公开(公告)号：US20060038067A1

公开(公告)日：2006-02-23

申请号：US10759742

申请日：2004-01-16

Applicant: Brian Dennis

Inventor： Brian Dennis

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/04

Abstract: Methods and apparatuses for launching and capturing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. The aircraft can then be retrieved from the recovery line. The boom can be retracted when not in use to reduce the volume it occupies.

Abstract translation: 描述了用于发射和捕获无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从包括可扩展起重臂的装置发射。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 然后可以从回收线检索飞机。 当不使用吊杆时，可以收起吊杆，以减少其占用的体积。

公开(公告)号：US06955324B2

公开(公告)日：2005-10-18

申请号：US10691724

申请日：2003-10-22

Applicant: Minas H. Tanielian

Inventor： Minas H. Tanielian

IPC: B64C13/20 ,  B64C27/20 ,  B64C39/02 ,  G01S3/786 ,  G05D1/00 ,  F41G7/00

CPC classification number: G01S3/786 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/208 ,  B64D2211/00 ,  G01S1/70 ,  G05D1/0022 ,  G05D1/101

Abstract: The present invention provides a position control system for a remote-controlled vehicle, a vehicle operated by the control system, and a method for operating a remote-controlled vehicle. An electromagnetic energy receiver is configured to receive an electromagnetic beam. The electromagnetic energy receiver is further configured to determine a position of the remote-controlled vehicle relative to a position of the electromagnetic beam. The vehicle is directed to maneuver to track the position of the electromagnetic beam.

公开(公告)号：US20050006525A1

公开(公告)日：2005-01-13

申请号：US10856360

申请日：2004-05-27

Applicant: David Byers ,  Gary Hall ,  Graham Hunter ,  Colen Kennell ,  Aleksander MacAnder ,  Judah Milgram ,  Jason Strickland

Inventor： David Byers ,  Gary Hall ,  Graham Hunter ,  Colen Kennell ,  Aleksander MacAnder ,  Judah Milgram ,  Jason Strickland

IPC: B64C1/00 ,  B64C1/06 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/02 ,  B64D5/00 ,  B64C27/22

CPC classification number: B64C1/068 ,  B64C1/061 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/105 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D5/00

Abstract: A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

Abstract translation: 中空的椭圆柱形船体适合地容纳中空矩形棱柱舱，由此四个纵向平行的外边缘与前者的内表面接触。 完全构造的飞机（非动力或动力）包括一体的船体加舱结构以及与其结合的鼻，尾和翼型结构。 机舱适合容纳用于货物存储的中空矩形模块。 当鼻部和/或尾部结构与整体的船体 - 舱室结构脱离时，模块被插入到舱室中，舱室被密封。 飞机被提升（例如，通过飞机，直升机，火箭或气球）到特定的高度并被释放，于是两翼完全出现，并且飞机实现控制的飞行直到到达其目的地。 在着陆后，鼻部和/或尾部结构与整体式的船体 - 舱室结构脱离，舱室被开封，模块从舱室中取出。

公开(公告)号：US06392213B1

公开(公告)日：2002-05-21

申请号：US09690000

申请日：2000-10-12

Applicant: Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

Inventor： Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

IPC: B64C351

CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load and high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单​​。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼片段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高负载和高温环境，并且可以容忍约16,000g的安装载荷。

公开(公告)号：US6056237A

公开(公告)日：2000-05-02

申请号：US882368

申请日：1997-06-25

Applicant: Richard L. K. Woodland

Inventor： Richard L. K. Woodland

IPC: B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C39/02 ,  B64D1/02 ,  B64D7/08 ,  B64D33/02 ,  F41G3/02 ,  F42B12/36 ,  F42B15/10 ,  F41G7/00 ,  B64C1/00

CPC classification number: B64C3/40 ,  B64C3/56 ,  B64C39/024 ,  B64C5/12 ,  B64D1/02 ,  B64D33/02 ,  B64D7/08 ,  F41G3/02 ,  F42B12/365 ,  F42B15/105 ,  F42B15/22 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/185 ,  B64C2201/203 ,  Y02T50/145

Abstract: The present invention is generally comprised of a sonotube-compatible unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV. The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section. The modular sections are attached to adjacent sections by uniform lock sealing rings and related components. The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming. A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight. Man-portable operation is accomplished by the use of a launch canister apparatus. The launch canister comprises retractable launch stabilizing legs, turbine engine exhaust orifices, and various antennas. The launch canister apparatus alternatively comprises a modified type "A", "B", or "C" sonotube launch canister. The system of the invention also comprises a portable Command, Control, Communications, Computer, and Intelligence (C4I) control and sensing analysis console. The console is preferably ruggedized, waterproof, shockproof, and comprises necessary control and analysis computers, input/output devices, antennas, and related hardware and software for vehicle and mission control. A C4I console and/or launch canisters may be transported by means of a backpack adapted for man portability.

Abstract translation: 本发明通常由声纳管相容的无人驾驶飞行器装置（以下称为无人机）和用于发射和控制无人机的系统组成。 无人机通常包括模块化部分，包括鼻部，有效载荷部分，机翼和燃料箱部分以及动力装置部分。 模块化部分通过均匀的锁定密封环和相关部件连接到相邻部分。 本发明包括一种能够进行预编程，通信或遥测任务编程的非常小的，便携式的，弹道发射的，自主的或半自主控制的车辆的装置。 可以在飞行中携带，使用或部署各种有效载荷包，包括应急用品，传感器和天线组件。 便携式操作通过使用发射罐装置来实现。 发射罐包括可伸缩发射稳定腿，涡轮发动机排气孔和各种天线。 发射罐装置可选地包括修改型“A”，“B”或“C”型超声波发射罐。 本发明的系统还包括便携式命令，控制，通信，计算机和智能（C4I）控制和感测分析控制台。 控制台最好是坚固耐用，防水，防震，并且包括必要的控制和分析计算机，输入/输出设备，天线以及用于车辆和任务控制的相关硬件和软件。 C4I控制台和/或发射罐可以通过适于人的便携性的背包来运输。

公开(公告)号：US5560568A

公开(公告)日：1996-10-01

申请号：US261901

申请日：1994-06-15

Applicant: Hugh Schmittle

Inventor： Hugh Schmittle

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

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C3/385 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/187 ,  B64D2201/00 ,  Y10S446/901

Abstract: Apparatus and method for recovering and arresting an aircraft on a floating platform is disclosed. The aircraft has a fuselage, a wing, and a source of propulsion for propelling the aircraft in flight. During landing approach, an inflatable cushion attached to the fuselage is deployed below the fuselage via inflation. In the inflated condition, a fastening material disposed on a downward facing surface of the cushion is thereby adapted to adhesively contact the floating platform deck so that the forward motion of the aircraft is slowed and arrested. In the preferred embodiment, the fastening material is one of male or female VELCRO.RTM. which is adapted to mate with corresponding VELCRO.RTM. material covering the platform deck.

Abstract translation: 公开了一种用于在浮动平台上恢复和拦截飞行器的装置和方法。 这架飞机有一个机身，一个机翼和一个推进的来源，用于在飞行中推进飞机。 在着陆过程中，通过充气将附着在机身上的充气垫部署在机身的下方。 在充气状态下，设置在缓冲垫的向下的表面上的紧固材料因此适于与浮动平台甲板粘合地接触，使得飞行器的向前运动变慢并且被阻止。 在优选实施例中，紧固材料是男性或女性VELCRO TM之一，其适于与覆盖平台甲板的相应的VELCRO TM材料配合。

公开(公告)号：US3980259A

公开(公告)日：1976-09-14

申请号：US564639

申请日：1975-04-02

Applicant: Richard David Greenhalgh ,  Ronald Alexander Saunders ,  George Reginald Seyfang

Inventor： Richard David Greenhalgh ,  Ronald Alexander Saunders ,  George Reginald Seyfang

IPC: B64C39/02 ,  B64D17/80

CPC classification number: B64C39/024 ,  B64D17/80 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/182 ,  B64C2201/205 ,  Y10S244/902

Abstract: A powered remotely piloted vehicle which is not controllable at the low landing speeds necessary for landing on a platform of small area is provided with a para-foil type wing deployable at the beginning of a recovery sequence, and is further provided with a rocket ejectable line which is passed to the landing platform and winched in so that the composite flight vehicle and deployed para-foil wing is drawn towards the platform after the manner of a kite.

Abstract translation: 在低平台上不能控制的低功率遥控车辆在降落在小平台的平台上所需的底盘上设置有可在恢复顺序开始时展开的对箔型翼，并且还设置有火箭弹出线 将其传递到着陆平台并绞盘，使得复合飞行器和部署的对箔翼沿着风筝的方式被吸引到平台上。

公开(公告)号：WO2016203279A1

公开(公告)日：2016-12-22

申请号：PCT/HU2016/000038

申请日：2016-06-13

Applicant: "BIZALOM" ZRT.

Inventor： GÁTI, Balázs

IPC: B64F1/06 ,  F41B3/03

CPC classification number: B64F1/06 ,  B64C2201/084 ,  F41B3/03

Abstract: The invention is a throwing device for throwing an object, particularly a winged aerial vehicle (26), the device comprising a throwing arm (10) having a throwing end (17) adapted for connecting the object thereto, a first shaft (14) rotatably connected to the throwing arm (10), and a support structure adapted for supporting the first shaft (14) allowing the rotation thereof. In the throwing device according to the invention the support structure comprises two support rods (12), each of which is connected to the first shaft (14) at respective lateral parts of the throwing arm (10), and, in a state wherein the throwing device is installed on a supporting surface (11), an actuating mass is connected to a second shaft (16) being rotatably connected to the throwing arm (10) between the connection of the first shaft (14) and the end of the throwing arm (10) being opposite the throwing end (17).

Abstract translation: 本发明是一种用于投掷物体的投掷装置，特别是一种有翼的空中飞行器（26），该装置包括具有适于将物体连接到其上的投掷端（17）的投掷臂（10），第一轴（14） 连接到投掷臂（10），以及适于支撑允许其旋转的第一轴（14）的支撑结构。 在根据本发明的投掷装置中，支撑结构包括两个支撑杆（12），每个支撑杆（12）在投掷臂（10）的相应横向部分处连接到第一轴（14），并且在其中 投掷装置安装在支撑表面（11）上，致动质量体连接到第二轴（16），第二轴（16）可旋转地连接到第一轴（14）的连接和投掷的端部之间的投掷臂（10） 臂（10）与投掷端（17）相对。

公开(公告)号：WO2015073091A1

公开(公告)日：2015-05-21

申请号：PCT/US2014/052829

申请日：2014-08-27

Applicant: ENGINEERED ARRESTING SYSTEMS CORPORATION

Inventor： TULLY, Andrew ,  PAGE, Dennis ,  WITHERS, Robert ,  NEELD, Kenneth ,  ORNER, Richard L.

IPC: B64F1/04 ,  B64F1/08 ,  B64C39/02

CPC classification number: B64F1/08 ,  B64C2201/084

Abstract: Embodiments of the present invention provide improvements to UAV launching systems. The disclosed launching system eliminates the use of hydraulic fluid and compressed nitrogen or air by providing an electric motor-driven tape that causes movement of a shuttle along a launcher rail.

Abstract translation: 本发明的实施例提供了对UAV发射系统的改进。 所公开的发射系统通过提供使电动机驱动的带子沿着发射轨运动，从而消除了液压流体和压缩的氮气或空气的使用。

公开(公告)号：WO2015046785A1

公开(公告)日：2015-04-02

申请号：PCT/KR2014/008464

申请日：2014-09-11

Applicant: (주)한국유에이브이

Inventor： 김무선 ,  홍용준

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C2201/084

Abstract: 개시된 무인항공기 발사장치는, 상방향을 향하도록 일정각도 경사지게 배치된 이동레일과;상기 이동레일을 따라 이동가능하게 구비되며 상부에 무인항공기가 안착되는 항공기이송체와; 일단은 상기 항공기이송체에 결합되고 타단은 렌치에 결합되어 상기 항공기이송체가 발사되는 추진력을 형성하는 견인와이어를 포함하는 이송체추진부와; 입력신호에 따라 상기 항공기이송체의 위치를 고정하거나 고정해제하는 이송체락킹부를 포함하며, 상기 견인와이어는 적어도 일영역에 상기 렌치에 구동에 의해 신장 또는 수축되며 상기 항공기이송체로 탄성력을 인가하는 탄성와이어를 포함하며, 상기 이송체락킹부는, 상기 항공기이송체의 양측에 회동가능하게 구비되어 상기 항공기이송체를 접촉지지하거나 이격되는 한 쌍의 락킹암과; 상기 락킹암이 회동되도록 상기 락킹암을 구동하는 락킹암구동부를 포함하며, 상기 항공기이송체는, 상기 레일삽입공간의 상하에 가로방향으로 배치되며 상기 이동레일과의 접촉에 의해 아이들회전하며 상기 항공기이송체의 이송을 안내하는 가이드베어링이 결합된 상부가이드축 및 하부가이드축과; 상기 레일삽입공간의 양측벽을 관통하여 상하로 결합되는 복수개의 수평지지축과; 상기 수평지지축을 탄성적으로 연결하며 상기 항공기이송체의 이송시 발생되는 충격을 완화하는 충격완충부재를 더 포함하하며, 상기 한 쌍의 락킹암은 "L"자 형태로 서로 마주보게 절곡형성되고, 상기 한 쌍의 락킹암의 사이에는 전후로 이동가능하게 배치되어 상기 락킹암을 회동시키는 락킹암구동부가 구비되며, 상기 락킹암은, 일단에 구비되어 상기 항공기이송체 내부로 삽입되는 삽입베어링과; 절곡영역에 배치되어 상기 락킹암구동부의 전후이동에 의해 상기 락킹암을 회전시키는 회전축과; 타단에 구비되어 상기 락킹암구동부와 접촉되는 회동베어링을 포함하는 것을 특징으로 한다.

Abstract translation: 公开了一种无人驾驶飞机发射装置，包括：移动轨道，其布置成以向上方向倾斜预定角度; 配置成沿着移动轨道移动的飞行器传送体，安装在飞行器传送体的上部的无人飞行器; 传送体推进单元，其包括牵引线，所述牵引线的一端联接到飞行器转移体，另一端联接到扳手，由此形成用于发射飞行器传送体的推进力; 以及转印体锁定单元，其用于锁定飞行器转移体的位置或根据输入信号释放锁定，其中牵引线在至少一个区域中包括通过扳手的驱动而延伸或收缩的弹性线，由此 向飞机转移体施加弹力; 转印体锁定单元包括一对锁定臂，可旋转地设置在飞行器传送体的两侧，并被构造成接触和支撑飞行器传送体或与飞行器传送体间隔开;以及锁定臂驱动单元，用于驱动 锁定臂使得锁定臂旋转; 飞行器传送体还包括在导轨插入空间的上部和下部沿宽度方向布置的上部和下部引导轴，并且构造成由于与移动轨道接触而空转，导向轴承联接到上部和 下引导件引导飞行器传送体的传送;多个水平支撑轴，其垂直穿过导轨插入空间的两个侧壁;以及冲击缓冲构件，弹性地连接水平支撑轴，并缓冲在飞行器转移期间产生的冲击 转运体; 一对锁定臂被弯曲并形成为彼此面对的L形，锁定臂驱动单元设置在该对锁定臂之间并且被布置成沿前后方向移动，从而旋转锁定臂; 并且锁定臂包括设置在其一端并插入飞行器传送体中的插入轴承，布置在弯曲区域中的旋转轴通过锁定臂驱动单元的向前/向后运动旋转锁定臂，以及设置在 其另一端与锁定臂驱动单元接触。