公开(公告)号：US20240343383A1

公开(公告)日：2024-10-17

申请号：US18299491

申请日：2023-04-12

Applicant: The Boeing Company

Inventor： Emily Georgia Rayner ,  Kevin Raylin Tsai ,  Ramón Augustin Burin ,  Bret Alan Bowers

IPC: B64C9/24 ,  B64C9/02 ,  B64C9/06 ,  B64C13/38

CPC classification number: B64C9/24 ,  B64C9/02 ,  B64C9/06 ,  B64C13/38

Abstract: The illustrative examples provide a slat movement system for use in an aircraft. An aircraft comprises a wing having a fixed edge and a wing front spar, and a moveable slat connected to the wing by a four bar linkage and a slat arm, the slat arm movable along a track comprising a slot terminating prior to the wing front spar.

公开(公告)号：US20150090843A1

公开(公告)日：2015-04-02

申请号：US14499549

申请日：2014-09-29

Applicant: AIRBUS OPERATIONS S.A.S.

Inventor： Bernard GUERING

IPC: B64C3/50 ,  B64C13/50 ,  B64C13/40 ,  B64C13/24 ,  B64C13/28

CPC classification number: B64C3/50 ,  B64C9/02 ,  B64C9/06 ,  B64C9/16 ,  B64C13/24 ,  B64C13/28 ,  B64C13/40 ,  B64C13/50 ,  B64C13/504 ,  Y02T50/32

Abstract: A high-lift trailing edge flap system for an aircraft wing unit is provided. In high-lift trailing edge flap system, the backward movement and the inclination of the trailing edge flap in the extended position are dissociated in order to allow for the incorporation of the actuating mechanism into the wing in the stowed position.

Abstract translation: 提供了一种用于飞机机翼单元的高升力后缘翼片系统。 在高升力后缘翼片系统中，向后移动和后缘翼片处于伸展位置的倾斜被解离，以允许致动机构结合到收起位置的翼中。

公开(公告)号：US20150083852A1

公开(公告)日：2015-03-26

申请号：US14034940

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  Michael R. Finn ,  Mark J. Gardner ,  Mark S. Good ,  Sarah A. Jones

IPC: B64C13/34

CPC classification number: B64C13/34 ,  B64C3/50 ,  B64C9/06 ,  B64C9/12 ,  B64C9/14 ,  B64C13/26 ,  Y02T50/32

Abstract: A variable camber system for an aircraft may include a variable camber trim unit (VCTU) positioned between an inboard device and an outboard device. The inboard device and the outboard device may be mounted to at least one of a leading edge and a trailing edge of a wing. The VCTU may include a speed sum gearbox having an inboard shaft coupled to the inboard device and an outboard shaft coupled to the outboard device. The VCTU may additionally include a VCTU electric motor engaged to the speed sum gearbox. The VCTU electric motor may be selectively operable in conjunction with the speed sum gearbox to rotate the outboard shaft independent of the inboard shaft in a manner causing the outboard device to be actuated independent of the inboard device.

Abstract translation: 用于飞行器的可变外倾角系统可以包括位于内侧装置和外侧装置之间的可变外倾角装置单元（VCTU）。 内侧装置和外侧装置可以安装到机翼的前缘和后缘中的至少一个。 VCTU可以包括速度和齿轮箱，其具有联接到内侧装置的内侧轴和联接到外侧装置的外侧轴。 VCTU可以另外包括接合到速度和齿轮箱的VCTU电动机。 VCTU电动机可以选择性地与速度总和齿轮箱一起操作，以独立于内侧轴旋转外侧轴，使得外部装置独立于内侧装置被致动。

公开(公告)号：US08083178B2

公开(公告)日：2011-12-27

申请号：US12294588

申请日：2007-05-21

Applicant: Franck Delaplace ,  Sophie Lambeaux ,  Frédéric Sauvinet

Inventor： Franck Delaplace ,  Sophie Lambeaux ,  Frédéric Sauvinet

IPC: B64C13/16 ,  B64C5/08

CPC classification number: B64C9/06 ,  B64C13/16 ,  B64C13/503 ,  G05D1/0808

Abstract: In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter (b2).

Abstract translation: 根据本发明，基于事故状况和速度，副翼的转向是弱负的（b0），或对应于飞行器的最大锋度（b1），或对应于后者的最佳提升（b2）。

公开(公告)号：US07825359B2

公开(公告)日：2010-11-02

申请号：US12458618

申请日：2009-07-17

Applicant: Tom Kusic

Inventor： Tom Kusic

IPC: F41G7/00

CPC classification number: B64C5/04 ,  B64C9/06

Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3. Thus, as well as forcing the rotate-able tube 3 to rotate, the ramjets would also push the rotate-able tube sideways. But as the rotate-able tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiraling motion of the missile when in flight.

Abstract translation: 具有多级导弹1形式的飞机，具有螺旋诱导组件2，其能够引导导弹以连续的螺旋运动而无导弹滚动。 冲压喷枪6b连接到能够围绕机身的环绕部分旋转的管3。 冲压喷枪6b能够相对于可旋转管3以可枢转的方式旋转在可旋转管3上，从而相对于可旋转管3的纵向轴线改变它们的间距。将冲压喷嘴6b旋转至 在管3的右侧大于另一冲头喷枪。冲击喷嘴之间的旋转差异使得冲压喷嘴6b在可旋转管3上施加比在冲击器旋转时右侧的冲压式喷射器更大的力 在同一个方向 因此，旋转力之间的不平衡使得可旋转管3旋转。 当旋转时，冲击器将在可旋转管3上施加横向力。因此，以及迫使可旋转管3旋转，冲击器也将侧向推动可旋转管。 但是当可旋转管被侧向推动时，其旋转，因此推动的横向方向不断旋转，导致在飞行中导弹的螺旋运动。

公开(公告)号：US07635104B1

公开(公告)日：2009-12-22

申请号：US11601804

申请日：2006-11-20

Applicant: Tom Kusic

Inventor： Tom Kusic

IPC: F41G7/00

CPC classification number: B64C5/04 ,  B64C9/06

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3a with respect to the rotate-able tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3a. Ramjet 6b is rotated as is another ramjet on the right side of the tube 3a. The rotate-able tube 3a is rotated by means of an electric motor 3b rotating a wheel 3c. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3a than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3a to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3a. Thus, the ramjets would push the rotate-able tube sideways. But as the rotate-able tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiraling motion of the aircraft when in flight.

Abstract translation: 具有螺旋诱导组件2的飞机1，其能够使飞机以不间断的旋转运动而飞行，而不会飞行。 冲压喷枪6b连接到能够围绕机身的环绕部分旋转的管3a。 冲压喷枪6b能够相对于可旋转管3a以可枢转的方式旋转在可旋转管3a上，从而相对于可旋转管3a的纵向轴线改变它们的俯仰。 Ramjet 6b与管3a右侧的另一冲头喷射一样旋转。 旋转管3a通过旋转轮3c的电动马达3b旋转。 当冲击器沿相同方向旋转时，冲压喷嘴6b之间的旋转差异使得冲压喷嘴6b在可旋转管3a上施加比右侧的冲压式喷射器更大的力。 因此，旋转力之间的不平衡使得可旋转管3a旋转。 当旋转时，冲击器将在可旋转管3a上施加横向力。 因此，冲击将横向推动可旋转管。 但是当可旋转管被侧向推动时，其旋转，因此推动的横向方向不断旋转，导致飞行器在飞行中的螺旋运动。

公开(公告)号：US20090001225A1

公开(公告)日：2009-01-01

申请号：US12075718

申请日：2008-03-13

Applicant: John Libby

Inventor： John Libby

IPC: B64C3/14 ,  B64C3/38

CPC classification number: B64C3/50 ,  B64C9/02 ,  B64C9/04 ,  B64C9/06 ,  B64C9/20 ,  Y02T50/14 ,  Y02T50/32

Abstract: A bipartite, full span airplane flap system having an inboard flap portion and an outboard flap portion, wherein the outboard flap portion includes an integrated aileron mounted on its substantially equivalent spanwise length. The outboard flap portion is adapted to translate between a first and a second position to create a functional slot between a bottom surface of the flap member leading part and a bottom surface of the airfoil trailing part to draw a portion of higher pressure air from the bottom surface of the airfoil through the functional slot to distribute the higher pressure air over a top surface of the outboard flap portion.

Abstract translation: 具有内侧翼片部分和外侧翼片部分的二分，全跨度飞行器翼片系统，其中所述外侧翼片部分包括安装在其基本相当的翼展长度上的集成副翼。 外侧翼片部分适于在第一和第二位置之间平移以在挡板构件引导部分的底表面和翼型后部的底表面之间形成功能槽，以从底部抽出一部分较高压力的空气 翼面的表面通过功能槽将高压空气分配在外侧翼片部分的顶表面上。

公开(公告)号：US07367532B2

公开(公告)日：2008-05-06

申请号：US11047194

申请日：2005-01-31

Applicant: John Libby

Inventor： John Libby

IPC: B64C9/16

CPC classification number: B64C3/50 ,  B64C9/02 ,  B64C9/04 ,  B64C9/06 ,  B64C9/20 ,  Y02T50/14 ,  Y02T50/32

Abstract: A bipartite, full span airplane flap system having an inboard flap portion and an outboard flap portion, wherein the outboard flap portion includes an integrated aileron mounted on its substantially equivalent spanwise length.

Abstract translation: 具有内侧翼片部分和外侧翼片部分的二分，全跨度飞行器翼片系统，其中所述外侧翼片部分包括安装在其基本相当的翼展长度上的集成副翼。

公开(公告)号：US20060169848A1

公开(公告)日：2006-08-03

申请号：US11047194

申请日：2005-01-31

Applicant: John Libby

Inventor： John Libby

IPC: B64C9/16

CPC classification number: B64C3/50 ,  B64C9/02 ,  B64C9/04 ,  B64C9/06 ,  B64C9/20 ,  Y02T50/14 ,  Y02T50/32

Abstract: A bipartite, full span airplane flap system having an inboard flap portion and an outboard flap portion, wherein the outboard flap portion includes an integrated aileron mounted on its substantially equivalent spanwise length.

Abstract translation: 具有内侧翼片部分和外侧翼片部分的二分，全跨度飞行器翼片系统，其中所述外侧翼片部分包括安装在其基本相当的翼展方向长度上的集成副翼。

公开(公告)号：US6079672A

公开(公告)日：2000-06-27

申请号：US993241

申请日：1997-12-18

Applicant: Lawrence Y. Lam ,  Michael Lam

Inventor： Lawrence Y. Lam ,  Michael Lam

IPC: B64C9/00 ,  B64C9/06

CPC classification number: B64C9/06 ,  B64C9/00 ,  Y02T50/32 ,  Y02T50/44

Abstract: An aircraft aileron system unique in its construction, method of deployment and the functional results obtained, is comprised of two panels located at the rear portion of the wing, in a spanwise direction and aligned with the wing's trailing edge. The panels are independently hinged at their leading edges and rotate to make angular deflections with respect to the wing. The upper, aileron panel is restricted to upward deflection only from its neutral position and in operation is deployed independently as an aileron. The lower, auxiliary flap panel is capable of both upward and downward deflections from its neutral position, and is deployed independently downward as an auxiliary flap. Both panels are deployed together upwardly only as an aileron. Alternatively, the aileron panel may be capable only of upward deployment while the auxiliary flap panel is capable of downward deployment only, to provide a simpler aileron system. For roll control of an aircraft during cruise, the aileron panel on one side only is deflected up while the aileron panel on the other side remains in its neutral position. The aileron system, in conjunction with flap arrangements, offers multiple aircraft control function with advantages over past and present systems for aircraft control.

Abstract translation: 其结构独特的飞行器副翼系统，部署方法和所获得的功能结果由位于机翼后部的翼面方向的两个面板组成，并与机翼的后缘对准。 面板在其前缘独立地铰接并旋转以相对于机翼产生角度偏转。 上副翼面板仅从其中立位置限制向上偏转，并且在操作中作为副翼单独部署。 下部辅助翼片板能够从其中立位置向上和向下偏转，并且作为辅助翼片独立地向下展开。 两个面板仅作为副翼部署在一起。 或者，副翼板仅能够向上展开，而辅助翼板仅能够向下展开，以提供更简单的副翼系统。 对于巡航期间的飞行器的滚动控制，一侧的副翼面板仅在另一侧的副翼面板保持在其中立位置时被偏转。 副翼系统结合皮瓣安排，提供多种飞机控制功能，具有优于过去和现在的飞机控制系统的优点。