公开(公告)号：US08014909B2

公开(公告)日：2011-09-06

申请号：US10575223

申请日：2004-03-25

Applicant: Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

Inventor： Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

IPC: G06F17/00 ,  B64C13/00

CPC classification number: B64C39/024 ,  B64C13/20 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/205 ,  G05D1/0027 ,  G05D1/0684

Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract translation: 用于控制飞机飞行的系统具有传感器（37,43），接收器（45）和数字控制系统（57），所有这些都被携带在飞行器上。 传感器（37,43）确定飞行器相对于地球的位置和飞行器的惯性运动。 接收器（45）接收传送参考车辆相对于地球的位置和移动的传送数据（51,55）。 控制系统（57）使用来自传感器（37,43）和接收器（45）的数据来计算飞机相对于参考车辆的位置和速度，然后命令飞行器上的飞行控制装置（33）进行操纵 飞行器以相对于参考车辆保持选定位置和/或速度的方式。 该系统允许使用图形或触觉的用户界面。

公开(公告)号：US07980510B2

公开(公告)日：2011-07-19

申请号：US10569653

申请日：2004-05-12

Applicant: Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

Inventor： Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

IPC: B64C11/46 ,  B64D27/00 ,  B64D33/00

CPC classification number: A63H27/02 ,  B64C39/028 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  Y10S244/903

Abstract: A small unmanned airplane includes; a main wing having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers placed at blade tips of left and right of the main wing; and two propellers installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

Abstract translation: 一架小型无人机包括 主翼具有下表面近似平坦的弧形翼型，其锥形形状变窄到其前端具有遮光角度的叶片尖端，其具有无风翼型的空气动力学表面的飞翼型，并且是低方位 比; 在主翼的左右两侧的后缘部分中大致极宽的可动翼片至少在水平飞行中具有二面角; 放置在主翼左右叶片尖端的垂直稳定器; 并安装在主翼顶面的两个螺旋桨。 这可以实现小型化和轻量化的小型无人驾驶飞机的个人承载能力和适合性，例如用手抛出。

公开(公告)号：US20110127378A1

公开(公告)日：2011-06-02

申请号：US13020970

申请日：2011-02-04

Applicant: William R. McDonnell

Inventor： William R. McDonnell

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将UAV（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

公开(公告)号：US07789339B2

公开(公告)日：2010-09-07

申请号：US11475085

申请日：2006-06-27

Applicant: Geoffrey S. Sommer

Inventor： Geoffrey S. Sommer

IPC: B64D5/00

CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

Abstract: Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

Abstract translation: 提供了用于形成具有高纵横比翼平台的多关节飞行系统（天基）的系统和/或方法，其可操作以在高海拔地区的感兴趣区域上游荡。 在某些示例性实施例中，自主模块化飞行器以翼尖到翼尖的方式连接在一起。 这样的模块化飞行器可以从日晒中获得其功率。 自主传单可以包括单独操作的传感器，或者在形成天空基础之后集体运行。 天空基优选地可以按照主要条件的要求进行聚合，分解和/或再聚集。 因此，可能提供“永远在车”的飞机。

公开(公告)号：US20100051741A1

公开(公告)日：2010-03-04

申请号：US12230638

申请日：2008-09-03

Applicant: Anvar Ismailov

Inventor： Anvar Ismailov

IPC: B64C1/00 ,  B64C3/38 ,  B64D37/04 ,  B64F1/04 ,  B64C11/00 ,  B64D27/24 ,  B64D27/00 ,  G05D1/02 ,  F41A9/00 ,  F42B15/00 ,  B64F1/02 ,  B64F1/00 ,  F02K7/00

CPC classification number: F42B10/64 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208 ,  F42B10/14

Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

Abstract translation: 用于军事，陆上安全等操作的无人驾驶飞行器包括设置有可折叠翼的机身，其具有前缘翼片和后缘副翼，其可以在发射时上升操作以控制翼折叠的飞行图案，翼部署成 在适当的时候打开展开位置。 车辆被容纳在发射的荚内，并且提供着陆甲板以在车辆返回陆地时减速和阻止车辆。

公开(公告)号：US20090257313A1

公开(公告)日：2009-10-15

申请号：US12372702

申请日：2009-02-17

Applicant: Dan T. Horak ,  Richard A. Burne

Inventor： Dan T. Horak ,  Richard A. Burne

IPC: G01S3/80

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/165 ,  F42B12/365 ,  G01S3/8083

Abstract: Embodiments for determining the bearings to targets from a remote location are disclosed. The apparatus consists of an array of acoustic sensors that is capable of autonomous flight. The array may be large in diameter, approximately one meter or greater. The apparatus is capable of navigating its flight to arrive at a predetermined location, measuring acoustic sound waves emitted by targets both during flight and after landing. The apparatus may then calculate the bearings to the targets and transmit this information to a remote location.

Abstract translation: 公开了从远程位置确定到目标​​的轴承的实施例。 该装置由能够自主飞行的声学传感器阵列组成。 该阵列的直径可以大，大约一米或更大。 该装置能够导航其飞行到达预定位置，测量在飞行中和着陆之后目标发出的声音波。 然后，设备可以计算到目标的轴承并将该信息传送到远程位置。

公开(公告)号：US07584925B2

公开(公告)日：2009-09-08

申请号：US11877201

申请日：2007-10-23

Applicant: Stephen W. Miller ,  Matthew Velazquez

Inventor： Stephen W. Miller ,  Matthew Velazquez

IPC: B64C3/56 ,  B64F1/04

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 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: 一种便携式无人机和发射系统，包括具有压力管的可折叠无人机; 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：US20090134273A1

公开(公告)日：2009-05-28

申请号：US11064287

申请日：2005-02-22

Applicant: Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

Inventor： Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

IPC: B64C1/00 ,  B28B5/00 ,  B64F1/04

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/165 ,  B64C2201/201

Abstract: An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container. In a second configuration, a launch assembly is provided, that includes an elastic tether connecting a UAV to an accelerated mass for gentle acceleration to flight speed under a stable tow.

Abstract translation: 提供无人驾驶飞行器（UAV），使用和制造具有成本效益，并且包括低数量的部件，允许任务规划人员以一次性方式使用无人机。 无人机包括具有中心体的机身和从中心体延伸的翼，限定内腔。 机身包括一个上部和下部壳体，每个都由整体塑料构成。 上壳体和下壳体之间具有限定了堆叠构造的燃料箱和有效载荷的壁。 机身还可以包括配置成包围有效载荷舱并有助于机身的中心体的有效载荷盖。 还提供发射组件。 在第一配置中，提供了一种发射组件，其包括用于容纳多个UAV的容器和启动无人机从容器的快速喷射的展开机构。 在第二构造中，提供了一种发射组件，其包括将UAV连接到加速质量块的弹性系绳，以在稳定的丝束下平缓加速到飞行速度。

公开(公告)号：US20090045295A1

公开(公告)日：2009-02-19

申请号：US11838731

申请日：2007-08-14

Applicant: Gert Lundgren

Inventor： Gert Lundgren

IPC: G05D1/08 ,  B64C27/22

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/165

Abstract: A vertical/short take-off and landing aircraft with a single proprotor assembly that has a pair of inline counter-rotating rotors. Two inline counter-rotating engines are directly connected to the rotors. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the proprotor assembly permits thrust to be directed forward to back and left to right to control pitch and roll when hovering. Varying the relative engine speeds controls yaw. The aircraft is adaptable as an unmanned vehicle.

Abstract translation: 具有单个推进器组件的垂直/短距起飞和着陆飞机，其具有一对在线的反向旋转的转子。 两个直列反向旋转发动机直接连接到转子上。 一个引擎在水平飞行中关闭以提高效率。 安装推进器组件的万向节允许推动力向前指向前向左并向左转，以便在悬停时控制俯仰和滚动。 改变相对发动机转速来控制偏航。 该飞机适用于无人驾驶的车辆。

公开(公告)号：US20080210818A1

公开(公告)日：2008-09-04

申请号：US11822278

申请日：2007-07-03

Applicant: Tien-Seng Chiu ,  Jay Willmott ,  Kirk Jenkins

Inventor： Tien-Seng Chiu ,  Jay Willmott ,  Kirk Jenkins

IPC: B64C1/00 ,  B64C1/10 ,  A45C5/00

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。