公开(公告)号：US20050230535A1

公开(公告)日：2005-10-20

申请号：US10823434

申请日：2004-04-13

Applicant: Robert Ruszkowski

Inventor： Robert Ruszkowski

IPC: B63G8/28 ,  B63G8/30 ,  B63G13/00 ,  B64C1/00 ,  B64C1/06 ,  B64C35/00 ,  B64C37/00 ,  B64C39/00 ,  B64C39/02 ,  F41F3/07 ,  F42B15/20

CPC classification number: B64C1/062 ,  B63G8/28 ,  B63G8/30 ,  B63G13/00 ,  B64C35/00 ,  B64C37/00 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/205 ,  F41F3/07 ,  F42B15/20

Abstract: A sea-launched and recovered unmanned aircraft is disclosed. The aircraft is jet-powered and has features and systems to maintain watertight integrity such that it may be released from a submerged submarine or dropped into a body of water by a ship or an aircraft. The aircraft is buoyant and remains at or near the water surface before its rockets are ignited. The rockets propel the air vehicle out of the sea and accelerate it to flying speed at which time a jet engine is started and the rockets are jettisoned. The air vehicle performs its mission independently or in conjunction with other ones of the air vehicles. The air vehicle then returns to an assigned splashdown point at sea via, for example, an engine-off “whip-stall” maneuver. A submarine or ship may retrieve the air vehicle and readies it for another mission.

Abstract translation: 披露了一架海上发射和回收的无人机。 飞机是喷气式动力的，并具有保持水密完整性的特征和系统，使得其可以从潜水艇释放或由船或飞机落入水体。 这架飞机是浮力的，并且在其火箭点火之前保持在水面或附近。 火箭将空中车辆推出大海，并将其加速到飞行速度，此时喷气发动机起动，火箭被放弃。 机动车辆独立地或与其他机动车辆一起执行任务。 然后，空中飞行器通过例如发动机关闭“鞭炮”操纵返回到海上指定的飞溅点。 潜艇或船只可以检索空中飞行器并准备进行另一个飞行任务。

公开(公告)号：US20050178892A1

公开(公告)日：2005-08-18

申请号：US10756024

申请日：2004-01-12

Applicant: J. Box ,  Jules Kish

Inventor： J. Box ,  Jules Kish

IPC: B64C27/14 ,  B64C39/02 ,  B64D35/02 ,  B64D35/00

CPC classification number: B64C27/14 ,  B64C39/028 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D35/02

Abstract: A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The two reduction stages provide a reduction ratio preferably having a value of at least 19, and most preferably greater than 24. The 1 transmission system is of small-size preferably having a maximum diameter less than twelve inches. The two stages of the transmission system may comprise any one (or parts of) of a number of configurations, including an in-line lay shaft configuration, an in-line star-star configuration an offset star-spur configuration, an offset compound idler configuration, an inline traction-internal gear configuration, and an inline traction planetary gear configuration. Preferably, the input stage of the transmission system is self-equilibrating such that first shaft can be supported without bearings and is operably coupled to the output shaft of the microturbine engine by an outside diameter piloted spline coupling mechanism. For vertical lift applications, a single traction stage along with a bevel gear assembly or other shaft transmission mechanism can be used to provide the necessary RPM reduction.

Abstract translation: 与微型涡轮发动机结合使用的用于推进飞机机体（例如基于螺旋桨的固定翼飞行器或基于转子的垂直升降飞机）或用于各种其它应用的传动系统。 微型涡轮发动机的输出轴优选地在72,000RPM和150,000RPM之间的转速下工作，输出功率在150HP和5HP之间（最优选地在50,000RPM和200,000RPM之间的扩展范围内工作，并且输出 功率在200 HP和5 HP之间）。 两个还原阶段提供优选具有至少19的值，最优选大于24的减小率。1传输系统的尺寸最小，最好具有小于12英寸的最大直径。 传动系统的两个阶段可以包括许多构造的任何一个（或多个部分），包括一个在线的卧式结构，一个星形星形配置，一个偏移星形齿轮配置，一个偏移复合惰轮 配置，内联牵引内齿轮配置和在线牵引行星齿轮配置。 优选地，传动系统的输入级是自平衡的，使得第一轴可以被支撑而没有轴承，并且通过外径引导的花键联接机构可操作地联接到微型涡轮发动机的输出轴。 对于垂直升降应用，可以使用单个牵引台以及锥齿轮组件或其他轴传动机构来提供必要的RPM减小。

公开(公告)号：US20050082421A1

公开(公告)日：2005-04-21

申请号：US10901132

申请日：2004-07-29

Applicant: Pietro Perlo ,  Denis Bollea ,  Bartolo Pairetti ,  Stefano Alacqua ,  Roberto Finizio ,  Cosimo Carvignese ,  Piermario Repetto ,  Gianfranco Innocenti

Inventor： Pietro Perlo ,  Denis Bollea ,  Bartolo Pairetti ,  Stefano Alacqua ,  Roberto Finizio ,  Cosimo Carvignese ,  Piermario Repetto ,  Gianfranco Innocenti

IPC: B64C29/00 ,  A63H27/127 ,  A63H29/22 ,  B64C27/20 ,  B64C39/02 ,  B64C15/00

CPC classification number: B64C39/024 ,  A63H27/12 ,  A63H29/22 ,  B64C27/20 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146

Abstract: The flying machine includes a supporting structure including a central rotational support having a vertical axis connected to an essentially horizontal, preferably annular, peripheral support part, coaxial with the central support, at least one upper rotor including a central hub rotatable about the axis of the central support of the supporting structure, an outer channel-section ring supported by the peripheral part of the supporting structure by contactless suspension means, preferably magnetic suspension means, and a plurality of blades which extend from the hub to the channel-section ring and which are inclined with respect to the horizontal plane; and motor devices carried at least partially by the peripheral part of the supporting structure and operable to cause rotation of the rotor with respect to this structure in a predetermined direction.

Abstract translation: 飞行器包括支撑结构，其包括中心旋转支撑件，该中心旋转支撑件具有连接到基本上水平的，优选环形的外围支撑部分的垂直轴线，该中心旋转支撑件与中心支撑件同轴，至少一个上转子包括可围绕 支撑结构的中心支撑，通过非接触式悬挂装置，优选磁悬浮装置由支撑结构的周边部分支撑的外部通道截面环，以及从轮毂延伸到通道截面环的多个叶片， 相对于水平面倾斜; 以及至少部分地由支撑结构的周边部分承载的马达装置，并且可操作以使转子相对于该结构在预定方向上旋转。

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。

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。

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

IPC: B64D1/04 ,  F42C15/42 ,  F42C11/06 ,  F42C11/00 ,  B64C39/02

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.

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

IPC: G01S17/02 ,  G01S17/89 ,  H04W4/021

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.

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

IPC: G05D1/00 ,  F41G7/30 ,  F41G7/22 ,  B64C9/00 ,  B64D47/08 ,  B64C39/02

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.

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

IPC: B64C13/16 ,  F41G7/22 ,  G05D1/12 ,  B64C39/02

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.

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

IPC: B64C39/02 ,  B64C3/26 ,  H04K3/00 ,  B64C3/38 ,  B64C39/10

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.