公开(公告)号：US20110073707A1

公开(公告)日：2011-03-31

申请号：US12233254

申请日：2008-09-18

Applicant: DAVID E. BOSSERT ,  Jeffrey N. Zerbe ,  Ray Sampson

Inventor： DAVID E. BOSSERT ,  Jeffrey N. Zerbe ,  Ray Sampson

IPC: B64F1/04 ,  B63G8/00 ,  H04Q5/22 ,  H01Q1/34

CPC classification number: F41F3/07 ,  B64C2201/201 ,  B64C2201/205 ,  F42B15/20

Abstract: Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.

Abstract translation: 根据本发明的各个方面的用于船舶部署的方法和装置可以与适于由船用车辆展开的可浮动壳体结合操作。 可浮动壳体可以适于从船用车辆发射并升起到地面。 诸如无人驾驶飞行器的资产可以从表面浮动的壳体部署。

公开(公告)号：US20100282906A1

公开(公告)日：2010-11-11

申请号：US12463400

申请日：2009-05-10

Applicant: Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

Inventor： Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

IPC: B64C3/00 ,  B64C1/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  F42B10/14 ,  F42B10/146 ,  F42B10/16 ,  F42B10/20

Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

Abstract translation: 层压翼结构包括至少一层金属材料和至少一层形状记忆聚合物（SMP）材料。 将SMP加热到其玻璃化转变带Tg的温度，以将机身周围的机翼卷绕成储存位置。 金属层必须足够薄以便在卷起时保持低于其屈服点。 在准备发射时，SMP材料被热激活，允许存储在金属材料层中的应变能在发射时将机翼返回到其展开位置。 一旦部署，SMP冷却到玻璃状态。 SMP材料可以用纤维增强以形成聚合物基质复合材料（PMC）。 SMP可用于为多个金属层提供剪切应变消除。 通过卸载将机翼从SMP返回到金属的原始展开位置所需的动力，聚合物不会获得永久变形，并且可以准确地展开机翼。

公开(公告)号：US20090236470A1

公开(公告)日：2009-09-24

申请号：US12051552

申请日：2008-03-19

Applicant: Emray R. Goossen ,  Yogendra Y. Sheoran

Inventor： Emray R. Goossen ,  Yogendra Y. Sheoran

IPC: B64F1/14

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64C2201/208 ,  B64F1/04

Abstract: A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster and a duct configured to direct airflow generated by the thruster includes a capture plate and an extension. The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.

Abstract translation: 用于捕获具有推进器和构造成引导由推进器产生的气流的管道的垂直起飞和着陆（VTOL）车辆的发射和捕获系统包括捕获板和延伸部。 捕获板被配置为改变气流并产生吸引到捕获板的管道的力。 延伸部联接到捕获板，并且被构造成至少有利于将VTOL车辆保持抵靠捕获板。

公开(公告)号：US07530527B2

公开(公告)日：2009-05-12

申请号：US10558312

申请日：2004-05-20

Applicant: Christopher Charles Kelleher

Inventor： Christopher Charles Kelleher

IPC: B64D5/00 ,  B64F1/04

CPC classification number: B64C37/02 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/101 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/201 ,  B64D5/00

Abstract: A heavier-than-air air vehicle, particularly a long endurance, solar powered, unmanned aerial vehicle (UAV) intended for “perpetual” flight within the stratosphere, is carried to its operational altitude suspended on a tether from a helium balloon. The tether is attached at or towards a tip of the UAV's wing so that it is carried in effectively a 90° banked attitude. At the desired altitude the UAV's powerplant is started and it flies on its tether in an upwardly-spiralling path relative to the balloon until a level or near level attitude is attained, when the tether is released and the UAV is permitted to assume free flight.

Abstract translation: 一架重型空中飞行器，特别是用于在平流层内“永久”飞行的长寿命的太阳能无人驾驶飞行器（UAV）被运载到悬挂在氦球系绳上的作战高度。 系绳连接在无人机翼的顶端或朝向无人机翼的尖端，以便有效地承载90度的坦克姿态。 在所需的高度，UAV的动力装置启动，并且相对于气球以相对于气囊的向上螺旋方式飞行，直到达到水平或接近水平的姿态时，系绳被释放并且UAV被允许进行自由飞行。

公开(公告)号：US07338010B2

公开(公告)日：2008-03-04

申请号：US10951041

申请日：2004-09-23

Applicant: David A. Corder ,  Jeffrey H. Koessler ,  George R. Webb

Inventor： David A. Corder ,  Jeffrey H. Koessler ,  George R. Webb

IPC: B64C3/56

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/145 ,  B64C2201/165 ,  B64C2201/201

Abstract: An air-launched aircraft includes deployable wings, elevons, and vertical fins that deploy from a fuselage during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and/or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The aircraft may be employed at a low cost for any of a wide variety of functions, such as surveillance, or as a decoy. The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.

Abstract translation: 一架空中飞机包括在飞行期间从机身部署的可部署的机翼，电梯和垂直翼片。 飞机可以包括用于操作电梯的控制系统，通信系统和用于为系统供电的电池。 此外，飞机可以包括与机身中的接口相配合的有效载荷模块。 有效载荷模块可以包括各种有效载荷中的任何一种，包括相机，传感器和/或雷达发射器。 该飞机可能是动力或无动力的，并且可能非常小，例如小于10kg（22磅）的量级。 飞机可以以低成本从事各种功能，例如监视或作为诱饵。 飞机的可展开的表面可以被配置成以预定的顺序部署，允许飞机在以翻滚模式发射之后自动进入受控飞行。

公开(公告)号：US07210654B1

公开(公告)日：2007-05-01

申请号：US10625399

申请日：2003-07-23

Applicant: Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

IPC: B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64F1/06 ,  F42B12/365 ,  Y02T50/82

Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

Abstract translation: 一种无人机载侦察系统，无人机载侦察系统，包括轻型便携式动力飞机和折叠式发射轨道，该飞机处于分解状态，发射导轨处于可折叠状态的箱体内，该箱体能够 由一个男人携带。 发射系统包括具有滑架组件的细长的发射轨道和用于将滑架组件从发射轨道的一端加速到另一端的推进装置。 滑架组件可释放地接合飞行器，以便将飞机从发射轨的一端推动到另一端。 推进可以是通过气缸爆炸和释放气体的弹药筒或弹性帘线。 飞机通过编程的机载计算机被引导通过空中，控制飞机的控制面和/或通过遥控。 飞机通常包含用于记录和发射从下面接地的图像的照相机。

公开(公告)号：US20060255205A1

公开(公告)日：2006-11-16

申请号：US11314316

申请日：2005-12-22

Applicant: Peter Gleich ,  Franz Maier

Inventor： Peter Gleich ,  Franz Maier

IPC: B64C3/56

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  F42B15/105

Abstract: A small aircraft has a fuselage (airframe), control apparatus, and a drive. A propeller electric drive, a power supply, a TV camera, data transmission and steering electronics, and a warhead and/or a weapon system are integrated in the fuselage. Collapsible and/or foldable wings, control surfaces, and propellers are positioned on the fuselage. The small aircraft according to the invention may be equipped with different weapon systems for combating different targets or for different missions.

Abstract translation: 一架小型飞机有机身（机体），控制装置和驱动器。 在机身中集成有螺旋桨电动驱动器，电源，电视摄像机，数据传输和转向电子装置以及弹头和/或武器系统。 可折叠和/或可折叠的机翼，控制表面和螺旋桨位于机身上。 根据本发明的小型飞机可配备有用于对抗不同目标或不同任务的不同武器系统。

公开(公告)号：US20060102783A1

公开(公告)日：2006-05-18

申请号：US10758956

申请日：2004-01-16

Applicant: Brian Dennis ,  Clifford Jackson ,  Brian McGeer ,  Andreas von Flotow

Inventor： Brian Dennis ,  Clifford Jackson ,  Brian McGeer ,  Andreas von Flotow

IPC: B64F1/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/06 ,  B64F1/222

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. The boom can be retracted when not in use to reduce the volume it occupies. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft and the recovery line.

Abstract translation: 描述了用于捕获和恢复无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 当不使用吊杆时，可以收起吊杆，以减少其占用的体积。 耦合到回收管线的张紧装置可以吸收与飞行器和回收管线的冲击相关联的力。

公开(公告)号：US20060091258A1

公开(公告)日：2006-05-04

申请号：US10976153

申请日：2004-10-29

Applicant: Tien Chiu ,  Jay Willmott

Inventor： Tien Chiu ,  Jay Willmott

IPC: B64C27/22

CPC classification number: B64C1/00 ,  A45C5/00 ,  A45C13/02 ,  B64C1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2201/203

Abstract: A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability while being readily separated so as to enable the UAV to break apart at these connection points and thereby absorb or dissipate impact upon landing. The UAV is capable of rapid assembly in the field for two-man launch and data retrieval, as well as quick disassembly into these five component parts for transport and storage in a highly compact transport case that can be carried as a backpack.

Abstract translation: 具有机身，鼻锥，左翼片，右翼片和尾部的模块化无人驾驶飞行器（UAV）。 尾部和鼻锥每个通过配合的隔板结构连接到机身，提供快速的连接能力，同时易于分离，以便使UAV在这些连接点处分裂，从而吸收或消散着陆时的冲击。 无人机能够在现场快速组装两人发射和数据检索，以及快速拆卸到这五个部件中，用于运输和存储，可以作为背包携带的高度紧凑的运输箱。

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。