公开(公告)号：US07789341B2

公开(公告)日：2010-09-07

申请号：US11105746

申请日：2005-04-14

Applicant: Paul E. Arlton ,  David J. Arlton

Inventor： Paul E. Arlton ,  David J. Arlton

IPC: B64C27/08

CPC classification number: B64C27/10 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract translation: 旋转翼车辆包括具有细长管状骨架或芯体的主体结构，以及具有转子的反向旋转同轴转子系统，每个转子具有单独的电动机，以围绕公共转子旋转轴线驱动转子。 转子系统用于在定向飞行中移动旋翼机。

公开(公告)号：US20090303081A1

公开(公告)日：2009-12-10

申请号：US12133040

申请日：2008-06-04

Applicant: Richard E. Annati ,  David E. Ekhaguere

Inventor： Richard E. Annati ,  David E. Ekhaguere

IPC: G08B21/00

CPC classification number: B64D47/06 ,  B64C2201/141 ,  B64C2201/145

Abstract: Systems and methods for anti-collision lights on a UAV. A method for passive anti-collision lights on a Micro-Aerial Vehicle (“MAV”) including determining a location of the MAV using a flight management computer configured to fly the MAV on a programmed path using data from a global positioning system and an inertial navigation system. The flight management system transmits light activation data and selectively activates at least one navigation light located on a visible surface of the MAV using the light activation data from the flight management computer.

Abstract translation: 无人机上防碰撞灯的系统和方法。 一种在微型飞行器（MAV）上的被动防碰撞灯的方法，包括使用飞行管理计算机确定MAV的位置，所述飞行管理计算机被配置为使用来自全球定位系统和惯性的数据的编程路径飞行MAV 导航系统。 飞行管理系统透射光激活数据，并使用来自飞行管理计算机的光激活数据选择性地激活位于MAV的可视表面上的至少一个导航灯。

公开(公告)号：US20080308685A1

公开(公告)日：2008-12-18

申请号：US12139402

申请日：2008-06-13

Applicant: DARWIN KENT DECKER

Inventor： DARWIN KENT DECKER

IPC: B64D27/02

CPC classification number: B64D27/24 ,  B64C11/305 ,  B64C17/06 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64D2211/00 ,  F02K5/00 ,  Y02T50/12 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar powered air vehicle that can stay aloft for indefinite periods of time. The vehicle employs photovoltaic solar cells for primary power and high speed counter-rotating flywheels for energy storage and steering of the vehicle. The flywheels are placed in the wing to reduce airfoil drag. A control law provides three-axis stabilized control of the vehicle by controlling propeller pitch to vary the speeds of the flywheels.

Abstract translation: 太阳能动力的空中飞行器，可以在高处保持无限期的时间。 车辆采用光伏太阳能电池用于主电力和高速反向旋转飞轮，用于车辆的储能和转向。 飞轮放置在机翼中以减少机翼拖动。 控制规则通过控制螺旋桨桨距来改变飞轮的速度来提供对车辆的三轴稳定控制。

公开(公告)号：US07431243B1

公开(公告)日：2008-10-07

申请号：US11277325

申请日：2006-03-23

Applicant: Michael J. Allen

Inventor： Michael J. Allen

IPC: G05D1/00 ,  B64C31/02 ,  B64C13/00 ,  B64C19/00 ,  G01C23/00

CPC classification number: G05D1/0005 ,  B64C2201/141

Abstract: The present invention provides a practical method for UAVs to take advantage of thermals in a manner similar to piloted aircrafts and soaring birds. In general, the invention is a method for a UAV to autonomously locate a thermal and be guided to the thermal to greatly improve range and endurance of the aircraft.

Abstract translation: 本发明提供了一种实用的方法，用于无人机以类似于驾驶飞机和飞鸟的方式利用热量。 通常，本发明是一种UAV自主定位热量并被引导到热量的方法，以极大地提高飞机的射程和耐久性。

公开(公告)号：US07237750B2

公开(公告)日：2007-07-03

申请号：US10976153

申请日：2004-10-29

Applicant: Tien Seng Chiu ,  Jay Willmott

Inventor： Tien Seng Chiu ,  Jay Willmott

IPC: B64C1/00

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。

公开(公告)号：US07195200B2

公开(公告)日：2007-03-27

申请号：US10679984

申请日：2003-10-06

Applicant: Akihiro Yamane

Inventor： Akihiro Yamane

IPC: B64C13/16

CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  G05D1/0669 ,  G05D1/0676

Abstract: An unmanned helicopter includes an altitude control device for giving a command of a collective pitch blade angle based on an altitude change rate command, etc., and performing altitude control of an airframe and takeoff device, upon reception of a takeoff start command from the ground, for causing the airframe to take off and climbing the airframe to a first altitude while increasing the collective pitch blade angle without performing the altitude control of the altitude control device and then causing the altitude control device to start the altitude control. The unmanned helicopter further includes descending device for causing the airframe to descend to a second altitude while changing descent rate command of the altitude control device and giving a descent rate command smaller than the descent rate command to the second altitude to the altitude control device for causing the airframe to descend from the second altitude to the ground.

Abstract translation: 一种无人直升机包括一个高度控制装置，用于根据高度变化率命令等给出一个共同的桨叶角度的命令，并且在从地面接收到起飞开始命令时执行机体和起飞装置的高度控制 用于使机身在不执行高度控制装置的高度控制的同时增加集体桨叶角度而使机身起飞并爬升到第一高度，然后使高度控制装置开始高度控制。 无人直升机进一步包括下降装置，用于使机身下降到第二高度，同时改变高度控制装置的下降速率指令，并将低于下降速率指令的下降率指令提供给第二高度，以向高度控制装置引起 机身从第二高度下降到地面。

公开(公告)号：US20060262646A1

公开(公告)日：2006-11-23

申请号：US11135931

申请日：2005-05-23

Applicant: Dan Horak ,  Richard Burne

Inventor： Dan Horak ,  Richard 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.

公开(公告)号：US20050178896A1

公开(公告)日：2005-08-18

申请号：US10774653

申请日：2004-02-04

Applicant: David Cylinder

Inventor： David Cylinder

IPC: B64C33/02 ,  B64C39/02 ,  B64C39/08

CPC classification number: B64C39/08 ,  B64C33/02 ,  B64C39/024 ,  B64C2201/025 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146

Abstract: A vehicle for flying and having a forward portion and a rearward portion opposite the forward. The vehicle includes a first pair of wings arranged at the forward portion of the vehicle, a second pair of wings arranged at the rearward portion of the vehicle, and a support structure. The support structure is connected to the forward pair of wings and connected to the rearward pair of wings, the support structure being arranged to drive the forward pair of wings alternately toward each other and apart and drives the second pair of wings alternately toward each other and apart.

Abstract translation: 用于飞行并具有向前部分和与向前相对的后部的车辆。 车辆包括布置在车辆前部的第一对翼，布置在车辆后部的第二对翼和支撑结构。 支撑结构连接到前一对翼部并且连接到后一对翼部，支撑结构被布置成相互交替地驱动前一对翼片并分开，并且将第二对翼片彼此交替地驱动， 分开

公开(公告)号：US06908061B2

公开(公告)日：2005-06-21

申请号：US10877082

申请日：2004-06-25

Applicant: Yutaka Akahori

Inventor： Yutaka Akahori

IPC: B64B1/06 ,  B64C39/02 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/02 ,  G08G5/00 ,  B64B1/00

CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

Abstract translation: 根据本发明的飞艇系统具有飞艇（110），基站（120）和至少三个测量点。 飞艇（110）在接收到来自基站（120）的指令时发射超声波。 测量点单元（S 1 -S 3）接收超声波，从而测量从飞艇（110）到相应测量点的距离。 并入基站（120）的MPU计算飞艇（110）的位置。 基站（120）通过向飞艇（110）发送飞行指令，基于计算出的位置来控制飞艇（110）的路线。 以这种方式，可以提供一种飞艇系统，使得飞行员不需要飞行飞艇，并且可以减少飞艇的负载重量和功率消耗。

公开(公告)号：US06626397B2

公开(公告)日：2003-09-30

申请号：US09895332

申请日：2001-07-02

Applicant: Aharon Yifrach

Inventor： Aharon Yifrach

IPC: B65C300

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

Abstract translation: 无人驾驶飞行器包括具有至少两个围绕中心部分大致对称​​布置的翼部的自主飞行翼。 每个翼部可枢转地附接到每个相邻部分，使得翼部可折叠以用于存储并且可展开。 优选的形式是所谓的具有四个翼部的海鸥翼。 车辆可以从母机飞行器编程，同时使用可能是无线的数据链路承载到部署区域。