公开(公告)号：US07637453B2

公开(公告)日：2009-12-29

申请号：US11605310

申请日：2006-11-29

Applicant: Tom Kusic

Inventor： Tom Kusic

IPC: F41G7/00

CPC classification number: B64C5/04 ,  B64C9/02 ,  B64C9/06 ,  B64C39/12

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 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 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，导致飞行器在飞行中的螺旋运动。

公开(公告)号：US20090283632A1

公开(公告)日：2009-11-19

申请号：US12507573

申请日：2009-07-22

Applicant: Brian Herman Morgan ,  David LeRoy Hagen

Inventor： Brian Herman Morgan ,  David LeRoy Hagen

IPC: B64C9/00

CPC classification number: B64C9/06 ,  B64C5/02 ,  B64C5/06 ,  B64C9/12 ,  Y02T50/32

Abstract: An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a plurality of thrusters mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface.

Abstract translation: 飞机姿态控制配置使得控制面能够在悬停或低空气速度条件下为飞行器提供姿态控制。 飞行器姿态控制结构包括安装在飞行器上用于推动空气的多个推进器，第一控制表面，其在第一推进器下游的位置处运动学地联接到飞行器，以使第一矢量力由推动的一部分产生 来自第一控制表面上的第一推进器的空气和在第二推进器下游的位置处运动学地联接到飞行器的第二控制表面，第一和第二控制表面在飞行器的纵向轴线的相对侧对称移位 所述第二控制表面被配置为相对于所述第一控制表面独立且可差分移动，以使第二向量力由所述第二控制表面上的来自所述第二推进器的被推动空气的一部分产生。

公开(公告)号：US20090230253A1

公开(公告)日：2009-09-17

申请号：US12294588

申请日：2007-05-21

Applicant: Franck Delaplace ,  Sophie Lambeaux ,  Frederic Sauvinet

Inventor： Franck Delaplace ,  Sophie Lambeaux ,  Frederic Sauvinet

IPC: B64C13/16 ,  B64C9/00 ,  G05D1/08

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（b2）的最佳提升。

公开(公告)号：US06554229B1

公开(公告)日：2003-04-29

申请号：US09581951

申请日：2000-09-20

Applicant: Lawrence Y. Lam ,  Michael Lam

Inventor： Lawrence Y. Lam ,  Michael Lam

IPC: B64C906

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

Abstract: An aircraft aileron system (10, 10) is comprised of two panels (12, 14, 28, 30, 62, 70) located at the rear portion of the wing (W24, 54), 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 (12, 30, 62) is restricted to upward deflection only from its neutral position and in operation is deployed independently as an aileron. The lower, auxiliary flap panel (14, 28, 70) 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 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.

Abstract translation: 飞机副翼系统（10,10）由位于机翼后部（W24,54）的两个面板（12,14,28,30,62,70）组成，沿翼展方向并与机翼 后缘。 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（12,30,62）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。 下辅助翼片板（14,28,70）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，辅助翼板仅能够向下展开，以提供更简单的副翼系统。 对于巡航期间飞机的滚动控制，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。

公开(公告)号：US20020109041A1

公开(公告)日：2002-08-15

申请号：US10067963

申请日：2002-02-08

Inventor： Tom Kusic

IPC: F42B015/01 ,  F42B010/00

CPC classification number: B64C9/06 ,  B64C5/04

Abstract: A missile 1 with a missile attachment 2 according to this invention. The missile attachment 2 consists of a tube 3 with a protruding section 4. The protruding section 4 has a concave forward facing surface area 5. The concave curvature is such that it is noticeable when the protruding section 4 is at the highest position on the tube 3. The tube is in the form of a cylindrical tube is fitted to the missile 1 so that it encircles part of the missile and such that it can rotate continuously relative to the missile 1 during flight of the misile.

Abstract translation: 具有根据本发明的导弹附件2的导弹1。 导弹附件2由具有突出部分4的管3组成。突出部分4具有凹入的前向表面区域5.凹曲面使得当突出部分4处于管子上的最高位置时是显着的 3.管子是圆柱形管子的形式，装在导弹1上，以便它包围导弹的一部分，并使得它可以在飞行过程中相对于导弹1连续旋转。

公开(公告)号：US06382566B1

公开(公告)日：2002-05-07

申请号：US09471987

申请日：1999-12-23

Applicant: Earl K. Ferrel ,  Richard P. Klingele ,  Wolfram Hansis ,  William B. Betters

Inventor： Earl K. Ferrel ,  Richard P. Klingele ,  Wolfram Hansis ,  William B. Betters

IPC: B64C328

CPC classification number: B64C9/06 ,  B64C9/16 ,  B64C13/50 ,  B64D45/0005 ,  B64D2045/001

Abstract: A system to accurately detect skewing of high lift devices. In one embodiment, the invention provides a system to sense the position of the inboard and outboard ends of each flap. This system preferably detects development of a skewed condition and shuts down the flap drive system before unacceptable aerodynamic or structural conditions occur. In one embodiment, a commercial aircraft has two trailing edge flaps on each wing. Each of the four flaps on the airplane is driven by two ballscrews, one near the outboard end and one near the inboard end of each flap. All ballscrews on all flaps are driven synchronously by a mechanical drive system. By comparing the revolutions of the ballscrews, the differential ballscrew travel can be determined. This differential is a direct measure of flap skew.

Abstract translation: 准确检测高升降装置倾斜的系统。 在一个实施例中，本发明提供了一种用于感测每个翼片的内侧和外侧端部的位置的系统。 该系统优选地在发生不可接受的空气动力学或结构状况之前检测倾斜状态的发展并且关闭翼片驱动系统。 在一个实施例中，商用飞行器在每个翼上具有两个后缘翼片。 飞机上的四个翼片中的每一个由两个滚珠丝杠驱动，一个靠近外侧端部，一个靠近每个翼片的内侧。 所有翼片上的所有滚珠丝杠均由机械驱动系统同步驱动。 通过比较滚珠丝杠的转数，可以确定差速滚珠丝杆行程。 该差速器是皮瓣偏斜的直接测量。

公开(公告)号：US5921506A

公开(公告)日：1999-07-13

申请号：US936631

申请日：1997-09-25

Applicant: Kari Appa

Inventor： Kari Appa

IPC: B64C9/06 ,  B64C9/28 ,  B64C13/50 ,  B64C3/44

CPC classification number: B64C13/503 ,  B64C9/06 ,  B64C9/28 ,  Y02T50/32 ,  Y02T50/44

Abstract: A flight control system comprises trailing edge airfoil members pivotally mounted at the trailing edge of each wing of an aircraft and selectively movable on a laterally extending axis between raised and lowered positions for imparting rolling motion to the aircraft. Leading edge airfoil members mounted adjacent the leading edge on each of the wings are movable transversely of the leading edge between a retracted position generally coextensive with the leading edge and an extended position protruding from the leading edge for imparting countervailing aerodynamic forces on the wings to counteract the effects of aeroelastic wing deformation caused in response to operation of the trailing edge airfoil members by increasing the angle of attack of the wing and lift producing surface area of the wing. A pair of actuator mechanisms are mounted on a wing box member at laterally spaced locations for moving the leading edge airfoil members between the retracted and extended positions. The actuator mechanisms are operable simultaneously such that, in one instance, they move the upper and lower control rods in unison to move the leading edge airfoil member between the retracted and extended positions with no change in its angular position relative to the wing and, in another instance, move the leading edge airfoil members to the extended position while exhibiting a nose down position relative to the wing and, in still another instance, move the leading edge airfoil members to the extended position while exhibiting a nose up position relative to the wing.

Abstract translation: 飞行控制系统包括后缘翼型件，其可枢转地安装在飞行器的每个翼的后缘处，并且可以在升高和降低的位置之间的横向延伸的轴线上选择性地移动，以向飞行器施加滚动运动。 靠近每个翼的前缘附近的前缘翼型件可以在前缘之间横向移动，在与前缘大致共同延伸的缩回位置和从前缘突出的延伸位置之间，用于在机翼上施加反作用力的空气动力以抵抗 响应于后缘翼型构件的操作而引起的气动弹性翼变形的影响通过增加机翼的迎角和提升机翼的产生表面积。 一对致动器机构以横向间隔开的位置安装在翼形箱构件上，用于使前缘翼型件在缩回位置和伸出位置之间移动。 致动器机构可以同时操作，使得在一种情况下，它们一致地移动上部和下部控制杆，以使前缘翼型件在缩回位置和伸出位置之间移动，相对于翼片的角位置没有变化，并且在 另一个实例，将前缘翼型件移动到延伸位置，同时相对于机翼呈现向下的位置，并且在另一种情况下，将前缘翼型件移动到延伸位置，同时相对于翼展现出向上的位置 。

公开(公告)号：US20240190556A1

公开(公告)日：2024-06-13

申请号：US18407605

申请日：2024-01-09

Applicant: JetZero, Inc.

Inventor： Mark Allan Page ,  Blaine Knight Rawdon

IPC: B64C23/06 ,  B64C9/06 ,  B64C13/24 ,  B64C39/10

CPC classification number: B64C23/076 ,  B64C9/06 ,  B64C39/10 ,  B64C13/24 ,  B64C2039/105

Abstract: Aspects relate to aircraft and methods of use for aerodynamic control with winglet surfaces. In an aspect an exemplary aircraft includes a first wing having a first winglet at a distal end of the wing, wherein the first winglet comprises at least a first control surface at a first trailing edge of the first winglet and a second wing having a second winglet at a distal end of the wing, wherein the second winglet comprises at least a second control surface at a second trailing edge of the second winglet.

公开(公告)号：US11993372B2

公开(公告)日：2024-05-28

申请号：US17637252

申请日：2020-07-20

Applicant: Japan Aerospace Exploration Agency

Inventor： Daichi Wada

IPC: B64C3/54 ,  B64C9/02 ,  B64C9/04 ,  B64C9/06

CPC classification number: B64C3/546 ,  B64C9/02 ,  B64C9/04 ,  B64C9/06 ,  B64C2003/543

Abstract: A morphing wing includes a pantograph mechanism capable of being extended and contracted in a predetermined direction, a plurality of flight feathers attached to the pantograph mechanism, connection members configured to connect flight feathers adjacent to each other among the plurality of flight feathers, a first rotating mechanism configured to rotate the pantograph mechanism around one axis of a plane that intersects the direction, and a second rotating mechanism configured to rotate the pantograph mechanism around another axis of the plane. Each of the plurality of flight feathers is configured so that an angle formed by adjacent flight feathers connected via the connection members increases as the pantograph mechanism extends.

公开(公告)号：US11952112B2

公开(公告)日：2024-04-09

申请号：US17734861

申请日：2022-05-02

Applicant: Airbus Operations GmbH

Inventor： Tobias Schreck ,  Bernhard Schlipf

IPC: B64C3/38 ,  B64C9/06 ,  B64C13/38

CPC classification number: B64C3/38 ,  B64C9/06 ,  B64C13/38

Abstract: A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to the high lift body. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to the high lift body.