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    Unmanned aerial vehicle
    55.
    发明授权
    Unmanned aerial vehicle 有权
    无人驾驶的航空机

    公开(公告)号：US09452820B1

    公开(公告)日：2016-09-27

    申请号：US14924304

    申请日：2015-10-27

    Applicant: Wirth Research Limited

    Inventor： Nicholas J. P. Wirth

    IPC: B64C3/56 ,  B64C3/16 ,  B64C39/02

    CPC classification number: B64C3/56 ,  B64C3/16 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/201

    Abstract: An unmanned aerial vehicle 2 comprising: a fuselage 4; and a wing 6 comprising a central wing section 12 pivotably mounted to the fuselage 4 and a pair of outer wing sections 14a, 14b pivotably mounted to the central wing section 12; wherein the wing 6 has a folded configuration in which the central wing section 12 and the outer wing sections 14a, 14b are stacked on top of one another and are aligned with a longitudinal axis of the fuselage 4; and a deployed configuration in which the central wing section 12 is substantially perpendicular to the fuselage 4 and the outer wing sections 14a, 14b extend from the central wing section 12 away from the fuselage 4.

    Abstract translation: 一种无人驾驶飞行器2，包括：机身4; 以及机翼6，其包括可枢转地安装到机身4的中心翼部分12和可枢转地安装到中心翼部分12的一对外翼部分14a，14b; 其中翼6具有折叠构造，其中中心翼部12和外翼部14a，14b彼此堆叠并且与机身4的纵向轴线对准; 以及中央翼部12基本上垂直于机身4并且外翼部14a，14b从中心翼部12远离机身4延伸的展开构造。

    Controlled Take-Off And Flight System Using Thrust Differentials
    56.
    发明申请
    Controlled Take-Off And Flight System Using Thrust Differentials 审中-公开
    使用推力差速控制起飞和飞行系统

    公开(公告)号：US20160244159A1

    公开(公告)日：2016-08-25

    申请号：US14862134

    申请日：2015-09-22

    Applicant: Transition Robotics, Inc.

    Inventor： JoeBen Bevirt

    IPC: B64C29/02 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C15/00 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/02 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

    Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in least two dimensions relative to the horizontal during takeoff. An aerial vehicle which uses a rotating platform of engines in fixed relationship to each other and which rotates relative to the wings of the vehicle for takeoff and landing.

    Abstract translation: 一种适用于垂直起飞和着陆的载人/无人机，使用相同的发动机起飞和着陆以及向前飞行。 一种飞行器，其适于在垂直方向上与翼起飞，而不是水平飞行姿态，以垂直姿态起飞，然后转变到水平飞行路径。 一种飞行器，其通过交替发动机的推力来控制起飞和着陆期间车辆的姿态，发动机的推力在起飞期间相对于水平线至少二维分开。 一种飞行器，其使用彼此固定关系并且相对于车辆的翼部旋转以便起飞和着陆的发动机的旋转平台。

    Modular articulated-wing aircraft
    57.
    发明授权
    Modular articulated-wing aircraft 有权
    模块化铰接翼飞机

    公开(公告)号：US09387926B2

    公开(公告)日：2016-07-12

    申请号：US13154796

    申请日：2011-06-07

    Applicant: Geoffrey S. Sommer

    Inventor： Geoffrey S. Sommer

    IPC: B64D5/00 ,  B64C39/02 ,  B64C37/02

    CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

    Abstract: Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

    Abstract translation: 提供了用于形成具有高纵横比翼平台的多关节飞行系统（天基）的系统和/或方法，其可操作以在高海拔地区的感兴趣区域上游荡。 在某些示例性实施例中，自主模块化飞行器以翼尖到翼尖的方式连接在一起。 这样的模块化飞行器可以从日晒中获得其功率。 自主传单可以包括单独操作的传感器，或者在形成天空基础之后集体运行。 天空基优选地可以按照主要条件的要求进行聚合，分解和/或再聚集。 因此，可能提供“永远在车”的飞机。

    TILT-BALL TURRET WITH GIMBAL LOCK AVOIDANCE
    58.
    发明申请
    TILT-BALL TURRET WITH GIMBAL LOCK AVOIDANCE 审中-公开
    TILT-BALL TURRET与GIMBAL LOCK AVOIDANCE

    公开(公告)号：US20160194092A1

    公开(公告)日：2016-07-07

    申请号：US14880073

    申请日：2015-10-09

    Applicant: AeroVironment, Inc.

    Inventor： Thomas SZAREK ,  Thomas OMER ,  Manolis Pavlos DIMOTAKIS ,  Jefferson C. McBRIDE

    IPC: B64D47/08 ,  H04N7/18 ,  B64C39/02

    CPC classification number: B64D47/08 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/123 ,  B64C2201/127 ,  F16M11/123 ,  F16M11/126 ,  F16M11/18 ,  H04N7/183

    Abstract: A turret assembly for attachment on the undersurface of an aircraft that reduces performance limitations due to gimbal lock and reduces the cross section profile of the assembly. The assembly includes a roll actuator including a drive shaft. A yoke having a cross member is coupled to the drive shaft and a pair of prongs. The yoke is rotated via the roll actuator and drive shaft along a roll axis oriented substantially parallel to the body of the aircraft. A turret is mounted on the prongs of the yoke. A tilt actuator is contained within the turret. The tilt actuator tilts the turret on a tilt axis relative to the yoke. The tilt axis is perpendicular to the roll axis.

    Abstract translation: 一种用于附接在飞行器下表面上的转塔组件，其减小由于万向节锁定而导致的性能限制并减小组件的横截面轮廓。 组件包括具有驱动轴的辊致动器。 具有横向构件的轭联接到驱动轴和一对插脚。 轭架通过辊子致动器和驱动轴沿着基本平行于飞行器主体的辊轴线旋转。 一个转塔安装在轭的叉子上。 转塔内装有一个倾斜致动器。 倾斜致动器相对于轭架在倾斜轴上倾斜转台。 倾斜轴垂直于辊轴。

    CONVERTIPLANE WITH NEW AERODYNAMIC AND TECHNICAL SOLUTIONS WHICH MAKE THEAIRCRAFT SAFE AND USABLE
    59.
    发明申请
    CONVERTIPLANE WITH NEW AERODYNAMIC AND TECHNICAL SOLUTIONS WHICH MAKE THEAIRCRAFT SAFE AND USABLE 有权
    具有新的航空和技术解决方案，使安全可靠的安全

    公开(公告)号：US20160167780A1

    公开(公告)日：2016-06-16

    申请号：US14908850

    申请日：2014-08-07

    Applicant: UNIT 1SRL

    Inventor： Pietro GIOVENGA

    IPC: B64C29/00 ,  B64C39/02 ,  B64C3/54

    CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/08 ,  Y02T50/14

    Abstract: A convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft includes a variable incidence front wing of variable span located below the fuselage and mounted on a structure in the form of a venturi tube, a rear wing having two propellers for controlling the stability of the vehicle in pitch and roll installed therein, two counter-rotating, pivotally mounted ducted propellers equipped with four flaps orthogonal to each other provided on the sides of the cockpit, engines placed behind the cockpit close to the center of gravity, a static balancing system for controlling the center of gravity of the aircraft consisting of a weight placed in the lower part of the fuselage, self-propelled on the track rack longitudinally to the fuselage, and a digital flight control system.

    Abstract translation: 转换飞机具有像直升机一样起飞的能力，然后像常规飞机一样水平飞行。 飞机包括位于机身下方的可变跨度的可变入射前翼，并安装在文丘里管形式的结构上，后翼具有两个螺旋桨，用于控制安装在其中的俯仰和滚动中的车辆的稳定性，两个计数器 旋转的，枢转安装的管道螺旋桨，其配备有四个彼此正交的翼片，设置在驾驶舱的两侧，放置在靠近重心的驾驶舱后面的发动机，用于控制飞行器重心的静态平衡系统， 放置在机身下部的重量，纵向自动推进到机身，以及数字飞行控制系统。

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