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公开(公告)号：EP1488998A1
公开(公告)日：2004-12-22
申请号：EP04013923.0
申请日：2004-06-14
申请人： The Boeing Company
CPC分类号： B64C3/50 , B64C3/58 , B64C9/00 , B64C39/12 , B64C2003/145 , Y02T50/12 , Y02T50/14 , Y02T50/32 , Y02T50/44
摘要： A mobile platform lift increasing system includes at least one wing-shaped structure having a leading edge (18), a trailing edge (20) and a chord length (22) perpendicularly measurable between the leading and trailing edges (18, 20). A rotatable control surface (34) is located near a trailing edge undersurface (42). The control surface length is approximately one to five percent of the chord length (22). A deployment device (48, 50) is positioned between the wing shaped structure and the control surface (34). The deployment device operably rotates the control surface through a plurality of positions ranging between an initial position (52) and a fully deployed position (58). Wing lift is increased at speeds up to approximately transonic speed by continuously rotating the control surface to accommodate variables including mobile platform weight change from fuel usage.
摘要翻译： 可移动平台升降机增加系统包括至少一个翼状结构，该翼状结构具有在前缘和后缘（18,20）之间垂直可测量的前缘（18），后缘（20）和弦长（22）。 可旋转的控制表面（34）位于后缘下表面（42）附近。 控制表面长度约为弦长（22）的百分之一至百分之五。 展开装置（48,50）位于翼形结构和控制表面（34）之间。 展开装置通过在初始位置（52）和完全展开位置（58）之间的多个位置可操作地旋转控制表面。 通过不断旋转控制面以适应各种变量，包括从燃料使用中移动平台重量变化，机翼升程以达到近似跨音速的速度增加。
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公开(公告)号：EP1475305A2
公开(公告)日：2004-11-10
申请号：EP04252374.6
申请日：2004-04-23
发明人： Buxton, Stephen John
摘要： A geared rotary actuator including first and second adjacent, axially aligned actuator slices (11,12), each slice having an epicyclic-type reduction gear train including a rotatable input sun gear (22), a planetary gear assembly (23, 24, 25) driven by the sun gear (22), and first and second output ring gears (26, 29, 31) driven by the planetary gears, the second output ring gear (29, 31) of each slice being an earth ring gear in use, and the actuator being characterised in that adjacent earth ring gears (29, 31) of the adjacent slices (11, 12) are interconnected by axially extending clip means (38) limiting the amount by which said adjacent earth ring gears can be displaced from one another in an axial direction while permitting limited tilting movement of one of the earth ring gears relative to the other to accommodate flexure of the actuator about its longitudinal axis in use.
摘要翻译： 一种包括第一和第二相邻的轴向对准的致动器切片（11,12）的齿轮旋转致动器，每个切片具有包括可旋转输入太阳齿轮（22）的行星式减速齿轮系，行星齿轮组件（23,24,25） ）和由行星齿轮驱动的第一和第二输出齿圈（26,29,31）驱动，每个切片的第二输出齿圈（29,31）是使用中的接地齿圈 并且所述致动器的特征在于，相邻切片（11,12）的相邻接地齿圈（29,31）通过轴向延伸的夹持装置（38）互连，限制所述相邻的地球环形齿轮可从其移位的量 另一个在轴向方向上，同时允许一个接地环形齿轮相对于另一个的有限倾斜运动，以适应致动器在使用中的纵向轴线的弯曲。
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公开(公告)号：EP1312545A3
公开(公告)日：2004-03-31
申请号：EP02024866.2
申请日：2002-11-08
摘要： Die vorliegende Erfindung betrifft ein aerodynamisches Profil mit verstellbarer Klappe, das einen vorderen Profilbereich (2) sowie einen in der Abströmung liegenden hinteren Profilbereich (3) aufweist und durch einen druckseitige sowie eine saugseitige Deckhaut (4, 5) begrenzt ist, wobei die druckseitige und die saugseitige Deckhaut (4, 5) im hinteren Profilbereich (3) in einer Profilhinterkante (6) zusammen laufen, und dadurch gekennzeichnet ist, dass im hinteren Profilbereich (2) an der Unterseite (4a) der druckseitigen Deckhaut (4) eine Klappe (7) derart schwenkbar gelagert ist, dass die Klappe (7) im Ruhezustand in Strömungsrichtung (S ström ) weisend an der Kontur der druckseitigen Deckhaut (4) anliegt und im ausgelenkten Zustand einen Winkel mit der druckseitigen Deckhaut (4) einschließt, wobei in die Klappe (7) eine luftdichte Gelenkverbindung (10) integriert ist, so dass im Windschatten der Klappe ein die Strömungsverhältnisse verbesserndes Wirbelsystem ausbildet.
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公开(公告)号：EP1328438A1
公开(公告)日：2003-07-23
申请号：EP01979274.6
申请日：2001-09-21
IPC分类号： B64C11/28
CPC分类号： B64C3/44 , B64C3/50 , B64C27/473 , B64C27/615 , B64C27/68 , B64C2027/7266 , Y02T50/34
摘要： A variable edge rotor blade (30) adapted to be driven by the rotor hub includes an airfoil section (30); a movable edge section (32) coupled to the airfoil section, and an actuator device (40) operating independently of the hub, disposed in the blade proximate the movable edge section, fixed to the airfoil section and coupled to the movable edge section for oscillating it between an increased lift and decreased lift position.
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公开(公告)号：EP1231137A3
公开(公告)日：2003-03-19
申请号：EP02075572.4
申请日：2002-02-12
申请人： THE BOEING COMPANY
摘要： A wing assembly (24,38) for an aircraft moveable slat system (20) has a fixed structure (40) and a contoured surface (42,44). The fixed structure has an exterior surface defining an external contour and an internal surface defining a cavity (50). The fixed structure also has one or more edges defining a cutout (26). The contoured surface is coupled to one or more of the edges of the cutout and extends into the cavity. The contoured surface promotes airflow from the cavity to the external contour. The result is a solution to aerodynamic losses that does not require an auxiliary track system or moving parts.
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公开(公告)号：EP0230060B1
公开(公告)日：1990-02-07
申请号：EP86201414.9
申请日：1986-08-11
申请人： THE BOEING COMPANY
发明人： Cole, James B.
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公开(公告)号：EP0080460A1
公开(公告)日：1983-06-08
申请号：EP81901947.0
申请日：1981-06-10
申请人： THE BOEING COMPANY
CPC分类号： B64C3/50 , B64C23/06 , Y02T50/14 , Y02T50/162
摘要： A series of flaps (21) along the leading edge of a highly swept-back wing (20) for a supersonic airplane; wherein, the spanwise series of the flaps (21) comprise a double-flap chordwise having fore and aft flap segments (22, 24). When the leading edge double-flap is positioned at a forward and downward angle-of-deflection relative to the wing (20), the fore-flap segment (22) is further positioned at an angle-of-deflection relative to the aft-flap segment (24). This difference in the deflection angles, between the fore-flap segment (22) and the aft-flap segment (24), creates a vortex flow region ahead of the wing leading edge; and this vortex functions to control separation of an upper surface boundary layer airflow, over the remainder of the upper surface of the wing (20). Also, the vortex flow will move in a spanwise direction outboard toward the tip of a swept-back wing (20), while remaining forward or ahead of the upper surface of the aft-flap segment (24). Additional embodiments relate to various other arrangements for creating a leading edge vortex flow to maintain attached flow over the remainder of the upper surface of the wing.
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公开(公告)号：EP4389594A1
公开(公告)日：2024-06-26
申请号：EP22214915.5
申请日：2022-12-20
摘要： The invention relates to a functionally improved fairing arrangement (26) for a high-lift mechanism (20) of an aircraft (10). The high-lift mechanism (20) includes a flap (22) to be arranged at a trailing edge (16) of an aircraft wing (12) and a mounting and guiding mechanism (24) for the flap (26). The fairing arrangement (26) comprises a flap side fairing unit (28) and a wing side fairing unit (30). The flap side fairing unit (28) comprises a flap side fairing (32) for covering an aft part of the mounting and guiding mechanism (24) and a flap side fairing mount (34) for mounting the flap side fairing (32) to the flap (22). The wing side fairing unit (30) comprises a wing side fairing (36) for covering a forward part of the mounting and guiding mechanism (24) and a wing side fairing mount (38) for mounting the wing side fairing (36) to the wing (12). The wing side fairing mount (38) is configured for connecting the wing side fairing (36) movably to the wing (12) such that the wing side fairing (36) is rotatable around an axis (39) directed at least partially in a vertical direction.
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公开(公告)号：EP4378827A1
公开(公告)日：2024-06-05
申请号：EP22210458.0
申请日：2022-11-30
发明人： Haunert, Jan , Schlipf, Bernhard , Krey, Dennis
CPC分类号： B64C2009/14320130101 , B64C9/16 , B64C3/50
摘要： Disclosed is a wing (3) for an aircraft (1), comprising a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5), the trailing edge high lift assembly (9) comprising a flap (11) and a connection assembly movably mounting the flap (11) to the main wing (5), such that the flap (11) is movable between at least one retracted position (12, 14) and at least one extended position (15), wherein in the at least one extended position (15) a gap (16) is present between a lower rear panel (17) of the main wing (5) and a leading edge section (19) of the flap (11), and wherein in the at least one retracted position (12, 14) the gap (16) is closed or minimized. The object of the invention, to provide a wing that might be used as a morphing wing capable of adjusting wing area, curvature, and angle of attack during the entire flight, while having optimized aerodynamic performance throughout all flap settings, is achieved in that the flap (11) is movable between at least one extended position (15), a first retracted position (12), and a second retracted position (14) where the flap (11) is moved beyond the first retracted position (12) in a forward direction (13), and the wing comprises a gap closing device (23) configured to close or minimize the gap (16) in both the first retracted position (12) and the second retracted position (14) of the flap (11), and to open the gap (16) in the at least one extended position (15) of the flap.
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公开(公告)号：EP3093235B1
公开(公告)日：2018-11-21
申请号：EP16166183.0
申请日：2016-04-20
申请人： Rolls-Royce plc
发明人： Moxon, Matthew
CPC分类号： B64D33/02 , B64C3/50 , B64C11/001 , B64C15/00 , B64C21/00 , B64D27/02 , B64D27/10 , B64D27/24 , B64D29/04 , B64D33/04 , B64D2027/026 , B64D2033/0226 , Y02T50/166 , Y02T50/44
摘要： 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.
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