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：EP2691299A1

公开(公告)日：2014-02-05

申请号：EP12712624.1

申请日：2012-03-27

Applicant: Institut Supérieur De L'Aéronautique Et De L'Espace

Inventor： MOSCHETTA, Jean-Marc ,  THIPYOPAS, Chinnapat

IPC: B64C39/02

CPC classification number: B64C39/028 ,  B64C25/36 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2201/18 ,  B64D45/06

Abstract: The invention relates to a microscale radio-controlled aerial vehicle, having a fixed wing (as opposed to a rotary wing) comprising propulsion means (23, 24), said vehicle comprising a means for traveling on the ground, which are attached to the side ends of a section (18) of the wing, the rotational axis Y1 of the wheels (25) being located in front of the center of gravity (31) of the micro-drone (40), the center of gravity (31) of the micro-drone (40) being located in front of the aerodynamic center (32) of the micro-drone, the rotational axis Y1 of the wheels (18) being aligned with the thrust axis of the propulsion means (23, 24), and the traveling means (25) including wheels (25) sized such that the radius D/2 thereof is greater than the distance between the rotational axis Y1 of the wheels and the trailing edge of the wing.

公开(公告)号：EP2616335A1

公开(公告)日：2013-07-24

申请号：EP11770063.3

申请日：2011-09-16

Applicant: Reiter, Johannes

Inventor： Reiter, Johannes

IPC: B64C29/00 ,  B64C29/02 ,  B64C39/02

CPC classification number: B64C29/00 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165

Abstract: The present invention relates to an aircraft (110) for vertical take-off and landing. The aircraft comprises a first wing (101), a second wing (102) and a fuselage (103). The first wing (101) comprises a first longitudinal wing axis (104) and the second wing (102) comprises a second longitudinal wing axis (104). The first wing (101) extends along the first longitudinal wing axis (104) and the second wing (102) extends along the second longitudinal wing axis (104) from the fuselage (103). The first wing (101) is tiltable with a first rotational direction around the first longitudinal wing axis (104) and the second wing (102) is tiltable with a second rotational direction around the second longitudinal wing axis (104). The wings (101, 102) are adapted in such a way that, in a fixed- wing flight mode, the wings (101, 102) do not rotate around a second axis (105). The wings (101, 102) are further adapted in such a way that, in a hover flight mode, the wings (101, 102) are tilted around the longitudinal wing axis (104) with respect to its orientation in the fixed- wing flight mode and that the wing (100) rotates around the second axis (105).

公开(公告)号：EP2540623A2

公开(公告)日：2013-01-02

申请号：EP12173757.1

申请日：2012-06-27

Applicant: Aerovel Corporation

Inventor： McGeer, Brian T. ,  Coatney, Robert S.

IPC: B64C39/02

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/182 ,  B64F1/04 ,  B64F1/22

Abstract: An aircraft 1, 101 capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for a small vessel. For retrieval, the aircraft hovers over a base apparatus 6 having one or more rails 5, 105 which bound a space into which the aircraft can safely descend. When the aircraft's measured position and velocity are appropriate, the aircraft descends promptly such that a spanwise component 4, 104 on the aircraft engages the rails. The teeth 8, 108 restrain the aircraft in position and orientation, while the rails bring the aircraft to rest. Articulation of the rails is used to park the aircraft in a servicing station 14. Connections for refueling, recharging, and/or functional checks are made in preparation for launch. Launch is effected by removing connections and restraints and articulating the rails to put the aircraft in an appropriate position and orientation. The aircraft uses its own thrust to climb out of the apparatus into free flight.

Abstract translation: 一种飞行器1，101能够推力传飞行的可自动检索，维修和使用适合于小容器设备启动。 进行检索，飞机悬停在具有结合的空间到其中的飞行器可以安全地下降一个或多个导轨5，105的基座装置6。 当测量飞机的位置和速度是适当的，飞机下降及时进行审查做了翼展组件4，104飞机上的接合铁轨。 牙齿8,108限制在位置和方向的飞机，而轨道带上飞机休息。 轨道的铰接用于停放飞机在维修站14联系加油，再充电，和/或功能检查在发射准备制成。 启动通过去除连接和约束和阐明导轨把飞机在合适的位置和方向进行。 该机使用它自己的推力爬出设备进入自由飞行。

公开(公告)号：EP2497555A1

公开(公告)日：2012-09-12

申请号：EP12155240.0

申请日：2012-02-13

Applicant: Parrot

Inventor： D'Haeyer, Frédéric ,  Rischmuller, Michael

IPC: A63H30/04 ,  A63H27/133 ,  G08C17/02 ,  G05B13/02 ,  B64C39/02 ,  B64C27/04

CPC classification number: A63H27/12 ,  A63H30/04 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2203/00 ,  G05D1/0202 ,  G08C17/02 ,  G08C2201/93

Abstract: Les moteurs respectifs du drone (10) sont commandables de manière différenciée pour piloter le drone en attitude et en vitesse. Un appareil de télécommande produit une commande de virage selon une trajectoire curviligne, cette commande comprenant un paramètre de sens du virage, à droite ou à gauche, et un paramètre définissant le rayon de courbure ce virage. Le drone reçoit cette commande et acquiert des mesures instantanées des composantes de la vitesse linéaire, des angles d'inclinaison et des vitesses angulaires du drone. A partir de la commande reçue et des mesures acquises sont générées des valeurs de consigne d'une boucle de contrôle des moteurs du drone, ces valeurs de consigne contrôlant la vitesse linéaire horizontale et l'inclinaison du drone par rapport à un repère lié au sol de manière à faire parcourir au drone la trajectoire curviligne (C) avec une vitesse tangentielle ( u ) prédéterminée.

Abstract translation: 该方法涉及用于无人驾驶飞机的控制回路产生的设定点值。 的设定值被用于控制水平线性速度和无人驾驶飞机的倾斜度（10）相对于与地面相关联的参考帧，使无人驾驶飞机遵循曲线路径（C）以预定的切向速度，其中，所述无人驾驶飞机是一个quadricopter 类型的具有多个转子的嗡嗡声。 所述控制步骤基于包括右转或左转方向参数和曲率半径瞬时设定值定义参数的命令实现。 因此独立claimsoft被包括为一个软件，其包括一组指令用于实现驾驶旋翼无人驾驶飞机的方法。

公开(公告)号：EP1750999B1

公开(公告)日：2012-07-11

申请号：EP05769703.9

申请日：2005-05-27

Applicant: Bertin Technologies

Inventor： LAVAL-JEANTET, Rémi ,  TROUCHET, Daniel ,  BROSSAY, Nicolas ,  BINETTI, Paolo

IPC: B64C27/20 ,  B64C27/10

CPC classification number: B64C27/10 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127

Abstract: The invention concerns a vertical take-off and landing miniature drone, comprising a substantially cylindrical annular fairing (10), two counter-rotating propellers (26, 32) mounted rotatably in the fairing about the axis thereof and driven at the same speed, and control surfaces, located between the cylindrical body and the fairing beneath the propellers, which comprise pivoting boxes (34) open at their upper and lower ends and containing profiled blades.

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：EP2212198A1

公开(公告)日：2010-08-04

申请号：EP08845839.3

申请日：2008-10-31

Applicant: Raytheon Company

Inventor： KINSEY, Lloyd, E. ,  KRANKING, Patrick, D.

IPC: B64C29/02

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

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。