公开(公告)号：US08444082B1

公开(公告)日：2013-05-21

申请号：US12859639

申请日：2010-08-19

申请人： Richard J Foch

发明人： Richard J Foch

IPC分类号： B64C3/56

CPC分类号： B64C3/10 ,  B64C23/072 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  Y02T50/12 ,  Y02T50/164

摘要： An air vehicle can be folded into or unfolded from a compact tubular storage container without assembly or disassembly of the air vehicle. The air vehicle includes a fuselage, two aerodynamic surfaces rotatably mounted on the fuselage along a common axis with at least one pivot mechanism, and at least one spring mechanism configured to deploy the aerodynamic surfaces so they extend outwardly from the body. In a stowed configuration, both aerodynamic surfaces are parallel to the fuselage for stowage of the aircraft in a container. Each aerodynamic surface has a winglet located at an outer edge of the tail portion of the aerodynamic surface, and a rudder on each winglet. The aircraft does not require a vertical stabilizer or rudder system on the fuselage. An outer backward-swept wing portion can be unfolded from the outer edge of each aerodynamic surface to increase the wing aspect ratio.

摘要翻译： 空中交通工具可以从紧凑的管状存储容器折叠进入或展开，而不需要组装或拆卸空中交通工具。 机动车辆包括机身，具有至少一个枢转机构的共同轴线可旋转地安装在机身上的两个空气动力学表面，以及至少一个弹簧机构，其构造成展开空气动力学表面，使得它们从主体向外延伸。 在收起的构造中，两个空气动力学表面平行于机身，用于将飞行器存储在容器中。 每个空气动力学表面具有位于空气动力学表面的尾部的外边缘处的小翼和在每个小翼上的舵。 飞机在机身上不需要垂直稳定器或方向舵系统。 外侧后掠翼部分可以从每个空气动力学表面的外边缘展开，以增加机翼纵横比。

公开(公告)号：US08336830B2

公开(公告)日：2012-12-25

申请号：US12245412

申请日：2008-10-03

申请人： David Scott Eberhardt

发明人： David Scott Eberhardt

IPC分类号： B64C3/54

CPC分类号： B64C3/54 ,  B64C23/072 ,  Y02T50/14 ,  Y02T50/164

摘要： Apparatus and methods provide for the use of retractable aircraft wing tips to increase the wingspan of an aircraft to decrease drag and increase fuel efficiency. According to various embodiments, a flexible lifting envelope is attached to an outboard end of an aircraft wing. Upon receiving pressurized air, the flexible lifting envelope extends outward to a lift-producing configuration that extends the span of the aircraft wing to which it is attached. When deflated, the flexible lifting envelope retracts into a stowed configuration to decrease the wingspan of the aircraft to allow for parking at airport gates or to alleviate flight loads. Various implementations provide for a telescoping wing tip and for a rolled wing tip.

摘要翻译： 装置和方法提供使用可伸缩飞行器翼尖以增加飞机的翼展以减少阻力并提高燃料效率。 根据各种实施例，柔性提升外壳连接到飞机机翼的外侧端。 在接收到加压空气时，柔性提升外壳向外延伸到提升产生构造，其延伸与其连接的飞机机翼的跨度。 当放气时，柔性起重信封缩回到收​​起的构型，以减少飞机的翼展，以允许在机场大门停车或减轻飞行载荷。 各种实施方式提供伸缩翼尖和用于卷起的翼尖。

公开(公告)号：US07497403B2

公开(公告)日：2009-03-03

申请号：US11483935

申请日：2006-07-10

申请人： Peter T. McCarthy

发明人： Peter T. McCarthy

IPC分类号： B64C23/06 ,  B64C3/00

CPC分类号： B64C23/072 ,  Y02T50/164

摘要： Methods for increasing the performance of a foil (100) by using tip droop (102) having an inward directed camber capable of generating an inward directed lifting force on the tip droop (102) in order to control spanwise flow conditions adjacent the tip (112) of a foil (100). Methods for varying the inward lifting shape of a tip droop (102) are provided along with methods for varying the angle of attack and camber of the tip droop (102) as the angle of attack of the foil (100) is changed and as spanwise flow conditions vary.

摘要翻译： 用于通过使用具有能够在尖端下垂（102）上产生向内定向的提升力的向内定向的外倾的尖端下垂（102）来增加箔（100）的性能的方法，以便控制与尖端（112）相邻的展开式流动状态 ）箔（100）。 提供改变尖端下垂（102）的向内提升形状的方法以及随着箔（100）的迎角变化而改变尖端下垂（102）的迎角和弯度的方法以及作为翼展方向 流量条件不同。

公开(公告)号：US06394397B1

公开(公告)日：2002-05-28

申请号：US09730702

申请日：2000-12-06

申请人： Hieu T. Ngo ,  Lisa E. Barlow

发明人： Hieu T. Ngo ,  Lisa E. Barlow

IPC分类号： B64C2300

CPC分类号： B64C27/463 ,  B64C23/072 ,  B64C2220/00 ,  Y02T50/164

摘要： A tip member is movable mount at the outboard end of a main lifting member such as a wing or rotor blade. The main lifting member at least at the outboard end has an internal cavity defined therein between pressure-side and suction-side surfaces of the main lifting member. The tip member is movable relative to the main lifting member between a neutral position in which the tip member presents substantially no obstacle to a spanwise component of flow over either suction-side or pressure-side surfaces at the outboard end of the main lifting member, and a position in which a portion of the tip member extends beyond on of the pressure-side and suction-side surfaces of the main lifting member so as to present an obstacle to the spanwise component of flow over that surface at the outboard end of the main lifting member and thereby locally affect the flow at the outboard end. An actuation system for the tip member is disposed in the cavity of the main lifting member and coupled with the tip member for moving the tip member so as to vary a distance by which the tip member extends beyond the surface of the main lifting member. The tip member can be placed in stationary positions, or can be cyclically moved for achieving various effects such a vibration abatement, noise suppression, or lift augmentation.

摘要翻译： 尖端构件可移动地安装在诸如机翼或转子叶片的主提升构件的外侧。 至少在外侧端部的主提升构件具有限定在主提升构件的压力侧和吸力侧表面之间的内部空腔。 顶端构件可在中间位置之间相对于主提升构件移动，其中尖端构件在主提升构件的外侧端部的任一吸入侧或压力侧表面上基本上没有阻碍跨越翼展方向的分量， 以及其中顶端部件的一部分延伸超过主提升部件的压力侧和吸入侧表面的位置，以便在该外表面上的该表面上的横向分量的障碍物 主提升构件，从而局部地影响外侧的流动。 用于尖端构件的致动系统设置在主提升构件的空腔中并与尖端构件联接以用于移动尖端构件，以便改变尖端构件延伸超过主提升构件的表面的距离。 尖端构件可以放置在静止位置，或者可以循环地移动，以实现减震，噪声抑制或提升增加等各种效果。

公开(公告)号：US2846165A

公开(公告)日：1958-08-05

申请号：US59377856

申请日：1956-06-25

申请人： AXELSON JOHN A

发明人： AXELSON JOHN A

IPC分类号： B64C5/08 ,  B64C23/06

CPC分类号： B64C23/072 ,  B64C5/08 ,  B64C23/076 ,  Y02T50/164

公开(公告)号：US20240336351A1

公开(公告)日：2024-10-10

申请号：US18393888

申请日：2023-12-22

申请人： AIRBUS OPERATIONS LIMITED

发明人： Norman WOOD

IPC分类号： B64C23/06 ,  B64C3/14

CPC分类号： B64C23/072 ,  B64C3/14 ,  B64C2003/146

摘要： A wing tip device for a fixed wing aircraft is disclosed having an alular-like projection, a first leading edge region having a first sweep angle, a second leading edge region outboard of the first leading edge region in a spanwise direction and having a second sweep angle greater than the first sweep angle, a third leading edge region outboard of the second leading edge region in the spanwise direction and adjacent a tip end of the wing tip device and having a third sweep angle greater than the first sweep angle. The second leading edge region is adapted to generate a first vortex, and the third leading edge region is adapted to generate a second vortex which builds towards the tip end of the wing tip device.

公开(公告)号：US11912397B2

公开(公告)日：2024-02-27

申请号：US17975046

申请日：2022-10-27

申请人： EMBRAER S.A.

发明人： Paulo Anchieta da Silva ,  Fabio Santos da Silva ,  Danillo Cafaldo dos Reis

IPC分类号： B22F10/20 ,  B64C23/06 ,  B33Y70/00 ,  B33Y80/00 ,  F03G7/06 ,  C21D6/00 ,  B22F10/28 ,  B22F12/90 ,  B22F10/64 ,  B64C3/18

CPC分类号： B64C23/065 ,  B33Y70/00 ,  B33Y80/00 ,  B64C23/072 ,  C21D6/004 ,  F03G7/06 ,  B22F10/20 ,  B22F10/28 ,  B22F10/64 ,  B22F12/90 ,  B22F2301/15 ,  B64C3/185 ,  C21D2201/01 ,  Y02T50/10 ,  B22F2999/00 ,  B22F10/28 ,  B22F7/06 ,  B22F2207/01 ,  B22F5/006

摘要： Thermally configurable structural elements (e.g., aircraft components such as an aircraft winglet spar) capable of assuming at least first and second structural configurations are provided whereby the structural element includes an integral actuation mechanism may be formed of sintered shape memory alloy (SMA) particles and sintered non-SMA particles formed by an additive layer manufacturing (ALM) process, such as 3D printing. The ALM process thereby provides by at least one thermally configurable region, and at least one non-thermally configurable region which is unitarily contiguous with the at least one thermally configurable region. The at least one thermally configurable region is capable of assuming at least first and second positional orientations in response to the presence or absence of a thermal input to thereby cause the structural element to assume the at least first and second structural configurations, respectively.

公开(公告)号：US20180148159A1

公开(公告)日：2018-05-31

申请号：US15881248

申请日：2018-01-26

申请人： The Boeing Company

发明人： Mark S. Good ,  Charles E. Jokisch

IPC分类号： B64C3/56 ,  F15B15/26 ,  B64C23/06 ,  F15B11/00

CPC分类号： B64C3/56 ,  B64C23/072 ,  F15B11/003 ,  F15B13/01 ,  F15B15/261 ,  F15B2015/268 ,  F15B2211/30515 ,  F15B2211/329 ,  F15B2211/72 ,  Y02T50/164

摘要： A folding wing tip system of an aircraft includes a latch pin actuator having a primary mechanical lock and a secondary hydraulic lock. The mechanical lock may include a lock cam movable between a lock position, in which the lock cam engages the latch pin, and an unlock position, in which the lock cam is disengaged from the latch pin, and a first lock actuator mechanically coupled to the lock cam and configured to provide a bias force pushing the lock cam toward the lock position. The hydraulic lock may be disposed in an unlatching hydraulic line and has an initial state, in which fluid flow through the unlatching hydraulic line is blocked thereby to hold the latch pin in the latched position, and an open state, in which fluid flow through the unlatching hydraulic line is permitted thereby to permit retraction of the latch pin to the unlatched position.

公开(公告)号：US20170361922A1

公开(公告)日：2017-12-21

申请号：US15675954

申请日：2017-08-14

申请人： The Boeing Company

发明人： Timothy James McMahon ,  John Scott Kruse ,  Adam L. Kehrer

IPC分类号： B64C23/06 ,  B64C3/38 ,  B64C5/08

CPC分类号： B64C23/065 ,  B64C3/38 ,  B64C5/08 ,  B64C23/072 ,  Y02T50/162 ,  Y02T50/164

摘要： A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least one actuator. A first end of each at least one actuator is coupled to the linking member, and a second end of each at least one actuator is coupleable to one of the wing base and the wing tip. The at least one actuator is operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base.

公开(公告)号：US20170355437A1

公开(公告)日：2017-12-14

申请号：US15618696

申请日：2017-06-09

申请人： Airbus Operations Limited ,  Airbus Operations GmbH

发明人： Benjamin BISHOP ,  Christoph WINKELMANN ,  Johannes RUPP

IPC分类号： B64C3/56 ,  F16C11/10

CPC分类号： B64C3/56 ,  B64C23/072 ,  F16C11/10 ,  Y02T50/14 ,  Y02T50/164

摘要： A wing (1) having a fixed wing (3) and a wing tip device (4) rotatable between a flight configuration and a ground configuration, a rotational joint (10) rotatably couples the wing tip device (4) to the fixed wing (3) and a locking mechanism (46) locks the wing tip device (4) in the flight and ground configurations. The locking mechanism (11) includes first and second locking members (51, 52) and first and second receiving members (53, 54), the locking mechanism (11) being configured to lock the wing tip device (4) in one of the flight configuration and ground configuration by receiving the first and second locking members (51, 52) in the first and second receiving members (53, 54) respectively, and to lock the wing tip device (4) in the other of the flight configuration and ground configuration by receiving the first locking member (51) in the second receiving member (54).