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。

公开(公告)号：US20050029400A1

公开(公告)日：2005-02-10

申请号：US10600400

申请日：2003-06-20

Applicant: Richard Ouellette ,  Aaron Kutzmann

Inventor： Richard Ouellette ,  Aaron Kutzmann

IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64D7/00

CPC classification number: B64C1/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/187 ,  B64D7/00

Abstract: A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.

Abstract translation: 模块化组件组可配置成形成多个具有飞行能力的平台。 多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。 主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。 多个任务专用面板各自可拆卸地连接到相对的壁之一。 至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。

公开(公告)号：US3669385A

公开(公告)日：1972-06-13

申请号：US3669385D

申请日：1970-10-08

Applicant: FAIRCHILD INDUSTRIES

Inventor： GLANTZ EARL ,  MCCOMAS JEAN W

IPC: B64C1/00 ,  B64C39/02 ,  B64D5/00 ,  B64C1/26

CPC classification number: B64D5/00 ,  B64C1/00 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/185

Abstract: An aircraft of improved of simplified construction having forward and aft generally cylindrical and substantially identical fuselage sections that are connected to a central fuselage section that houses an engine that has an inlet located above the forward fuselage section for powering the aircraft in flight. The central long axis of the aft fuselage section is located above the central long axis of the forward fuselage section. Wings are connected to the central fuselage section and a tail assembly is connected to the aft portion of the aft fuselage section. Many of the component parts of the aircraft are interchangeable and the aircraft is especially suited for use as a drone for towing aerial targets.

Abstract translation: 具有改进的简化结构的飞机具有前后大体上圆柱形和基本相同的机身部分，其连接到中央机身部分，该中央机身部分容纳具有位于前机身部分上方的入口的发动机，用于为飞行器提供动力。 后部机身部分的中心长轴位于前机身部分的中心长轴上方。 翼连接到中央机身部分，尾部组件连接到后机身部分的后部。 飞机的许多组成部分是可互换的，飞机特别适用于作为无人驾驶用于拖曳空中目标的飞机。

公开(公告)号：WO2014058510A2

公开(公告)日：2014-04-17

申请号：PCT/US2013/051959

申请日：2013-07-25

Applicant: BYE UAS, INC. ,  BYE, George ,  BICKEL, Matt

Inventor： BYE, George ,  BICKEL, Matt

IPC: B64C19/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/185 ,  B64C2211/00

Abstract: The present invention provides an Unmanned Aircraft System, including an integrated unmanned aerial vehicle and all related components and subsystems that can be packaged and transported as a kit, and customized to fit desired mission profiles, and easily repaired by replacement of damaged components or subsystems. The present invention further provides unmanned aircraft system components and subsystems that facilitate low power and low noise operation, and extended flight times.

Abstract translation: 本发明提供了一种无人驾驶飞机系统，其包括集成的无人驾驶飞行器以及可以作为套件来包装和运输的所有相关部件和子系统，并且定制以适应期望的任务轮廓并且易于修理 通过更换损坏的部件或子系统。 本发明还提供了有助于低功率和低噪音操作以及延长飞行时间的无人驾驶飞机系统部件和子系统。

公开(公告)号：WO2006086005A2

公开(公告)日：2006-08-17

申请号：PCT/US2005026820

申请日：2005-07-29

Applicant: BERNARD CHARLES W

Inventor： BERNARD CHARLES W

IPC: B64C13/00

CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/146 ,  B64C2201/167 ,  B64D39/00 ,  G05D1/0027

Abstract: An aircraft attack interdiction system using an unmanned interdiction aircraft piloted using a remote control system. In-flight refueling system, weapons launcher systems and intelligence gathering equipment are mounted on the interdiction aircraft. A remote flight control operator to remotely fly the interdiction aircraft can be based on a remote flight control commander aircraft that can be flown at safe distances from targets that are attacked by the interdiction aircraft

Abstract translation: 使用遥控系统驾驶的无人拦截飞机的飞机攻击拦截系统。 飞机加油系统，武器发射系统和情报搜集设备都安装在拦截飞机上。 远程飞行拦截飞机的远程飞行控制操作员可以基于远程飞行控制指挥员飞机，该飞机可以与安全距离被拦截飞机攻击的目标飞行

公开(公告)号：WO2006006151A1

公开(公告)日：2006-01-19

申请号：PCT/IL2005/000714

申请日：2005-07-06

Applicant: ELBIT SYSTEMS LTD. ,  SIRKIS, Omri

Inventor： SIRKIS, Omri

IPC: 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 Vehicule (uav) (2) including an engine (4) and an airframe (6), including means for performing a deep stall maneouvre; at least one inflatable sleeve (12) connected or connectable to the airframe (6), and means for inflating the sleeve (12) during flight, wherein the inflated sleeve (12) extends along the lower side of the airframe (6) 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（4）和机身（6）的无人驾驶飞机（uav）（2），其中包括用于执行深度失速行动的手段; 连接或连接到机身（6）的至少一个可充气套筒（12）以及用于在飞行期间使套筒（12）膨胀的装置，其中所述充气套筒（12）沿着所述机身（6）的下侧延伸，以便 在深层失速登陆期间保护相同。 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。

公开(公告)号：WO2014058510A3

公开(公告)日：2014-06-19

申请号：PCT/US2013051959

申请日：2013-07-25

Applicant: BYE UAS INC ,  BYE GEORGE ,  BICKEL MATT

Inventor： BYE GEORGE ,  BICKEL MATT

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/185 ,  B64C2211/00

Abstract: The present invention provides an Unmanned Aircraft System, including an integrated unmanned aerial vehicle and all related components and subsystems that can be packaged and transported as a kit, and customized to fit desired mission profiles, and easily repaired by replacement of damaged components or subsystems. The present invention further provides unmanned aircraft system components and subsystems that facilitate low power and low noise operation, and extended flight times.

Abstract translation: 本发明提供了一种无人驾驶飞行器系统，包括一个综合的无人驾驶飞行器以及所有相关的组件和子系统，可以作为一个工具包进行打包和运输，并进行定制，以适应所需的任务轮廓，并通过更换损坏的组件或子系统进行修理。 本发明还提供了便于低功率和低噪声操作以及延长飞行时间的无人飞行器系统部件和子系统。

公开(公告)号：WO2006069304A2

公开(公告)日：2006-06-29

申请号：PCT/US2005/046755

申请日：2005-12-22

Applicant: AURORA FLIGHT SCIENCES CORPORATION ,  PARKS, Robert

Inventor： PARKS, Robert

CPC classification number: F01D9/065 ,  B64C29/0075 ,  B64C29/0083 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/167 ,  B64D27/18 ,  B64D29/04 ,  B64D33/02 ,  F02C6/12 ,  F02C7/042 ,  F02K3/00 ,  F05D2220/90

Abstract: A system and method for tilting an engine in a vertical take-off and landing/short take-off and landing aircraft (VTOL/STOL A/C) is provided comprising a main control system, an engine tilting mechanism, and an air flow volume detector, which is located in the engine. The system and method tilt the engine to maximize engine performance based on a variety of parameters including the air flow volume so that forward and horizontal speeds are maximized at the appropriate times, and also to reduce radar cross section and infra-red visibility.

Abstract translation: 提供了一种用于在垂直起飞和着陆/短起飞和着陆飞机（VTOL / STOL A / C）中倾斜发动机的系统和方法，包括主控制系统，发动机倾斜机构和空气流量 检测器，位于发动机中。 该系统和方法基于包括空气流量的各种参数来倾斜发动机以使发动机性能最大化，使得在适当的时间使前进和水平速度最大化，并且还减少雷达截面和红外可见度。

公开(公告)号：WO2003004352A1

公开(公告)日：2003-01-16

申请号：PCT/JP2002/006031

申请日：2002-06-17

Applicant: セイコーエプソン株式会社

Inventor： 赤堀 豊

IPC: B64B1/06

CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

Abstract: An airship system, comprising an airship (110), a base station (120), and at least three measurement points, wherein, when the airship (110) receiving an instruction from the base station (120) transmits ultrasonic wave, the measurement point units (S1 to S3) receive the ultrasonic wave to measure distances between the airship and the three measurement points and an MPU incorporated in the base station (120) calculates the position of the airship (110) and, according to the calculated position, the base station (120) transmits a navigation instruction to the airship (110) to control the route of the airship (110), whereby the operation of the airship by an operator can be eliminated, and the weight of loads mounted on the airship and the power consumption thereof can be reduced.

Abstract translation: 一种飞艇系统，包括飞艇（110），基站（120）和至少三个测量点，其中当接收到来自基站（120）的指令的飞艇（110）发射超声波时，测量点 单元（S1至S3）接收超声波以测量飞艇与三个测量点之间的距离，并且包含在基站（120）中的MPU计算飞艇（110）的位置，并且根据计算的位置， 基站（120）向飞艇（110）发送导航指令以控制飞艇（110）的路线，由此可以消除操作者的飞艇的操作，并且安装在飞艇上的载荷和 其功耗可以降低。

公开(公告)号：KR1020170134184A

公开(公告)日：2017-12-06

申请号：KR1020170025271

申请日：2017-02-27

Applicant: 더 보잉 컴파니

Inventor： 인영다니엘킴 ,  라이언에스.윌슨

IPC: B64C39/02 ,  B64D27/20 ,  H01Q1/28 ,  G01S13/00

CPC classification number: G01S7/021 ,  B64C3/38 ,  B64C30/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/12 ,  B64C2201/167 ,  B64D5/00 ,  F02K7/10 ,  F05D2220/10 ,  F42B10/48 ,  G01S7/003 ,  G01S13/003 ,  G01S13/87 ,  G05D1/0011 ,  G05D1/0088 ,  H01Q1/287

Abstract: 바이스태틱레이더타겟검출을위한시스템은 UAV(14)의초음속순항을제공하는램제트엔진(30)을갖는무인항공기(UAV)(14)를이용한다. 펼쳐질수 있는안테나아암들(22)은반사레이더펄스들의바이스태틱수신을위한패시브레이더수신기를지원한다. UAV(14)는레이더범위한계를넘는공역내의 UAV 비행프로파일을가지고동작한다. 펼쳐질수 있는안테나아암들(22)은초음속순항을위한제1 수축된포지션을갖고, 공기제동기로서작동하고레이더수신기의보어사이트정렬을제공하는제2 확장된포지션으로의펼침을위해적용된다. 모선항공기(10)는레이더펄스들을전송하기위한레이더송신기를가지고, 레이더범위한계밖의항공기비행프로파일을가지고동작한다. 통신데이터링크는 UAV(14)와전술모선항공기(10)를동작가능하게상호연결하고, UAV 레이더안테나(46)에서의반사레이더펄스들의바이스태틱수신에의해생성된데이터를모선항공기(10)에전송한다.

Abstract translation: 用于双基地雷达目标检测的系统利用带有提供UAV 14的超音速巡航的冲压式喷气发动机30的UAV 14。 可展开的天线臂22支持用于双基接收反射雷达脉冲的无源雷达接收器。 无人机14在超出雷达范围限制的空域中以无人机飞行剖面进行操作。 可展开的天线臂（22）具有用于超音速巡航的第一缩回位置时，作为空气制动被施加到第二延伸位置，以提供一个雷达接收机的视轴对准的公开内容，将采取行动。 主板飞机10具有用于传输雷达脉冲的雷达发射器，并且在雷达范围界限之外的飞行器飞行剖面中操作。 通信数据链路被发送到UAV（14）和上述汇流条的飞机可能的互连的操作（10），和UAV雷达天线46，总线10的飞机，通过eseoui的双基地接收机产生的数据反射的雷达脉冲 的。