公开(公告)号：US20140239118A1

公开(公告)日：2014-08-28

申请号：US13774157

申请日：2013-02-22

Applicant: Itzhak Sapir

Inventor： Itzhak Sapir

IPC: B64C39/02 ,  B64F1/10

CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/102 ,  F41F3/042 ,  F41F3/052 ,  F42B10/16 ,  F42B15/08

Abstract: A device for releaseably retaining a wing of an aerial vehicle in a folded orientation in a bore of a tube is disclosed. A retaining element is bound around the folded wing elements of a foldable-winged UAV so that the maximum diameter of the folded and bound UAV is less than the diameter of the bore. A releasable retaining fastener is provided and configured whereby the fastener releases when the UAV is propelled through and exits the bore, releasing the retaining element after which the wings of the UAV unfold and return to a flight orientation. The retaining element may include a tether for the retention and reuse of the device after a launch.

Abstract translation: 公开了一种用于在管的孔中以折叠方向可释放地保持空中飞行器的翼的装置。 保持元件围绕可折叠翼型UAV的折叠翼元件结合，使得折叠和结合的UAV的最大直径小于孔的直径。 可释放的固定紧固件被设置并构造成当UAV被推进通过和离开孔时紧固件释放，释放保持元件，在此之后，UAV的机翼展开并返回到飞行方位。 保持元件可以包括用于在发射之后保持和重新使用设备的系绳。

公开(公告)号：US08662441B2

公开(公告)日：2014-03-04

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: B64F1/10

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：US08584984B2

公开(公告)日：2013-11-19

申请号：US13620249

申请日：2012-09-14

Applicant: Robert Parks ,  Adam Woodworth ,  Peter Lively ,  Thomas Vaneck ,  Kimberly Kohlhepp ,  Justin McClellan

Inventor： Robert Parks ,  Adam Woodworth ,  Peter Lively ,  Thomas Vaneck ,  Kimberly Kohlhepp ,  Justin McClellan

IPC: B64C3/30

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/127

Abstract: A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

Abstract translation: 公开了一种可用于能够在85,000英尺或以上的高度操作的高空飞机的折叠翼。 可折叠翼可以采用螺旋折叠展开，其中可折叠翼的每个片段之间的铰链稍微偏离垂直线。 连续定位的翼片彼此折叠。 或者，铰链基本上垂直，使得每个相应的翼段相对于下一个翼段线性地折叠。 具有可充气臂的充气肋可以被充气以提供抵抗两个相邻臂的力，从而将翼段展开完整的180度旋转。

公开(公告)号：US20130099049A1

公开(公告)日：2013-04-25

申请号：US13278493

申请日：2011-10-21

Applicant: Jack W. Reany ,  Terry M. Sanderson

Inventor： Jack W. Reany ,  Terry M. Sanderson

IPC: B64C3/56

CPC classification number: B64C3/56 ,  B64C2201/102

Abstract: A wing includes a spar, and a pair of flexible skins that are attached to the spar. The spar is at the leading edge of the wing, and the skins extend toward the trailing edge of the wing. The wing deploys from a stowed condition, in which the skins are curved in the same direction around a fuselage of an aircraft, to a deployed condition, in which the skins provide the wing with an airfoil cross-sectional shape, for example with the skins curve in opposite direction. A lock is used to maintain the skins in the deployed state, with the lock for example located at the trailing edge of the wing. The lock may be a mechanical mechanism that automatically locks the wing in the deployed state, preventing the wing from returning to the stowed state.

Abstract translation: 翼包括翼梁，以及一对连接到翼梁的柔性皮。 翼梁位于机翼的前缘，皮面朝向机翼的后缘延伸。 机翼从收起的状态部署，其中皮肤沿着飞机的机身在相同的方向上弯曲到部署状态，其中皮肤为翼提供翼型横截面形状，例如与皮肤 曲线相反。 使用锁来将皮肤保持在展开状态，例如锁定位于翼的后缘。 锁可以是机械机构，其将机翼自动地锁定在展开状态，防止机翼返回到收起状态。

公开(公告)号：US20120325965A1

公开(公告)日：2012-12-27

申请号：US13516453

申请日：2010-12-17

Applicant: Alfram V. Bright ,  Richard Wlezien

Inventor： Alfram V. Bright ,  Richard Wlezien

IPC: B64C3/30 ,  B64C3/56

CPC classification number: B64C3/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/127 ,  D06M10/001 ,  D06M10/10 ,  D06M15/327 ,  E04H12/00 ,  F03D13/20 ,  H05G2/00 ,  Y02E10/728

Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements which find use in rapidly deploying and supporting the wing of an aerial vehicle.

Abstract translation: 本发明提供了新颖的可膨胀和可固化的支撑元件，及其制造和使用方法。 特别地，本发明提供了充气和可固化的支撑元件，其可用于快速展开和支撑飞行器的机翼。

公开(公告)号：US20120232722A1

公开(公告)日：2012-09-13

申请号：US13478520

申请日：2012-05-23

Applicant: Christopher E. Fisher ,  Marc L. Schmalzel ,  Steven Chambers ,  Justin B. McAllister

Inventor： Christopher E. Fisher ,  Marc L. Schmalzel ,  Steven Chambers ,  Justin B. McAllister

IPC: G05D1/00

CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/102

Abstract: Methods, systems, and devices for determining system/device configuration and setting a mode of operation based on the determined configuration. An air vehicle processor: (a) receives a component information 14 set of at least one external component; (b) determine a mode of operation, by the processor having a current mode of operation setting, based on the received component information and at least one of: an initial mode of operation setting and the current mode of operation setting; (c) determines whether all of the one or more received component information sets match a configuration requirement; (d) transitions to a flight-ready status if the determination is a conjunctive match; and (e) transition to a reset status if the determination is not a conjunctive match.

Abstract translation: 用于确定系统/设备配置并基于所确定的配置来设置操作模式的方法，系统和设备。 一种飞行器处理器：（a）接收至少一个外部部件的部件信息14组; （b）基于接收到的分量信息和至少一个操作设置模式和当前操作模式设置中的至少一个来确定具有当前操作模式设置的处理器的操作模式; （c）确定所述一个或多个接收到的分量信息集合是否匹配配置要求; （d）如果确定是联合匹配，则转换到飞行就绪状态; 和（e）如果确定不是联合匹配，则转换到复位状态。

公开(公告)号：US08258447B2

公开(公告)日：2012-09-04

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: F42B15/01

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：US20120138727A1

公开(公告)日：2012-06-07

申请号：US13097394

申请日：2011-04-29

Applicant: Jeremy F. Fisher

Inventor： Jeremy F. Fisher

IPC: F42B15/01 ,  B64D1/02 ,  B64C3/56 ,  F42B10/14

CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。

公开(公告)号：US08104713B2

公开(公告)日：2012-01-31

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: B64C3/54

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。

公开(公告)号：US08070090B2

公开(公告)日：2011-12-06

申请号：US12486023

申请日：2009-06-17

Applicant: Steven K. Tayman

Inventor： Steven K. Tayman

IPC: B64C27/22

CPC classification number: B64C27/24 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/108

Abstract: Systems and methods for transitioning an aircraft between helicopter and fixed wing flight modes are provided. In one embodiment, an aircraft comprises a plurality of wings each having a spar and a flap; a flap actuator configured to move the flap with respect to the spar; and a center section rotatably coupled to each spar. The center section includes at least one spar actuator configured to rotate at least one of the wings about a rotational axis of the spar when the aircraft transitions between helicopter and fixed wing flight modes.

Abstract translation: 提供了在直升机和固定翼飞行模式之间转换飞机的系统和方法。 在一个实施例中，飞机包括多个翼，每个翼具有翼梁和翼片; 翼片致动器，其构造成相对于翼梁运动翼片; 以及可旋转地联接到每个翼梁的中心部分。 中心部分包​​括至少一个翼梁致动器，其构造成当飞机在直升机和固定翼飞行模式之间转换时围绕翼梁的旋转轴线旋转至少一个翼。