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    Winged multi-rotor flying craft with payload accomodating shifting structure and automatic payload delivery
    44.
    发明授权
    Winged multi-rotor flying craft with payload accomodating shifting structure and automatic payload delivery 有权

    公开(公告)号：US09714087B2

    公开(公告)日：2017-07-25

    申请号：US14583388

    申请日：2014-12-26

    Applicant: Hari Matsuda

    Inventor： Hari Matsuda

    IPC: B64C29/02 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/141

    Abstract: A vertical takeoff/landing capable, multi-engine aircraft with an airfoil without elevator or rudder surfaces is provided. Strut apertures accommodate vertical and horizontal translation of the airfoil in reference to engine supporting struts which are disposed through the apertures, opposite ends of the struts extending to opposite sides of the airfoil, wherein the struts are adjustably attached to the airfoil. A first and second plurality of engines are attached to ends of the struts, an attachment position of the plurality of engines to the struts is horizontally adjustable. A computerized engine controller, controls thrusts of the engines, to enable the aircraft to vertically lift off/land and re-orient itself to horizontally fly, and perform thrust-initiated elevator and rudder emulating flight. An external payload-to-delivery mating mechanism is attached to the bottom of the payload, which mates to a pole leading to the payload receptacle. Transceivers facilitate precise transfer of the payload.

    SYSTEM AND METHOD FOR FLYING TRUCKS
    46.
    发明申请
    SYSTEM AND METHOD FOR FLYING TRUCKS 审中-公开
    用于飞行卡车的系统和方法

    公开(公告)号：US20160318609A1

    公开(公告)日：2016-11-03

    申请号：US15144708

    申请日：2016-05-02

    Applicant: Other Lab, LLC

    Inventor： Peter Sturt Lynn ,  Becker van Niekerk ,  Saul Thomas Griffith

    IPC: B64D9/00 ,  B64C29/00 ,  B64C3/56 ,  B64C39/10 ,  B64C39/06 ,  B64C3/16 ,  B64C39/02 ,  B64D1/22

    CPC classification number: B64C3/16 ,  B64C3/56 ,  B64C27/20 ,  B64C29/0033 ,  B64C39/024 ,  B64C39/06 ,  B64C39/062 ,  B64C39/066 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/108 ,  B64C2201/128 ,  B64D1/22 ,  Y02T50/12

    Abstract: A tethered wing comprising an aerodynamic wing body defining external and internal faces and a plurality of rotors disposed on the wing body. The tether wing can further include a tether configured to extend and retract. The tethered wing can be configured to perform a payload pickup maneuver that includes coupling the tether to a payload with the tether in an extended configuration, taking off in a vertical flight configuration proximate to the tethered payload, transitioning to a horizontal flight configuration over the tethered payload and circling and ascending over the tethered payload to lift the tethered payload into the air via the tether.

    Abstract translation: 一种拴翼，其包括限定外表面和内表面的空气动力学翼体和设置在翼体上的多个转子。 系绳翼还可以包括构造成延伸和缩回的系绳。 拴系机翼可以被配置为执行有效载荷拾取操作，其包括将系绳耦合到具有扩展配置的系绳的有效载荷，在垂直飞行配置中靠近有束缚的有效载荷起飞，转换到拴系的水平飞行配置 有效载荷并盘旋并在有系统的有效载荷上升起，以将系留的有效载荷通过系绳提升到空气中。

    Aerial vehicle with separation of winged surfaces in first and second flexed states
    48.
    发明授权
    Aerial vehicle with separation of winged surfaces in first and second flexed states 有权
    在第一和第二弯曲状态下分离有翼表面的飞行器

    公开(公告)号：US09296468B1

    公开(公告)日：2016-03-29

    申请号：US14032800

    申请日：2013-09-20

    Applicant: Brandebury Tool Company, Inc.

    Inventor： William B. Harvey ,  Matthew G. Amsellem

    IPC: B64C3/40 ,  B64C39/02

    CPC classification number: B64C3/40 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/102

    Abstract: Embodiments include an aerial vehicle. Two winged surfaces are provided in communication with a fuselage. The surfaces are in communication at a front edge via a cuff, at a midsection via a first resilient member, and at a trailing edge via a second resilient member. As the aerial vehicle is in flight, it is subject to loads. The connections of the surfaces provides flexibility and resiliency to maintain the surfaces in communication with the fuselage and to allow regulated separation of the winged surfaces at their rear edges in a first direction in a first flexed state and at their front edges in a second direction, different from the first direction, in a second flexed state.

    Abstract translation: 实施例包括飞行器。 提供与机身连通的两个翼状表面。 这些表面经由袖带在前边缘处经由第一弹性构件在中间连接，并且在后缘处经由第二弹性构件连通。 当飞行器在飞行中时，它将受到负载的影响。 表面的连接提供了灵活性和弹性，以保持与机身连通的表面，并且允许翼形表面在其后边缘处以第一弯曲状态的第一方向和在其第二方向的前边缘处被调节分离， 与第一方向不同，处于第二弯曲状态。

    Multi-Role Aircraft With Interchangeable Mission Modules
    49.
    发明申请
    Multi-Role Aircraft With Interchangeable Mission Modules 审中-公开
    具有可互换任务模块的多角色飞机

    公开(公告)号：US20160075423A1

    公开(公告)日：2016-03-17

    申请号：US14951358

    申请日：2015-11-24

    Applicant: Abe Karem

    Inventor： Abe Karem

    IPC: B64C1/00 ,  B64C25/10 ,  B64C39/10 ,  B64C3/56 ,  B64C1/06

    CPC classification number: B64C39/10 ,  B64C1/00 ,  B64C1/0009 ,  B64C1/061 ,  B64C1/065 ,  B64C1/26 ,  B64C3/56 ,  B64C25/10 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/126 ,  B64C2211/00 ,  B64D37/00 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/43

    Abstract: A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

    Abstract translation: 飞行可操作的，真正模块化的飞机具有飞行器核心，一个或多个外翼构件，机身，驾驶舱，前后联轴器，尾翼和尾翼部分可在其运行寿命期间可拆卸地联接和/或更换 的飞机。 在优选实施例中，飞机核心容纳推进发动机，航空电子设备，至少80％的燃料和所有起落架。 飞机核心优选地构造有弯曲的前向和后部复合翼梁，其在中心部分处传递载荷，同时容纳中翼构造。 飞机核心优选地具有大的中心空间，其大小可互换地携带军械发射器，监视有效载荷，电子对抗措施和其他类型的货物。 考虑的飞机可能相当大，例如具有至少80英尺的翼展。

    Long endurance aircraft
    50.
    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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