公开(公告)号：KR1020150120401A

公开(公告)日：2015-10-27

申请号：KR1020157024101

申请日：2013-08-23

Applicant: 디펜스 테크놀로지 인스티튜트(퍼블릭 올거니제이션) ,  로얄 타이 네이비 ,  세리 엔터프라이즈스 씨오., 엘티디. ,  카사마 헬리콥터 씨오., 엘티디.

Inventor： 따오른,카사마

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/048

Abstract: 본발명은트윈편향제어시스템(TYCS)를구비한수직이착륙무인항공기(VTOL UAV)이다. TYCS는메인회전자중심대에연결된보조회전자들(6)로구성된다. 이들은기어박스(3)로부터회전력을획득하여 VTOL UAV의이동을좌측및 우측방향으로제어할뿐만아니라공기중에서 VTOL UAV를상하로들어올리는수직방향으로충분한상승이이루어질때까지메인회전자중심대를중심으로한 메인회전자(5)의회전으로부터유도된토크에대응하기위한반-토크를생성한다. 이뿐만아니라, TYCS는메인회전자(5)의회전으로인한수직축을중심으로한 토크의균형을맞추는데도움이된다. 이를통해 VTOL UAV를항상수직축에평행하게정렬시킬수 있고, 이에따라비행중에외부조종사나자동비행제어시스템으로부터제어가필요없다.

公开(公告)号：KR1020170115330A

公开(公告)日：2017-10-17

申请号：KR1020160042843

申请日：2016-04-07

Applicant: 하상균

Inventor： 하상균

IPC: B64C39/02 ,  B64D1/18 ,  B64C21/02 ,  B64D45/00 ,  A62C3/02

CPC classification number: B64C39/024 ,  A62C3/0242 ,  B64C21/02 ,  B64C2201/02 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/12 ,  B64C2201/127 ,  B64C2201/146 ,  B64D1/18 ,  B64D45/00

Abstract: 본발명은소방용날개없는무인비행체에관한것으로, 날개를사용하지않고비행하면서소화용약제를자동분출하여, 소방용으로사용하기위한것이다. 이를위하여본 발명은, 중앙에개구부가형성되고단면형상이원통인케이스로이루어지는비행몸체부, 비행몸체부의케이스내부에구비되며모터와팬을케이스에내장하고팬에의해공기를유입및 토출시키는공기유입구와공기토출구를비행몸체부의케이스상부와하부에각각구비하여팬에의한상부공기의흡입과하부로의강제토출을통해비행몸체부에비행을위한추력을작용시키는추력발생부, 비행몸체부의케이스외측에구비되며지상의비행제어부에서송출되는모터구동을위한원격제어신호를수신하여추력제어부의모터작동을제어하는원격수신부, 추력발생부와원격수신부및 시스템의각 부에동작전원을공급하는전원공급부, 및비행몸체부의케이스내부에구비되며케이스의외부로노출된약제주입구와약제분사노즐을각각구비하여소화용약제를주입하여저장하거나분사하는약제저장부를포함하는무인비행체를제공하여, 열감지를통해화재현장등에신속하게투입되어화재진압을위한소방용으로사용가능하게한다.

公开(公告)号：KR1020060110471A

公开(公告)日：2006-10-25

申请号：KR1020050032736

申请日：2005-04-20

Applicant: 오원섭

Inventor： 오원섭

IPC: B64C29/00

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/162

Abstract: A vertical takeoff and landing aircraft is provided to prevent unbalance of a lift force appearing in a pulsator when the air plane straightly flies by rotating a blade in a case. A vertical takeoff and landing aircraft includes a body(120), at least two rotation section(130), and a case(201). The rotation section includes a rotational shaft and a blade. The rotation section is connected to the body. The case covers the body and the rotation section. An opening is formed in the case. The case has a duct-like shape in which the opening is formed so as to surround the rotation section. The case includes a side wall at the circumference of the blade of the rotation section.

Abstract translation: 提供垂直起降飞机，以防止当飞机通过在壳体中旋转叶片而直线飞行时出现在波轮中的升力的不平衡。 垂直起降飞机包括主体（120），至少两个旋转部分（130）和壳体（201）。 旋转部分包括旋转轴和叶片。 旋转部分连接到主体。 外壳覆盖主体和旋转部分。 在该情况下形成开口。 壳体具有其中形成围绕旋转部分的开口的管状形状。 壳体包括在旋转部分的叶片的圆周处的侧壁。

公开(公告)号：US09972212B1

公开(公告)日：2018-05-15

申请号：US15188904

申请日：2016-06-21

Applicant: Amazon Technologies, Inc.

Inventor： Samuel Sperindeo ,  Benji Barash ,  Yves Albers Schoenberg ,  Daniel Buchmueller

IPC: G05D3/00 ,  G08G5/00 ,  B64C39/02 ,  B64D47/08 ,  H04N7/18 ,  G06K9/62 ,  H04N17/00 ,  G06T7/60 ,  G06T7/40 ,  G06K9/52

CPC classification number: G08G5/0069 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/145 ,  B64D47/08 ,  G06K9/52 ,  G06K9/6215 ,  G06T7/408 ,  G06T7/60 ,  G06T2207/30204 ,  H04N7/185 ,  H04N17/002

Abstract: This disclosure describes systems, methods, and apparatus for automating the verification of aerial vehicle sensors as part of a pre-flight, flight departure, in-transit flight, and/or delivery destination calibration verification process. At different stages, aerial vehicle sensors may obtain sensor measurements about objects within an environment, the obtained measurements may be processed to determine information about the object, as presented in the measurements, and the processed information may be compared with the actual information about the object to determine a variation or difference between the information. If the variation is within a tolerance range, the sensor may be auto adjusted and operation of the aerial vehicle may continue. If the variation exceeds a correction range, flight of the aerial vehicle may be aborted and the aerial vehicle routed for a full sensor calibration.

公开(公告)号：US09920706B1

公开(公告)日：2018-03-20

申请号：US15009080

申请日：2016-01-28

Applicant: Dmitriy Yavid ,  Stephen Jon Blank

Inventor： Dmitriy Yavid ,  Stephen Jon Blank

IPC: F02G1/02 ,  B64G1/40 ,  F01B17/02 ,  F03G7/00 ,  B64C39/02 ,  H05B7/18 ,  F01B29/10

CPC classification number: F02G1/02 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/06 ,  B64G1/40 ,  B64G1/409 ,  F01B17/02 ,  F01B17/022 ,  F01B17/025 ,  F01B29/10 ,  F03G7/00 ,  H05B7/18

Abstract: Methods of laser powering unmanned aerial vehicles (UAV) with heat engines are disclosed. The laser powered heat engines are used in conjunction with devices for absorbing laser optical radiation, turning the laser optical radiation into heat, supplying the heat to a working fluid of the heat engine and harvesting mechanical work from expanding working fluid in the heat engine.

公开(公告)号：US09694894B2

公开(公告)日：2017-07-04

申请号：US14324306

申请日：2014-07-07

Applicant: Athene Works Limited

Inventor： Nicholas James Deakin

IPC: B64B1/20 ,  B64B1/02 ,  B64B1/08 ,  B64B1/10 ,  B64B1/12 ,  B64B1/14 ,  B64B1/38 ,  H01Q1/36 ,  H01Q9/27 ,  B64B1/64

CPC classification number: B64B1/02 ,  B64B1/08 ,  B64B1/10 ,  B64B1/12 ,  B64B1/14 ,  B64B1/20 ,  B64B1/38 ,  B64B1/64 ,  B64B2201/00 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  H01Q1/36 ,  H01Q9/27

Abstract: An aerial vehicle comprises an elongate envelope within which are at least one first compartment for holding a lighter than air gas and at least one second compartment for holding atmospheric air and said at least one second compartment having an inlet and an outlet and at least one pair of wings extending laterally from the envelope; said wings being planar units with a leading and trailing edge, the width of the wings from their leading edges to their trailing edges being substantially less than the length of the envelope with airfoil portions fitted between the leading and trailing edges of the wing: the top and bottom of the wings are mirror images of one another; in which forward motion of the vehicle is obtainable without trust through alternate diving and climbing motion.

公开(公告)号：US09677466B2

公开(公告)日：2017-06-13

申请号：US14966180

申请日：2015-12-11

Applicant: AIRBUS GROUP SAS

Inventor： Hichem Smaoui ,  Bruno Rechain ,  Fabien Retho

IPC: F02B65/00 ,  B64C39/02 ,  F02B37/00 ,  F02B33/40 ,  F01D15/10 ,  F02C6/12 ,  F02C6/14 ,  F02C6/20 ,  B60K6/24 ,  B60K6/38 ,  B60K6/40 ,  B60K6/44 ,  B60K6/387 ,  B60K6/442 ,  B64D27/02

CPC classification number: F02B65/00 ,  B60K6/24 ,  B60K6/387 ,  B60K6/40 ,  B60K6/442 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/048 ,  B64D2027/026 ,  F01D15/10 ,  F02B33/40 ,  F02B37/00 ,  F02C6/12 ,  F02C6/14 ,  F02C6/206 ,  F05D2220/329 ,  F05D2220/40 ,  F05D2220/62 ,  F05D2220/76 ,  F05D2220/90 ,  F05D2260/42 ,  Y02T10/144 ,  Y02T10/6234 ,  Y02T10/6295 ,  Y02T50/64 ,  Y02T50/671

Abstract: A method of managing a power demand to assure the operation of a pilotless aircraft. The aircraft includes an internal combustion engine supplying a maximum principal power which can vary. The management method is particularly suitable for a rotary wing pilotless aircraft. It guarantees the storage of an amount of electrical energy at least equal to a recovery energy of the aircraft in the event of failure of the internal combustion engine. This recovery energy enables the control of autorotation and landing of the aircraft.

公开(公告)号：US20160096613A1

公开(公告)日：2016-04-07

申请号：US14849814

申请日：2015-09-10

Applicant: Jonathon Thomas Johnson ,  Elizabeth V.M. Johnson

Inventor： Jonathon Thomas Johnson ,  Elizabeth V.M. Johnson

IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64C25/34 ,  B64C25/10

CPC classification number: B64C39/024 ,  B64C25/32 ,  B64C29/04 ,  B64C2025/325 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/16 ,  B64C2201/18

Abstract: Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system.

Abstract translation: 目前的飞机技术包括固定翼，多转子和矢量引擎设计。 固定翼技术和矢量引擎技术的综合已经实施，但仅限于传统的固定翼设计飞机。 所提出的飞机设计具有机身预期的创新，改进的矢量引擎设计系统和起落架系统。

公开(公告)号：US20100012790A1

公开(公告)日：2010-01-21

申请号：US12426162

申请日：2009-04-17

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C29/04

CPC classification number: B64C3/385 ,  B64C17/06 ,  B64C27/20 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/14

Abstract: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

Abstract translation: 一架垂直起降（VTOL）的空中客车。 机动车可以载人或无人驾驶。 在一个实施例中，空中交通工具包括安装在机身中的两个被覆盖的螺旋桨，机身和陀螺仪稳定盘。 陀螺稳定盘可以被配置成通过足够的质量和/或足够的角速度来提供足够的角动量，使得在飞行的各个阶段期间航空器的陀螺仪稳定。 在一个实施例中，机身固定地附接到被覆盖的螺旋桨。 在另一个实施例中，被覆盖的螺旋桨可枢转地安装在机身上。

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。