公开(公告)号：WO2018175037A1

公开(公告)日：2018-09-27

申请号：PCT/US2018/019423

申请日：2018-02-23

Applicant: RAYTHEON COMPANY

Inventor： SUMMERS, Matt H. ,  KOEHLER, Frederick B. ,  VILLARREAL, James K. ,  LANGHENRY, Mark T.

IPC: B64D27/02 ,  C06B33/06 ,  C06D5/06 ,  F02K9/94 ,  F02K9/95 ,  B64G1/40

CPC classification number: B64D27/023 ,  B64C2201/046 ,  B64C2201/167 ,  B64D31/02 ,  B64G1/403 ,  B64G1/404 ,  C06B33/06 ,  C06D5/06 ,  F02K9/08 ,  F02K9/94 ,  F02K9/95 ,  F02K9/97 ,  F05D2220/80 ,  F05D2240/35

Abstract: Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical input and even extinguished by interrupting the electrical to control a secondary thrust profile (e.g., amplitude, transition rates) to fulfill the needs of a given takeoff, inflight or landing maneuver and provide a smooth transition in and out of the maneuver. Multiple pairs of fixed thrusters (opposite sides of the fuselage), a single pair of gimbaled thrusters or a hybrid of fixed and gimbaled thrusters may be configured to provide all such maneuvers. Flight control inputs are passed back and forth through an interface to enable the thrust assist.

公开(公告)号：WO2018027220A1

公开(公告)日：2018-02-08

申请号：PCT/US2017/045739

申请日：2017-08-07

Applicant: WILKINSON, Christopher

Inventor： WILKINSON, Christopher

IPC: B64C39/02 ,  G05B15/02

CPC classification number: B64C39/024 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/22 ,  F41H3/00 ,  F41H13/0012 ,  F41H13/0093 ,  G01S7/38

Abstract: A law enforcement drone system is provided. The system features an unmanned aerial vehicle, having a wireless transceiver, an airframe, a propulsion system, a navigation mechanism, a processor, a memory, a power source, and at least one fuel tank. The system also features a control system having a wireless transceiver, an input device, capable of receiving a user's input and converting the user's input to electrical signals, a processor, and a memory. The control system is in wireless communication with the vehicle such that the control system is capable of utilizing the propulsion system in substantially real-time.

Abstract translation:

提供执法无人机系统。 该系统具有无人驾驶飞行器，具有无线收发器，机身，推进系统，导航机构，处理器，存储器，电源和至少一个燃料箱。 该系统还具有具有无线收发器，能够接收用户输入并将用户输入转换为电信号的输入设备，处理器和存储器的控制系统。 控制系统与车辆进行无线通信，使得控制系统能够基本上实时地利用推进系统。

公开(公告)号：WO2017131823A2

公开(公告)日：2017-08-03

申请号：PCT/US2016/052091

申请日：2016-09-16

Applicant: WILKINSON, Christopher

Inventor： WILKINSON, Christopher

IPC: B64C13/24 ,  A63H30/04

CPC classification number: B64C39/024 ,  B64C2201/02 ,  B64C2201/046 ,  B64C2201/082 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/206 ,  B64C2201/22

Abstract: An unmanned aerial combat vehicle system is disclosed. The system provides for an unmanned aerial combat vehicle that is capable of performing reconnaissance, disrupting enemy communications, or delivering a weaponized payload. The unmanned aerial combat vehicle may also be equipped with a cloaking mechanism, where it can mask it' s heat signature, or simulate an image on its outer surface.

Abstract translation: 公开了一种无人空中作战车辆系统。 该系统提供了一种无人驾驶的空中作战车辆，能够执行侦察，破坏敌方通信或发射武器化的有效载荷。 无人驾驶飞行器也可以配备隐形装置，它可以掩盖它的热特征，或者在其外表面模拟图像。

公开(公告)号：EP3057857A4

公开(公告)日：2017-07-26

申请号：EP14854105

申请日：2014-10-15

Applicant: ELWHA LLC

Inventor： HYDE RODERICK A ,  WOOD LOWELL L JR ,  DUNCAN WILLIAM DAVID ,  KARE JORDIN T ,  MALASKA STEPHEN L ,  MYHRVOLD NATHAN P ,  PETROSKI ROBERT C ,  WEAVER THOMAS ALLAN

IPC: B62D63/02 ,  B62D63/04 ,  B64D39/00 ,  B64F3/02

CPC classification number: B64C39/024 ,  B64C39/022 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/12 ,  B64C2201/127 ,  B64C2201/145 ,  B64C2201/146 ,  B64C2201/208 ,  B64F1/00

Abstract: A motor vehicle system includes a motor vehicle including an aircraft landing portion, and an actively propelled unmanned aircraft configured to be supported on the aircraft landing portion. The vehicle and aircraft are configured such that the vehicle can provide at least one of fuel and electrical energy to the aircraft while the aircraft is supported on the aircraft landing portion.

Abstract translation: 一种机动车辆系统包括具有飞机着陆部分的机动车辆和被配置为支撑在飞机着陆部分上的主动推进的无人驾驶飞机。 车辆和飞机构造成使得当飞机支撑在飞机着陆部分上时，车辆可以向飞机提供燃料和电能中的至少一种。

公开(公告)号：EP3057857A1

公开(公告)日：2016-08-24

申请号：EP14854105.5

申请日：2014-10-15

Applicant: ELWHA, LLC

Inventor： HYDE, Roderick A. ,  WOOD, Lowell L., Jr. ,  DUNCAN, William David ,  KARE, Jordin T. ,  MALASKA, Stephen L. ,  MYHRVOLD, Nathan P. ,  PETROSKI, Robert C. ,  WEAVER, Thomas Allan

IPC: B62D63/02 ,  B62D63/04 ,  B64F3/02 ,  B64D39/00

CPC classification number: B64C39/024 ,  B64C39/022 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/12 ,  B64C2201/127 ,  B64C2201/145 ,  B64C2201/146 ,  B64C2201/208 ,  B64F1/00 ,  G05D1/0094

Abstract: A motor vehicle system includes a motor vehicle including an aircraft landing portion, and an actively propelled unmanned aircraft configured to be supported on the aircraft landing portion. The vehicle and aircraft are configured such that the vehicle can provide at least one of fuel and electrical energy to the aircraft while the aircraft is supported on the aircraft landing portion.

Abstract translation: 机动车辆系统包括包括飞行器着陆部分的机动车辆和被配置为被支撑在飞行器着陆部分上的主动推进无人飞行器。 车辆和飞行器构造成使得当飞机被支撑在飞行器着陆部分上时，车辆可以向飞机提供燃料和电能中的至少一种。

公开(公告)号：EP1370460A1

公开(公告)日：2003-12-17

申请号：EP02703709.2

申请日：2002-02-26

Applicant: Walmsley, Eric Ronald

Inventor： Walmsley, Eric Ronald

IPC: B64C39/00 ,  B64C39/06 ,  B64D27/26

CPC classification number: B64C27/20 ,  B64C39/001 ,  B64C39/024 ,  B64C39/06 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/162

Abstract: A circular VTOL aircraft with a central vertically mounted turboprop engine (14), driving contra-rotating co-axial propellers (24), above a central jet engine, or engines (12), horizontally mounted on a turntable (11) and steerable through 360 degrees. The turboprop provides vertical thrust from propellers compressing air from an upper circular intake (5) downward through a circular funnel-shaped rotor-chamber (6), to a circular vent (10) at the base of the aircraft. The resulting column of compressed air gives lift for VTOL operations and a cushion of air in flight. The horizontally mounted turbine provides acceleration, retro-thrust and directional control for horizontal flight and vectored thrust for VTOL. An alternative engine configuration (Figure 9), replaces the turboprop and propellers with a vertical turbojet or rocket-engine system providing direct vertical thrust via four control vents (12/14), with an optional horizontal vectored thrust vent (15/37). he aircraft. Fuel-tanks are installed around the central engines. The flight-deck is at the top-centre of the craft above the engines, which are detachable for maintenance.

公开(公告)号：EP0629164A4

公开(公告)日：1995-07-12

申请号：EP93907455

申请日：1993-03-12

Applicant: SCHMITTLE HUGH J

Inventor： SCHMITTLE HUGH J

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C39/024 ,  B64C3/385 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

Abstract: The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66).

公开(公告)号：KR1019890000530B1

公开(公告)日：1989-03-20

申请号：KR1019820003604

申请日：1982-08-11

Applicant: 레이테온 이-시스템즈 인코포레이티드

Inventor： 찰스에이취.터버주니어 ,  프레데릭에이.베렌스 ,  존에이취.헌튼

IPC: B64C39/02

CPC classification number: F41G7/22 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208 ,  B64F1/06 ,  F41G7/007

Abstract: The remotely piloted aircraft has control surfaces asymmetrical in the pitch and yaw planes, a sensor, and a guidance system operative in the terminal portions of the flight of the aircraft in a yaw-to- turn mode with a zero roll rate. The system has a directional sensor for providing azimuth and elevation error signals. A device provides guidance signals indicative of the rate of change of the azimuth and elevation signals. A guidance programmer responds to the guidance signals for providing pitch control and yaw control signals. An altitude sensor provides an altitude control signal. Roll, pitch and yaw rate gyros provide a rate control signal and a three axis autopilot.

Abstract translation: 遥控飞行器具有在俯仰和偏航平面中不对称的控制表面，传感器和在零滚动速率的偏航 - 转弯模式下在飞行器的飞行的终端部分中操作的引导系统。 该系统具有用于提供方位角和仰角误差信号的方向传感器。 装置提供指示方位角和仰角信号变化率的指导信号。 指导程序员响应用于提供俯仰控制和偏航控制信号的引导信号。 高度传感器提供高度控制信号。 滚动，俯仰和偏航率陀螺仪提供速率控制信号和三轴自动驾驶仪。

公开(公告)号：US20180251218A1

公开(公告)日：2018-09-06

申请号：US15760259

申请日：2016-09-16

Applicant: Christopher Wilkinson

Inventor： Christopher Wilkinson

IPC: B64C39/02 ,  B64D1/04

CPC classification number: B64C39/024 ,  B64C2201/02 ,  B64C2201/046 ,  B64C2201/082 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/206 ,  B64C2201/22 ,  B64D1/04

Abstract: An unmanned aerial combat vehicle system is disclosed. The system provides for an unmanned aerial combat vehicle that is capable of performing reconnaissance, disrupting enemy communications, or delivering a weaponized payload. The unmanned aerial combat vehicle may also be equipped with a cloaking mechanism, where it can mask it's heat signature, or simulate an image on its outer surface.

公开(公告)号：US20140027579A1

公开(公告)日：2014-01-30

申请号：US13790655

申请日：2013-03-08

Applicant: Gerald Miller ,  James Stewart

Inventor： Gerald Miller ,  James Stewart

IPC: B64C19/00

CPC classification number: B64C19/00 ,  B64C39/028 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/203 ,  F41F3/042 ,  F41G7/008 ,  F41G7/2206 ,  F41G7/2253 ,  F41G7/2293 ,  F42B12/20 ,  F42B12/365 ,  F42B15/01 ,  F42B15/10 ,  G05D1/12

Abstract: An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.

Abstract translation: 一种无人驾驶飞行器，其包括在搜索操作模式下操作的控制器，其中采集传感器的接收器搜索目标并使飞行控制表面以向下的螺旋路径引导车辆，其中采集传感器检测到的操作的终端操作 目标并使飞行控制表面引导车辆朝向目标;以及激活操作模式，其中触发传感器检测到与车辆预定距离内的目标，并且控制器激活响应者。