公开(公告)号：WO2011137335A1

公开(公告)日：2011-11-03

申请号：PCT/US2011/034543

申请日：2011-04-29

Applicant: ELBIT SYSTEMS OF AMERICA, LLC ,  FISHER, Jeremy, F.

Inventor： FISHER, Jeremy, F.

IPC: B64C3/56 ,  B64D1/02 ,  F42B15/10

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，耦合到机身并可操作以通过飞行推进声纳浮标的发动机，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进行飞行的位置。 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。

公开(公告)号：WO2009059173A1

公开(公告)日：2009-05-07

申请号：PCT/US2008/082041

申请日：2008-10-31

Applicant: RAYTHEON COMPANY ,  KINSEY, Lloyd, E. ,  KRANKING, Patrick, D.

Inventor： KINSEY, Lloyd, E. ,  KRANKING, Patrick, D.

IPC: B64C29/02

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

Abstract translation: 根据本发明的各个方面的用于变换航空器的方法和装置可以与被配置为围绕其纵向轴线旋转飞行器的发射系统一起操作。 枢转地连接到飞行器的提升表面可以被定位成使得飞行器的旋转导致提升表面在飞行器上产生提升力。 该升降机使得飞行器在提升表面旋转到第二位置之前陀螺地升高，使得飞行器从陀螺仪模式转换为固定翼型飞行器。 然后可以再次旋转提升表面，以允许飞行器作为自动陀螺仪着陆。

公开(公告)号：WO2007078473A3

公开(公告)日：2008-01-24

申请号：PCT/US2006045548

申请日：2006-11-29

Applicant: ITT MFG ENTERPRISES INC ,  PAGE GREGORY S

Inventor： PAGE GREGORY S

IPC: B64F1/10

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  F42B15/36

Abstract: A takeoff assist device for an air vehicle, such as an unmanned air vehicle is provided. The device features an electric motor and is much less complex and lighter than takeoff assist devices heretofore known. A body member is shaped to fit to a portion of the air vehicle. The body member defines a housing in which the majority of the components are housed, including the electric motor, a motor controller, an electrical power source and a main controller. A propeller is attached to a shaft of the electric motor outside of the housing and rotates with a shaft of the electric motor. In addition, there is a latch mechanism that removeably attaches the body member to the host air vehicle for takeoff, and then is controlled to release from the air vehicle after it is airborne at a desired airspeed and altitude. The electric motor-driven takeoff assist device can launch an air vehicle with minimal auxiliary equipment and can be remotely controlled to launch from a site at which a takeoff ready vehicle can be left for extended periods of time.

Abstract translation: 提供了一种用于空中客车的起飞辅助装置，例如无人机。 该装置具有电动机，并且比迄今为止已知的起飞辅助装置复杂和轻巧。 身体构件被成形为适合于空中车辆的一部分。 主体构件限定了容纳大部分部件的壳体，包括电动马达，马达控制器，电源和主控制器。 螺旋桨安装在外壳外的电动机的轴上，并与电动机的轴一起旋转。 此外，还有一个可将主体部件可移除地连接到主机空中的起飞位置的闩锁机构，然后在空气车辆以期望的空速和高度空降后被控制以释放。 电动马达起飞辅助装置可以发射具有最小辅助设备的空中飞行器，并且可以远程控制以从起飞准备好的车辆可以长时间留下的地点发射。

公开(公告)号：WO2007086055A1

公开(公告)日：2007-08-02

申请号：PCT/IL2007/000090

申请日：2007-01-25

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD. ,  SOMECH, Haim

Inventor： SOMECH, Haim

IPC: B64C39/02 ,  B63B35/52 ,  B64D17/80 ,  B64F1/02

CPC classification number: B64C39/024 ,  B63B35/52 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/145 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/185 ,  B64C2201/205 ,  B64F1/02

Abstract: The invention provides a system, method and landing device for landing an aircraft (50) with respect to a predetermined landing location (P). The aircraft is configured for powered flight at least when the parafoil (60) is deployed, and includes an automatic landing system for controllably executing a landing approach maneuver for the aircraft while in free powered flight with the parafoil deployed to enable the aircraft to be brought into overlying proximity with the landing location. A landing device in the form of an energy absorbing landing net arrangement (20) is provided at the landing location for enabling the aircraft to be landed thereon at least partially vertically when in overlying proximity, and for dampening the landing impact of the aircraft.

Abstract translation: 本发明提供了一种用于相对于预定着陆位置（P）降落飞机（50）的系统，方法和着陆装置。 该飞机至少在翼展（60）部署时配置为动力飞行，并且包括一个自动着陆系统，用于在自由动力飞行中可控制地执行飞机的着陆进场操纵，其中部署了翼型飞机以使飞机能够被带到 与着陆位置相邻。 在着陆位置处设置能量吸收着陆网装置（20）形式的着陆装置，用于使飞机在覆盖在邻近位置时至少部分垂直地落在其上，并用于减轻飞机的着陆冲击。

公开(公告)号：WO2007078473A2

公开(公告)日：2007-07-12

申请号：PCT/US2006/045548

申请日：2006-11-29

Applicant: ITT MANUFACTURING ENTERPRISES, INC. ,  PAGE, Gregory, S.

Inventor： PAGE, Gregory, S.

IPC: B64F1/04

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  F42B15/36

Abstract: A takeoff assist device for an air vehicle, such as an unmanned air vehicle is provided. The device features an electric motor and is much less complex and lighter than takeoff assist devices heretofore known. A body member is shaped to fit to a portion of the air vehicle. The body member defines a housing in which the majority of the components are housed, including the electric motor, a motor controller, an electrical power source and a main controller. A propeller is attached to a shaft of the electric motor outside of the housing and rotates with a shaft of the electric motor. In addition, there is a latch mechanism that removeably attaches the body member to the host air vehicle for takeoff, and then is controlled to release from the air vehicle after it is airborne at a desired airspeed and altitude. The electric motor-driven takeoff assist device can launch an air vehicle with minimal auxiliary equipment and can be remotely controlled to launch from a site at which a takeoff ready vehicle can be left for extended periods of time.

Abstract translation: 提供了一种用于空中客车的起飞辅助装置，例如无人机。 该装置具有电动机，并且比迄今为止已知的起飞辅助装置复杂且轻巧。 身体构件被成形为适合于空中车辆的一部分。 主体构件限定了容纳大部分部件的壳体，包括电动马达，马达控制器，电源和主控制器。 螺旋桨安装在外壳外的电动机的轴上，并与电动机的轴一起旋转。 此外，存在一个可将主体部件可移除地附接到主机空中车辆用于起飞的闩锁机构，并且随后被控制以在所需的空速和高度空降后从空中车辆释放。 电动马达起飞辅助装置可以发射具有最少辅助设备的空中飞行器，并且可以远程控制以从起飞准备好的车辆可以长时间留下的地点发射。

公开(公告)号：WO2005023642A2

公开(公告)日：2005-03-17

申请号：PCT/US2004/004720

申请日：2004-02-19

Applicant: AAI CORPORATION ,  MILLER, Stephen, W. ,  VELAZQUEZ, Matthew, T.

Inventor： MILLER, Stephen, W. ,  VELAZQUEZ, Matthew, T.

IPC: B64B

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

Abstract translation: 提供了一种便携式无人驾驶飞行器和发射系统，其包括具有压力管的可折叠无人驾驶飞行器; 用于发射气体的发射气藏; 操作地连接到发射气体储存器并具有位于空中载体的压力管中的自由端的发射管; 位于发射管内的自由活塞; 和自由活塞止挡件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中，并且将自由活塞从初始位置推动到自由活塞由自由活塞停止的终止位置。

公开(公告)号：WO1993017908A1

公开(公告)日：1993-09-16

申请号：PCT/US1993002267

申请日：1993-03-12

Applicant: SCHMITTLE, Hugh

IPC: B64C03/38

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).

Abstract translation: 垂直起落架飞机（10）包括一个自由翼（16），其在机身（12）的相对侧上具有彼此连接的翼，用于联合自由旋转，并且在飞行员，计算机或遥控器下进行差速俯仰设置。 在电梯（26），方向舵（24）和机翼的差距俯仰设置上分别进行垂直发射，俯仰，偏转和滚转控制。 在发射时，升降机（26）将机身（12）向下方延伸以改变推力矢量并向飞行器提供水平速度，由此自由翼（16）相对于机身（12）旋转成大致水平的方向以提供 在水平飞行期间升降。 从水平到垂直飞行的过渡是通过相反的过程实现的，并且飞机可以在弹性表面（例如网）（66）中或其上轻轻回收。

公开(公告)号：KR1020170078847A

公开(公告)日：2017-07-07

申请号：KR1020177017487

申请日：2010-09-09

Applicant: 에어로바이론먼트, 인크.

Inventor： 미랄레스,카로스토마스 ,  수,구안에이치. ,  앤드류코브,오렉산드르 ,  맥네일,존

IPC: B64F1/06 ,  B64C39/02 ,  F42B39/14 ,  F41A21/02 ,  F41F3/042 ,  B64F1/04 ,  B64C13/20

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14 ,  B64C13/20 ,  B64C2201/084

Abstract: 무인항공기(UAV) 발사관(100)은, 직육면체개구(305) 둘레에배치된적어도하나의내부프리프레그기재층(370); 직육면체개구(305) 둘레에배치된적어도하나의외부프리프레그기재층(380); 및적어도하나의내부프리프레그기재층(340)과적어도하나의외부프리프레그기재층(380) 사이에배치된하나이상의구조판(structural panel, 341~344)을포함한다. UAV 발사관(100)은, 내벽으로정의된발사장치체적내에서무인항공기(UAV)에맞물리도록구성되고, 내벽에서압력밀봉을제공하도록치수가정해지며내벽에테더링된테더링이탈피(700, 740)를포함하며, 이때 테더링이탈피(700, 740)는고압체적을향해배향된개방단및 이탈피(700)의중공(910) 내에서부착된테더(740)를구비하여중공으로이루어지며, 내벽에부착되어고압체적을유지하거나기저내벽(1013)에부착된다. 시스템은, 통신노드(1500~1505); 및발사전 상태에서통신노드(1500~1505)로부터명령입력을수신하고이에응답하도록구성된 UAV를포함하는발사장치(1520)를포함한다.

公开(公告)号：KR101710248B1

公开(公告)日：2017-02-24

申请号：KR1020147032342

申请日：2013-04-16

Applicant: 윈텍 애로우메이커 인코퍼레이티드

Inventor： 존스존찰스 ,  그리고리프아르템이고르비치 ,  에스피노사루이스카를로스

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C2201/084

Abstract: 휴대용무인항공시스템(UAS) 발사장치는내부트랙을갖는레일조립체, 및내부트랙내에서이동하도록구성된베이스를갖는캐리지조립체를포함한다. 캐리지조립체는또한 UAS를지지하도록구성된크래들, 및크래들을베이스위에지지하도록구성된브래킷을포함한다. UAS 발사장치는발사제어시스템을포함하며, 발사제어시스템은발사제어시스템이발사신호를수신할때까지캐리지조립체를발사-준비위치에고정시키도록구성된다. UAS 발사장치는또한캐리지조립체및 레일조립체와맞물리도록구성된하나이상의탄성부재를포함한다. 일단캐리지조립체가발사-준비위치로이동되면, 하나이상의탄성부재에의해긴장이캐리지조립체에가해진다. 캐리지조립체의해제는탄성부재의긴장에의해발생된힘이캐리지조립체를발사위치를향해추진시키는것을가능하게한다.

Abstract translation: 便携式无人机系统发射器（UAS）发射器包括具有内部轨道的轨道组件和具有被配置为在内部轨道内平移的底座的滑架组件。 托架组件还包括支架，其构造成支撑UAS和支架，所述托架被构造成支撑在基座上方的托架。 UAS发射器包括发射控制系统，其配置成将支架组件固定在发射准备位置，直到发射控制系统接收到发射信号。 UAS发射器还包括一个或多个弹性构件，其构造成接合滑架组件和轨道组件。 一旦滑架组件被转换到发射就绪位置，则通过一个或多个弹性构件将应变施加到滑架组件。 托架组件的释放使得由弹性构件的应变产生的力能够将托架组件推向发射位置。

公开(公告)号：KR1020150001841A

公开(公告)日：2015-01-06

申请号：KR1020147032342

申请日：2013-04-16

Applicant: 윈텍 애로우메이커 인코퍼레이티드

Inventor： 존스존찰스 ,  그리고리프아르템이고르비치 ,  에스피노사루이스카를로스

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64F1/04

Abstract: 휴대용 무인 항공 시스템(UAS) 발사장치는 내부 트랙을 갖는 레일 조립체, 및 내부 트랙 내에서 이동하도록 구성된 베이스를 갖는 캐리지 조립체를 포함한다. 캐리지 조립체는 또한 UAS를 지지하도록 구성된 크래들, 및 크래들을 베이스 위에 지지하도록 구성된 브래킷을 포함한다. UAS 발사장치는 발사 제어 시스템을 포함하며, 발사 제어 시스템은 발사 제어 시스템이 발사 신호를 수신할 때까지 캐리지 조립체를 발사-준비 위치에 고정시키도록 구성된다. UAS 발사장치는 또한 캐리지 조립체 및 레일 조립체와 맞물리도록 구성된 하나 이상의 탄성 부재를 포함한다. 일단 캐리지 조립체가 발사-준비 위치로 이동되면, 하나 이상의 탄성 부재에 의해 긴장이 캐리지 조립체에 가해진다. 캐리지 조립체의 해제는 탄성 부재의 긴장에 의해 발생된 힘이 캐리지 조립체를 발사 위치를 향해 추진시키는 것을 가능하게 한다.

Abstract translation: 便携式无人机系统发射器（UAS）发射器包括具有内部轨道的轨道组件和具有被配置为在内部轨道内平移的底座的滑架组件。 托架组件还包括支架，其构造成支撑UAS和支架，所述托架被构造成支撑在基座上方的托架。 UAS发射器包括发射控制系统，其配置成将支架组件固定在发射准备位置，直到发射控制系统接收到发射信号。 UAS发射器还包括一个或多个弹性构件，其构造成接合滑架组件和轨道组件。 一旦滑架组件被转换到发射就绪位置，则通过一个或多个弹性构件将应变施加到滑架组件。 托架组件的释放使得由弹性构件的应变产生的力能够将托架组件推向发射位置。