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    UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION
    22.
    发明申请
    UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION 有权
    不定期的空中客车航向转向

    公开(公告)号：US20140172200A1

    公开(公告)日：2014-06-19

    申请号：US14016602

    申请日：2013-09-03

    Applicant: AEROVIRONMENT, INC.

    Inventor： Carlos Miralles

    IPC: B64C13/16

    CPC classification number: B64C13/16 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/165 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  G05D1/12

    Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.

    Abstract translation: 一种包括具有翼元件和尾部元件的无人飞行器（UAV）的系统，其被配置成滚动以通过滚动来成角度地定向UAV，以便在其后期终点阶段将UAV的纵向平面与目标对准。 一种UAV身体重定向的方法，包括：（a）由处理器确定基于身体固定框架的目标点和视轴之间的距离的视轴角度误差校正值; 和（b）实现UAV机动，其包括将目标点平移到身体固定框架中的重定向目标点的角度角色率分量，以经由偏移角度校正值来保持偏移角度。

    Multi-Hybrid Aircraft Engine
    24.
    发明申请
    Multi-Hybrid Aircraft Engine 审中-公开

    公开(公告)号：US20190186418A1

    公开(公告)日：2019-06-20

    申请号：US16326717

    申请日：2017-08-28

    Applicant: Bingham Robert A.

    Inventor： Orlorunfemi Jacob Azundah

    IPC: F02K5/00 ,  B64D27/24 ,  B64D27/16

    CPC classification number: F02K5/00 ,  B64C2201/04 ,  B64D27/16 ,  B64D27/24 ,  B64D2027/026 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/4031

    Abstract: A multi-hybrid aircraft engine that includes a primary compressor 1, a multiplier 199 comprising a drive block, a driven block, driven block pistons 54, and primary shafts 78 and 41; an output shaft 105, and a speed regulator 167. The multi-hybrid aircraft engine is configured such that the primary compressor 1 is fluidly connected to the drive block 46 which is mechanically connected to the driven block 57. The primary compressor 1 pumps compressible fluid to the drive block 46 through the speed regulator 167 to drive the drive block 46, which in turn, drives the primary shafts 78 and 41. The primary shafts 78 and 41 drive the driven block 57, which pumps fluid via the driven block pistons 54, to the drive block 46 through the speed regulator 167 to increase the flow rate of compressible fluid within the multi-hybrid aircraft engine. Furthermore, the driven block 57 provides a shaft 68 that is connected to sets of planetary gears 62 connected to an output shaft 105 that drives a propeller 186.

    ROTARY-WING VEHICLE AND SYSTEM
    26.
    发明申请
    ROTARY-WING VEHICLE AND SYSTEM 审中-公开

    公开(公告)号：US20170247107A1

    公开(公告)日：2017-08-31

    申请号：US15056408

    申请日：2016-02-29

    Applicant: GeoScout, Inc.

    Inventor： Istvan Hauer ,  Cyril Blank ,  Allan Vaitses

    IPC: B64C39/02 ,  B64C27/12 ,  B64D35/06 ,  B64C27/08

    CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C27/12 ,  B64C2201/027 ,  B64C2201/04 ,  B64C2201/108 ,  B64C2201/14 ,  B64D35/06

    Abstract: An apparatus comprising a body defining a first vertical axis, two or more frame members each having a longitudinal axis and having an inner-end and an outer-end connected to the body at the inner-end and where a first horizontal geometrical plane is generally coincident with the longitudinal axis of each of the two or more frame members and where the first horizontal geometrical plane is generally orthogonal to the first vertical axis, two or more rotary-wings each comprising one or more blades whose rotation defines a first rotational axis which is configurable to be nearly parallel with the first vertical axis and comprising a second rotational axis which is configurable to be approximately parallel first horizontal geometrical plane where a first of the two or more rotary-wings having a blade-inner-end and a first blade-outer-end rotatably connected by its blade-inner-end to a first transmission is disposed substantially on the outer-end of a first of the two or more frame members, a second of the two or more rotary-wings having a blade-inner-end and a blade-outer-end rotatably connected by its blade-inner-end to a second transmission is disposed substantially on the outer-end of a second of the two or more frame members, where each of the first rotational axes is disposed on the opposite side of plane which is coincident with the first vertical axis, where the direction of rotation of a first of the two or more rotary-wings about its first rotational axis is opposite of that of the second of the two or more rotary-wings about its first rotational axis, and, where the rotational disk defined by the rotation of the blade-outer-end of the first of the two or more rotary-wings is at least partially coincident with rotational disk defined by the rotation of the blade-outer-end of the second of the two or more rotary-wings.

    Long range hybrid electric airplane
    28.
    发明申请
    Long range hybrid electric airplane 审中-公开
    长距离混合电动飞机

    公开(公告)号：US20080184906A1

    公开(公告)日：2008-08-07

    申请号：US11703362

    申请日：2007-02-07

    Applicant: Joseph B. Kejha

    Inventor： Joseph B. Kejha

    IPC: B64C11/00 ,  F42B15/00

    CPC classification number: B64D27/24 ,  B64C39/024 ,  B64C2201/04 ,  B64D27/02 ,  B64D2027/026 ,  Y02T50/64 ,  Y02T90/44

    Abstract: An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe.

    Abstract translation: 一种先进的内燃电动混合动力飞机，其飞行范围和飞行时间至少比传统等效飞机的两倍，同时使用相同数量的任何所需的燃料。 这是通过使用2-3x小型超轻型发动机进行巡航，并且在起飞和爬升期间由锂电池供电的超轻型电动机实现。 电动马达在巡航和下降期间成为发电机，对所述电池进行充电。 飞机还具有暂时的静电隐身能力，并通过电动备用电源增加安全性。 由于其高效率，操作成本大大降低。 附加功能包括高度先进的，最小的阻力和重量的机身。

    マルチロータ航空機
    29.
    发明专利
    マルチロータ航空機 审中-公开

    公开(公告)号：JP2017533863A

    公开(公告)日：2017-11-16

    申请号：JP2017543702

    申请日：2015-10-28

    Applicant: アーセーセー イノヴァチオン アーベー ,  アーセーセー イノヴァチオン アーベー

    Inventor： アンダース ユング ,  アンダース ユング

    IPC: B64D35/04 ,  B64C29/00 ,  B64C39/02

    CPC classification number: B64D35/04 ,  A63H27/12 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/04 ,  B64C2201/06 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64D37/00

    Abstract: マルチロータ航空機(1、1’、1''、1'''、1''''、1'''''、1'''''')は、少なくとも三つの油圧モータ(11、21、31)と、それぞれが前記少なくとも三つの油圧モータ(11、21、31)の一つにより回転可能な少なくとも三つのロータ(10、20、30)と、少なくとも一つのパワーユニット(2)と、それぞれが前記少なくとも三つの油圧モータ(11、21、31)の一つに加圧流体を供給して駆動することにより前記少なくとも三つのロータ(10、20、30)の一つを回転させるための少なくとも三つの第一油圧ポンプ(12、22、32)と、前記少なくとも三つの油圧モータ(11、21、31)へ分配される加圧流体の流れを変更することによって、前記マルチロータ航空機の動作制御を行なう制御ユニット(6)とを備えている。前記少なくとも三つの油圧ポンプ(12、22、32)から前記少なくとも三つの油圧モータ(11、21、31)への加圧流体の流れのそれぞれを制御する少なくとも一つの制御弁(13、23、33)によって、前記少なくとも三つの油圧モータ(11、21、31)へ分配される加圧流体の流れが個別に制御可能である。【選択図】図2

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