公开(公告)号：US20130306789A1

公开(公告)日：2013-11-21

申请号：US13475371

申请日：2012-05-18

Applicant: Suneal Guptaa ,  Jeremy Bley

Inventor： Suneal Guptaa ,  Jeremy Bley

IPC: B64C3/56 ,  B65B43/00 ,  B65D6/00 ,  B65B11/00

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  F42B10/16 ,  Y02T50/14

Abstract: An air vehicle, as well as a method for folding an air vehicle for storage, may include a fuselage and a wing connected to the fuselage. The wing may include two ends positioned opposite from each other, and the wing may be substantially perpendicular to the fuselage. At least one of the ends may define a space therebetween the fuselage and the wing. The space may be sized to receive a potion of the wing when the wing is wrapped around the fuselage.

Abstract translation: 一种空中飞行器以及用于折叠用于存储的空中飞行器的方法可以包括机身和连接到机身的机翼。 机翼可以包括彼此相对定位的两个端部，并且机翼可以基本上垂直于机身。 端部中的至少一个可以限定机身和机翼之间的空间。 当机翼围绕机身缠绕时，该空间的大小可以接收机翼的一部分。

公开(公告)号：US08528863B2

公开(公告)日：2013-09-10

申请号：US12463400

申请日：2009-05-10

Applicant: Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

Inventor： Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

IPC: B64C3/20 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  F42B10/14 ,  F42B10/146 ,  F42B10/16 ,  F42B10/20

Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

Abstract translation: 层压翼结构包括至少一层金属材料和至少一层形状记忆聚合物（SMP）材料。 将SMP加热到其玻璃化转变带Tg的温度，以将机身周围的机翼卷绕成储存位置。 金属层必须足够薄以便在卷起时保持低于其屈服点。 在准备发射时，SMP材料被热激活，允许存储在金属材料层中的应变能在发射时将机翼返回到其展开位置。 一旦部署，SMP冷却到玻璃状态。 SMP材料可以用纤维增强以形成聚合物基质复合材料（PMC）。 SMP可用于为多个金属层提供剪切应变消除。 通过卸载将机翼从SMP返回到金属的原始展开位置所需的动力，聚合物不会获得永久变形，并且可以准确地展开机翼。

公开(公告)号：US08469307B2

公开(公告)日：2013-06-25

申请号：US13270872

申请日：2011-10-11

Applicant: Paul E Arlton ,  David J Arlton

Inventor： Paul E Arlton ,  David J Arlton

IPC: B64C27/10 ,  B64C27/54 ,  B64C27/58

CPC classification number: B64C27/10 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract translation: 旋转翼车辆包括具有细长管状骨架或芯体的主体结构，以及具有转子的反向旋转同轴转子系统，每个转子具有单独的电动机，以围绕公共转子旋转轴线驱动转子。 转子系统用于在定向飞行中移动旋翼机。

公开(公告)号：US20130146716A1

公开(公告)日：2013-06-13

申请号：US13324193

申请日：2011-12-13

Applicant: Jonathan David Gettinger

Inventor： Jonathan David Gettinger

IPC: B64C3/56 ,  B64C3/50

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C5/12 ,  B64C2201/102

Abstract: Deployment and control actuation mechanisms are incorporated in unmanned aerial vehicles having folding wings and/or folding canards and/or a folding vertical stabilizer. The folding canards and folding vertical stabilizer can be deployed using respective four-bar over-center mechanisms. Elevators pivotably mounted to the folding canards and a rudder pivotably mounted to the folding vertical stabilizer can be controlled by means of respective twist link mechanisms. The folding wings have respective wing roots that are driven by respective gas springs to pivot on bearings about a wing root hub having control servo wire paths.

Abstract translation: 部署和控制致动机构被并入具有折叠翼和/或折叠的猫和/或折叠的垂直稳定器的无人驾驶飞行器中。 可以使用相应的四杆过中心机构来部署折叠式鸭子和折叠式垂直稳定器。 可枢转地安装到折叠卡瓦的电梯和可枢转地安装到折叠垂直稳定器的舵可以通过相应的扭转连杆机构来控制。 折叠翼具有相应的翼根，其由相应的气弹簧驱动，以围绕具有控制伺服线路径的翼根轮毂的轴承枢转。

公开(公告)号：US08262032B2

公开(公告)日：2012-09-11

申请号：US12616812

申请日：2009-11-12

Applicant: Terry M. Sanderson ,  David R. Sar

Inventor： Terry M. Sanderson ,  David R. Sar

IPC: B64C3/48 ,  B64C3/44 ,  B64C3/56 ,  B64C3/00

CPC classification number: B64C3/185 ,  B64C3/48 ,  B64C3/56 ,  B64C2201/102

Abstract: A wing, such as a wing for an unmanned aerial vehicle (UAV), includes a beam or box that can be selectively expanded from a collapsed condition, to increase the thickness of the wing. The beam may include a pair of plates that are close together when the beam is in a collapsed condition, and separate from one another to put the beam in an expanded condition. The plates may be substantially parallel to each other, and may have shape memory foam and/or resilient devices, such as coil springs, between them, in order to provide a force to separate the plates before, during, and/or after deployment of the wing. The expandable/collapsible beam may have a lock mechanism to lock it into place when the beam is in an expanded condition.

Abstract translation: 诸如用于无人驾驶飞行器（UAV）的机翼的机翼包括可以从折叠状态选择性地扩展的梁或箱，以增加机翼的厚度。 梁可以包括一对板，当梁处于折叠状态时，彼此分离并将梁放置在膨胀状态下，它们靠近在一起。 板可以基本上彼此平行，并且在它们之间可以具有形状记忆泡沫和/或弹性装置，例如螺旋弹簧，以便在部署之前，期间和/或之后提供力分离板 机翼。 可膨胀/可折叠的梁可以具有锁定机构，以在梁处于膨胀状态时将其锁定到位。

公开(公告)号：US20120205488A1

公开(公告)日：2012-08-16

申请号：US13367494

申请日：2012-02-07

Applicant: David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

Inventor： David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

IPC: B64F1/04

CPC classification number: B64C39/024 ,  B63G8/30 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/205

Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

Abstract translation: 用于发射无人机（UAV）有效载荷的系统包括发射管，液体火箭和发射控制组件。 火箭定位在发射管中，并包含无人机的有效载荷。 增压组件可以包括部分地填充有液体的罐。 气瓶内充满压缩气体。 液体被气体预加压或在发射前与气体混合，使得在发射时，液体和气体推进阶段将火箭发射到阈值高度。 无人机有效载荷在达到阈值高度后部署。 可选的稳定管可以连接到发射管，其可以浮动用于水基操作。 可选的系绳可以连接到液体火箭，以在达到远地点之前停止其飞行。 无人机有效载荷不直接由气/液混合发射。 还公开了一种启动无人机有效载荷的方法。

公开(公告)号：US20110073709A1

公开(公告)日：2011-03-31

申请号：US12628610

申请日：2009-12-01

Applicant: Alexandra L. Blake ,  David B. Hatfield ,  Rudy A. Eisentraut ,  Peter J. Drake

Inventor： Alexandra L. Blake ,  David B. Hatfield ,  Rudy A. Eisentraut ,  Peter J. Drake

IPC: B64C1/14 ,  F16J15/02 ,  B29C65/48

CPC classification number: F16J15/104 ,  B64C1/14 ,  B64C1/30 ,  B64C1/32 ,  B64C2201/102 ,  F42B10/14 ,  Y10T156/10

Abstract: A frangible seal includes a first region penetratable by a deployable structure configured to selectably extend through an opening in a housing and extend beyond an outer surface of the housing, and a second region configured to adhere to a portion of the outer surface of the housing surrounding the opening. The first region and the second region includes a polymer layer having a metalized surface (e.g., aluminized polyimide) and a non-metalized surface, and an ablative coating provided on the metalized surface of the polymer layer.

Abstract translation: 易碎的密封件包括可展开结构的第一区域，该第一区域构造成可选择地延伸穿过壳体中的开口并且延伸超过壳体的外表面，并且第二区域被构造成粘附到外壳的外表面的一部分周围 开幕。 第一区域和第二区域包括具有金属化表面（例如镀铝聚酰亚胺）和非金属化表面的聚合物层和设置在聚合物层的金属化表面上的烧蚀涂层。

公开(公告)号：US07866610B2

公开(公告)日：2011-01-11

申请号：US12005600

申请日：2007-12-28

Applicant: Samuel Hall Bousfield

Inventor： Samuel Hall Bousfield

IPC: B64C3/54

CPC classification number: B64C3/56 ,  B64C3/18 ,  B64C3/52 ,  B64C2201/102

Abstract: This invention relates generally to a collapsible, nesting wing structure with or without wing warp flight control. The invention also incorporates means to maintain wing extension during flight, methods of wing construction for nesting collapsible wings, and control surfaces for collapsible wings.

Abstract translation: 本发明一般涉及具有或不具有翼型经线飞行控制的可折叠的嵌套翼结构。 本发明还包括在飞行期间维持机翼延伸的方法，用于嵌套可折叠翼的翼结构的方法以及用于可折叠翼的控制表面。

公开(公告)号：US20100264260A1

公开(公告)日：2010-10-21

申请号：US12425844

申请日：2009-04-17

Applicant: ROBERT E. HAMMERQUIST

Inventor： ROBERT E. HAMMERQUIST

IPC: B64C3/56

CPC classification number: B64C3/56 ,  B64C2201/102 ,  F42B10/14

Abstract: A wing pivot mechanism that is configured to pivot two wings about a single pivot axis of a vehicle, such as an aircraft. The wing pivot mechanism includes a hub, a set of gears positioned at least partially within an interior region of the hub, and two wings that are rotatably connected to the hub. Each wings includes a gear surface extending therefrom. Each gear of the hub assembly engages a gear of a respective wing such that rotation of the gears of the hub assembly causes rotation of the gears of the wings and pivoting of the wings about the single pivot axis in opposite rotational directions between a stowed position and a deployed position. A releasable locking mechanism is provided for locking the wings in a fixed rotational position in both the deployed position and the stowed position.

Abstract translation: 翼部枢转机构，其构造成围绕诸如飞机的车辆的单个枢转轴线枢转两个翼。 翼枢转机构包括轮毂，至少部分地定位在轮毂的内部区域内的一组齿轮，以及可旋转地连接到轮毂的两个翼。 每个翼包括从其延伸的齿轮表面。 轮毂组件的每个齿轮接合相应机翼的齿轮，使得轮毂组件的齿轮的旋转引起机翼的齿轮的旋转，并且机翼围绕单个枢转轴线以相反的旋转方向在收起位置和 部署位置。 提供了可释放的锁定机构，用于将翼片在展开位置和收起位置两者中锁定在固定的旋转位置。

公开(公告)号：US20100237192A1

公开(公告)日：2010-09-23

申请号：US12406173

申请日：2009-03-18

Applicant: Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

Inventor： Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

IPC: B64C3/30 ,  B64C3/38

CPC classification number: B64C3/30 ,  B64C2201/102 ,  B64C2201/105 ,  F42B10/14 ,  F42B10/146 ,  F42B10/20

Abstract: A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box forms a first portion of the wing. A skin having a plurality of rigid plates affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.

Abstract translation: 增强的充气翼改善了OML的公差，并加强了至少在高负载区域中的机翼。 这种方法提供具有增加的表面面积的具有翼的装备受限的空中车辆，以改善飞行耐力或空气动力学控制。 翼盒形成翼的第一部分。 具有固定到其上的多个刚性板的皮肤被充气以形成机翼的第二部分，以增加弦长或延长机翼跨度。 皮肤适当地用泡沫充气以形成固体翼。