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公开(公告)号：US20050081708A1
公开(公告)日：2005-04-21
申请号：US10495131
申请日：2002-10-24
Applicant: James O'Dwyer
Inventor： James O'Dwyer
IPC: F41A9/72 , B63G1/00 , B64C39/02 , B64D7/00 , B64D7/04 , B64D7/08 , F41A21/08 , F41A21/20 , F41A21/36 , F41A21/48 , F41A23/00 , F42B5/03
CPC classification number: B64D7/00 , B64C2201/121 , B64D7/04 , B64D7/08 , F41A21/48 , F41A23/00 , F42B5/035
Abstract: A vehicular weapons platform (30) including a plurality of barrel assemblies (10), wherein each barrel assembly includes a barrel (11), a plurality of projectiles (14) axially disposed within the barrel for operative sealing engagement with the bore of the barrel (11) and discrete propellant charges (15) for propelling respective projectiles sequentially through the muzzle of the barrel; and at least one of said plurality of barrel assemblies (10) includes a barrel which also forms a structural member of the weapons platform. In one preferred form, the weapons platform takes the form of a small combat aerial vehicle (SCAV) (30), wherein the barrel assemblies (10) form the airframe. A method of constructing a weapons platform from the barrel assemblies is also described.
Abstract translation: 一种包括多个筒体组件（10）的车辆武器平台（30），其中每个筒体组件包括筒体（11），多个射出件（14），其轴向设置在所述筒体内，用于与所述筒体 （11）和离散的推进剂装料（15），用于依次通过枪管的枪口推动各射弹; 并且所述多个筒组件（10）中的至少一个包括还形成武器平台的结构构件的筒体。 在一种优选形式中，武器平台采取小作战飞行器（SCAV）（30）的形式，其中枪管组件（10）形成机身。 还描述了从筒组件构造武器平台的方法。
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公开(公告)号：US20030127559A1
公开(公告)日：2003-07-10
申请号：US10084749
申请日：2002-02-26
Inventor： Eric Ronald Walmsley
IPC: B64C029/00
CPC classification number: B64C27/20 , B64C29/0066 , B64C39/001 , B64C39/024 , B64C39/06 , B64C39/062 , B64C2201/027 , B64C2201/046 , B64C2201/048 , B64C2201/108 , B64C2201/121 , B64C2201/127
Abstract: A circular VTOL aircraft with a central vertically mounted jet or rocket engine 7, (or engines) having below vertical thrust vents 14 at cardinal points, together with a jet rocket engine 20 (or engines) horizontally mounted on turntable pod 16 which is steerable through 360 degrees and centrally situated below the vertical engine (s). Alternatively the horizontal engine can be replaced by central thrust vent 36 delivering thrust from the vertical engine to vectored thrust nozzle 37 attached to the turntable. Thrust from the four vertical thrust vents is controlled by valves 21 giving VTOL thrust control as well as pitch and bank control. The horizontal engine provides acceleration and retro-thrust for horizontal flight and directional control through 360 degrees. The passenger cabin is situated in the main body of the aircraft. Fuel tanks are installed around the central engines. The flight-deck is situated at the top-centre of the craft above the engines, which are detachable for maintenance.
Abstract translation: 一个圆形垂直起降飞机，其中心垂直安装的喷气式或火箭发动机7（或发动机）在主要点处具有低于垂直推力通风口14，以及水平安装在转盘舱16上的喷气式火箭发动机20（或发动机），该喷射式火箭发动机20可引导通过 360度并位于垂直发动机的下方。 或者，水平发动机可以由中心推力孔36代替，其将来自垂直发动机的推力传递到附接到转盘的向量推力喷嘴37。 来自四个垂直推力通风口的推力由阀门21控制，提供垂直起动器推力控制以及俯仰和组合控制。 水平发动机提供加速度和逆向推力，用于水平飞行和360度方向控制。 客舱位于飞机的主体。 燃油箱安装在中央发动机周围。 飞行甲板位于发动机上方的工艺的顶部中心，可拆卸以进行维护。
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公开(公告)号：US11650036B2
公开(公告)日：2023-05-16
申请号：US17712447
申请日：2022-04-04
Applicant: Ensign-Bickford Aerospace & Defense Company
Inventor： Edris Raji , Kurt Nelson , Matthew Bragoni , Andrew Kochanek , John Fiske , Craig Boucher , John A. Graham , Jarrett Jacobson , John Benner , Scott Crespi , Michael Ronzello
CPC classification number: F42C15/42 , B64C39/024 , B64D1/04 , F42C11/006 , F42C11/06 , B64C2201/121 , B64C2201/146
Abstract: A system that is mountable to an unmanned vehicle and a method of operation is provided. The system includes an attachment plate configured to couple to the unmanned vehicle, the attachment plate having a first feature. A control module is configured to removably couple to the attachment plate, the control module having one or more processors and a power source, the control module having a pin arranged to move from a first position to a second position when the control module is coupled to the attachment plate, the one or more processors being energized when the pin is moved from the first position to the second position. A payload having an energetic element is provided, the payload being coupled to the control module.
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公开(公告)号：US20190004176A1
公开(公告)日：2019-01-03
申请号：US15443173
申请日：2017-02-27
Applicant: Raytheon BBN Technologies Corp.
Inventor： Brian R. Van Voorst
CPC classification number: G01S17/026 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64C2201/12 , B64C2201/121 , B64C2201/141 , B64C2201/146 , F41H11/02 , F41H13/0006 , G01S7/4817 , G01S7/495 , G01S7/51 , G01S17/023 , G01S17/66 , G01S17/87 , G01S17/89 , G01S17/933 , G05D1/0016 , G05D1/0088 , G05D1/0094 , G05D1/101 , G05D1/12 , G06K9/0063 , G06K2209/21 , G06T17/05 , G08G5/0026 , G08G5/0069 , G08G5/0082 , H04W4/021
Abstract: A system comprising includes a plurality of three dimensional line-scanner LIDAR sensors disposed to provide a set of fanned beams that travel from one horizon into the air to the other horizon arranged to provide a light fence to detect an object that breaks the light fence and a sensor processor connected to the plurality of three dimensional multi-beam line-scanner LIDAR sensors to establish a vector of travel and a velocity of the object that passes through the multi-beam light fence at the location of where the beams are broken.
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公开(公告)号：US20180356822A1
公开(公告)日：2018-12-13
申请号：US16051481
申请日：2018-07-31
Applicant: AeroVironment, Inc.
Inventor： William J. Nicoloff , Eric M. Sornborger , Lars B. Cremean
CPC classification number: G05D1/0094 , B64C9/00 , B64C39/024 , B64C2201/021 , B64C2201/121 , B64C2201/123 , B64C2201/14 , B64D47/08 , F41G7/2253 , F41G7/2293 , F41G7/30
Abstract: An aircraft including a wing system, a plurality of control surfaces, a camera mounted on a camera pod, and a control system. The camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the aircraft, between a directly forward-looking orientation and a side-looking orientation. The control system controls the control surfaces such that they induce a significant aircraft yaw causing an identified target to be within the field of view of the camera with the camera in the directly forward-looking orientation.
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Patent Agency Ranking
公开(公告)号：US20180093755A1
公开(公告)日：2018-04-05
申请号：US15689945
申请日：2017-08-29
Applicant: AeroVironment, Inc.
Inventor： Carlos Thomas Miralles
CPC classification number: B64C13/16 , B64B2201/00 , B64C39/024 , B64C2201/04 , B64C2201/121 , B64C2201/141 , B64C2201/165 , F41G7/2253 , F41G7/2286 , F41G7/2293 , G05D1/12
Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.
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77.发明申请公开(公告)号：US20180009525A1
公开(公告)日：2018-01-11
申请号：US15071018
申请日：2016-03-15
Applicant: Selex Galileo Inc.
Inventor： Matthew Keegan , Stephen Leonard Engelson Wyatt
CPC classification number: B64C39/024 , B64C3/26 , B64C3/38 , B64C39/10 , B64C2201/021 , B64C2201/042 , B64C2201/121 , B64C2201/162 , G06F2221/2143 , H04K3/20
Abstract: A system and method for conducting electronic warfare on a target site includes the use of a small unmanned aircraft system (SUAS) having a fuselage and a Prandtl wing, wherein at least two electric ducted fans are positioned on the fuselage. A power system of the SUAS has a plurality of hydrogen fuel cells positioned within the Prandtl wing. An electronic warfare payload is carried by the fuselage, wherein the electronic warfare payload and the at least two electric ducted fans are powered by at least a portion of the plurality of hydrogen fuel cells. During an operation, the SUAS may launch near an IAD site and initiate an electronic warfare effect on an integrated air defense site with electronic warfare payload carried by the SUAS to interfere with at least one surface-to-air missile (SAM) system.
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公开(公告)号：US20170307401A1
公开(公告)日：2017-10-26
申请号：US15608696
申请日：2017-05-30
Applicant: TEXTRON INNOVATIONS INC.
Inventor： James M. McCollough , Erik Oltheten , Nicholas Lappos
CPC classification number: G01C23/00 , B60Q1/00 , B64C27/00 , B64C27/006 , B64C27/04 , B64C27/52 , B64C29/00 , B64C39/024 , B64C2201/108 , B64C2201/121 , B64D43/00 , B64D45/00 , G01C21/00 , G01D7/02 , G05D17/02
Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.
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公开(公告)号：US20170261604A1
公开(公告)日：2017-09-14
申请号：US15443182
申请日：2017-02-27
Applicant: Raytheon BBN Technologies Corp.
Inventor： Brian R. Van Voorst
CPC classification number: G01S17/026 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64C2201/12 , B64C2201/121 , B64C2201/141 , B64C2201/146 , F41H11/02 , F41H13/0006 , G01S7/4817 , G01S7/495 , G01S7/51 , G01S17/023 , G01S17/66 , G01S17/87 , G01S17/89 , G01S17/933 , G05D1/0016 , G05D1/0088 , G05D1/0094 , G05D1/101 , G05D1/12 , G06K9/0063 , G06K2209/21 , G06T17/05 , G08G5/0026 , G08G5/0069 , G08G5/0082 , H04W4/021
Abstract: A system includes a long range LIDAR tracking system to track a target drone and provide detection and tracking information of the target drone; a control system to process the detection and tracking information and provide guidance information to intercept the target drone; and a high powered intercept drone controlled by supervised autonomy, the supervised autonomy provided by processing the detection and tracking information of the target drone and sending guidance information to the intercept drone to direct the intercept drone to the target drone.
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公开(公告)号：US20160364989A1
公开(公告)日：2016-12-15
申请号：US15183653
申请日：2016-06-15
Applicant: ImageKeeper LLC
Inventor： Jerry Speasl , Mike Patterson , Mark Roberts
CPC classification number: G08G5/0034 , B64C39/024 , B64C2201/042 , B64C2201/066 , B64C2201/08 , B64C2201/082 , B64C2201/121 , B64C2201/126 , B64C2201/128 , B64C2201/145 , B64C2201/20 , B64C2201/201 , B64C2201/205 , B64C2201/206 , B64C2201/208 , B64F1/222 , G06Q10/08 , G08G5/0069 , G08G5/0082 , G08G5/0091
Abstract: A base module may be used to receive and house one or more unmanned aerial vehicles (UAVs) via one or more cavities. The base module receives commands from a manager device and identifies a flight plan that allows a UAV to execute the received commands. The base module transfers the flight plan to the UAV and frees the UAV. Once the UAV returns, the base module once again receives it. The base module then receives sensor data from the UAV from one or more sensors onboard the UAV, and optionally receives additional information describing its flight and identifying success or failure of the flight plan. The base module transmits the sensor data and optionally the additional information to a storage medium locally or remotely accessible by the manager device.
Abstract translation: 基座模块可以用于经由一个或多个空腔接收和容纳一个或多个无人机（UAV）。 基本模块从管理器设备接收命令，并识别允许UAV执行接收到的命令的飞行计划。 基地模块将飞行计划转移到无人机，并释放无人机。 一旦UAV返回，基本模块再次接收它。 然后，基本模块从UAV上的一个或多个传感器接收来自UAV的传感器数据，并且可选地接收描述其飞行并识别飞行计划的成功或失败的附加信息。 基本模块将传感器数据和可选的附加信息传输到本地或由管理器设备远程访问的存储介质。
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