公开(公告)号：EP3315787A1

公开(公告)日：2018-05-02

申请号：EP17194522.3

申请日：2017-10-03

Applicant: Rolls-Royce Corporation

Inventor： Power, Bronwyn ,  Rivers, Jonathan

IPC: F04D29/32 ,  B64C11/00 ,  F01D5/14 ,  F01D5/22 ,  F02K3/04 ,  F02K3/072 ,  F02C9/58 ,  B64D27/00

CPC classification number: F04D29/282 ,  B23K2101/001 ,  B63H1/16 ,  B64C11/001 ,  B64C11/06 ,  B64C2201/162 ,  B64C2201/165 ,  B64D2027/005 ,  F01D5/143 ,  F01D5/225 ,  F02C9/58 ,  F02K3/04 ,  F02K3/072 ,  F04D29/326 ,  F04D29/329 ,  F04D29/34 ,  F05D2220/323 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2220/36

Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about -5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.

Abstract translation: 风扇系统包括具有多个叶片和环翼型件的转子，所述多个叶片可旋转地连接到轮毂和环翼型件。 该风扇系统可以包括具有多个叶片和环形翼型的第二反向旋转设置的转子。 第一和第二环形翼型具有弧形形状和大约-5度和大约45度之间的迎角，更优选地介于大约5度和大约30度之间。 可选地，出口导向叶片可以安装在具有环形翼型的一个或多个转子的后方。

公开(公告)号：EP3083398A1

公开(公告)日：2016-10-26

申请号：EP14821826.6

申请日：2014-12-17

Applicant: Neva Aerospace Ltd.

Inventor： BROTHERTON-RATCLIFFE, David ,  MARTIN, Laurent

IPC: B64C27/20 ,  B64C37/02 ,  B64C27/30

CPC classification number: B64C29/0033 ,  B64C27/20 ,  B64C27/30 ,  B64C37/02 ,  B64C39/024 ,  B64C2027/8227 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2211/00 ,  B64D27/10 ,  B64D27/24 ,  B64D35/04 ,  B64D35/06 ,  B64D2041/002 ,  G01C21/16 ,  G05D1/0088 ,  G08G5/0034

Abstract: A VTOL aircraft is disclosed comprising a plurality of autonomous lifting modules wherein each autonomous lifting module is composed of a physical structure in which are mounted one or more electric ducted fans, an electrical energy storage system to drive the electric ducted fans, a charging and energy storage monitoring system to charge and monitor the electrical energy storage system, an inertial navigation system, electronic speed controllers to control the electric ducted fans and one or more microcomputers assuring (a) module flight stability by control of the electric ducted fans given the input of the inertial navigation system, (b) flight planning and (c) inter-module communication.

公开(公告)号：EP2154066A3

公开(公告)日：2014-10-08

申请号：EP09162589.7

申请日：2009-06-12

Applicant: Honeywell International Inc.

Inventor： Ohanian III, Osgar John

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162

Abstract: Disclosed herein is a propulsion system (300), which may be implemented in an air-vehicle (100), such as a ducted-fan organic air-vehicle. The propulsion system (300) comprises (a) a power source, (b) a fan located within a duct and powered by the power source, (c) a plurality of vanes (302) arranged in an x-clocked configuration and configured to produce control moments from the flow generated by the fan. The maximum control moments, which can be created by the vanes (302) in the x-clocked configuration, are substantially oriented along the flight axes of the air-vehicle (100) or the principle axis of the maximum moment of inertia.

公开(公告)号：EP2716543A1

公开(公告)日：2014-04-09

申请号：EP12187089.3

申请日：2012-10-03

Applicant: Sensefly S.A.

Inventor： Beyeler, Antoine ,  Klaptocz, Adam ,  Roberts, James F. ,  Zimmermann, Loic ,  Zufferey, Jean-Christophe

IPC: B64C1/26

CPC classification number: B64C1/26 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/187 ,  B64C2201/20

Abstract: This invention relates to a connection set that is used to attach and transfer force and torque between a wing (2a, 2b), comprising a lifting surface and a control surface (9) connected together by a hinge, and the central body (1) of an aircraft, which contains a servo-motor (10) used for actuating said control surface (9). The wing (2a, 2b) is connected to the central body (1) using a connection set comprised of two components. First, an attachment mechanism (3, 4, 5, 6) is used to align the wings (2a, 2b) relative to the central body (1) and to transfer the aerodynamic forces acting on the wing (2a, 2b) to the central body (1), preventing the wing (2a, 2b) from bending at its connection point. Second, a torque coupling mechanism (7, 8) is used to actuate the control surfaces that are present on the wings using servomotors (10) that are embedded within the central body (1). The connection set is engaged and disengaged using a single motion and does not require additional connection of electrical cables or mechanical fixations.

Abstract translation: 本发明涉及一种用于在包括提升表面和通过铰链连接在一起的控制表面（9）的翼（2a，2b）之间附接和传递力和扭矩的连接组，以及中心体（1） 其包含用于致动所述控制表面（9）的伺服电动机（10）。 翼（2a，2b）使用由两个部件组成的连接组件连接到中心体（1）。 首先，使用附接机构（3,4,5,6）来相对于中心体（1）对准翼（2a，2b）并将作用在机翼（2a，2b）上的空气动力传递到 中心体（1），防止机翼（2a，2b）在其连接点处弯曲。 第二，扭矩联接机构（7,8）用于使用嵌入在中心体（1）内的伺服电动机（10）致动存在于机翼上的控制表面。 连接组使用单一动作进行接合和分离，不需要额外连接电缆或机械固定。

公开(公告)号：EP2181921A3

公开(公告)日：2014-03-12

申请号：EP09168642.8

申请日：2009-08-25

Applicant: Honeywell International, Inc.

Inventor： BOULDIN, Bruce Dan ,  BURDISSO, Ricardo

IPC: B64C27/20 ,  B64C39/02 ,  B64D33/02

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  B64D2033/0206

Abstract: A strut support system for a ducted fan unmanned aerial vehicle (12) to suppress noise comprising: a ducted fan fuselage (14) that defines an opening (42); an engine that extends longitudinally through the opening in the fuselage; a drive mechanism rotatably mounted to the engine, wherein a fan is mounted on the drive mechanism within a duct defined by the opening; and a plurality of struts (18) extending between the ducted fan fuselage and the engine each comprising a first leg (20) and a second leg (22) joined together by a curvilinear junction (24), wherein the first leg is attached to the ducted fan fuselage and the second leg is attached to the engine, wherein the plurality of struts are positioned upstream of the fan, wherein the junction between the first leg of each of the plurality of struts and the ducted fan fuselage is outside the highlight (26) of the ducted fan fuselage's leading edge (28).

公开(公告)号：EP2003057A3

公开(公告)日：2011-05-11

申请号：EP08157886.6

申请日：2008-06-09

Applicant: Honeywell International Inc.

Inventor： Goossen, Emray R.

IPC: B64C39/02 ,  B64D1/22

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/126 ,  B64C2201/128 ,  B64C2201/162 ,  B64D1/22

Abstract: A manipulator arm system (1) on a ducted air-fan UAV is disclosed herein. The target site may be accurately located by the UAV, and the manipulator system may accurately locate the payload at the target site. The manipulator arm may select tools from a toolbox located on-board the UAV to assist in payload placement or the execution of remote operations. The system may handle the delivery of mission payloads, environmental sampling, and sensor placement and repair.

公开(公告)号：EP1988014A3

公开(公告)日：2010-12-08

申请号：EP08155550.0

申请日：2008-05-01

Applicant: Honeywell International Inc.

Inventor： Colclough, John C.

IPC: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/02

CPC classification number: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/162 ,  Y02T50/14

Abstract: A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward fliglit operation without significantly impacting hover stability. One or more retractable wings (301) are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

公开(公告)号：EP2186726A2

公开(公告)日：2010-05-19

申请号：EP09169295.4

申请日：2009-09-02

Applicant: Honeywell International, Inc.

Inventor： Collette, Daniel Ross

IPC: B64C27/20 ,  B64C39/02 ,  B64D37/04 ,  B64D37/06 ,  B64D37/22

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  B64D37/04 ,  B64D37/06 ,  B64D37/22 ,  Y10T137/86212 ,  Y10T137/86348

Abstract: A vertical non-bladdered fuel tank (10) for a ducted fan vehicle comprising: a pod (12) that releasably connects to a core vehicle of a ducted fan vehicle, a vertical fuel tank contained by the pod, wherein the vertical fuel tank is centered between the fore (14) and aft (16) sides of the pod, an outlet (18) in a floor (20) of the vertical fuel tank located adjacent to a sidewall (22) on the fore side of the vertical fuel tank, wherein the outlet is coupled to a draw tube (24) contained by the core vehicle, and a pressure release vent (26) located at the highlight of the pod's duct.

Abstract translation: 一种用于管道式风扇车辆的垂直非风扇燃料箱（10），包括：可释放地连接到管道式风扇车辆的核心车辆的舱（12），由舱架容纳的垂直燃料箱，其中垂直燃料箱是 位于所述荚的前部（14）和后部（16）侧之间，所述立式燃料箱的地板（20）中的出口（18）位于所述垂直燃料箱的前侧附近的侧壁（22） ，其中所述出口连接到由所述核心车辆所容纳的牵引管（24）以及位于所述舱的管道的高亮处的压力释放通风口（26）。

公开(公告)号：EP2154066A2

公开(公告)日：2010-02-17

申请号：EP09162589.7

申请日：2009-06-12

Applicant: Honeywell International Inc.

Inventor： Ohanian III, Osgar John

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162

Abstract: Disclosed herein is a propulsion system (300), which may be implemented in an air-vehicle (100), such as a ducted-fan organic air-vehicle. The propulsion system (300) comprises (a) a power source, (b) a fan located within a duct and powered by the power source, (c) a plurality of vanes (302) arranged in an x-clocked configuration and configured to produce control moments from the flow generated by the fan. The maximum control moments, which can be created by the vanes (302) in the x-clocked configuration, are substantially oriented along the flight axes of the air-vehicle (100) or the principle axis of the maximum moment of inertia.

Abstract translation: 本文公开了一种推进系统（300），其可以在诸如管道式风扇有机机动车辆的空中飞行器（100）中实现。 推进系统（300）包括（a）电源，（b）位于管道内并由电源供电的风扇，（c）以x时钟配置布置的多个叶片（302） 从风扇产生的流量产生控制力矩。 由X形钟形构造中的叶片302产生的最大控制力矩大体上沿着空中车辆（100）的飞行轴线或最大惯性矩的主轴线定向。

公开(公告)号：EP2151379A2

公开(公告)日：2010-02-10

申请号：EP09161737.3

申请日：2009-06-02

Applicant: Honeywell International Inc.

Inventor： Collette, Daniel Ross ,  Helsing, JR., Joseph Scott

IPC: B64C27/20 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2211/00

Abstract: A pod (240) for an unmanned aerial vehicle is provided that may be removed and reattached to the vehicle. The pod comprises an outer shell, within which a variety of payloads may be carried. A first surface on the vehicle frame comprises a plurality of connects or electrical traces. The plurality of attachments are used to removably attach the pods to the first surface. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

Abstract translation: 提供用于无人驾驶飞行器的舱（240），其可以被移除并重新连接到车辆。 荚包括外壳，可在其内携带各种有效载荷。 车架上的第一表面包括多个连接或电迹线。 多个附件用于将荚可拆卸地附接到第一表面。 因此，简单地通过将不同的荚移除并附接到固定的车辆核心，可以使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚被附接到框架时，它们增强了车辆的空气动力学。