公开(公告)号：US07975959B2

公开(公告)日：2011-07-12

申请号：US11528647

申请日：2006-09-28

Applicant: Arie Perry ,  Ran Braier

Inventor： Arie Perry ,  Ran Braier

IPC: B64C25/50

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/187 ,  B64F1/00 ,  Y02T50/82

Abstract: A method for transferring airplanes and an unmanned airplane transfer system. The airplane transferring system includes: receiving a transfer signal responsive of a movement of an airplane control component; and transferring an airplane, by an unmanned airplane transfer system, in response to the transfer signal.

Abstract translation: 一种用于转移飞机和无人驾驶飞机转移系统的方法。 飞机传送系统包括：响应飞机控制部件的运动接收传送信号; 并且通过无人驾驶飞行器传送系统来响应于传送信号传送飞机。

公开(公告)号：US20110108675A1

公开(公告)日：2011-05-12

申请号：US12742667

申请日：2009-01-06

Applicant: Miron Tuval

Inventor： Miron Tuval

IPC: B64C3/32 ,  B64C39/08

CPC classification number: B64C3/16 ,  B64C3/32 ,  B64C11/001 ,  B64C39/024 ,  B64C39/04 ,  B64C39/066 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/165

Abstract: A wing that includes a lower portion that is located between two curved portions; wherein the lower portion is substantially flat and the two curved portions extend above the lower portion; wherein the wing defines a space that is wider than twice a diameter of a propeller that introduces a quasi-laminar stream if positioned in proximity to the wing and is circulated at a desired speed. The curved portions can be arcuated ends of the wing.

Abstract translation: 机翼，其包括位于两个弯曲部分之间的下部; 其中所述下部基本上是平坦的，并且所述两个弯曲部分在所述下部的上方延伸; 其中所述机翼限定了比推进器的直径大两倍的空间，所述推进器引入准层流，如果定位在机翼附近并以期望的速度循环。 弯曲部分可以是机翼的弧形末端。

公开(公告)号：US07922115B2

公开(公告)日：2011-04-12

申请号：US11789079

申请日：2007-04-23

Applicant: Richard D. Colgren ,  Lance C. Holly ,  William R. Donovan

Inventor： Richard D. Colgren ,  Lance C. Holly ,  William R. Donovan

IPC: B64C1/00 ,  B64C3/00

CPC classification number: B64C9/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2211/00

Abstract: The present invention is an unmanned air vehicle designed for reconnaissance, surveillance, data acquisition, and general research. The air vehicle is a monoplane that consists of several pieces that can easily be assembled using a minimal amount of tools. The air vehicle consists of a forward and aft fuselage section, two identical horizontal stabilizers, and four identical wing sections. The aircraft can fly with all four wing sections, or with just two wing sections (the short wing configuration). Each of the four wing sections of the air vehicle can be interchanged with any of the other wing sections for the purpose of minimizing assembly time and spare parts.

Abstract translation: 本发明是专为侦察，监视，数据采集和一般研究而设计的无人机。 空中飞行器是一个单翼飞机，由几个可以使用最少量的工具轻松组装的部件组成。 机动车由前后机身部分，两个相同的水平稳定器和四个相同的机翼部分组成。 飞机可以与所有四个翼部分飞行，也可以只飞过两个翼部（短翼配置）。 为了最小化组装时间和备件，飞行器车辆的四个翼部分中的每一个可以与任何其它翼部分互换。

公开(公告)号：US07837151B1

公开(公告)日：2010-11-23

申请号：US11523175

申请日：2006-09-18

Applicant: Frank Garcia, Jr.

Inventor： Frank Garcia, Jr.

IPC: B64D39/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64D39/04

Abstract: A system for the hookup of either a manned or unmanned air vehicle with a refueling air vehicle. A probe extending from an air vehicle being refueled is joined to a drogue at the end of a boom on a refueling air vehicle. In bringing the probe into the drogue an optical sensor on one of the vehicles is employed in conjunction with optical beacons on the other vehicle with the sensor measuring the relative motion between the probe and the drogue and generating a control signal for controlling motion of the probe relative to the drogue. The positioning of the probe relative to the drogue is accurately controlled during the fueling operation by a rigid actuator mechanism formed by a rod sidably fitted within a sleeve, the rod being driven by a tensioned reel in response to control signals. One end of the actuator is connected to the drogue while the other end is connected to the refueling aircraft to form a triangular configuration, allowing only small interaction forces thereby restraining relative motion between the probe and the drogue.

Abstract translation: 一种载人或无人驾驶飞行器与加油车辆的连接系统。 从被加油的空气车辆延伸的探头在加油飞行器上的吊杆末端连接到水龙头上。 在使探头进入锥套时，其中一个车辆上的光学传感器与另一车辆上的光学信号灯一起使用，传感器测量探头和锥套之间的相对运动，并产生用于控制探头运动的控制信号 相对于流氓。 探针相对于锥套的定位在加油操作期间通过由杆适于安装在套筒内的杆形成的刚性致动器机构被精确地控制，杆由响应于控制信号的张紧卷轴驱动。 致动器的一端连接到锥套，而另一端连接到加油飞机以形成三角形构造，仅允许小的相互作用力，从而限制探头和锥套之间的相对运动。

公开(公告)号：US07712702B2

公开(公告)日：2010-05-11

申请号：US11603810

申请日：2006-11-21

Applicant: Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

IPC: B64F1/06

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

Abstract translation: 描述了发射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，飞行器可以从包括沿发射导向装置移动的发射台的装置发射。 当滑架和/或发射引导件的部分相对于彼此移动时，托架可以加速。 由发射托架携带的夹具可以具有至少一个与飞行器接触的抓握部分，同时发射托架沿着发射轴加速。 当发射架减速时，至少一个把手部分可以与飞行器脱离接触，释放飞机起飞。 制动器可以在发射后阻止夹具的运动。

公开(公告)号：US20100065288A1

公开(公告)日：2010-03-18

申请号：US12210130

申请日：2008-09-12

Applicant: Osman Ersed Akcasu

Inventor： Osman Ersed Akcasu

IPC: B64D1/00

CPC classification number: F41G7/30 ,  A62C3/025 ,  A62C99/009 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/145 ,  B64D1/16 ,  F41G7/346 ,  F41G7/36 ,  F42B12/36 ,  F42B12/50 ,  F42B15/105

Abstract: A guided fire-retardant-containing bomb comprises a container with retractable wings, tail and elevators having the form factor of a conventional release vehicle, where the control surfaces are coupled via a controller to a GPS with inertial guidance control and an ability to receive external instructions, and a charge core to disintegrate and disperse the fire retardant or water.

Abstract translation: 引导阻燃的炸弹包括具有伸缩翼的容器，具有常规释放车辆的形状因子的尾部和电梯，其中控制表面通过控制器耦合到具有惯性引导控制的GPS并具有接收外部的能力 说明书和电荷核心，以分解和分散阻燃剂或水。

公开(公告)号：US20090206193A1

公开(公告)日：2009-08-20

申请号：US11450720

申请日：2006-06-09

Applicant: David J. File

Inventor： David J. File

IPC: B64C3/54 ,  B64C1/00

CPC classification number: B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  Y02T50/14

Abstract: An apparatus for increasing an aerodynamic surface area of an aircraft, e.g., a wing thereof, includes coaxially disposed first and second elongated airfoils and an inflatable device arranged to move the first airfoil coaxially relative to the second airfoil. The second airfoil has a root end fixed to the vehicle and an opposite outboard end, and the first airfoil is arranged to move axially between a retracted position generally inboard of the outboard end of the second airfoil and a deployed position generally outboard thereof. When the movable airfoil is deployed, a latching mechanism locks it in position. The inflatable device can include a collapsible duct that is sealed at one end and coupled at a second end to an inflating source, such as a reservoir of a compressed gas or a pyrotechnic gas generator.

Abstract translation: 用于增加飞行器（例如其翼）的空气动力学表面积的装置包括同轴布置的第一和第二细长翼型件以及布置成使第一翼型件相对于第二翼型件同轴地移动的可充气装置。 第二翼型件具有固定到车辆的根部端部和相对的外侧端部，并且第一翼型件布置成在第二翼型件的外侧端部的大致内侧的缩回位置和大致在其外侧的展开位置之间轴向移动。 当可移动翼片展开时，闩锁机构将其锁定就位。 可膨胀装置可以包括可折叠的管道，其在一端被密封并且在第二端处连接到充气源，例如压缩气体或烟火气体发生器的储存器。

公开(公告)号：US07542828B2

公开(公告)日：2009-06-02

申请号：US11160645

申请日：2005-07-01

Applicant: Daniel W. Steele ,  Joseph R. Chovan

Inventor： Daniel W. Steele ,  Joseph R. Chovan

IPC: G01C23/00 ,  B64C13/20

CPC classification number: B64D7/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165

Abstract: A small, reusable interceptor unmanned air vehicle (UAV), an avionics control system for the UAV, a design method for the UAV and a method for controlling the UAV, for interdiction of small scale air, water and ground threats. The UAV includes a high performance airframe with integrated weapon and avionics platforms. Design of the UAV first involves the selection of a suitable weapon, then the design of the interceptor airframe to achieve weapon aiming via airframe maneuvering. The UAV utilizes an avionics control system that is vehicle-centric and, as such, provides for a high degree of autonomous control of the UAV. A situational awareness processor has access to a suite of disparate sensors that provide data for intelligently (autonomously) carrying out various mission scenarios. A flight control processor operationally integrated with the situational awareness processor includes a pilot controller and an autopilot controller for flying and maneuvering the UAV.

Abstract translation: 一种小型，可重复使用的拦截无人机（UAV），无人机的航空电子控制系统，无人机的设计方法和无人机的控制方法，阻止小规模空中，水和地面威胁。 无人机包括具有集成武器和航空电子平台的高性能机身。 无人机的设计首先涉及选择合适的武器，然后设计拦截机体，以通过机身操纵实现武器瞄准。 无人机使用以车辆为中心的航空电子控制系统，因此提供了对UAV的高度自主控制。 情境感知处理器可以访问一套不同的传感器，可以智能地（自主地）执行各种任务场景。 与情境感知处理器可操作地集成的飞行控制处理器包括飞行员控制器和用于飞行和操纵无人机的自动驾驶仪控制器。

公开(公告)号：US20090026314A1

公开(公告)日：2009-01-29

申请号：US11782850

申请日：2007-07-25

Applicant: ELIE HELOU, JR.

Inventor： ELIE HELOU, JR.

IPC: B64C1/20 ,  B64C1/00

CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

Abstract translation: 用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。 翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。 轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。 梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。 飞机被认为是无人机。

公开(公告)号：US20080217486A1

公开(公告)日：2008-09-11

申请号：US11714436

申请日：2007-03-05

Applicant: Todd M. Colten ,  Scott E. Morgan ,  Christopher A. Launer

Inventor： Todd M. Colten ,  Scott E. Morgan ,  Christopher A. Launer

IPC: B64C3/38

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2211/00

Abstract: An unmanned aerial vehicle (UAV) is designed for low-speed, low altitude, long endurance missions typical to UAVs of this size and class. The UAV structure is configured to be substantially impervious to small arms fire and to have a very small representative radar cross-section. The UAV is modular such that the main wings and tail wing assembly are quickly and easily, detached from the fuselage for ease of transport and to provide an airframe that is quickly and easily adapted to any particular mission.

Abstract translation: 无人机（UAV）专为低速，低空，长寿命的任务而设计，适用于这种规模和类别的无人机。 UAV结构被配置为基本上不受小武器的威胁，并且具有非常小的代表性雷达横截面。 无人机是模块化的，使得主翼和尾翼组件快速容易地从机身脱离，以便于运输，并提供快速且容易地适应于任何特定任务的机身。