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    Deep Stall Aircraft Landing
    151.
    发明申请
    Deep Stall Aircraft Landing 有权
    深停机飞机着陆

    公开(公告)号：US20160163206A1

    公开(公告)日：2016-06-09

    申请号：US14936632

    申请日：2015-11-09

    Applicant: AEROVIRONMENT INC.

    Inventor： Christopher E. Fisher ,  Thomas Robert Szarek ,  Justin B. McAllister ,  Pavel Belik

    IPC: G08G5/02 ,  B64C39/02 ,  G05D1/00

    CPC classification number: G08G5/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/14 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/18 ,  B64D31/00 ,  G05D1/0011 ,  G05D1/0676

    Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.

    Abstract translation: 定义直立方向和倒置方向的飞机，地面站; 以及用于远程控制飞机飞行的控制系统。 地面站具有自动地面功能，使飞机以反方向反转，失速和可控地降落，以保护从飞机向下延伸的有效载荷和舵。 在直立方向，地面站描绘从第一架飞机摄像机的视图。 当切换到倒置方向时：（1）地面站描绘从第二架飞机照相机的视图，（2）飞机切换红色和绿色翼灯的颜色，将副翼延伸为反转翼片，（3） 控制系统适应地面站控制器的倒置方向。 飞机起落架是当飞机处于直立方向时位于机翼上方的扩展的聚丙烯垫。

    RECONFIGURABLE UNMANNED AIRCRAFT SYSTEM
    152.
    发明申请
    RECONFIGURABLE UNMANNED AIRCRAFT SYSTEM 有权
    可重新配置的无人驾驶飞机系统

    公开(公告)号：US20160159472A1

    公开(公告)日：2016-06-09

    申请号：US14639369

    申请日：2015-03-05

    Applicant: Elwha LLC

    Inventor： ALISTAIR K. CHAN ,  JESSE R. CHEATHAM, III ,  HON WAH CHIN ,  WILLIAM DAVID DUNCAN ,  RODERICK A. HYDE ,  MURIEL Y. ISHIKAWA ,  JORDIN T. KARE ,  TONY S. PAN ,  ROBERT C. PETROSKI ,  CLARENCE T. TEGREENE ,  DAVID B. TUCKERMAN ,  THOMAS ALLAN WEAVER ,  LOWELL L. WOOD, JR.

    IPC: B64C27/08 ,  B64C27/37 ,  B64D45/00

    CPC classification number: B64C27/08 ,  B64C13/02 ,  B64C27/37 ,  B64C27/54 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165 ,  B64D1/00 ,  B64D45/00

    Abstract: A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base. A method of configuring an aircraft having a set of rotors on a mission to carry a payload comprises the steps of determining properties of the payload including at least mass properties, determining the manner in which the payload will be coupled to the aircraft, determining configuration for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload, and positioning the set of rotors in the configuration for the aircraft to perform the mission.

    Abstract translation: 公开了一种可重新配置的无人机系统。 还公开了一种用于配置可重新配置的无人驾驶飞行器的系统和方法，以及用于在空域中操作和管理可重新配置的无人飞行器的系统和方法。 该飞机是有选择地可重构的，以修改飞行特性。 飞机包括一组转子。 相对于基座的至少一个转子的位置可以通过转子相对于起重臂的平移，悬臂相对于基座的枢转以及起重臂相对于基座的平移的至少一个来改变。 使得可以通过至少一个转子相对于基座的位置的配置来修改飞行特性。 一种在任务上配置具有一组转子的承载有效载荷的飞行器的方法包括以下步骤：确定所述载荷的属性至少包括质量属性，确定所述有效载荷将与飞行器耦合的方式，确定 转子组中的每个转子至少部分地考虑有效载荷的属性，并将该组转子定位在飞行器的构型中以执行任务。

    Rotary-wing drone with gearless-drive and fast-mounting propellers
    153.
    发明授权
    Rotary-wing drone with gearless-drive and fast-mounting propellers 有权
    带无齿轮驱动和快速安装螺旋桨的旋翼式无人机

    公开(公告)号：US09359070B2

    公开(公告)日：2016-06-07

    申请号：US14539753

    申请日：2014-11-12

    Applicant: PARROT

    Inventor： Christine Caubel

    IPC: B64C27/08 ,  B64C27/48 ,  B64C39/02 ,  A63H27/00

    CPC classification number: B64C27/08 ,  A63H27/12 ,  B64C27/48 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108

    Abstract: Each propulsion unit of the drone comprises a propeller (20) and a rotary-cage synchronous electric motor whose stator is connected to the drone body. The propulsion unit in of the gearless type, the rotor of the motor being rotationally integral with the propeller hub (24). The rotor is integral with an upper flange (56) extending in a radial plane with respect to the axis of rotation. Reversible means are provided for the fast coupling of the propeller to the rotor, implementing studs (62) with an enlarged head (66) formed on the flange, which cooperate with homologous curvilinear buttonholes (32) formed on the hub. The switching from the decoupled position to the locked position is operated by relative rotation of the propeller hub with respect to the flange by a fraction of a turn, in an opposite direction with respect to the direction of rotation of the motor.

    Abstract translation: 无人机的每个推进单元包括螺旋桨（20）和定子连接到无人机体的旋转笼同步电动机。 在无齿轮型的推进单元中，马达的转子与螺旋桨毂（24）旋转地成一体。 转子与在相对于旋转轴线的径向平面中延伸的上凸缘（56）成一体。 提供可逆装置用于螺旋桨与转子的快速联接，实现螺柱（62），其具有形成在凸缘上的扩大的头部（66），其与形成在轮毂上的同源曲线形孔（32）配合。 从解耦位置到锁定位置的切换通过螺旋桨轮毂相对于凸缘相对于马达的旋转方向相反方向相对于凸缘相对转动的方式进行操作。

    Observation Device
    155.
    发明申请
    Observation Device 审中-公开
    观察装置

    公开(公告)号：US20160122018A1

    公开(公告)日：2016-05-05

    申请号：US14925005

    申请日：2015-10-28

    Applicant: DENSO CORPORATION ,  NIPPON SOKEN, INC. ,  THE UNIVERSITY OF TOKYO

    Inventor： Takenori MATSUE ,  Koji KAWASAKI ,  Michihiro MATSUURA ,  Masami KUROSAKA ,  Masayuki INABA

    IPC: B64C39/02 ,  H04N7/18 ,  B64D47/08 ,  G05D1/08

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/141 ,  G05D1/0094 ,  G05D1/0858 ,  H04N7/185

    Abstract: A observation device includes an aircraft and an observation unit attached to the aircraft that observes a target within a predetermined view angle. The aircraft includes a base, at least two thrusters that generate a propulsion force including lift, actuators that change a direction of the propulsion force generated by the thrusters with respect to the base, an inertial measurement unit (IMU) that detects an orientation of the base with respect to a ground surface, and a controller that controls the thrusters and the actuators based on the orientation of the base detected by the IMU. The observation unit is fixedly attached to the base and the aircraft is configured to fly in any arbitrary orientation with respect to the ground surface through a combination of a magnitude of the propulsion force and the direction of the propulsion force of each of the thrusters.

    Abstract translation: 观察装置包括飞机和观察单元，其附接到在预定视角内观察目标的飞行器。 飞行器包括基座，至少两个产生包括升力的推进力的推进器，改变由推进器相对于基座产生的推进力的方向的致动器;惯性测量单元（IMU），其检测 基于相对于地面的基座，以及控制器，其基于由IMU检测到的基座的取向来控制推进器和致动器。 观察单元固定地附接到基座，并且飞行器被构造成通过推进力的大小和每个推进器的推进力方向的组合相对于地面以任何方向飞行。

    ROTARY PROPELLER DRONE WITH INTEGRATED POWER STORAGE
    156.
    发明申请
    ROTARY PROPELLER DRONE WITH INTEGRATED POWER STORAGE 审中-公开
    旋转螺旋桨与集成电力存储

    公开(公告)号：US20160068266A1

    公开(公告)日：2016-03-10

    申请号：US14632106

    申请日：2015-02-26

    Applicant: David W. Carroll

    Inventor： David W. Carroll

    IPC: B64C39/02 ,  B64D35/02

    CPC classification number: B64C39/024 ,  B64C11/20 ,  B64C2201/042 ,  B64C2201/108 ,  B64D27/24 ,  B64D35/02 ,  Y02T50/44 ,  Y02T50/62

    Abstract: An electrically powered unmanned aircraft system (UAS or drone) including a propeller including a core formed by battery material layers as a power source and integrated as a structural component of the drone. The battery material layers can be a graphene super capacitor or a nanopore battery structure. Power available from the integrated battery material layers can be used to power an electric motor included with the drone and operating to rotate the propeller.

    Abstract translation: 一种电动无人飞行器系统（UAS或无人机），其包括螺旋桨，其包括由作为动力源的电池材料层形成的芯体并且被集成为无人机的结构部件。 电池材料层可以是石墨烯超级电容器或纳米孔电池结构。 可从集成电池材料层获得的功率可用于为无人机所附带的电动机提供动力并操作以旋转螺旋桨。

    Long endurance aircraft
    157.
    发明授权
    Long endurance aircraft 有权
    长耐力飞机

    公开(公告)号：US09272783B2

    公开(公告)日：2016-03-01

    申请号：US12058520

    申请日：2008-03-28

    Applicant: Jerome Pearson

    Inventor： Jerome Pearson

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102

    Abstract: A long endurance powered aircraft includes a fuselage, a propeller coupled to the fuselage, a wing coupled to the fuselage, and an energy storage system disposed within the fuselage. The wing includes an adjustable surface area including solar cells configured to collect incident solar energy and convert the collected incident solar energy to electrical energy for powering the aircraft during daylight flight. The energy storage system is configured to convert excess electrical energy converted from collected incident solar energy to chemical energy, store the chemical energy, and convert the stored chemical energy to electrical energy for powering the aircraft during night flight.

    Abstract translation: 长寿命动力飞机包括机身，与机身相连的螺旋桨，与机身相连的机翼，以及设置在机身内的能量存储系统。 机翼包括可调节的表面区域，包括被配置为收集入射的太阳能并且将收集的入射太阳能转换成电能的太阳能电池，以在日间飞行期间为飞机供电。 能量存储系统被配置为将从收集的入射太阳能转换的过量电能转换成化学能，存储化学能，并将存储的化学能转换成电能，以在夜间飞行期间为飞行器供电。

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