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公开(公告)号：US20170343645A1
公开(公告)日：2017-11-30
申请号：US15165663
申请日：2016-05-26
Applicant: The Boeing Company
Inventor： Inyoung Daniel Kim , Ryan S. Wilson
CPC classification number: G01S7/021 , B64C3/38 , B64C9/326 , B64C30/00 , B64C39/024 , B64C2201/021 , B64C2201/082 , B64C2201/12 , B64C2201/122 , B64C2201/167 , B64D5/00 , B64D7/00 , B64D47/02 , F02K7/10 , F05D2220/10 , F42B10/48 , G01S7/003 , G01S13/003 , G01S13/87 , G05D1/0011 , G05D1/0088 , H01Q1/287
Abstract: A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a ramjet providing supersonic cruise of the UAV. Deployable antenna arms support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV and the tactical mothership aircraft, transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the mothership aircraft.
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公开(公告)号：US20170057635A1
公开(公告)日：2017-03-02
申请号：US14843329
申请日：2015-09-02
Applicant: THE BOEING COMPANY
Inventor： James David Strayer
CPC classification number: B64C39/024 , B63G3/04 , B63G2008/004 , B63G2008/008 , B64C2201/027 , B64C2201/088 , B64C2201/108 , B64C2201/167 , B64C2201/201 , B64C2201/205
Abstract: A drone launch system includes a canister defining an internal cavity, and a drone positioned within the internal cavity in a stowed state. The drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister. A method for launching a drone, the method includes positioning the drone in a stowed state in an internal cavity of a canister, ejecting the drone from the canister, and transitioning the drone into a deployed state after the ejecting operation.
Abstract translation: 无人机发射系统包括限定内部空腔的罐和位于收纳状态的内部空腔内的无人机。 无人机被配置为从罐排出并从收起状态转换到罐外部的展开状态。 一种用于发射无人机的方法，该方法包括将无人机处于收起状态，将其从罐中排出，将喷射器从罐排出，并且在喷射操作之后将无人机转换成展开状态。
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公开(公告)号：US08492692B2
公开(公告)日：2013-07-23
申请号：US13097394
申请日：2011-04-29
Applicant: Jeremy F. Fisher
Inventor： Jeremy F. Fisher
CPC classification number: F42B15/10 , B64C39/024 , B64C2201/021 , B64C2201/084 , B64C2201/102 , B64C2201/122 , B64C2201/165 , B64C2201/167 , B64C2201/201 , B64C2201/205 , F41F1/08 , F41F3/042
Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.
Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。
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公开(公告)号：US20070023570A1
公开(公告)日：2007-02-01
申请号：US11192171
申请日：2005-07-29
Applicant: Charles Bernard
Inventor： Charles Bernard
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。 飞机上的加油系统，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，该飞机可以在距离被拦截飞机攻击的目标的安全距离处飞行。
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公开(公告)号：US06908061B2
公开(公告)日：2005-06-21
申请号：US10877082
申请日：2004-06-25
Applicant: Yutaka Akahori
Inventor： Yutaka Akahori
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 according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.
Abstract translation: 根据本发明的飞艇系统具有飞艇（110），基站（120）和至少三个测量点。 飞艇（110）在接收到来自基站（120）的指令时发射超声波。 测量点单元（S 1 -S 3）接收超声波，从而测量从飞艇（110）到相应测量点的距离。 并入基站（120）的MPU计算飞艇（110）的位置。 基站（120）通过向飞艇（110）发送飞行指令，基于计算出的位置来控制飞艇（110）的路线。 以这种方式，可以提供一种飞艇系统，使得飞行员不需要飞行飞艇，并且可以减少飞艇的负载重量和功率消耗。
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Patent Agency Ranking
公开(公告)号：US06626397B2
公开(公告)日：2003-09-30
申请号：US09895332
申请日：2001-07-02
Applicant: Aharon Yifrach
Inventor： Aharon Yifrach
IPC: B65C300
CPC classification number: B64C39/024 , B64C3/56 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/102 , B64C2201/123 , B64C2201/127 , B64C2201/141 , B64C2201/146 , B64C2201/167 , B64C2201/201 , B64D5/00 , Y10S244/90 , Y10S244/901
Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.
Abstract translation: 无人驾驶飞行器包括具有至少两个围绕中心部分大致对称布置的翼部的自主飞行翼。 每个翼部可枢转地附接到每个相邻部分，使得翼部可折叠以用于存储并且可展开。 优选的形式是所谓的具有四个翼部的海鸥翼。 车辆可以从母机飞行器编程，同时使用可能是无线的数据链路承载到部署区域。
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公开(公告)号：US09694894B2
公开(公告)日：2017-07-04
申请号：US14324306
申请日：2014-07-07
Applicant: Athene Works Limited
Inventor： Nicholas James Deakin
IPC: B64B1/20 , B64B1/02 , B64B1/08 , B64B1/10 , B64B1/12 , B64B1/14 , B64B1/38 , H01Q1/36 , H01Q9/27 , 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.
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公开(公告)号：US09616997B2
公开(公告)日：2017-04-11
申请号：US14944482
申请日：2015-11-18
Applicant: Aurora Flight Sciences Corporation
Inventor： Robert Parks , Adam Woodworth , Tom Vaneck , Justin McClellan
CPC classification number: B64C37/00 , B60F5/02 , B63G8/001 , B63G8/08 , B63G2008/005 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/08 , B64C2201/102 , B64C2201/127 , B64C2201/165 , B64C2201/167 , F42B15/20
Abstract: A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure, at least one vertical stabilizer structure, and at least one horizontal stabilizer structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.
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公开(公告)号：US20120138727A1
公开(公告)日：2012-06-07
申请号：US13097394
申请日：2011-04-29
Applicant: Jeremy F. Fisher
Inventor： Jeremy F. Fisher
CPC classification number: F42B15/10 , B64C39/024 , B64C2201/021 , B64C2201/084 , B64C2201/102 , B64C2201/122 , B64C2201/165 , B64C2201/167 , B64C2201/201 , B64C2201/205 , F41F1/08 , F41F3/042
Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.
Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。
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公开(公告)号：US20090026314A1
公开(公告)日：2009-01-29
申请号：US11782850
申请日：2007-07-25
Applicant: ELIE HELOU, JR.
Inventor： ELIE HELOU, JR.
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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