公开(公告)号：EP1924495B1

公开(公告)日：2016-11-30

申请号：EP06851409.0

申请日：2006-06-28

Applicant: Sommer, Geoffrey S.

Inventor： Sommer, Geoffrey S.

IPC: B64C37/02 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

公开(公告)号：EP3089244A1

公开(公告)日：2016-11-02

申请号：EP16166830.6

申请日：2016-04-25

Applicant: Albufera Energy Storage, S.L.

Inventor： RODRÍGUEZ SOLER, Paloma ,  CHACÓN GUADALIX, Joaquín José ,  FATAS LAHOZ, Enrique ,  OCÓN ESTEBAN, Pilar ,  PINO MARTÍNEZ, Mikel

IPC: H01M4/46 ,  H01M4/50 ,  H01M6/04 ,  H01M4/06 ,  H01M4/36 ,  H01M4/62

CPC classification number: H01M6/045 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/101 ,  B64C2201/125 ,  B64C2201/141 ,  B64C2201/165 ,  H01M4/06 ,  H01M4/366 ,  H01M4/463 ,  H01M4/50 ,  H01M4/622 ,  H01M4/625 ,  H01M6/02 ,  H01M2004/027 ,  H01M2004/028 ,  H01M2220/30 ,  H01M2300/0002

Abstract: The present invention relates to an electrochemical cell characterised in that it comprises at least a positive electrode which comprises manganese oxide physically separated from at least a negative electrode which comprises an aluminium alloy, and wherein said positive and negative electrodes are electrically connected through a neutral pH electrolyte. Further, the present invention relates to the use of the electrochemical cell, preferably as a button battery in hearing aids.

Abstract translation: 电化学电池技术领域本发明涉及一种电化学电池，其特征在于，其至少包括正电极，其包括与至少一种包含铝合金的负极物理分离的氧化锰，并且其中所述正电极和负极通过中性pH电连接 电解质。 此外，本发明涉及电化学电池，优选地作为助听器中的钮扣电池的用途。

公开(公告)号：EP2879954A2

公开(公告)日：2015-06-10

申请号：EP13845941.7

申请日：2013-07-25

Applicant: Bye UAS Inc.

Inventor： BYE, George ,  BICKEL, Matt

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/185 ,  B64C2211/00

Abstract: The present invention provides an Unmanned Aircraft System, including an integrated unmanned aerial vehicle and all related components and subsystems that can be packaged and transported as a kit, and customized to fit desired mission profiles, and easily repaired by replacement of damaged components or subsystems. The present invention further provides unmanned aircraft system components and subsystems that facilitate low power and low noise operation, and extended flight times.

公开(公告)号：EP2814734A1

公开(公告)日：2014-12-24

申请号：EP13709050.2

申请日：2013-02-13

Applicant: Reiter, Johannes

Inventor： Reiter, Johannes

IPC: B64C29/02 ,  B64C39/02 ,  B64C29/00 ,  B64C39/00 ,  B64C27/16 ,  B64C27/18

CPC classification number: B64C27/00 ,  B64C3/385 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0075 ,  B64C29/02 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to a device for generating aerodynamic lift and in particular an aircraft (100) for vertical take-off and landing. A wing arrangement (110) comprises at least one propulsion unit (111), wherein the propulsion unit (111) comprises a rotating mass which is rotatable around a rotary axis (117). The wing arrangement (110) is mounted to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis (112) of the wing arrangement (110) and such that the wing arrangement (110) is rotatable with respect to the fuselage (101) around a further rotary axis that differs to the longitudinal wing axis (112). An adjusting mechanism adjusts a tilting angle of the wing arrangement (110) around the longitudinal wing axis (112) under influence of a precession force (Fp) which forces the wing arrangement (110) to tilt around the longitudinal wing axis (112).

Abstract translation: 用于产生气动升力的装置技术领域本发明涉及一种用于产生气动升力的装置，尤其涉及一种用于垂直起飞和着陆的飞机（100）。 机翼装置（110）包括至少一个推进单元（111），其中推进单元（111）包括可围绕旋转轴线（117）旋转的旋转质量。 机翼装置（110）安装到机身（101），使得机翼装置（110）可围绕机翼装置（110）的纵向机翼轴线（112）倾斜并且使得机翼装置（110）可旋转 相对于机身（101）绕与纵向机翼轴线（112）不同的另一旋转轴线旋转。 调节机构在迫使机翼布置（110）围绕纵向机翼轴线（112）倾斜的进动力（Fp）的影响下调节机翼布置（110）围绕纵向机翼轴线（112）的倾斜角度。

公开(公告)号：EP2799332A2

公开(公告)日：2014-11-05

申请号：EP14002518.0

申请日：2005-04-14

Applicant: Arlton, Paul E. ,  Arlton, David J.

Inventor： Arlton, Paul E. ,  Arlton, David J.

IPC: B64C27/10 ,  B64C27/22 ,  B64C39/02

CPC classification number: B64C27/10 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle (1) includes a body structure having an elongated tubular backbone or core (40), and a counter-rotating coaxial rotor system (3, 5) having rotors with each rotor having a separate motor (54, 61) to drive the rotors about a common rotor axis of rotation (7), The rotor system is used to move the rotary wing vehicle (1) in directional flight.

Abstract translation: 旋翼机（1）包括具有细长管状骨架或芯（40）的本体结构和具有转子的反向旋转同轴转子系统（3,5），每个转子具有单独的电机（54,61） 驱动转子围绕共同的转子旋转轴（7）。转子系统用于在定向飞行中移动旋翼机（1）。

公开(公告)号：EP2253536A4

公开(公告)日：2014-07-16

申请号：EP08767003

申请日：2008-01-09

Applicant: ZUBKOV SERGEY GENNADIEVICH ,  REZNICHENKO VYCHESLAV IVANOVICH ,  KHMEL DMITRY SERGEEVICH

Inventor： KHMEL DMITRY SERGEEVICH

IPC: B64C27/57 ,  B64C11/30 ,  B64C27/80

CPC classification number: B64C11/306 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

公开(公告)号：EP2673192A1

公开(公告)日：2013-12-18

申请号：EP12714935.9

申请日：2012-02-08

Applicant: Voss, Andreas

Inventor： Voss, Andreas

IPC: B64C15/00 ,  B64C17/04 ,  B64C39/02 ,  B64C39/06

CPC classification number: B64C15/00 ,  B64C17/04 ,  B64C39/024 ,  B64C39/028 ,  B64C39/066 ,  B64C39/068 ,  B64C2201/104 ,  B64C2201/165

Abstract: The invention relates to a remote-controlled small flying object comprising at least one lift area (17), comprising at least one pair of propeller drives (12, 13), and comprising a weight element (20), the position of which can be varied to vary the centre of gravity of this small flying object (10) in the longitudinal direction of the small flying object (10). In order to accomplish a more compact and robust design with improved flying characteristics, the lift area (17) of the small flying object (10) is arranged above a plane formed by the axes of rotation of the propeller drives (12, 13) to generate a lifting force for vertical takeoff and/or landing.

公开(公告)号：EP1713689B1

公开(公告)日：2012-08-01

申请号：EP04821333.4

申请日：2004-03-25

Applicant: The Insitu Group

Inventor： MCGEER, Brian T. ,  ROESELER, Cory ,  VON FLOTOW, Andreas

IPC: B64F1/06 ,  B64C39/02

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.

公开(公告)号：EP2435306A2

公开(公告)日：2012-04-04

申请号：EP10732752.0

申请日：2010-05-26

Applicant: Israel Aerospace Industries Ltd.

Inventor： WOLFF, Amit ,  DEKEL, Guy ,  ZIVAN, Lior

IPC: B64C29/00

CPC classification number: B64C29/0033 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2211/00

Abstract: In embodiments, a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, include at least three propulsion units that provide vertical thrust for vectored thrust flight, in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector thereof. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle.

Abstract translation: 在实施例中，用于向空中交通工具提供推进和控制以及用于操作车辆的系统和方法包括至少三个推进单元，其提供用于向量推力飞行的垂直推力，其中至少一个或两个推进单元也 通过适当地倾斜相应的推进单元来改变其推力矢量，为向量推力巡航或空气动力学飞行提供推力。 同时，三个或更多的推进单元被操作以在向量推力飞行（悬停，巡航等）期间或在用于控制的空气动力学飞行期间在三个正交轴线（俯仰，滚动和偏航）周围产生对空中飞行器的控制力矩 机动车。

公开(公告)号：EP2261120A1

公开(公告)日：2010-12-15

申请号：EP10181036.4

申请日：2003-10-07

Applicant: Fuji Jukogyo Kabushiki Kaisha

Inventor： Yamane, Akihiro

IPC: B64C39/02 ,  G05D1/06

CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  G05D1/0669 ,  G05D1/0676

Abstract: The present invention discloses a landing method of an unmanned helicopter comprising changing a collective pitch blade angle based on a blade angle command calculated based on the deviation between a fed-back altitude and an altitude command and the deviation between a fed-back altitude change rate and an altitude change rate command, descending, and determining that the helicopter has landed, if the blade angle command of a predetermined value or less continues for a predetermined time.

Abstract translation: 本发明公开了一种无人直升机的着陆方法，包括基于基于反馈高度和高度命令之间的偏差计算的叶片角度指令和反馈高度变化率之间的偏差来改变总共桨叶角度 如果预定值或更小的叶片角度指令持续预定时间，则下降并确定直升机降落的高度变化率指令。