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    INFLATABLE AIRFOIL SYSTEM HAVING REDUCED RADAR AND INFRARED OBSERVABILITY
    61.
    发明申请
    INFLATABLE AIRFOIL SYSTEM HAVING REDUCED RADAR AND INFRARED OBSERVABILITY 审中-公开

    公开(公告)号：US20180257760A1

    公开(公告)日：2018-09-13

    申请号：US15981623

    申请日：2018-05-16

    Applicant: The Boeing Company

    Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

    IPC: B64C3/30 ,  B64C39/02

    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.

    Air-launchable container for deploying air vehicle
    66.
    发明授权
    Air-launchable container for deploying air vehicle 有权

    公开(公告)号：US09776719B2

    公开(公告)日：2017-10-03

    申请号：US14018493

    申请日：2013-09-05

    Applicant: Raytheon Company

    Inventor： Erick W. Elkins ,  Matthew Glenn Murphy ,  Scott D. Thomas

    IPC: B64D1/12 ,  B64C39/02

    CPC classification number: B64D1/12 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/206

    Abstract: A container is used to launch a small aircraft, such as an unmanned aerial vehicle (UAV), from a host aircraft. The container protects the UAV from stresses during the initial ejection from a launcher that is part of the host aircraft. The initial stresses may be due to turbulence in the vicinity of the host aircraft, high airspeed, and/or tumbling that may result from the ejection from the host aircraft moving at a high airspeed. The container may deploy a drag device, such as a drogue chute, to slow the container down and reorient the container, prior to deployment of the UAV from the container. During the time between ejection from the host aircraft and deployment from the container, the UAV may be powered up and acquire data, such as global positioning system (GPS) data, to allow the UAV a “hot start” enabling immediate mission commencement.

    Aerial vehicle with depolyable components
    68.
    发明授权
    Aerial vehicle with depolyable components 有权
    具有可拆卸部件的飞行器

    公开(公告)号：US09580165B1

    公开(公告)日：2017-02-28

    申请号：US15092219

    申请日：2016-04-06

    Applicant: Area-I Inc.

    Inventor： Nicholas Robert Alley ,  Joshua Lemming Steele ,  Jesse Owen Williams ,  Daniel Kuehme ,  Jonathan Caleb Phillips

    IPC: B64C3/56 ,  B64C3/54 ,  B64C13/24 ,  B64C39/02

    CPC classification number: B64C3/40 ,  B64C1/36 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C11/28 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2211/00 ,  Y02T50/14 ,  Y02T50/44

    Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

    Abstract translation: 公开了一种具有可部署组件（UAVDC）的无人机。 UAVDC可以包括机身，至少一个机翼和至少一个控制面。 在一些实施例中，UAVDC还可以包括推进装置和/或模块化有效载荷。 UAVDC可以被配置成多个布置。 例如，在紧凑的布置中，UAVDC可以包括存放在机身上的至少一个翼片和装在机身上的至少一个控制表面。 在部署的布置中，UAVDC可以包括从机身部署的至少一个翼和从机身部署的至少一个控制表面。 在扩展的布置中，UAVDC可以包括至少一个可伸缩的翼，以增加展开布置的翼展。

    In-flight reconfigurable hybrid unmanned aerial vehicle
    69.
    发明授权
    In-flight reconfigurable hybrid unmanned aerial vehicle 有权
    飞行中可重构混合无人机

    公开(公告)号：US09550567B1

    公开(公告)日：2017-01-24

    申请号：US14524956

    申请日：2014-10-27

    Applicant: Amazon Technologies, Inc.

    Inventor： Jack Erdozain, Jr. ,  Berk Ozturk ,  Nicholas Hampel Roberts ,  Brian C. Beckman

    IPC: B64C27/22 ,  B64C29/02 ,  B64C3/54 ,  B64C39/02 ,  B64D27/24 ,  B64D47/08

    CPC classification number: B64C29/02 ,  B64C1/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/18 ,  Y02T50/14

    Abstract: This disclosure is directed to an unmanned aerial vehicle (“UAV”) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a wing. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing.

    Abstract translation: 本公开涉及通过将UAV的方向改变大约九十度而在垂直飞行构型和水平飞行构型之间转换的无人驾驶飞行器（“UAV”）。 无人机可以包括联接到机翼的推进单元。 机翼可以包括通过枢转可旋转地联接在一起的翼段，当机身垂直于水平线时，枢轴旋转以将推进单元围绕UAV的质心定位。 在这种垂直飞行配置中，无人机可以执行垂直飞行或悬停。 在垂直飞行期间，UAV可以使机翼经由枢轴向外延伸，使得机翼段基本上彼此平行地定位，并且翼类似于常规的固定翼。 在机翼延伸的情况下，UAV采取水平飞行配置，提供从机翼产生的向上升力。

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