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    UNMANNED AERIAL VEHICLE HAVING AN IMPROVED AERODYNAMIC CONFIGURATION
    141.
    发明申请
    UNMANNED AERIAL VEHICLE HAVING AN IMPROVED AERODYNAMIC CONFIGURATION 有权
    具有改进的航空配置的无人驾驶的空中客车

    公开(公告)号：US20110248123A1

    公开(公告)日：2011-10-13

    申请号：US13140233

    申请日：2009-12-01

    Applicant: Abraham Abershitz

    Inventor： Abraham Abershitz

    IPC: B64C39/02 ,  B64C39/10 ,  B64C5/00

    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。

    MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED THRUST CONTROL
    143.
    发明申请
    MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED THRUST CONTROL 有权
    具有显着控制的模块化MINIATURE UNMANNED飞机

    公开(公告)号：US20110057074A1

    公开(公告)日：2011-03-10

    申请号：US12556225

    申请日：2009-09-09

    Applicant: Adam Woodworth ,  Brandon Suarez

    Inventor： Adam Woodworth ,  Brandon Suarez

    IPC: G05D1/00 ,  B64C13/00

    CPC classification number: B64C15/00 ,  B64C29/0033 ,  B64C39/02 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2211/00

    Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

    Abstract translation: 描述了一种无人驾驶飞机。 飞机包括机身，连接到机身后部的一对翅片，连接到机身底部的一对二面支架，第一推力矢量模块和第二推力矢量模块以及电子模块。 电子模块向两个推力矢量模块提供命令。 两个推力矢量模块被配置为通过直接控制飞行器的俯仰，滚动和偏航中的每一个的推力矢量来向飞行器提供侧向和纵向控制。 使用直接铰接的电动机作为推力矢量模块使飞机能够在宽范围的空速下执行紧半径的转弯。

    FLYING-WING AIRCRAFT
    144.
    发明申请
    FLYING-WING AIRCRAFT 有权
    飞行飞机

    公开(公告)号：US20110001001A1

    公开(公告)日：2011-01-06

    申请号：US12865429

    申请日：2009-02-02

    Applicant: Ashley Christopher Bryant

    Inventor： Ashley Christopher Bryant

    IPC: B64C29/00 ,  B64C39/10

    CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

    Abstract: A vertical take-off and landing (VTOL) flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms (56) are employed, the arms (56) of fore and aft propulsion units (52,54; 53,55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51 ; 78) may have fins (47;84), slats (81) and flaps (82) and other aerodynamic control-surfaces, and enlarged strakes (84) may incorporate rudder surfaces (80). Only one propulsion unit (21) may be mounted at each extremity and additional fan units (48,83) may be used.

    Abstract translation: 垂直起降（VTOL）飞翼飞机具有一对推进矢量推进单元（2,3; 4,5），其安装在飞行器俯仰轴线（PA）的前后，位于横梁（6,7） ）在机翼结构（1）的相对两端，前部单元（2; 4）和下方的后部单元（3; 5），机翼结构（1）。 推进单元（2-5）直接地或经由臂（56）枢转到斜面（6,7），用于单独的角位移，用于偏航，俯仰和滚动中的推进向导操纵的飞行器，并且用于悬停和 向前和向后飞行 当使用臂（56）时，前后推进单元（52,54; 53,55）的臂（56）通过链条驱动器（57-60）或连杆（61）相互配合。 机翼结构（1; 51; 78）可以具有翅片（47; 84），板条（81）和翼片（82）和其它空气动力学控制表面，并且扩大的横条（84）可以包括舵表面（80）。 每个末端只安装一个推进单元（21），并且可以使用附加的风扇单元（48,83）。

    Aerial vehicle with variable aspect ratio deployable wings
    145.
    发明申请
    Aerial vehicle with variable aspect ratio deployable wings 有权
    具有可变纵横比可展翅的飞行器

    公开(公告)号：US20100282917A1

    公开(公告)日：2010-11-11

    申请号：US11707088

    申请日：2007-02-16

    Applicant: Hank O'Shea

    Inventor： Hank O'Shea

    IPC: B64C3/54 ,  B64C3/56

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/102

    Abstract: Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.

    Abstract translation: 本发明的实施例涉及用于配置以调整响应于飞行任务参数车辆纵横比的飞行器的机翼结构。 机翼装置可以包括一对能够在部署到第一翅位置限定第一长宽比的翼组件。 每个翼组件可以具有一个向前内侧机翼枢转地连接到机身和后部内侧机翼枢转地连接到托架上。 前向内侧机翼和每个组件的后部内侧机翼可以连接，形成一个双平面结构。 另外，所述各组件可以包括一组翼外侧配置从内侧翼伸缩到伸出位置翅限定第二纵横比大于第一纵横比更大的。

    ANNULAR AIRBORNE VEHICLE
    147.
    发明申请
    ANNULAR AIRBORNE VEHICLE 有权

    公开(公告)号：US20100044496A1

    公开(公告)日：2010-02-25

    申请号：US12594719

    申请日：2008-04-16

    Applicant: Harry George Dennis Gosling

    Inventor： Harry George Dennis Gosling

    IPC: B64C15/12 ,  B64C9/00

    CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

    Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis. A direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device and/or a magnitude of thrust of the first propulsion device can be adjusted independently of the magnitude of thrust of the second propulsion device. In certain embodiments the wing-body appears swept forward when viewed from a first viewing angle, and swept backward when viewed from a second viewing position at right angles to the first viewing angle.

    Abstract translation: 一种机载车辆，其具有限定翼体轴线的翼体，并且当沿翼体轴线观察时呈现大致环形，所述环形空间的内部限定在两端敞开的管道。 提供了包括一对或多对推进装置的推进系统，每对推进装置包括安装到翼体上并定位在包括翼体轴线的平面的第一侧上的第一推进装置，以及安装到 翼体并且定位在包括翼体轴线的平面的第二侧上。 可以独立于第二推进装置的推力方向来调节第一推进装置的推力方向，和/或可以独立于第二推进装置的推力的大小来调节第一推进装置的推力的大小。 在某些实施例中，当从第一视角观察时，翼体呈向前扫掠，并且当从与第一视角成直角的第二观察位置观看时向后扫掠。

    SYSTEMS AND METHODS FOR CAPTURING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT
    148.
    发明申请
    SYSTEMS AND METHODS FOR CAPTURING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT 有权
    用于捕获和控制未经规定的飞机的恢复后运动的系统和方法

    公开(公告)号：US20100025528A1

    公开(公告)日：2010-02-04

    申请号：US11775600

    申请日：2007-07-10

    Applicant: Clifford Jackson

    Inventor： Clifford Jackson

    IPC: B64F1/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/165 ,  B64C2201/182

    Abstract: Systems and methods for capturing and controlling post-recovery motion of an unmanned aircraft are disclosed herein. An aircraft system in accordance with one embodiment of the invention, for example, can include a line capture assembly carried by an unmanned aircraft having a fuselage and a lifting surface. The line capture assembly can include a flexible support line having a first portion attached to an attachment point on the fuselage and a second portion extending from the attachment point spanwise along the lifting surface of the aircraft. The line capture assembly can also include an engagement device coupled to the second portion of the support line. The engagement device is releasably secured to the lifting surface.

    Abstract translation: 本文公开了用于捕获和控制无人飞行器的恢复后运动的系统和方法。 例如，根据本发明的一个实施例的飞行器系统可以包括由具有机身和提升表面的无人飞行器承载的线捕获组件。 线捕获组件可以包括柔性支撑线，其具有附接到机身上的附接点的第一部分和从飞行器的提升表面沿着方向从附接点延伸的第二部分。 线捕获组件还可以包括联接到支撑线的第二部分的接合装置。 接合装置可释放地固定到提升表面。

    Unmanned aerial vehicle and launch assembly
    150.
    发明授权
    Unmanned aerial vehicle and launch assembly 有权
    无人机和发射组件

    公开(公告)号：US07556219B2

    公开(公告)日：2009-07-07

    申请号：US11064287

    申请日：2005-02-22

    Applicant: Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

    Inventor： Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

    IPC: B64F1/04

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/165 ,  B64C2201/201

    Abstract: An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container. In a second configuration, a launch assembly is provided, that includes an elastic tether connecting a UAV to an accelerated mass for gentle acceleration to flight speed under a stable tow.

    Abstract translation: 提供无人驾驶飞行器（UAV），使用和制造具有成本效益，并且包括低数量的部件，允许任务规划人员以一次性方式使用无人机。 无人机包括具有中心体的机身和从中心体延伸的翼，限定内腔。 机身包括一个上部和下部壳体，每个都由整体塑料构成。 上壳体和下壳体之间具有限定了堆叠构造的燃料箱和有效载荷的壁。 机身还可以包括配置成包围有效载荷舱并有助于机身的中心主体的有效载荷盖。 还提供发射组件。 在第一配置中，提供了一种发射组件，其包括用于容纳多个UAV的容器和启动无人机从容器的快速喷射的展开机构。 在第二构造中，提供了一种发射组件，其包括将UAV连接到加速质量块的弹性系绳，以在稳定的丝束下平缓加速到飞行速度。

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