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    Modular aircraft system
    43.
    发明授权
    Modular aircraft system 有权
    模块化飞机系统

    公开(公告)号：US09505484B1

    公开(公告)日：2016-11-29

    申请号：US15096216

    申请日：2016-04-11

    Applicant: Nasser M. Al-Sabah

    Inventor： Nasser M. Al-Sabah

    IPC: B64C3/38 ,  B64C13/00 ,  B64C9/00 ,  B64C13/20 ,  B64C9/32 ,  B64D27/02 ,  B64C3/34 ,  B64D47/08 ,  B64D15/00 ,  B64C39/02 ,  B64D37/00 ,  B64D27/14 ,  B64D27/20

    CPC classification number: B64C3/38 ,  B64C1/26 ,  B64C3/34 ,  B64C5/06 ,  B64C9/00 ,  B64C9/326 ,  B64C13/00 ,  B64C13/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/063 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/16 ,  B64C2201/165 ,  B64C2211/00 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D37/00 ,  B64D39/00 ,  B64D47/08 ,  Y02T50/32

    Abstract: The modular aircraft system includes a single fuselage having a permanently installed empennage and plural sets of wing modules and engine modules, with each wing and engine module optimized for different flight conditions and missions. The fuselage and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module is also provided. Turboprop, single turbojet, and dual turbojet engine modules are provided for installation depending upon mission requirements for any given flight. The aircraft is primarily adapted for use as an autonomously operated or remotely operated unmanned aerial vehicle.

    Abstract translation: 模块化飞机系统包括具有永久安装的尾翼和多组翼模块和发动机模块的单个机身，每个机翼和发动机模块针对不同的飞行条件和任务进行了优化。 机身和每个模块配置为快速拆卸和安装模块，以最大限度地减少飞机的停机时间。 在具有较高耐久性和/或重量承载能力的情况下，为相对高速飞行提供具有相对较低纵横比的短翼。 为长距离和耐力航班提供高长宽比的长翼，速度并不是绝对重要的。 还提供了中跨翼模块。 提供涡轮螺旋桨发动机，单涡轮喷气发动机和双涡轮喷气发动机模块用于安装，具体取决于任何给定航班的任务要求。 该飞机主要适用于自主操作或远程操作的无人驾驶飞行器。

    IN-FLIGHT BATTERY RECHARGING SYSTEM FOR AN UNMANNED AERIAL VEHICLE
    44.
    发明申请
    IN-FLIGHT BATTERY RECHARGING SYSTEM FOR AN UNMANNED AERIAL VEHICLE 审中-公开
    用于无人驾驶飞机的飞行式电池充电系统

    公开(公告)号：US20160325834A1

    公开(公告)日：2016-11-10

    申请号：US15149972

    申请日：2016-05-09

    Applicant: Curtis Asa Foster

    Inventor： Curtis Asa Foster

    IPC: B64C39/02 ,  B64D27/24 ,  B64C27/14

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/066 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/24

    Abstract: An in-flight battery recharging system for Unmanned Aerial Vehicle (UAV). This invention converts byproducts of a multi-rotor unmanned aerial vehicle's conventional propulsion system operation and airframe movements to generate electricity that, in turn, is used to power the propulsion system's electric motors, power onboard electronic components, and recharge the battery that initially powers the propulsion system's electric motors. Having this ability of recharging the battery in-flight gives an unmanned aerial vehicle a much improved flight time and range, thereby greatly increasing its utility.

    Abstract translation: 无人机（UAV）的飞行中电池充电系统。 本发明转化了多转子无人驾驶飞行器的常规推进系统操作和机身运动的副产物，以产生电力，其又被用于为推进系统的电动机提供动力，并且对电子组件进行动力，以及对最初为 推进系统的电动机。 在飞行中为电池充电的能力给无人驾驶飞行器提供了大大改进的飞行时间和范围，从而大大提高了其效用。

    HYBRID AIRCRAFT
    46.
    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
    47.
    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。

    Ducted fan core for use with an unmanned aerial vehicle
    48.
    发明授权
    Ducted fan core for use with an unmanned aerial vehicle 失效
    用于无人驾驶飞行器的风扇内芯

    公开(公告)号：US08387911B2

    公开(公告)日：2013-03-05

    申请号：US12179690

    申请日：2008-07-25

    Applicant: Daniel Ross Collette

    Inventor： Daniel Ross Collette

    IPC: B64C29/00

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

    Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

    Abstract translation: 提供用于无人驾驶飞行器的管道风扇芯，其容纳各种有效载荷。 风扇风扇芯包括框架，附接到发动机，变速箱组件，风扇和多个控制叶片。 框架上的第一表面包括多个连接或电迹线。 多个连接用于可拆卸地附接携带各种有效载荷的各种吊舱。 因此，可以简单地通过将不同的荚移除并附接到固定的车辆核心，使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚附接到框架时，它们增强了车辆的空气动力学。

    Unmanned air vehicles and method of landing same
    49.
    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。

    Cargo aircraft
    50.
    发明授权
    Cargo aircraft 有权
    货机

    公开(公告)号：US07699267B2

    公开(公告)日：2010-04-20

    申请号：US11782850

    申请日：2007-07-25

    Applicant: Elie Helou, Jr.

    Inventor： Elie Helou, Jr.

    IPC: B64C1/22

    CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

    Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

    Abstract translation: 用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。 翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。 轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。 梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。 飞机被认为是无人机。

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