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    Micro Hybrid Generator System Drone
    113.
    发明申请
    Micro Hybrid Generator System Drone 有权
    微型混合发电机系统无人机

    公开(公告)号：US20160311544A1

    公开(公告)日：2016-10-27

    申请号：US15202771

    申请日：2016-07-06

    Applicant: Top Flight Technologies, Inc.

    Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

    IPC: B64D27/24 ,  B64D33/08 ,  B64C27/00 ,  B64C39/02 ,  B64C27/08

    CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

    Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.

    Abstract translation: 一种包括至少一个转子电动机的无人驾驶飞行器。 转子电机由微型混合发电系统供电。 微型混合发电机系统包括被配置为向至少一个转子电动机提供电力的可再充电电池，被配置为产生机械功率的小型发动机，耦合到小型发动机的发电机电动机，并且被配置为使用由 小型发动机，桥式整流器，被配置为将由发电电动机产生的交流电力转换为直流电力，并将DC电力提供给可再充电电池和至少一个转子电动机中的一个或两者;以及电子控制单元， 所述小型发动机的节气门至少部分地基于至少一个负载的功率需求，所述至少一个负载包括所述至少一个转子电动机。

    UN-MANNED AERIAL VEHICLE
    116.
    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
    117.
    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
    118.
    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
    119.
    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。

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