中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

568 records (took 0.03 seconds)

    Air-launchable container for deploying air vehicle
    292.
    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
    294.
    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
    295.
    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。

    Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles
    297.
    发明授权
    Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles 有权
    在无人驾驶飞行器上部署并致动翼型的机构

    公开(公告)号：US09533758B2

    公开(公告)日：2017-01-03

    申请号：US14590464

    申请日：2015-01-06

    Applicant: The Boeing Company

    Inventor： Jonathan David Gettinger

    IPC: B64C5/12 ,  B64C39/02 ,  B64C3/56

    CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C5/12 ,  B64C2201/102

    Abstract: Deployment and control actuation mechanisms are incorporated in unmanned aerial vehicles having folding wings and/or folding canards and/or a folding vertical stabilizer. The folding canards and folding vertical stabilizer can be deployed using respective four-bar over-center mechanisms. Elevators pivotably mounted to the folding canards and a rudder pivotably mounted to the folding vertical stabilizer can be controlled by means of respective twist link mechanisms. The folding wings have respective wing roots that are driven by respective gas springs to pivot on bearings about a wing root hub having control servo wire paths.

    Abstract translation: 部署和控制致动机构被并入具有折叠翼和/或折叠的猫和/或折叠的垂直稳定器的无人驾驶飞行器中。 可以使用相应的四杆过中心机构来部署折叠式鸭子和折叠式垂直稳定器。 可枢转地安装到折叠卡瓦的电梯和可枢转地安装到折叠垂直稳定器的舵可以通过相应的扭转连杆机构来控制。 折叠翼具有相应的翼根，其由相应的气弹簧驱动，以围绕具有控制伺服线路径的翼根轮毂的轴承枢转。

    Aerial vehicle with separation of winged surfaces in first and second flexed states
    299.
    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。

    Long endurance aircraft
    300.
    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。

Patent Agency Ranking