公开(公告)号：KR1020120106771A

公开(公告)日：2012-09-26

申请号：KR1020127016102

申请日：2010-11-24

Applicant: 에어로바이론먼트, 인크.

Inventor： 피셔,크리스토퍼이. ,  슈말젤,마크엘. ,  챔벌스,스티븐 ,  매칼리스터,저스틴비.

IPC: B64F5/00 ,  G06F19/00 ,  B64C3/18

CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/102

Abstract: 시스템/장치 구성을 결정하고, 결정된 구성에 기반하여 작동 모드를 설정하는 방법(160), 시스템(200), 및 장치(110)를 포함한다. 항공기 처리기(110)는 (a) 적어도 하나의 외부 부품의 부품 정보 세트(14)를 수신하고, (b) 현재 작동 모드 설정을 구비한 처리기(110)에 의해, 수신된 부품 정보 및 초기 작동 모드 설정과 현재 작동 모드 설정 중 적어도 하나에 기반하여, 작동 모드를 결정하고(162), (c) 하나 이상의 수신된 부품 정보 세트 모두가 구성 요건에 부합하는지를 판단하고(163), (d) 공동 부합하는 것으로 판단한 경우, 비행 준비 상태로 전환하고(166), (e) 공동 부합하지 않는 것으로 판단한 경우, 재설정 상태로 전환한다(164).

公开(公告)号：EP3299279B1

公开(公告)日：2018-10-17

申请号：EP16203012.6

申请日：2016-12-08

Applicant: Bell Helicopter Textron Inc.

Inventor： IVANS, Steven Ray ,  ROSS, Brent Chadwick

IPC: B64C3/56 ,  B64C29/00 ,  B64C39/02 ,  B64D35/04 ,  B64D27/14

CPC classification number: B64C3/56 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/102 ,  B64C2201/108 ,  B64D27/14 ,  B64D35/04 ,  Y02T50/14

Abstract: An aircraft (100) has a fuselage (102), an engine (112) disposed within the fuselage (102), a rotatable wing (104) disposed above the fuselage (102) and selectively rotatable about a wing rotation axis, and a plurality of interconnect driveshafts (128) disposed within the rotatable wing (104), and at least one drive system component that is connected between the engine (112) and the interconnect driveshaft (128) is disposed along the wing rotation axis.

公开(公告)号：EP3374260A1

公开(公告)日：2018-09-19

申请号：EP16864692.5

申请日：2016-04-21

Applicant: Area-I Inc.

Inventor： ALLEY, Nicholas Robert ,  STEELE, Joshua Lemming ,  WILLIAMS, Jesse Owen ,  KUEHME, Daniel ,  PHILLIPS, Jonathan Caleb

IPC: B64C3/56

CPC classification number: B64C3/40 ,  B64C1/36 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C11/28 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2211/00 ,  Y02T50/14 ,  Y02T50/44

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

公开(公告)号：EP3368413A1

公开(公告)日：2018-09-05

申请号：EP16788767.8

申请日：2016-10-28

Applicant: BAE Systems PLC

Inventor： WRIGHT, Julian, David ,  COLOSIMO, Nicholas, Giacomo, Robert ,  WARSOP, Clyde

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/18

Abstract: An air vehicle (10) comprising a main body (12)and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12), at least a first propulsion device (16) associated with a first of said wing members (14a) and a second propulsion device (16) associated with a second of said wing members (14b), each said propulsion device (16) being arranged and configured to generate linear thrust relative to said main body (12), in use, the air vehicle further comprising a control module for generating a control signal configured to change a mode of flying of said air vehicle, in use, between a fixed wing mode (Figure 2) and a rotary wing mode (Figure 3), wherein, in said fixed wing mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body (12) is the same as the direction of thrust generated by the second propulsion device (16), and in said second mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body is opposite to that generated by the second propulsion device (16).

公开(公告)号：EP3041739B1

公开(公告)日：2018-08-29

申请号：EP14799061.8

申请日：2014-04-28

Applicant: Raytheon Company

Inventor： ELKINS, Erick W. ,  MURPHY, Matthew G. ,  THOMAS, Scott D.

IPC: B64C39/02

CPC classification number: B64D1/12 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/206

Abstract: A container is used to launch a small aircraft, such as an unmanned aerial vehicle (UAV), from a host aircraft. The container protects the UAV from stresses during the initial ejection from a launcher that is part of the host aircraft. The initial stresses may be due to turbulence in the vicinity of the host aircraft, high airspeed, and/or tumbling that may result from the ejection from the host aircraft moving at a high airspeed. The container may deploy a drag device, such as a drogue chute, to slow the container down and reorient the container, prior to deployment of the UAV from the container. During the time between ejection from the host aircraft and deployment from the container, the UAV may be powered up and acquire data, such as global positioning system (GPS) data, to allow the UAV a “hot start” enabling immediate mission commencement.

公开(公告)号：EP3286083A1

公开(公告)日：2018-02-28

申请号：EP16718861

申请日：2016-04-20

Applicant: COOK GEORGE MICHAEL

Inventor： COOK JONATHAN EDWARD ,  COOK MICHAEL KEVIN

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2211/00

Abstract: An aerial delivery assembly (10) for autonomously delivering a load to a target location, the assembly comprising an airframe which comprises a main body (12), at least one deployable lift providing structure (30), the lift providing structure being moveable between a stowed position and a deployed position; and at least one deployable and adjustable control structure (34, 36, 38, 39) for controlling the flight of the assembly and moveable between a stowed position and a deployed position. The main body (12) comprises a compartment for receiving a load to be delivered. The assembly further comprises a control unit (20) comprising an actuation module for use in adjusting the control structure (34,36, 38, 39), wherein the control unit is releaseably connected to the airframe such that it is reusable in an aerial delivery assembly having a different airframe.

公开(公告)号：EP2516256B1

公开(公告)日：2017-11-22

申请号：EP10843503.3

申请日：2010-12-17

Applicant: Tufts University

Inventor： BRIGHT, Alfram, V. ,  WLEZIEN, Richard

IPC: B64C3/30 ,  B64C3/56

CPC classification number: B64C3/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/127 ,  D06M10/001 ,  D06M10/10 ,  D06M15/327 ,  E04H12/00 ,  F03D13/20 ,  H05G2/00 ,  Y02E10/728

Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements rapidly inflated and rigidized using an acrylic adhesive and UV light generated by combustion, which find use, for example, in rapidly deploying and supporting the wing of an aerial vehicle and wind turbine towers.

公开(公告)号：EP2858898B1

公开(公告)日：2017-10-18

申请号：EP13832668.1

申请日：2013-06-07

Applicant: AeroVironment, Inc.

Inventor： ANDRYUKOV, Oleksandr

IPC: B64C39/00

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201

公开(公告)号：EP3055203A1

公开(公告)日：2016-08-17

申请号：EP15703674.0

申请日：2015-01-22

Applicant: Northrop Grumman Systems Corporation

Inventor： TORRE, Christopher N.

IPC: B64C1/30 ,  B64C3/56 ,  B64C39/02

CPC classification number: B64C3/56 ,  B64C1/30 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/201

Abstract: An unmanned aerial vehicle (UAV) can be deployed from a small stowed package for flight and stowed back into the package after the flight is complete is disclosed. The UAV is retracted to a volume that is less than half of its fully deployed volume. This allows the UAV to be transported to any desired field position on a truck or other convenient transportation. The UAV may also be launched from a ship deck. In a further aspect, the flexible deployment of the UAV will allow a single UAV to be used in place of multiple types of UAVs.

公开(公告)号：EP2714512A2

公开(公告)日：2014-04-09

申请号：EP12723862.4

申请日：2012-05-23

Applicant: Blue Bear Systems Research Limited

Inventor： GREEN, John ,  GEOGHEGAN, Philip ,  SNOOK, Michael Alexander

IPC: B64C39/02 ,  B64C27/605 ,  B64C27/32 ,  B64C27/58

CPC classification number: B64C27/605 ,  B64C27/00 ,  B64C27/08 ,  B64C27/32 ,  B64C27/50 ,  B64C27/58 ,  B64C27/59 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/108 ,  B64D27/02 ,  B64D27/24 ,  B64F1/04

Abstract: Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.

Abstract translation: 本发明的实施例涉及一种火箭或弹道发射旋翼飞行器。