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    Aerial vehicle with separation of winged surfaces in first and second flexed states
    172.
    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
    173.
    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
    174.
    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。

    Hybrid Axial/Cross-Flow Fan Multi-Rotor Aerial Vehicle
    177.
    发明申请
    Hybrid Axial/Cross-Flow Fan Multi-Rotor Aerial Vehicle 有权
    混合轴向/横流风扇多转子飞行器

    公开(公告)号：US20160009387A1

    公开(公告)日：2016-01-14

    申请号：US14689443

    申请日：2015-04-17

    Applicant: Propulsive Wing, LLC

    Inventor： Joseph Kummer ,  Jimmie B. Allred, III

    IPC: B64C27/20 ,  B64C11/00 ,  B64C11/46 ,  B64C27/26

    CPC classification number: B64C29/0025 ,  B64C29/0066 ,  B64C29/0083 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  Y02T50/12

    Abstract: A hybrid axial/cross-flow fan aerial vehicle includes both axial and cross-flow fan propulsion for efficient hover and forward flight performance. The axial fans provide primarily vertical thrust, while the cross-flow fan provides horizontal, as well as vertical, thrust. The vehicle takes off vertically, is capable of hover, and can fly forward by vectoring the thrust of the cross-flow fan system. This approach provides large internal cargo capacity and high forward flight speeds.

    Abstract translation: 混合轴向/横流风扇航空器包括轴向和横流风扇推进，用于高效悬停和前进飞行性能。 轴流风扇主要提供垂直推力，而横流风扇提供水平和垂直推力。 车辆垂直起飞，可以悬停，并且可以通过向量来推动横流风扇系统的推力飞行。 这种方法提供了大的内部货物能力和高的前进飞行速度。

    Thrust Plane Orientation Device
    179.
    发明申请
    Thrust Plane Orientation Device 审中-公开
    推力平面定向装置

    公开(公告)号：US20150251749A1

    公开(公告)日：2015-09-10

    申请号：US14641294

    申请日：2015-03-06

    Applicant: Paul Edward Sherman

    Inventor： Paul Edward Sherman

    IPC: B64C15/02 ,  B64C13/00 ,  B64C1/00

    CPC classification number: B64C3/385 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/028

    Abstract: The Primary Plane Orientation Device may be orientated such that the lifting surface, and or propulsion group of the aerial vehicle rotates about an axis through the Primary Plane. The Primary Plane, then, may be orientated at any chosen angular offset from the vehicle axis such that the lifting surfaces can produce thrust at said angle to the vehicle axis. The orientation of the Primary plane may then smoothly transform to other desired angles such that the aerial vehicle remains unstalled during conversion between VTOL-rotary and fixed wing flight. The lifting surface, and/or propulsion groups may then be fixed in any orientation to the axis of the vehicle to produce fixed wing lift, or propulsion in line with the fuselage or at various offsets from the fuselage.

    Abstract translation: 主平面定向装置可以被定向成使得飞行器的提升表面和/或推进组围绕通过主平面的轴线旋转。 然后，主平面可以定位在与车辆轴线的任何选定的角度偏移处，使得提升表面可以以与车辆轴线成所述角度产生推力。 然后，主平面的方向可以平滑地转换到其它期望的角度，使得空中飞行器在垂直旋转和固定翼飞行之间的转换期间保持未安装。 提升表面和/或推进组然后可以以任何方向固定到车辆的轴线，以产生固定翼升降机，或与机身一致的推进或与机身的各种偏移。

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