公开(公告)号：WO2005123502A2

公开(公告)日：2005-12-29

申请号：PCT/US2004/041583

申请日：2004-12-13

Applicant: ADVANCED CERAMICS RESEARCH, INC. ,  MULLIGAN, Anthony, C. ,  TROUDT, Christopher, D. ,  DOUGLAS, Jason, Michael, K.

Inventor： MULLIGAN, Anthony, C. ,  TROUDT, Christopher, D. ,  DOUGLAS, Jason, Michael, K.

IPC: B64C15/00

CPC classification number: G05D1/0094 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/205 ,  B64C2201/208

Abstract: Methods and apparatuses provide surveillance of a convoy. At least one unmanned aerial vehicle (UAV) obtains images around the convoy's position to provide information about potential hostile activity while the UAV follows a generally curvilinear path around the convoy as instructed by one of the convoy vehicles. Path planner algorithm software is executed by the controlling convoy vehicle in which position and velocity information regarding the unmanned aerial vehicle and the convoy are processed to determine values of control variables. The determined values are sent to the unmanned aerial vehicle over a wireless communications channel. The path of the surveillance vehicle may be changed in order to provide evasive measures to avoid an attack on the surveillance vehicle by an adversary.

Abstract translation: 方法和设备对车队进行监视。 至少一架无人驾驶飞行器（UAV）获取围绕车队位置的图像，以提供关于潜在敌对行为的信息，而无人机按照车队车辆指示的方式沿着车队周围的大致曲线路径。 路径规划器算法软件由控制车队车辆执行，其中处理关于无人机和车队的位置和速度信息以确定控制变量的值。 所确定的值通过无线通信信道发送到无人驾驶飞行器。 监视车辆的路径可能会改变，以便提供回避措施，以避免对手对监控车辆的攻击。

公开(公告)号：WO2005076788A3

公开(公告)日：2005-12-22

申请号：PCT/US2004009212

申请日：2004-03-25

Applicant: INSITU GROUP ,  MCGEER BRIAN T ,  ROESELER CORY ,  VON FLOTOW ANDREAS

Inventor： MCGEER BRIAN T ,  ROESELER CORY ,  VON FLOTOW ANDREAS

IPC: B64C3/56 ,  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 (150) can be launched from an apparatus that includes a launch carriage (120) that moves along a launch axis. A gripper (180) carried by the launch carriage can have at least one grip Portion (181) 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 fuselage of the aircraft as the launch carriage (120) decelerates, releasing the aircraft (150) for takeoff.

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（150）可以从包括沿着发射轴移动的发射台（120）的装置发射。 由发射托架承载的夹持器（180）可以具有与飞行器接触的至少一个手柄部分（181），同时发射托架沿着发射轴加速。 随着发射台（120）减速，至少一个把手部分可以与飞机的机身脱离接触，释放飞机（150）以起飞。

公开(公告)号：WO2005014390A2

公开(公告)日：2005-02-17

申请号：PCT/US2004/001033

申请日：2004-01-17

Applicant: THE INSITU GROUP ,  DENNIS, Bryan, D. ,  JACKSON, Clifford ,  MCGEER, Brian, T. ,  ROESELER, Cory ,  VONFLOTOW, Andreas, H.

Inventor： DENNIS, Bryan, D. ,  JACKSON, Clifford ,  MCGEER, Brian, T. ,  ROESELER, Cory ,  VONFLOTOW, Andreas, H.

IPC: B64B

CPC classification number: B64F1/02 ,  B63B27/26 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for assembling, launching, recovering, disassembling, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

Abstract translation: 描述了组装，发射，恢复，拆卸，捕获和存储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，飞行器可以由操作者很少或没有手动接合的容器组装。 容器可以包括用于控制飞行器部件的运动的引导结构。 飞机可以从包括可伸缩吊杆的装置发射。 可以扩展繁荣部署一个恢复线，以便在飞行中捕获飞机。 飞机然后可以返回到其发射平台，拆卸并存储在容器中，再次与操作员和飞机之间的很少或没有直接的手动接触。

公开(公告)号：WO2004060743A2

公开(公告)日：2004-07-22

申请号：PCT/US2003/039332

申请日：2003-12-09

Applicant: UNIVERSITY OF FLORIDA ,  IFJU, Peter ,  LEE, Kyu-Ho ,  ALBERTANI, Roberto ,  MITRYK, Shawn, J. ,  BORIA, Frank, J. ,  ABDULRAHIM, Mujahid

Inventor： IFJU, Peter ,  LEE, Kyu-Ho ,  ALBERTANI, Roberto ,  MITRYK, Shawn, J. ,  BORIA, Frank, J. ,  ABDULRAHIM, Mujahid

IPC: B64B

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过简单地从管中释放微型飞行器而从管展开。

公开(公告)号：WO1994016942A1

公开(公告)日：1994-08-04

申请号：PCT/US1994000590

申请日：1994-01-21

Applicant: FREEWING AIRCRAFT CORPORATION

Inventor： FREEWING AIRCRAFT CORPORATION ,  RUTAN, Elbert, L. ,  SCHMITTLE, Hugh, J.

IPC: B64C03/38

CPC classification number: B64C29/02 ,  B64C3/385 ,  B64C29/0033 ,  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: A VTOL/STOL free wing aircraft (100) includes a free wing (110) having wings on opposite sides of a fuselage (102) connected to one another respectively adjacent fixed wing inboard or center root sections (117) fixedly attached to the fuselage (102) for free rotation about a spanwise axis (112). Horizontal and vertical tail surfaces (138, 140) are located at the rear end of a boom assembly (120) rotatably connected to the fuselage (102). A gearing (150) or screw rod (160) arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage (102) in relation to the tail boom assembly (120) to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight.

Abstract translation: VTOL / STOL自由翼飞机（100）包括在机身（102）的相对侧上具有翅片的自由翼（110），它们分别相互连接，分别邻接固定在机身上的固定翼或固定地连接到机身的中心根部（117） 102），用于绕翼展轴线（112）自由旋转。 水平和垂直尾部表面（138,140）位于可旋转地连接到机身（102）的悬臂组件（120）的后端。 由飞行员或遥控操作员控制的传动装置（150）或螺杆（160）布置选择地相对于尾臂组件（120）相对地枢转机身（102），以使得机身能够呈现倾斜或起起落架构 以启用VTOL / STOL航班。

公开(公告)号：WO1985002349A1

公开(公告)日：1985-06-06

申请号：PCT/JP1983000428

申请日：1983-12-02

Applicant: IZUTSUYA, Kiyonobu

IPC: A63H27/12

CPC classification number: F02B75/243 ,  B64C27/06 ,  B64C27/12 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  F02B75/34

Abstract: A small, radio-controlled helicopter with an internal-combustion engine with two opposed, simultaneous-ignition cylinders to reduce ignition vibrations applied to the helicopter body. Thus, when this small helicopter is equipped with apparatus for video recording or photography, it is possible to obtain clear picture images while preventing any unwanted movement of the camera. In addition, various other operations, such as the spreading of pharmaceuticals and the guiding of lead ropes, can be conducted stably.

公开(公告)号：US20180244386A1

公开(公告)日：2018-08-30

申请号：US15893992

申请日：2018-02-12

Applicant: Top Flight Technologies, Inc.

Inventor： Long N. Phan

IPC: B64C39/02 ,  B64C27/12 ,  G08G5/00 ,  G01W1/02

CPC classification number: B64C39/024 ,  B64C27/12 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/125 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/208 ,  B64D2027/026 ,  G01W1/02 ,  G01W1/08 ,  G08G5/0069 ,  G08G5/0091

Abstract: An unmanned aerial vehicle includes an atmospheric sensor configured to measure an atmospheric condition. The unmanned aerial vehicle includes a rotor motor configured to drive rotation of a propeller of the unmanned aerial vehicle. The unmanned aerial vehicle includes a hybrid energy generation system including a rechargeable battery configured to provide electrical energy to the rotor motor; an engine configured to generate mechanical energy; and a generator coupled to the engine and configured to generate electrical energy from the mechanical energy generated by the engine, the electrical energy generated by the generator being provided to at least one of the rechargeable battery and the rotor motor.

公开(公告)号：US10035596B2

公开(公告)日：2018-07-31

申请号：US15693789

申请日：2017-09-01

Applicant: Top Flight Technologies, Inc.

Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

IPC: B64C27/08 ,  B64C39/02 ,  B64C27/00 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64F3/02 ,  G05D1/10

CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.

公开(公告)号：US20180118361A1

公开(公告)日：2018-05-03

申请号：US15542418

申请日：2016-01-11

Applicant: KOREAN AIR LINES CO., LTD.

Inventor： Seung Kie CHOI ,  Shin Je CHO ,  Sang Hun LEE

IPC: B64D31/06 ,  F02D9/02 ,  F02D41/14 ,  F02D41/26

CPC classification number: B64D31/06 ,  B64C39/024 ,  B64C2201/044 ,  B64D33/08 ,  F02D9/02 ,  F02D41/0002 ,  F02D41/14 ,  F02D41/1401 ,  F02D41/26 ,  F02D2200/021 ,  F02D2400/06 ,  Y02T10/42

Abstract: The present invention relates to a system for maintaining a constant temperature of an engine in an unmanned aerial system with an autothrottle limiting device, the system comprising: an autopilot 100 for issuing a throttle command; an autothrottle limiting device 200 for automatically limiting an upper limit of the throttle command issued by the autopilot 100; and a rotary engine 300 for feeding an internal temperature of the engine of the autopilot 100 back to the autothrottle limiting device 200. Thus, the system is applicable to all the kinds of unmanned aerial systems employing an air-cooling rotary engine (i.e. reciprocating engine), uses the existing autopilot of the unmanned aerial system without modification, improves the reliability and life of the engine, and safely takes the aerial vehicle back without accidents in the engine even though communication with a terrestrial system is interrupted.

公开(公告)号：US09957035B2

公开(公告)日：2018-05-01

申请号：US14172035

申请日：2014-02-04

Applicant: Texas A&M University System

Inventor： John Valasek ,  James Franklin May ,  Andrew Beckett ,  Cecil C. Rhodes, Jr.

IPC: B64C1/26 ,  B64C1/22 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C1/26 ,  B64C1/22 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/128 ,  B64C2211/00

Abstract: The present invention relates to an aircraft. The aircraft includes a fuselage module for receiving a payload. The fuselage module includes a plurality of internal connections. The aircraft includes a wing module adjustably coupled to the fuselage module and a tail module coupled to the wing module. The wing module may be adjusted relative to the fuselage module to adjust a location of an aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft. A main landing gear may be adjusted relative to the fuselage module to adjust the location of the aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft.