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    LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV)
    241.
    发明申请
    LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV) 审中-公开
    无人机（UAV）发射管约束系统

    公开(公告)号：WO2013126111A2

    公开(公告)日：2013-08-29

    申请号：PCT/US2012/067086

    申请日：2012-11-29

    Applicant: AEROVIRONMENT, INC. ,  SU, Guan ,  RODRIGUEZ, Marcos

    Inventor： SU, Guan ,  RODRIGUEZ, Marcos

    IPC: B64C1/22

    CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

    Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

    Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射设备，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），管 （440），所述管（440）包括配置成可控制地阻碍所述AV突片（510）经过所述突片止挡件（515）的行程的突片止挡件（515），以及一对相对的突片引导件 700），其被配置为定位AV标签（510）以在标签止挡（515）上行进。

    UAV KIT
    242.
    发明申请
    UAV KIT 审中-公开
    无人机套件

    公开(公告)号：WO2012130790A3

    公开(公告)日：2013-01-03

    申请号：PCT/EP2012055298

    申请日：2012-03-26

    Applicant: PROX DYNAMICS AS ,  MUREN PETTER

    Inventor： MUREN PETTER

    IPC: B64C39/02 ,  A63H27/10

    CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C39/028 ,  B64C2201/024 ,  B64C2201/127 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2203/00 ,  B64D47/08

    Abstract: The embodiments herein disclose a personal UAV kit for storing, preparing and remote control of micro UAVs (40). The UAV kit includes a base unit (10), a control unit (30) and at least one UAV. The UAVs can typically be a winged aircraft with foldable wings or a helicopter with a two-bladed or foldable rotor. The base unit comprises UAV compartments for housing at least one UAV, bay (14) for storing the control unit, batteries and electronic components for charging, communication, control and processing and storing of data. In addition, the system includes an eye near display device for viewing system information and sensor data, typically live video, transmitted from the UAV.

    Abstract translation: 本文的实施方案公开了用于存储，准备和远程控制微型无人机（40）的个人UAV套件。 UAV套件包括基本单元（10），控制单元（30）和至少一个UAV。 无人机通常可以是具有可折叠翼的有翼飞机或具有双叶片或可折叠转子的直升机。 基座单元包括用于容纳至少一个UAV的UAV隔间，用于存储控制单元的舱（14），用于对数据进行充电，通信，控制和处理和存储的电池和电子组件。 此外，该系统包括用于观看系统信息的眼睛附近，以及从UAV发送的通常是实时视频的传感器数据。

    METHODS AND APPARATUS FOR MARINE DEPLOYMENT
    245.
    发明申请
    METHODS AND APPARATUS FOR MARINE DEPLOYMENT 审中-公开
    海上部署的方法和装置

    公开(公告)号：WO2009079045A2

    公开(公告)日：2009-06-25

    申请号：PCT/US2008076769

    申请日：2008-09-18

    Applicant: RAYTHEON CO ,  BOSSERT DAVID ,  ZERBE JEFF ,  SAMPSON RAY

    Inventor： BOSSERT DAVID ,  ZERBE JEFF ,  SAMPSON RAY

    IPC: B64F1/06

    CPC classification number: F41F3/07 ,  B64C2201/201 ,  B64C2201/205 ,  F42B15/20

    Abstract: Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.

    Abstract translation: 根据本发明的各个方面的用于船舶部署的方法和装置可以与适于由船用车辆展开的可浮动壳体结合操作。 可浮动壳体可以适于从船用车辆发射并升起到地面。 诸如无人驾驶飞行器的资产可以从表面浮动的壳体部署。

    UNMANNED AERIAL SURVEILLANCE DEVICE
    247.
    发明申请
    UNMANNED AERIAL SURVEILLANCE DEVICE 审中-公开
    不定期的空中监视装置

    公开(公告)号：WO2007084186A2

    公开(公告)日：2007-07-26

    申请号：PCT/US2006/032105

    申请日：2006-08-17

    Applicant: CHANG INDUSTRY, INC. ,  DE LA TORRE, Samuel

    Inventor： DE LA TORRE, Samuel

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/203

    Abstract: An aerial surveillance device is provided, comprising an image capturing device capable of being supported by an airframe structure above the ground. The airframe structure includes a body portion defining a longitudinal axis and configured to support the image-capturing device. A tail portion having control surfaces is operably engaged with the body portion along the axis. Transversely-extending wing portions are directly engaged with the body portion. Each wing portion is defined by longitudinally-opposed spars extending from a spaced-apart disposition at the body portion to a common connection distally from the body portion. The spars have a fabric extending therebetween to provide a wing surface. A support member extends along an aerodynamic center, transversely to the body portion, of each wing portion, to tension and rigidify the wing portions so as to provide a positive camber for the wing portions and to form an airfoil.

    Abstract translation: 提供了一种空中监视装置，其包括能够由地面上方的机身结构支撑的图像捕获装置。 机身结构包括限定纵向轴线并构造成支撑图像捕获装置的主体部分。 具有控制表面的尾部部分沿着轴线与主体部分可操作地接合。 横向延伸的翼部直接与主体部分接合。 每个翼部分由纵向相对的翼梁限定，该翼梁从主体部分处的间隔布置延伸到远离主体部分的公共连接。 翼梁具有在其间延伸的织物以提供机翼表面。 支撑构件沿每个翼部横向于主体部分的空气动力学中心延伸，以张紧和刚化翼部，以便为翼部提供正弧形并形成翼型。

    STOWABLE DESIGN FOR UNMANNED AERIAL VEHICLE
    248.
    发明申请
    STOWABLE DESIGN FOR UNMANNED AERIAL VEHICLE 审中-公开
    无人机的可携式设计

    公开(公告)号：WO2006073750A2

    公开(公告)日：2006-07-13

    申请号：PCT/US2005/045715

    申请日：2005-12-16

    Applicant: ALMAN, James

    Inventor： ALMAN, James

    IPC: B64D45/02

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203

    Abstract: An unmanned aerial vehicle (UAV) having a design for optimum stowability and low cost. The UAV having a collapsible wing section which can be easily removed from the fuselage, allowing for quick assembly and disassembly and ease of portability. The unmanned aerial vehicle includes a primary wing assembly, a fuselage, a means for propelling the unmanned aerial vehicle , and means for remotely controlling the unmanned aerial vehicle. The primary wing assembly includes a wing having a center spar and two outwardly diverging side spars. The wing also has a pliable flexible material supported by the center spar and the at least two outwardly diverging side spars. The pylon is connected to the wing and supports the wing. The fuselage is connected to the pylon such that the pylon extends away from the fuselage and spaces the wing a distance from the fuselage. The fuselage includes a tail having a rudder located along a trailing edge and elevators located along the trailing edge.

    Abstract translation: 无人驾驶飞行器（UAV）具有最佳装载性和低成本的设计。 该无人机具有可折叠的机翼部分，可以轻松地从机身上拆下，从而实现快速装配和拆卸，便于携带。 无人驾驶飞行器包括主翼组件，机身，用于推进无人飞行器的装置和用于远程控制无人飞行器的装置。 主翼组件包括具有中心翼梁和两个向外发散侧翼的翼。 机翼还具有由中心翼梁和至少两个向外分开的侧翼支撑的柔韧柔性材料。 塔架连接到机翼并支撑机翼。 机身连接到塔架，使得塔架远离机身延伸并将机翼与机身隔开一段距离。 机身包括尾部，其尾部有一个方向舵，后部有电梯，电梯位于尾部。

    ARTILLERY LAUNCHED FLYER ASSEMBLY
    249.
    发明申请
    ARTILLERY LAUNCHED FLYER ASSEMBLY 审中-公开
    ARTILLERY推出飞行器总成

    公开(公告)号：WO0232762A3

    公开(公告)日：2004-01-08

    申请号：PCT/US0131631

    申请日：2001-10-11

    Applicant: DRAPER LAB CHARLES S

    Inventor： MARTORANA RICHARD T ,  ANDERSON JAMIE ,  SPEARING SIMON MARK ,  KESSLER SETH ,  APPLEBY BRENT ,  BERGMANN EDWARD ,  GEORGE SEAN ,  JACOBSON STEVEN ,  FLYER DONALD ,  DRELA MARK ,  KIRKOS GREGORY ,  MCFARLAND WILLIAM JR

    IPC: B64C39/02 ,  F42B15/10 ,  B64C3/56

    CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

    Abstract: A flyer assembly (10) is adapted for launching with, transit in, and deployment from an artillery shell (22). The flyer assembly (10) includes a jettisonable shroud (12) and a flyer (14). The flyer (14) is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer (14) is positionable within the shroud (12) with the flyer axis parallel to the shroud axis and the shell axis. The flyer (14) includes a body member disposed about the flyer axis, and a foldable wing assembly (20) mounted to the body member. THe wing assembly (20) is characterized by a plurality of nested wing segments (32) when the flyer is in the first state. THe wing assembly (20) is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly (10) is launched from an artillery cannon, and can thus reach a target quickly, without expending energy stored with theflyer. During launch, the flwyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along eht flyer axis.

    Abstract translation: 传单组件（10）适用于从炮弹（22）发射，转运和展开。 传单组件（10）包括可喷射的护罩（12）和传单（14）。 飞翼（14）适于在处于第一状态时承受沿飞行器轴线的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单（14）可定位在护罩（12）内，飞翼轴线平行于护罩轴线和外壳轴线。 传单（14）包括围绕飞行器轴线设置的主体构件和安装到主体构件的可折叠翼组件（20）。 当翼片处于第一状态时，翼组件（20）的特征在于多个嵌套翼段（32）。 翼组件（20）可配置成展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件（10）从炮兵炮发射，并且因此能够快速地达到目标，而不会消耗与飞行器一起存储的能量。 在发射过程中，飞镖耦合到护罩上，以便在飞行器沿着飞行器轴线的加速期间将传单的一部分保持在张紧状态。

    FLYER ASSEMBLY
    250.
    发明申请
    FLYER ASSEMBLY 审中-公开
    飞机装配

    公开(公告)号：WO0232762A9

    公开(公告)日：2003-02-20

    申请号：PCT/US0131631

    申请日：2001-10-11

    Applicant: DRAPER LAB CHARLES S

    Inventor： MARTORANA RICHARD T ,  ANDERSON JAMIE ,  SPEARING SIMON MARK ,  KESSLER SETH ,  APPLEBY BRENT ,  BERGMANN EDWARD ,  GEORGE SEAN ,  JACOBSON STEVEN ,  FLYER DONALD ,  DRELA MARK ,  KIRKOS GREGORY ,  MCFARLAND WILLIAM JR

    IPC: B64C39/02 ,  F42B15/10 ,  B64C

    CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

    Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load an high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

    Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单​​。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 机翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高温环境的高负载，并且可以承受大约16,000g的安装载荷。

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