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    PROPELLER
    83.
    发明申请
    PROPELLER 有权
    螺旋桨

    公开(公告)号：US20160159458A1

    公开(公告)日：2016-06-09

    申请号：US14560964

    申请日：2014-12-04

    Applicant: JONATHON J. LINCH ,  Kyle M. Rahrig

    Inventor： JONATHON J. LINCH ,  Kyle M. Rahrig

    IPC: B64C11/00 ,  B64C11/08 ,  B64C11/18

    CPC classification number: B64C11/001 ,  B64C11/08 ,  B64C11/18 ,  B64C39/024 ,  B64C39/10 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/162 ,  B64C2220/00 ,  Y02T50/12

    Abstract: A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. At least one propeller blade is fixedly attached to both the hub and ring shroud and extends radially therebetween for mutual rotation therewith. At least one stub blade has a first stub end radially spaced from a second stub end. The first stub end is fixedly attached to a selected one of the hub and ring shroud. The second stub end is cantilevered from the first stub end and is radially interposed between the first stub end and the selected one of the hub and ring shroud.

    Abstract translation: 螺旋桨包括同轴地围绕纵向轴线的轮毂。 环形护罩同轴地围绕纵向轴线并与轮毂径向间隔开。 至少一个螺旋桨叶片固定地附接到轮毂和环形护罩上并且在其间径向延伸以与其相互旋转。 至少一个短刀片具有与第二短截线径向间隔开的第一短截线端。 第一短截线端部固定地连接到轮毂和环形护罩中的所选择的一个。 第二短截线端部从第一短截线端部悬臂，并且径向插入在第一短截线端与轮毂和环形护罩中选定的一个之间。

    SOLAR POWERED AIRPLANE
    84.
    发明申请
    SOLAR POWERED AIRPLANE 审中-公开
    太阳能动力飞机

    公开(公告)号：US20160144969A1

    公开(公告)日：2016-05-26

    申请号：US14283149

    申请日：2014-05-20

    Applicant: The Boeing Company

    Inventor： Blaine Knight Rawdon ,  Aaron J. Kutzmann

    IPC: B64D27/24 ,  B64C23/06 ,  B64C3/18

    CPC classification number: B64D27/24 ,  B64C3/185 ,  B64C23/069 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2211/00 ,  B64D2211/00 ,  Y02T50/164 ,  Y02T50/55

    Abstract: A solar powered aircraft including a modular main wing and a pair of relatively large modular winglets attached to the transverse end portions of the main wing. To collect solar radiation, including relatively low-angle radiation, solar panels are mounted to both the main wing and the winglets. In some embodiments, the aspect ratio of the main wing is relatively low, such as between 9 and 15, i.e., the main wing is relatively deep compared to its wing span. In some embodiments, the winglets are relatively long, such as in the range of 0.2 to 0.7 times the length of the main wing semi-span. In some embodiments, a truss-like spar passes through and helps support the wing and the winglets.

    Abstract translation: 一种太阳能飞机，其包括模块化主翼和连接到主翼的横向端部的一对相对较大的模块化小翼。 为了收集太阳辐射，包括相对低角度的辐射，太阳能电池板安装在主翼和小翼上。 在一些实施例中，主翼的纵横比相对较低，例如在9和15之间，即主翼与其翼跨相比相对较深。 在一些实施例中，小翼片相对较长，例如在主翼半跨的长度的0.2至0.7倍的范围内。 在一些实施例中，桁架状翼梁穿过并有助于支撑机翼和小翼。

    Dual mode flight vehicle
    87.
    发明授权
    Dual mode flight vehicle 有权
    双模飞行器

    公开(公告)号：US09266609B1

    公开(公告)日：2016-02-23

    申请号：US14518770

    申请日：2014-10-20

    Applicant: Insitu, Inc.

    Inventor： Peter J. Kunz

    IPC: B64C27/22 ,  B64C29/00

    CPC classification number: B64C29/0008 ,  B64C17/04 ,  B64C29/0091 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104

    Abstract: A fixed wing flight vehicle has wing, a center-mounted propulsion unit and a pod that is moveable between a center of the wing and a displaced position at or near one end of the wing. When the pod is at or near the center of the wing, that is, having a center of mass at or near a thrust vector of the propulsion unit, the flight vehicle flies with the characteristics of a regular fixed wing aircraft. However, when the pod is translated to the position at or near an end of the wing, an overall center of mass of the flight vehicle is substantially offset from the thrust vector of the propulsion unit. This causes the flight vehicle to spin like a samara, e.g., a maple seed, so that the flight vehicle can take off or land in a very limited space, much like a helicopter.

    Abstract translation: 固定翼飞行器具有机翼，中心安装的推进单元和荚，其可以在翼的中心和机翼的一端或附近的位移位置之间移动。 当荚在机翼的中心处或附近时，即具有在推进单元的推力矢量处或附近的质心时，飞行器具有常规固定翼飞机的特征。 然而，当货舱被翻译到机翼末端或其附近的位置时，飞行车辆的整体质心基本上偏离推进装置的推力矢量。 这使得飞行车辆像萨马拉一样旋转，例如枫树种子，使得飞行车辆能够在非常有限的空间中起飞或着陆，就像直升机一样。

    Multi-role aircraft with interchangeable mission modules
    89.
    发明授权
    Multi-role aircraft with interchangeable mission modules 有权
    具有可互换任务模块的多角色飞机

    公开(公告)号：US09221532B2

    公开(公告)日：2015-12-29

    申请号：US14205156

    申请日：2014-03-11

    Applicant: Abe Karem

    Inventor： Abe Karem

    IPC: B64C1/00 ,  B64C3/56 ,  B64C1/06 ,  B64C39/10 ,  B64C39/02 ,  B64D37/00 ,  B64C1/26

    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。

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