin Cottet

An aircraft comprises at least one wing comprising a trailing edge flap that is selectively moveable between a stowed position and an extended position. The aircraft also includes a fuselage comprising a first gear door on a side of the fuselage and a second gear door on a bottom of the fuselage. The first gear door is moveable in a gear door envelope between a closed position and an open position. The wing is coupled to the fuselage in a low-wing configuration. A landing gear assembly is coupled to the fuselage and is selectively moveable between a retracted position and a deployed position. The trailing edge flap may be extended simultaneously with, before, or after deployment of the landing gear assembly and opening of the first gear door.

271. RETRACTABLE BLADE STRUCTURE WITH A SPLIT TRAILING EDGE

申请号: PCT/IB2009000118

申请日: 2009-01-23

公开（公告）号: WO2009095758A3

公开（公告）日: 2010-04-22

发明人: DEHLSEN JAMES G P

This invention relates to blades, such as airfoils or rotor blades, in the field of aviation, or to blades of electric power-generating devices or fluid pumping devices, and more particularly to a structural support for a blade which has an outer aerodynamic module with a telescoping feature which, when extended out, increases the airfoil or blade diameter or length. The inventive extendible blade structure comprises an extender blade module (2) and a base blade module (8), the extender blade module (2) comprising a carrier airfoil shell (10) housing an extender blade (11), and an adjusting device for positioning the extender blade (11) between a retracted position within the carrier airfoil shell (10) and an extended position. The extender blade (11) is provided with trailing edge flaps (26, 28) and a support structure (34b) between the trailing edge flaps (26, 28), the flaps (26, 28) being urged together to form a trailing edge in the extended position, the carrier airfoil shell (10) is provided with a carrier airfoil shell support structure (24) and slots (56, 58) formed at upper and lower sides of the carrier airfoil shell support structure (24), each slot (56, 58) being adapted to accommodate one of the flaps (26, 28), the flaps (26, 28) being forced apart and guided into the slots (56, 58) by the carrier airfoil shell support structure (24) in the retracted position of the extender blade (11), and the carrier airfoil shell support structure (24) and the support structure (34b) of the extender blade (11) rest against each other between the flaps (26, 28).

272. Antriebs- und Führungsvorrichtung für an einem Flugzeugtragflügel angeordnetes Klappensystem

申请号: EP86108914.2

申请日: 1986-07-01

公开（公告）号: EP0215211A1

公开（公告）日: 1987-03-25

发明人: Pohl, Ulrich, Ing. grad.; Renken, Jürgen, Dr.-Ing.

Eine Antriebs- und Führungsvorrichtung für ein an einem Flugzeugtragflügel (1) angeordnetes Klappensystem, bei dem es sich insbesondere um ein in Spannweitenrichtung in einzelne Segmente unterteiltes Hinterkantenklappen­system handelt, besteht aus mit den Segmenten (2-5) gekoppelten Spindelgetrieben (25,28,29) sowie aus Führungs­schienen (16), die die Bahnkurve der Segmente beim Ein- und Ausfahren festlegen. Das An­triebssystem für die Spindelgetriebe ist dabei so ausgebildet, daß die Vorschubge­schwindigkeiten der einzelnen Spindelgetriebe unabhängig voneinander kontrollierbar sind.

273. Jet engine exhaust nozzle system

申请号: US3667680D

申请日: 1970-04-24

公开（公告）号: US3667680A

公开（公告）日: 1972-06-06

发明人: WEED WILLARE N

A variable area two-stage ejection nozzle exhaust system for a turbojet engine having an afterburner. wherein, a primary nozzle has spherical segments contained within a spherical shell housing which spherical segments are pivotally adjustable in response to augmented and non-augmented engine operation to provide for an efficient exhaust nozzle exit area choke plane; and a secondary nozzle with aerodynamically actuated trailing edge flaps for varying the secondary exhaust nozzle exit area in response to primary nozzle pressure variations and airplane Mach number. Also provided within the primary nozzle are separate clamshell type blocker doors which, in combination with fluid flow turning vanes incorporated into the primary nozzle wall, turn the fluid flow to obtain reverse thrust from the turbojet engine. For engine sound suppression, an increase in the primary nozzle exit area at power settings below normal cruise power produces a sound suppression mode through the over expansion of the exhaust gases. At higher engine power settings, one embodiment for sound suppression is accomplished by rotating channel spokes into the exit gas flow and at the same time rotating internal clamshells to uncover openings to suppression tubes that are rotated outward into the free-stream airflow. The suppression tube exits are sized to equal the area of the flow blocked by the channel spokes to maintain engine/exhaust area match.

274. Pale de giravion munie d'un volet orientable à l'aide d'au moins une rotule principale dont le premier arbre est solidaire dudit volet

申请号: EP06021787.4

申请日: 2006-10-18

公开（公告）号: EP1783049A1

公开（公告）日: 2007-05-09

发明人: Lorin de la Grandmaison, Francois; Morant, Michel; Ardesi, Olivier; Gaffiero, Jacques

La présente invention concerne une pale (1) de rotor de giravion qui comporte au moins un volet (5) orientable de bord de fuite, ce volet (5) étant apte à effectuer un pivotement autour d'un axe charnière virtuel (Y') orienté sensiblement selon l'envergure de la pale (1) et du volet (5). La pale (1) est remarquable en ce que le volet (5) est pourvu d'au moins une rotule principale (30) munie d'une cage interne (32) ainsi que d'une cage externe (33) et d'un premier arbre (31) solidaire dudit volet (5), la partie avant (33') de la cage externe (33) de la rotule principale (30) étant reliée à un actionneur (10) linéaire qui est agencé dans la pale (1) et qui permet le pivotement du volet (5), le premier arbre (31) de la rotule principale (30) étant sensiblement perpendiculaire à l'axe charnière virtuel (Y') de rotation du volet (5).

275. EXTENDIBLE AIRFOIL TRACK ASSEMBLY

申请号: EP87200084

申请日: 1981-07-08

公开（公告）号: EP0227643A3

公开（公告）日: 1988-07-20

发明人: COLE, JAMES BYRON

An actuation and extension mechanism for aerodynamic high-lift devices such as a wing leading edge slat or a wing trailing edge flap; wherein an aerodynamic panel (20) is connected to one end of an extendible track member (23) that is supported and guided by its other end through rollers (26) fixedly mounted to wing rib structure (l5). The track member incorporates a separate rack gear segment (24) internally thereof as part of the extension or retraction mechanism and this combination of track and gear segment provides the primary support and drive means to the high-lift device, without compromising the structural strenth, safety, or operational reliability of said combination.

276. Air foil having adjustable shape

申请号: US702157

申请日: 1985-02-15

公开（公告）号: US4582278A

公开（公告）日: 1986-04-15

发明人: Stuart R. Ferguson

An airfoil with an adjustable aerodynamic shape for lowering the landing speed of high performance aircraft. A thin secondary skin is applied to the top primary skin of the aircraft's wing surface. Pressurized fluid is introduced to the cavity formed between the primary skin and the secondary skin to cause a rounding of the upper surface of the airfoil in conjunction with lowering of leading and trailing edge flaps. A plurality of contour members of predetermined lengths and at spaced locations connect the secondary skin and upper surface of the primary skin so as to define the particular contour desired. The leading edge of the secondary skin is hinged to the forward spar of the airfoil. One or more actuators acting through a linkage apply tension to the trailing edge of the secondary skin and draw it down into contiguous relationship with the primary skin of the wing surface for high speed operation.

277. FLAP CONTROL FOR WIND TURBINE BLADES

申请号: PCT/EP2010/068042

申请日: 2010-11-23

公开（公告）号: WO2011064214A2

公开（公告）日: 2011-06-03

发明人: WESTERGAARD, Carsten Hein

A wind turbine blade has one or more trailing edge flaps. An actuator mechanism for the flaps comprises a shaft extending along the blade length driven by a motor arrangement toward the blade root. The flap is connected to the shaft through a linkage so that rotation of the shaft pivots the flap about a hinge line. The linkage may be non-rigid and coupled to the shaft through a roller, or rigid and coupled to the shaft through a crank arm mounted on the shaft. An offset actuation mechanism is provided for imparting movement to the linkage in addition to movement due to rotation of the shaft.

278. AILE D'AERONEF COMPRENANT UN VOLET MOBILE DE BORD DE FUITE ENTRAINE PAR UN MOTEUR ELECTRIQUE LINEAIRE

申请号: PCT/EP2017/078003

申请日: 2017-11-02

公开（公告）号: WO2018083145A1

公开（公告）日: 2018-05-11

发明人: LANGER, Hugues; SCIARRABONE, Steve; DEBAISIEUX, Stéphane

L'invention concerne une aile d'aéronef comprenant un volet mobile de bord de fuite (16), l'aile comprenant un dispositif (50) de mise en mouvement de ce volet, le dispositif étant équipé : - d'une poutre (51) portant un rail de guidage; - d'un chariot (52a) monté mobile sur le rail (20); - d'une liaison articulée (40a) entre le chariot (52a) et une ferrure (30) solidaire du volet; - d'un organe de basculement (29) du volet mobile; - d'une liaison articulée (40b) entre la ferrure (30) et l'organe de basculement (29); et - d'une liaison articulée (40c) entre l'organe de basculement (29) et la poutre (51). Selon l'invention, le dispositif (50) comprend un moteur électrique linéaire (22) comportant un ensemble primaire (52) équipé du chariot (52a) qui intègre des bobines (55), et un ensemble secondaire (54) comportant une voie magnétique agencée sur le rail (20).