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    AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH TWO WING ARRANGEMENTS
    253.
    发明申请
    AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH TWO WING ARRANGEMENTS 审中-公开
    用于双向安装的垂直起落架的飞机

    公开(公告)号：US20150232178A1

    公开(公告)日：2015-08-20

    申请号：US14378604

    申请日：2013-02-13

    Applicant: Johannes REITER

    Inventor： Johannes Reiter

    IPC: B64C29/00 ,  B64C37/00 ,  B64C3/38

    CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C3/385 ,  B64C27/00 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0075 ,  B64C29/02 ,  B64C37/00 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

    Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

    Abstract translation: 本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。 第一机翼装置（110）安装到机身（100），使得第一机翼装置（110）能围绕第一机翼装置（110）的第一纵向机翼轴线（111）倾斜，并且使得第一机翼装置 （110）能够围绕机身轴线（101）旋转。 第二机翼装置（120）包括至少一个推进单元（122），其中第二机翼装置（120）安装到机身（100）上，使得第二机翼装置（120）可围绕第二纵向机翼轴线 （121），并且使得所述第二机翼装置（120）能够围绕所述机身轴线（101）旋转。 第一机翼装置（110）和第二机翼装置（120）以这样的方式适配，使得在固定翼飞行模式中，第一机翼装置（110）和第二机翼装置（120）不围绕 机身轴（101）。 第一机翼装置（110）和第二机翼装置（120）进一步适于以悬停飞行模式，第一机翼装置（110）和第二机翼装置（120）围绕相应的 第一纵向翼片轴线（111）和相应的第二纵向翼片轴线（121）相对于其在固定翼飞行模式中的定向，并且第一翼形装置（110）和第二翼形装置（120）围绕机身旋转 轴（101）。

    STOWABLE AND DEPLOYABLE UNMANNED AERIAL VEHICLE
    254.
    发明申请
    STOWABLE AND DEPLOYABLE UNMANNED AERIAL VEHICLE 有权
    可持续和可配置的无人机

    公开(公告)号：US20150225072A1

    公开(公告)日：2015-08-13

    申请号：US14179697

    申请日：2014-02-13

    Applicant: Northrop Grumman Systems Corporation

    Inventor： Christopher N. Torre

    IPC: B64C3/56 ,  B64C39/02

    CPC classification number: B64C3/56 ,  B64C1/30 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/201

    Abstract: An unmanned aerial vehicle (UAV) can be deployed from a small stowed package for flight and stowed back into the package after the flight is complete is disclosed. The UAV is retracted to a volume that is less than half of it's fully deployed volume. This allows the UAV to be transported to any desired field position on a truck or other convenient transportation. The UAV may also be launched from a ship deck. In a further aspect, the flexible deployment of the UAV will allow a single UAV to be used in place of multiple types of UAVs.

    Abstract translation: 飞行完成后，可以从一个小型收起的包装中部署无人驾驶飞行器（UAV）并将其收回包装。 UAV被缩回到小于其完全部署卷的一半的卷。 这样可以将无人机运送到卡车上的任何所需的现场位置或其他方便的交通工具。 无人机也可以从船甲板上发射。 在另一方面，UAV的灵活部署将允许使用单个UAV来代替多种类型的UAV。

    System and method for compact and combinable aerial vehicle capable of vertical/short takeoff and landing
    256.
    发明授权
    System and method for compact and combinable aerial vehicle capable of vertical/short takeoff and landing 有权
    能够进行垂直/短时起飞和着陆的紧凑型和可组合式飞行器的系统和方法

    公开(公告)号：US08936212B1

    公开(公告)日：2015-01-20

    申请号：US12861986

    申请日：2010-08-24

    Applicant: Qiang Fu ,  Xu Zhang

    Inventor： Qiang Fu ,  Xu Zhang

    IPC: B64C15/12

    CPC classification number: B64C37/02 ,  B64C3/56 ,  B64C29/0033 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/165 ,  Y02T50/14

    Abstract: System and method to construct vertical and/or short takeoff and landing (V/STOL) aerial vehicles capable of being folded into compact size, and capable of be combined with one or more such vehicles to form bigger composite aerial vehicles. Airframe of the vehicle comprises a plurality of wings on lateral or periphery of thrust generators, wherein arrangements of wings make it possible to optionally fold wings without moving thrust generators. Folding transforms such vehicles into ground vehicles which can share roads and house parking lots with conventional ground vehicles. Therefore such vehicles can be used as V/STOL flying cars. Means are provided for attaching to and detaching from one or more similarly equipped vehicles in flight or before takeoff, so that multiple vehicles can form a large composite vehicle. Compactness, combinability and V/STOL capability enable versatile applications.

    Abstract translation: 构建能够折叠成紧凑尺寸的垂直和/或短起飞（V / STOL）飞行器的系统和方法，并且能够与一个或多个这样的车辆组合以形成更大的复合飞行器。 车辆的机身包括在推力发生器的侧面或周边上的多个翼，其中翼的布置使得可以可选地折叠翼而不移动推力发生器。 折叠将这种车辆转换成可与常规地面车辆共享道路和房屋停车场的地面车辆。 因此，这种车辆可以用作V / STOL飞行车。 提供了用于在飞行中或起飞之前附接和分离一个或多个类似装备的车辆的装置，使得多个车辆可以形成大型复合车辆。 紧凑性，组合性和V / STOL功能可实现多种应用。

    INFLATABLE AIRFOIL SYSTEM HAVING REDUCED RADAR AND INFRARED OBSERVABILITY
    258.
    发明申请
    INFLATABLE AIRFOIL SYSTEM HAVING REDUCED RADAR AND INFRARED OBSERVABILITY 审中-公开
    具有减少雷达和红外可观察性的可充气飞行器系统

    公开(公告)号：US20140255189A1

    公开(公告)日：2014-09-11

    申请号：US14250385

    申请日：2014-04-11

    Applicant: The Boeing Company

    Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

    IPC: B64C3/30

    CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

    Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

    Abstract translation: 一种用于操作翼型系统的方法和装置。 可能产生气体。 气体可以被送入包括可膨胀的气翼和截面的充气翼型系统中。 可膨胀翼型件可以具有内端和外端，其中可膨胀翼型可以由许多基本上通过电磁波通过可充气翼型的材料构成。 该部分可以具有多个开口，其中可充气翼片的内端可以与该部分相关联。 该部分可以被配置为与机身相关联。 开口的数量可以被配置为提供与可膨胀翼型件的内部的通信。 具有开口数量的部分可以被配置为减少遇到该部分的电磁波的反射。

    Automatic configuration control of a device
    259.
    发明授权
    Automatic configuration control of a device 有权
    设备的自动配置控制

    公开(公告)号：US08761967B2

    公开(公告)日：2014-06-24

    申请号：US13478520

    申请日：2012-05-23

    Applicant: Christopher E. Fisher ,  Marc L. Schmalzel ,  Steven Chambers ,  Justin B. McAllister

    Inventor： Christopher E. Fisher ,  Marc L. Schmalzel ,  Steven Chambers ,  Justin B. McAllister

    IPC: B64C37/02 ,  G06F19/00

    CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/102

    Abstract: Methods, systems, and devices for determining system/device configuration and setting a mode of operation based on the determined configuration. An air vehicle processor: (a) receives a component information set of at least one external component; (b) determine a mode of operation, by the processor having a current mode of operation setting, based on the received component information and at least one of: an initial mode of operation setting and the current mode of operation setting; (c) determines whether all of the one or more received component information sets match a configuration requirement; (d) transitions to a flight-ready status if the determination is a conjunctive match; and (e) transition to a reset status if the determination is not a conjunctive match.

    Abstract translation: 用于确定系统/设备配置并基于所确定的配置来设置操作模式的方法，系统和设备。 一种飞行器处理器：（a）接收至少一个外部部件的部件信息组; （b）基于接收到的分量信息和至少一个操作设置模式和当前操作模式设置中的至少一个来确定具有当前操作模式设置的处理器的操作模式; （c）确定所述一个或多个接收到的分量信息集合是否匹配配置要求; （d）如果确定是联合匹配，则转换到飞行就绪状态; 和（e）如果确定不是联合匹配，则转换到复位状态。

    Aircraft wing with flexible skins
    260.
    发明授权
    Aircraft wing with flexible skins 有权
    飞机机翼具有柔软的外观

    公开(公告)号：US08714476B2

    公开(公告)日：2014-05-06

    申请号：US13278493

    申请日：2011-10-21

    Applicant: Jack W. Reany ,  Terry M. Sanderson

    Inventor： Jack W. Reany ,  Terry M. Sanderson

    IPC: B64C3/38

    CPC classification number: B64C3/56 ,  B64C2201/102

    Abstract: A wing includes a spar, and a pair of flexible skins that are attached to the spar. The spar is at the leading edge of the wing, and the skins extend toward the trailing edge of the wing. The wing deploys from a stowed condition, in which the skins are curved in the same direction around a fuselage of an aircraft, to a deployed condition, in which the skins provide the wing with an airfoil cross-sectional shape, for example with the skins curve in opposite direction. A lock is used to maintain the skins in the deployed state, with the lock for example located at the trailing edge of the wing. The lock may be a mechanical mechanism that automatically locks the wing in the deployed state, preventing the wing from returning to the stowed state.

    Abstract translation: 翼包括翼梁，以及一对连接到翼梁的柔性皮。 翼梁位于机翼的前缘，皮面朝向机翼的后缘延伸。 机翼从收起的状态部署，其中皮肤沿着飞机的机身在相同的方向上弯曲到部署状态，其中皮肤为翼提供翼型横截面形状，例如与皮肤 曲线相反。 使用锁来将皮肤保持在展开状态，例如锁定位于翼的后缘。 锁可以是机械机构，其将机翼自动地锁定在展开状态，防止机翼返回到收起状态。

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