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    UN-MANNED AERIAL VEHICLE
    342.
    发明申请
    UN-MANNED AERIAL VEHICLE 有权
    无人驾驶的航空机

    公开(公告)号：US20160009363A1

    公开(公告)日：2016-01-14

    申请号：US14172035

    申请日：2014-02-04

    Applicant: Texas A&M University System

    Inventor： John Valasek ,  James Franklin May ,  Andrew Beckett ,  Cecil C. Rhodes, JR.

    IPC: B64C1/26 ,  B64D9/00 ,  B64C3/38 ,  B64C25/08 ,  B64C1/00 ,  B64C25/04

    CPC classification number: B64C1/26 ,  B64C1/22 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/128 ,  B64C2211/00

    Abstract: The present invention relates to an aircraft. The aircraft includes a fuselage module for receiving a payload. The fuselage module includes a plurality of internal connections. The aircraft includes a wing module adjustably coupled to the fuselage module and a tail module coupled to the wing module. The wing module may be adjusted relative to the fuselage module to adjust a location of an aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft. A main landing gear may be adjusted relative to the fuselage module to adjust the location of the aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft.

    Abstract translation: 本发明涉及飞机。 飞机包括用于接收有效载荷的机身模块。 机身模块包括多个内部连接。 飞机包括可调节地联接到机身模块的翼模块和耦合到翼模块的尾模块。 机翼模块可以相对于机身模块进行调节，以调整飞行器的空气动力学中心的位置，以维持飞行器的空气动力学中心的位置与飞行器的重心的位置之间的预定距离 。 可以相对于机身模块调整主起落架以调整飞行器的空气动力学中心的位置，以维持飞行器的空气动力学中心的位置与飞行器的重心位置之间的预定距离 飞机。

    HYBRID AIRCRAFT
    343.
    发明申请
    HYBRID AIRCRAFT 审中-公开
    混合飞机

    公开(公告)号：US20150151844A1

    公开(公告)日：2015-06-04

    申请号：US14407395

    申请日：2013-05-16

    Applicant: Siemens Aktiengesellschaft

    Inventor： Frank Anton ,  Swen Gediga ,  Johannes Wollenberg

    IPC: B64D27/24

    CPC classification number: B64D27/24 ,  B64C31/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64D2027/026 ,  Y02T50/64 ,  Y10S903/903

    Abstract: The invention relates to a hybrid aircraft (F). According to the invention, a suitable position for mounting an energy generation unit (14) in the aircraft is identified, said energy generation unit comprising an internal combustion engine (34) and an electric generator (30) that is coupled thereto via a shaft. Independently of the position of the energy generation unit (14), a position is also identified for a thrust generation unit (12) comprising an electric motor (24) and a propeller (20) that is coupled thereto via a shaft (22). When the aircraft (F) is built, the thrust generation unit (12) and the energy generation unit (14) are disposed in the positions identified therefor. The generator (30) is then coupled to the electric motor (24) via an electric transmission device (16).

    Abstract translation: 本发明涉及混合动力飞机（F）。 根据本发明，识别出在飞行器中安装能量产生单元（14）的合适位置，所述能量产生单元包括内燃机（34）和通过轴与其连接的发电机（30）。 独立于能量产生单元（14）的位置，还为包括经由轴（22）联接到其上的电动机（24）和螺旋桨（20）的推力产生单元（12）识别位置。 当建造飞机（F）时，将推力产生单元（12）和能量产生单元（14）设置在由此识别的位置。 发电机（30）然后通过电力传输装置（16）耦合到电动机（24）。

    AERIAL VEHICLE AND METHOD OF FLIGHT
    344.
    发明申请
    AERIAL VEHICLE AND METHOD OF FLIGHT 有权
    空中客车和飞行方法

    公开(公告)号：US20140339356A1

    公开(公告)日：2014-11-20

    申请号：US14324306

    申请日：2014-07-07

    Applicant: Athene Works Limited

    Inventor： Nicholas James DEAKIN

    IPC: B64B1/02 ,  B64B1/64

    CPC classification number: B64B1/02 ,  B64B1/08 ,  B64B1/10 ,  B64B1/12 ,  B64B1/14 ,  B64B1/20 ,  B64B1/38 ,  B64B1/64 ,  B64B2201/00 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  H01Q1/36 ,  H01Q9/27

    Abstract: An aerial vehicle comprises an elongate envelope within which are at least one first compartment for holding a lighter than air gas and at least one second compartment for holding atmospheric air and said at least one second compartment having an inlet and an outlet and at least one pair of wings extending laterally from the envelope; said wings being planar units with a leading and trailing edge, the width of the wings from their leading edges to their trailing edges being substantially less than the length of the envelope with airfoil portions fitted between the leading and trailing edges of the wing: the top and bottom of the wings are mirror images of one another; in which forward motion of the vehicle is obtainable without trust through alternate diving and climbing motion.

    Abstract translation: 一种空中飞行器包括一个细长的外壳，其中至少有一个用于保持比空气气体轻的第一隔间和至少一个用于保持大气空气的第二隔室，并且所述至少一个第二隔室具有入口和出口以及至少一对 的翼从信封横向延伸; 所述翼是具有前缘和后缘的平面单元，翼从其前缘到其后缘的宽度基本上小于具有机翼部分装配在翼的前缘和后缘之间的封套的长度：顶部 翅膀的底部是彼此的镜像; 其中车辆的向前运动通过交替的潜水和爬坡运动而不被信任地获得。

    AIR COOLING SYSTEM FOR AN UNMANNED AERIAL VEHICLE
    345.
    发明申请
    AIR COOLING SYSTEM FOR AN UNMANNED AERIAL VEHICLE 有权
    空气冷却系统用于不经营的空中客车

    公开(公告)号：US20140220873A1

    公开(公告)日：2014-08-07

    申请号：US14127163

    申请日：2012-06-29

    Applicant: Callan Murray Bleechmore ,  John Howard Tubb ,  Donald Andrew Railton ,  Stephen John Karay ,  Pouria Mehrani

    Inventor： Callan Murray Bleechmore ,  John Howard Tubb ,  Donald Andrew Railton ,  Stephen John Karay ,  Pouria Mehrani

    IPC: F01P1/06

    CPC classification number: F01P1/06 ,  B64C39/024 ,  B64C2201/044 ,  B64D33/08 ,  F01P1/02 ,  F01P2050/20

    Abstract: An air cooling system for an unmanned aerial vehicle including a propeller (14) driven by an engine (12) has at least one cooling air duct (22) to direct cooling air to cool a vehicle component e.g. a cylinder head. The duct has at least one air inlet and at least one air outlet. Operation of the propeller causes a pressure differential between the air outlet (24,124) and the air inlet (23,123) which draws air through said cooling air duct (22). A cowling (16) can cover at least part of the engine, and can form a plenum and have the supply of cooling air through a front face aperture (164) or side walls (17) of the engine cowl (16).

    Abstract translation: 一种用于包括由发动机（12）驱动的螺旋桨（14）的无人驾驶飞行器的空气冷却系统具有至少一个冷却风道（22），以引导冷却空气来冷却车辆部件，例如， 气缸盖。 管道具有至少一个空气入口和至少一个空气出口。 螺旋桨的操作导致空气出口（24,124）和空气通过所述冷却风道（22）的空气入口（23,123）之间的压力差。 整流罩（16）可以覆盖发动机的至少一部分，并且可以形成通风室，并且通过发动机整流罩（16）的前面孔（164）或侧壁（17）供应冷却空气。

    Hybrid power for ducted fan unmanned aerial systems
    348.
    发明授权
    Hybrid power for ducted fan unmanned aerial systems 有权
    用于风扇无人驾驶空中系统的混合动力

    公开(公告)号：US08128019B2

    公开(公告)日：2012-03-06

    申请号：US12334098

    申请日：2008-12-12

    Applicant: Richard E. Annati ,  Patrick L. O'Brien

    Inventor： Richard E. Annati ,  Patrick L. O'Brien

    IPC: B64C29/00

    CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64D27/24 ,  Y02T50/64

    Abstract: A propulsion system for a vertical take-off and landing ducted fan aerial vehicle is provided, the propulsion system comprising an internal combustion engine, an electric motor that comprises a motor generator, a motor drive and a battery. The motor drive and battery are integrated into the aerial vehicle and provide power to the ducted fan aerial vehicle. The electric motor may comprise a ring motor generator. In operation, this dual propulsion system serves as a weight-efficient option to allow for two sources of power on a ducted fan unmanned aerial vehicle.

    Abstract translation: 提供了一种用于垂直起飞和降落的风扇飞行器的推进系统，该推进系统包括内燃机，包括电动发电机，电机驱动器和电池的电动机。 电动机驱动器和电池被集成到飞行器中，并向管道风扇飞行器提供电力。 电动机可以包括环形电动发电机。 在操作中，这种双推进系统作为一种重量选择，允许在风扇无人驾驶飞行器上的两个电源。

    Unmanned air vehicles and method of landing same
    349.
    发明授权
    Unmanned air vehicles and method of landing same 有权
    无人驾驶飞行器和降落方法相同

    公开(公告)号：US08123162B2

    公开(公告)日：2012-02-28

    申请号：US11098529

    申请日：2005-04-05

    Applicant: Omri Sirkis

    Inventor： Omri Sirkis

    IPC: B64C25/56 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187

    Abstract: There is provided an Unmanned Air Vehicle (UAV) including an engine and an airframe, including means for performing a deep stall maneuver at least one inflatable sleeve connected or connectable to the airframe, and means for inflating the sleeve during flight, wherein the inflated sleeve extends along the lower side of the airframe so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

    Abstract translation: 提供了包括发动机和机身的无人机（UAV），包括用于对连接或可连接到机身的至少一个充气套筒进行深度失速操纵的装置，以及用于在飞行期间使套筒充气的装置，其中，所述膨胀套筒 沿着机身的下侧延伸，以便在深度失速着陆期间保护它们。 还提供了一种用于操作无人机（UAV）的方法，包括发动机和机身。

    Remote engine/electric helicopter industrial plat form
    350.
    发明申请
    Remote engine/electric helicopter industrial plat form 审中-公开
    遥控发动机/电动直升机工业平台

    公开(公告)号：US20100096490A1

    公开(公告)日：2010-04-22

    申请号：US12288307

    申请日：2008-10-18

    Applicant: Kevin Patrick Gordon

    Inventor： Kevin Patrick Gordon

    IPC: B64C27/04 ,  B64C1/06 ,  B64C1/08 ,  B64C37/02 ,  G05D1/00 ,  B64C19/00 ,  B64C17/00

    CPC classification number: G05D1/102 ,  B64C27/10 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148

    Abstract: The invention is an unmanned flying helicopter aircraft platform (“aircraft platform”) that can be powered by either interchangeable electric motors or by fuel powered internal combustion engines. The aircraft platform is surrounded by a lightweight exoskeleton cage that protects the rotor blades from coming into contact with external objects. The aircraft platform uses a weight located on the bottom side of the aircraft platform that can be remotely moved to adjust the center of gravity in order to navigate in any direction. The aircraft platform has a place on its bottom side where attachments can be added or removed which allows the aircraft platform to be used for multiple different purposes. The aircraft platform can be flown and operated either remotely using a hand held control unit or it can be flown and operated by an onboard pilot located in the human carrying attachment.

    Abstract translation: 本发明是可由可互换电动机或燃料动力内燃机驱动的无人飞行直升机飞机平台（“飞机平台”）。 飞机平台由一个轻质的外骨架围拢，保护转子叶片与外部物体接触。 飞机平台使用位于飞机平台底部的重物，可以远程移动以调整重心，以便在任何方向上导航。 飞机平台在其底部有一个位置，可以添加或移除附件，从而允许飞机平台用于多种不同的目的。 飞机平台可以使用手持控制单元进行远程飞行和操作，也可以通过位于人体携带附件中的飞行员飞行员进行飞行和操作。

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