公开(公告)号：WO2017058329A3

公开(公告)日：2017-05-11

申请号：PCT/US2016041167

申请日：2016-07-06

Applicant: NORTHROP GRUMMAN SYSTEMS CORP

Inventor： LINCH JONATHON J ,  RAHRIG KYLE M

IPC: B64C11/00 ,  B64C39/02

CPC classification number: B64C11/001 ,  B64C39/024 ,  B64C39/10 ,  B64C2039/105 ,  B64C2201/024 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. The ring shroud includes an inner ring surface and a radially spaced, oppositely facing outer ring surface. At least one propeller blade is fixedly attached to both the hub and the inner ring surface and extends radially therebetween for mutual rotation therewith. At least one extending blade has a first extending blade end radially spaced from a second extending blade end. The first extending blade end is fixedly attached to the outer ring surface. The second extending blade end is cantilevered from the first extending blade end and is radially spaced from the ring shroud.

Abstract translation: 螺旋桨包括同轴地围绕纵向轴线的轮毂。 环罩围绕纵轴同轴，并与轮毂径向隔开。 环罩包括内环表面和径向隔开的相对朝外环表面。 至少一个螺旋桨叶片固定地连接到轮毂和内环表面并且在其间径向延伸以与其一起相互旋转。 至少一个延伸叶片具有与第二延伸叶片端部径向隔开的第一延伸叶片端部。 第一延伸刀片端部固定地附接到外部环表面。 第二延伸刀片端部从第一延伸刀片端部悬伸并且与环状护罩径向隔开。

公开(公告)号：WO2016089569A1

公开(公告)日：2016-06-09

申请号：PCT/US2015/060197

申请日：2015-11-11

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： LINCH, Jonathon J. ,  RAHRIG, Kyle M.

IPC: B64C11/00

CPC classification number: B64C11/001 ,  B64C11/08 ,  B64C11/18 ,  B64C39/024 ,  B64C39/10 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/162 ,  B64C2220/00 ,  Y02T50/12

Abstract: A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. At least one propeller blade is fixedly attached to both the hub and ring shroud and extends radially therebetween for mutual rotation therewith. At least one stub blade has a first stub end radially spaced from a second stub end. The first stub end is fixedly attached to a selected one of the hub and ring shroud. The second stub end is cantilevered from the first stub end and is radially interposed between the first stub end and the selected one of the hub and ring shroud.

Abstract translation: 螺旋桨包括同轴地围绕纵向轴线的轮毂。 环形护罩同轴地围绕纵向轴线并与轮毂径向间隔开。 至少一个螺旋桨叶片固定地附接到轮毂和环形护罩上并且在其间径向延伸以与其相互旋转。 至少一个短刀片具有与第二短截线径向间隔开的第一短截线端。 第一短截线端部固定地连接到轮毂和环形护罩中的所选择的一个。 第二短截线端部从第一短截线端部悬臂，并且径向插入在第一短截线端与轮毂和环形护罩中选定的一个之间。

公开(公告)号：WO2016039788A1

公开(公告)日：2016-03-17

申请号：PCT/US2014/069141

申请日：2014-12-08

Applicant: SANDIA CORPORATION

Inventor： HOBART, Clinton, G. ,  MORSE, William, D. ,  BICKERSTAFF, Robert, James

IPC: B64C37/00

CPC classification number: B60F5/02 ,  B60F3/0007 ,  B60F3/003 ,  B60F5/006 ,  B63G8/001 ,  B63G8/08 ,  B63G2008/004 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/082 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2211/00 ,  B64D47/08

Abstract: A MEUV that is able to navigate aerial, aquatic, and terrestrial environments through the use of different mission mobility attachments is disclosed. The attachments allow the MEUV to be deployed from the air or through the water prior to any terrestrial navigation. The mobility attachments can be removed or detached by and from the vehicle during a mission.

Abstract translation: 公开了能够通过使用不同的任务移动附件导航航空，水上和陆地环境的MEUV。 附件允许在任何地面导航之前从空中或通过水部署MEUV。 在任务期间，移动附件可以从车辆移除或拆卸。

公开(公告)号：WO2015160394A2

公开(公告)日：2015-10-22

申请号：PCT/US2015/011149

申请日：2015-01-13

Applicant: ADVANCED PRODUCT DEVELOPMENT, LLC

Inventor： MCDONNELL, William Randall

IPC: B64C3/10 ,  B64F1/04 ,  B64F3/00

CPC classification number: B64C3/10 ,  B63H9/0685 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/082 ,  B64C2201/182 ,  B64C2201/205 ,  B64C2201/208 ,  B64F1/02 ,  B64F1/04 ,  B64F1/222 ,  Y02T50/12 ,  Y02T50/826

Abstract: An asymmetric aircraft (1) and an aircraft (1) that can operate from small ships (8) and be stored in high density with three aircraft or more in one helicopter hangar (107) without needing a landing gear or wing fold. These aircraft slide into and out of the hangar on dollies (90) like circuit boards in a computer and are launched and recovered using a large towed parafoil (6).

Abstract translation: 一种不对称的飞机（1）和一种飞机（1），其能够从小型船舶（8）中操作并以高密度储存在一个直升机机库（107）中，具有三架或更多架飞机而不需要 起落架或机翼折叠。 这些飞机可以像计算机中的电路板一样滑入和滑出飞机库（90），使用大型拖曳翼伞（6）启动和回收。

公开(公告)号：WO2014053298A1

公开(公告)日：2014-04-10

申请号：PCT/EP2013/068994

申请日：2013-09-13

Applicant: SENSEFLY S.A.

Inventor： BEYELER, Antoine ,  KLAPTOCZ, Adam ,  ROBERTS, James F. ,  ZIMMERMANN, Loic ,  ZUFFEREY, Jean-Christophe

IPC: B64C1/26

CPC classification number: B64C1/26 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/187 ,  B64C2201/20

Abstract: This invention relates to a connection set that is used to attach and transfer force and torque between a wing (2a, 2b), comprising a lifting surface and a control surface (9) connected together by a hinge, and the central body (1 ) of an aircraft, which contains a servo-motor (10) used for actuating said control surface (9). The wing (2a, 2b) is connected to the central body (1 ) using a connection set comprised of two components. First, an attachment mechanism (3, 4, 5, 6) is used to align the wings (2a, 2b) relative to the central body (1 ) and to transfer the aerodynamic forces acting on the wing (2a, 2b) to the central body (1 ), preventing the wing (2a, 2b) from bending at its connection point. Second, a torque coupling mechanism (7, 8) is used to actuate the control surfaces that are present on the wings using servomotors (10) that are embedded within the central body (1 ). The connection set is engaged and disengaged using a single motion and does not require additional connection of electrical cables or mechanical fixations.

Abstract translation: 本发明涉及一种用于在包括提升表面和通过铰链连接在一起的控制表面（9）的翼（2a，2b）之间附接和传递力和扭矩的连接组件，以及中心体（1） 其包含用于致动所述控制表面（9）的伺服电动机（10）。 翼（2a，2b）使用由两个部件组成的连接组件连接到中心体（1）。 首先，使用附接机构（3,4,5,6）来相对于中心体（1）对准翼（2a，2b）并将作用在机翼（2a，2b）上的空气动力传递到 中心体（1），防止机翼（2a，2b）在其连接点处弯曲。 第二，使用扭矩耦合机构（7,8）来使用嵌入在中心体（1）内的伺服电动机（10）致动存在于机翼上的控制表面。 连接组件使用单一动作进行接合和分离，不需要额外连接电缆或机械固定。

公开(公告)号：WO2010070631A1

公开(公告)日：2010-06-24

申请号：PCT/IL2009/001128

申请日：2009-12-01

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD. ,  ABERSHITZ, Abraham

Inventor： ABERSHITZ, Abraham

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187

Abstract: The present invention relates to an unmanned air vehicle (105), comprising a body having front (121) and rear (122) sections with at least one pair of end plates (110) connected to said body, wherein one end plate within said at least one pair of end plates is connected to the left side of said body and another end plate within said at least one pair of end plates is connected to the right side of said body, each end plate having upper and lower sections (111,112), wherein: a) said upper section is positioned above a mean line of said body; b) said lower section is positioned below said mean line of said body; and c) a ratio of the area of said upper section to the area of said lower section is less than 1.

Abstract translation: 本发明涉及一种无人驾驶飞行器（105），其包括具有前部（121）和后部（122）部分的主体，所述主体部分具有连接到所述主体的至少一对端板（110），其中，所述内部 至少一对端板连接到所述主体的左侧，并且在所述至少一对端板内的另一个端板连接到所述主体的右侧，每个端板具有上部和下部（111,112）， 其中：a）所述上部分位于所述主体的平均线之上; b）所述下部部分位于所述主体的平均线下方; 和c）所述上部区域与所述下部区域的面积之比小于1。

公开(公告)号：WO2008085536A3

公开(公告)日：2008-10-02

申请号：PCT/US2007069569

申请日：2007-05-23

Applicant: AVID LLC ,  WILSON SAMUEL B ,  GELHAUSEN PAUL ,  TURNBULL ANDY ,  ROBERTS MICHAEL ,  GUERERRO IGNACIO ,  BECKER KIM

Inventor： WILSON SAMUEL B ,  GELHAUSEN PAUL ,  TURNBULL ANDY ,  ROBERTS MICHAEL ,  GUERERRO IGNACIO ,  BECKER KIM

IPC: F41G7/00 ,  F41H13/00

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/162 ,  B64C2201/206 ,  B64D5/00

Abstract: The present invention provides a system for reconnaissance using autonomous unmanned airborne vehicles (UAV). The system comprises a mothership, which is generally a fixed wing fuel tank capable of providing a suitable surface for flight (lift) and one or more elements for attachment of individual UAVs. The system further comprises one or more UAVs that are detachably connected to the mothership, and which are independently controllable for reconnaissance and tracking. The system and its individual parts are reusable and independently controllable, permitting low cost reconnaissance over wide areas of geography.

Abstract translation: 本发明提供一种使用自主无人驾驶飞行器（UAV）进行侦察的系统。 该系统包括母舰，其通常是能够为飞行（提升）提供合适的表面的固定翼燃料箱和用于附接各个无人机的一个或多个元件。 该系统还包括一个或多个UAV，其可拆卸地连接到母舰，并且可独立控制以用于侦察和跟踪。 该系统及其各个部件是可重复使用的并且可独立控制，允许在广泛的地理区域进行低成本侦察。

公开(公告)号：WO2008099192A1

公开(公告)日：2008-08-21

申请号：PCT/GB2008/000534

申请日：2008-02-15

Applicant: THE UNIVERSITY OF SHEFFIELD ,  KUO, Chen-Ming ,  BOLLER, Christian

Inventor： KUO, Chen-Ming ,  BOLLER, Christian

IPC: B64C15/12 ,  B64C39/02

CPC classification number: B64C15/12 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/165

Abstract: An aerial vehicle comprising an aerofoil (2), a generally forward facing propeller (10), a drive motor (6) arranged to drive the propeller about a drive axis to generate thrust, and mounting means (32) on which the propeller is pivotably mounted so that the drive axis can be moved relative to the aerofoil thereby to vary the direction of the thrust, the vehicle further comprising thrust control means (14, 18) arranged to control pivoting of the propeller so as to control the direction of the thrust, thereby to control the direction of travel of the vehicle.

Abstract translation: 一种飞行器，包括机翼（2），大致向前的螺旋桨（10），驱动马达（6），驱动马达（6）布置成驱动螺旋桨绕驱动轴线产生推力;以及安装装置（32），螺旋桨可枢转 安装成使得驱动轴线能够相对于机翼移动从而改变推力的方向，车辆还包括推力控制装置（14,18），其布置成控制螺旋桨的枢转以控制推力的方向 从而控制车辆的行驶方向。

公开(公告)号：WO2006059324A1

公开(公告)日：2006-06-08

申请号：PCT/IL2005/001276

申请日：2005-11-30

Applicant: ISRAEL AIRCRAFT INDUSTRIES LTD. ,  SIRKIS, Omri

Inventor： SIRKIS, Omri

IPC: B64C9/18 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C9/18 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/201

Abstract: A method for landing a fixed wing aircraft is provided in which an inversion maneuver is performed so that the aircraft's back is facing the ground, and the aircraft's underside is facing away from the ground. After initiation or completion of this maneuver, deep stall is induced, and the aircraft descends almost vertically to land on its upper side, thus minimizing impact loads or damage on its underside. In a particular aerodynamic arrangement configured for carrying out the method, a flap (24), which may be stowed during normal flight, is deployed in a manner such as to aerodynamically induce a negative pitching moment on the aircraft and deep stall.

Abstract translation: 提供了一种用于着陆固定翼飞机的方法，其中执行反演机动，使得飞机的背面面向地面，并且飞机的下侧面向远离地面。 在开始或完成这个机动之后，引起深度失速，飞机几乎垂直下降，降落在其上侧，从而最小化其下侧的冲击载荷或损坏。 在配置用于执行该方法的特定空气动力学配置中，可以以正常飞行中的方式存放的翼片（24）以空气动力学方式在飞行器和深度档位上引起负俯仰时刻。

公开(公告)号：WO2006028494A2

公开(公告)日：2006-03-16

申请号：PCT/US2005/004922

申请日：2005-02-15

Applicant: THE BOEING COMPANY ,  BOLLING, John, G.

Inventor： BOLLING, John, G.

IPC: B64D39/00

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104

Abstract: An in-flight refueling system for an unmanned aircraft is responsive to sensed forces acting on a refueling receptacle of the aircraft by a separate refueling probe, to control movements of the aircraft as it is being refueled to reduce the magnitude of the sensed forces and thereby maintain the coupling of the aircraft with the refueling probe.

Abstract translation: 用于无人驾驶飞机的飞行中加油系统响应于通过单独的加油探针作用在飞机的加油容器上的感测力，以控制飞机在被加油时的运动，以减小感测力的大小，从而 保持飞机与加油探头的耦合。