公开(公告)号：US06547181B1

公开(公告)日：2003-04-15

申请号：US10157502

申请日：2002-05-29

申请人： Zachary C. Hoisington ,  Blaine K. Rawdon

发明人： Zachary C. Hoisington ,  Blaine K. Rawdon

IPC分类号： B64C338

CPC分类号： B60V1/08 ,  B64C23/072 ,  Y02T50/164

摘要： A variable sweep winglet with a negative dihedral angle is provided for a ground effect vehicle. The winglet is positionable at a sweep angle to control the winglet tip clearance from ground. Variable winglet tip clearance reduces the risk of damage or instability due to collision with the ground or water, thereby permitting more efficient flight at lower altitude with an equivalent safety. The winglet is generally positioned by an actuator. The actuator is controlled by a flight control system, or by other manual or automatic systems. A sensor may also be included for determining whether an object lies in the path of the winglet. The sensor communicates with the flight control system in order to vary the sweep of the winglet to increase clearance from the ground or water, thus avoiding impact with the object.

摘要翻译： 为地面效应车辆提供具有负二面角的可变扫掠小翼。 小翼可以以扫掠角度定位，以控制小翼尖端距离地面。 可变小翼尖间隙减少了由于与地面或水碰撞而导致的损坏或不稳定的风险，从而允许在较低高度上更有效地飞行，具有相当的安全性。 小翼通常由致动器定位。 执行器由飞行控制系统或其他手动或自动系统控制。 还可以包括传感器以确定物体是否位于小翼的路径中。 传感器与飞行控制系统通信，以便改变小翼的扫掠以增加与地面或水的间隙，从而避免与物体的撞击。

公开(公告)号：US06270039B1

公开(公告)日：2001-08-07

申请号：US09416622

申请日：1999-10-12

申请人： Jussi Linjama

发明人： Jussi Linjama

IPC分类号： B64C338

CPC分类号： B64C13/24 ,  B64C9/02 ,  B64C13/30 ,  Y02T50/44

摘要： The invention relates to a hinge for movable control surfaces in an aircraft. The hinge comprises two hinge lugs placed at a distance from one another. The hinge lugs include connecting lugs with an elongated connecting piece therebetween. An actuator is connected to the connecting piece conveying the force by means of fastening lugs to the hinge and further onto the control surface. The connecting piece is pivoted to the connecting lugs so that it can revolve about its longitudinal axis when moving the control surface. The invention also relates to a connecting piece intended to be used with a hinge like the one described above. The connecting piece is an elongated element including journals at both ends from where the connecting piece is rotatably pivoted about its longitudinal axis between the connecting lugs on the hinge. A middle portion of the connecting piece between the journals is flat and tapers towards the journals.

摘要翻译： 本发明涉及一种用于飞行器中可移动控制表面的铰链。 铰链包括彼此相隔一定距离放置的两个铰链凸耳。 铰链凸耳包括连接凸耳，其间具有细长的连接件。 致动器通过紧固凸耳连接到连接件，将连接件传递到铰链并进一步传递到控制表面上。 连接件枢转到连接凸耳，使得当移动控制表面时，连接件可围绕其纵向轴线旋转。本发明还涉及一种用于与如上所述的铰链一起使用的连接件。 连接件是细长元件，其包括在两端的轴颈，连接片从铰接件上的连接凸耳之间的纵向轴线可旋转地枢转。 期刊之间的连接件的中间部分是扁平的并且朝着期刊逐渐变细。

公开(公告)号：US06264136B1

公开(公告)日：2001-07-24

申请号：US09123118

申请日：1998-07-27

申请人： Paul H. Weston

发明人： Paul H. Weston

IPC分类号： B64C338

CPC分类号： B64C3/385 ,  B64C9/18 ,  B64C39/04 ,  Y02T50/14 ,  Y02T50/32

摘要： The aircraft (20,50,60) combines a low aspect ratio lifting body (21) and a higher aspect ratio wing (30). Horizontal and vertical tail surfaces (26, 24) are connected to the rear of the lifting body (21) by one or more booms (23). The wing (30) is attached to the lifting body (21) such that it can be rotated about a spanwise axis (39) and it's aerodynamic center is located behind the aerodynamic center of the lifting body (21). The wing (30) contains adjustable surfaces (31, 32) to change the wing's camber for lift and roll control. A lever arrangement (FIG. 7) controlled by the pilot or remote control operator selectively and relatively pivots the wing (30) and contours the wing surfaces for camber to optimize the lift and control of the lifting body (21) and the wing (30) for maximum efficiency in all flight modes.

摘要翻译： 飞机（20,50,60）组合了低纵横比提升体（21）和较高纵横比的翼（30）。 水平和垂直的尾部表面（26,24）通过一个或多个悬臂（23）连接到提升体（21）的后部。 翼（30）附接到提升体（21），使得其能够绕翼展方向轴线（39）旋转，并且其空气动力学中心位于提升体（21）的空气动力学中心的后面。 机翼（30）包含可调节的表面（31,32），以改变机翼的弧度以进行升降控制。 选择性地由飞行员或遥控操作员控制的杠杆装置（图7）并且相对地枢转翼（30）并且使翼面轮廓成轮廓以优化提升体（21）和翼（30）的提升和控制 ），以便在所有飞行模式下实现最大效率。

公开(公告)号：US06260798B1

公开(公告)日：2001-07-17

申请号：US09425609

申请日：1999-10-22

申请人： Thierry Casiez ,  Carlos Cesnik ,  Mark Drela ,  Staci N. Jenkins ,  Mark Spearing

发明人： Thierry Casiez ,  Carlos Cesnik ,  Mark Drela ,  Staci N. Jenkins ,  Mark Spearing

IPC分类号： B64C338

CPC分类号： B64F1/04 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  Y02T50/14

摘要： A compact, aerodynamic wing assembly constructed and arranged so as to withstand a force due to acceleration in at least one direction includes at least two wing segments, each of the wing segments having a span-wise axis, and a airfoil cross section normal to the span axis. The wing segments are preferably disposed mutually adjacent and end to end. For each pair of wing segments, the wing further includes a pivot assembly fixedly attached to the wing segments at an end of each of the wing segments along the span-wise axis. The pivot assembly forms an articulation axis for relative movement between each the pair of wing segments, such that the wing assembly converts, upon a predetermined stimulus, from a stowed configuration characterized by nested wing segments, to a deployed configuration characterized by a substantially uninterrupted aerodynamic surface. The wing assembly is preferably constructed and arranged to withstand forces due to acceleration in at least two directions, including 15,000 g's forward and 4,000 g's rebound accelerations. The invention further comprises a flying structure constructed and arranged so as to withstand an acceleration force directed along a main axis. The flying structure includes a body disposed about the main axis, and at least one wing assembly pivotally mounted to the body. The wing assembly is constructed and arranged so as to convert, upon a predetermined stimulus, from a stowed configuration characterized by nested wing segments, to a deployed configuration characterized by a substantially uninterrupted aerodynamic surface.

摘要翻译： 构造和布置为承受由于至少一个方向上的加速度而产生的力的紧凑的空气动力学翼组件包括至少两个翼段，每个翼段具有跨度轴线，并且翼型横截面垂直于 跨度轴。 翼片段优选地彼此相邻并且端对端设置。 对于每对翼段，机翼还包括枢转组件，该枢轴组件沿翼展轴线固定地连接到每个翼片段的端部处的翼段。 枢轴组件形成用于每对翼段之间的相对运动的铰接轴线，使得翼组件在预定的刺激下将由嵌套的翼片段特征的收起构型转换成展开的构型，其特征在于基本上不间断的空气动力学 表面。 翼组件优选地构造和布置成承受由于至少两个方向上的加速的力，包括15,000g的向前和4,000g的回弹加速度。 本发明还包括一个构造和布置以便承受沿主轴定向的加速力的飞行结构。 飞行结构包括围绕主轴设置的主体，以及枢转地安装到主体的至少一个翼组件。 机翼组件被构造和布置成在预定的刺激下从由特征为嵌套的翼段的收起构型转换到特征在于基本上不间断的空气动力学表面的展开构型。

公开(公告)号：US06745979B1

公开(公告)日：2004-06-08

申请号：US10277687

申请日：2002-10-22

申请人： Zhuo Chen

发明人： Zhuo Chen

IPC分类号： B64C338

CPC分类号： B64C3/40 ,  B64C3/56 ,  B64C39/08 ,  B64G1/002 ,  B64G1/14 ,  Y02T50/14

摘要： A spacecraft such as a fly back booster or a reusable launch vehicle, or an aerospace plane has a fuselage and a set of scissors wings consisting of two main wings. Both of the main wings are rotatably mounted on the fuselage and can be yawed at opposite directions. If the spacecraft is launched vertically, both of its main wings can be yawed to be generally parallel with its fuselage so that it can connect with other vehicle or vehicles to form different launch configurations. When the spacecraft or aerospace plane is flying in the air, landing, or taking off horizontally, it can yaw both of its main wings in opposite directions to maximize its lift-to-drag ratio by optimizing the yaw angle of the main wings according to flying conditions. It can also produce desired aerodynamic characteristics such as forming a high drag configuration by adjusting the yaw angle of its main wings. The scissors wings can be used on a spacecraft that is launched vertically on the ground, or a spacecraft that is carried to the air and launched in the mid-air, or a spacecraft that takes off horizontally like an aircraft or glider. The scissors wings can also be used on an aerospace plane.

摘要翻译： 诸如飞回式加速器或可重复使用的运载火箭或航空航天飞机的航天器具有机身和一组由两个主翼组成的剪刀翼。 两个主翼都可旋转地安装在机身上，并且可以在相反的方向上偏航。 如果航天器垂直发射，则它的两个主翼可以被偏转以与其机身大致平行，以便它可以与其他车辆或车辆连接以形成不同的发射配置。 当航天器或航空航天飞机在空中飞行，着陆或水平起飞时，它可以以相反的方向偏航两个主翼，以通过根据主翼优化主翼的偏航角来最大化其提升阻力比 飞行条件。 它还可以产生所需的空气动力特性，例如通过调节其主翼的偏航角来形成高阻力构型。 剪刀翼可以用于垂直发射在地面上的航天器，也可以被运送到空中并在空中发射的航天器，或者像飞机或滑翔机水平起飞的航天器。 剪刀翼也可以在航空航天飞机上使用。

公开(公告)号：US06601795B1

公开(公告)日：2003-08-05

申请号：US10227130

申请日：2002-08-23

申请人： Zhuo Chen

发明人： Zhuo Chen

IPC分类号： B64C338

CPC分类号： B64C3/40 ,  B64C39/08 ,  Y02T50/14

摘要： An air vehicle, such as an aircraft, an unmanned air vehicle, a missile, or an aero bomb that has a fuselage and two main wings each of which has a left side wing and a right side wing. Both of the main wings are rotatably mounted on the fuselage via one or two pivots or hollow turrets so that both of them can be yawed during flight to optimize flying efficiency under various flying conditions.

摘要翻译： 诸如飞机，无人驾驶飞行器，导弹或具有机身的航空炸弹和每个具有左侧翼和右侧翼的两个主翼的航空器。 两个主翼通过一个或两个枢轴或空心炮塔可旋转地安装在机身上，使得它们在飞行中可以偏航，以在各种飞行条件下优化飞行效率。

公开(公告)号：US06530544B2

公开(公告)日：2003-03-11

申请号：US09978555

申请日：2001-10-18

申请人： Jérôme Milliere

发明人： Jérôme Milliere

IPC分类号： B64C338

CPC分类号： B64C9/02 ,  B64C13/24 ,  F16C11/045 ,  F16C2326/43 ,  Y10T403/32861

摘要： A device (22) fitted with ribs is placed on a cylindrical rod (20) so that it is fixed to it in bending. The device (22) is formed of at least three ribs connected to each other at their ends, and at least one pair of elements in the form of a star connecting the ribs together, at least close to its central region. This device enables the rod (20) to apply an approximately radial force to the center of the rod through an actuator onto webs (24) bearing on its ends, minimizing the mass for a given spacing of the webs (24). The device is particularly applicable to the control of aircraft control surfaces.

摘要翻译： 装配有肋的装置（22）放置在圆柱形杆（20）上，使其在弯曲时固定到其上。 装置（22）由至少三个在它们的端部彼此连接的肋形成，并且至少一对星形连接肋的形式的元件至少接近其中心区域。 该装置使得杆（20）能够通过致动器将大致径向的力施加到杆的中心到位于其端部上的幅材（24）上，从而使幅材（24）的给定间隔最小化质量。 该装置特别适用于飞机控制面的控制。

公开(公告)号：US06764044B2

公开(公告)日：2004-07-20

申请号：US10174976

申请日：2002-06-20

申请人： Tom Kusic

发明人： Tom Kusic

IPC分类号： B64C338

CPC分类号： B64C5/04 ,  B64C5/10 ,  B64C9/00 ,  B64C9/02 ,  B64C13/16 ,  B64C13/18

摘要： An airplane 1 with a spiral inducing assembly 2 which is capable of inducing the airplane to travel in a continuous spiralling motion without the airplane rolling. Two fins 6 and 17 are attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3 with respect to the rotatable tube 3, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3. Fin 6 is larger than fin 17. The difference in sizes between the fins makes the larger fin 6 exert a greater force on the rotatable tube 3 than the smaller fin 17 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus causes the rotatable tube 3 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3. Thus, as well as forcing the rotatable tube 3 to rotate, the fins 6, 17 would also push the rotatable tube sideways. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion of the airplane when in flight.

摘要翻译： 具有螺旋引导组件2的飞机1，其能够引导飞机以连续的螺旋运动而不飞机滚动。 两个翅片6和17连接到能够围绕机身的环绕部分旋转的管3。 散热片6,17能够相对于可旋转管3以可枢转的方式旋转在可旋转的管3上，从而相对于可旋转管3的纵向轴线改变它们的螺距。翅片6大于翅片17。 散热片之间的尺寸差异使得较大的翅片6在散热片一致倾斜时，可旋转管3上施加比较小翅片17更大的力。 因此，翅片之间的空气动力学不平衡使得可旋转管3旋转。 当与纵向轴线一致地倾斜时，两个翼片6,17将在可旋转的管3上施加横向力。因此，同时迫使可旋转的管3旋转，翅片6,17还将推动 侧向旋转管。 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，导致飞机在飞行中的螺旋运动。

公开(公告)号：US06659396B1

公开(公告)日：2003-12-09

申请号：US10200692

申请日：2002-07-22

申请人： Henry August

发明人： Henry August

IPC分类号： B64C338

CPC分类号： B64C39/12 ,  B64C3/16 ,  B64C5/04 ,  B64C5/12 ,  B64C30/00 ,  B64C39/068 ,  B64G1/14 ,  Y02T50/12

摘要： An air vehicle having an elongated body structure, which has an aft portion and an arch wing device that is coupled to the aft portion of the body structure. The arch wing device includes a lower wing, which has a swept back leading edge and a swept back trailing edge, an upper wing, which has a swept back leading edge and a swept back trailing edge, and a pair of interconnecting portions that couple each of the opposite outboard lateral edges of the upper wing to an associated outboard lateral edge of the lower wing.

摘要翻译： 一种具有细长主体结构的空中车辆，其具有联接到车身结构的后部的后部部分和拱形翼片装置。 拱翼装置包括下翼，其具有扫掠的前缘和扫掠的后缘，上翼具有扫掠的前缘和扫掠的后缘，以及一对互连部分，其将每个 的上翼的相对的外侧边缘到下翼的相关联的外侧边缘。

公开(公告)号：US06626398B1

公开(公告)日：2003-09-30

申请号：US10143603

申请日：2002-05-10

申请人： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

发明人： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

IPC分类号： B64C338

CPC分类号： B64C39/024 ,  B64C39/068 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185

摘要： The present invention provides an unmanned airborne reconnaissance vehicle having a fuselage, a forward wing pair and a rearward wing pair vertically separated by a gap and staggered fore and aft therebetween such that a general biplane configuration is formed. The present invention provides a pair of wing tip plates for joining the wing tips of the forward and rearward wings. The unmanned airborne reconnaissance vehicle of the present invention includes a power plant to propel the vehicle through the air and a generally T-shaped tail having a vertical stabilizer including a rudder and a full span elevator.

摘要翻译： 本发明提供了一种无人机载侦察车辆，其具有机身，前翼对和后翼对，其间隔开间隔并在前后交错，从而形成一般的双翼面构型。 本发明提供了一对用于连接前翼和后翼的翼尖的翼尖板。 本发明的无人机载侦察车辆包括通过空气推动车辆的动力装置和具有垂直稳定器的大致T形的尾部，其包括舵和全跨越电梯。