公开(公告)号：EP2840022A1

公开(公告)日：2015-02-25

申请号：EP13181174.7

申请日：2013-08-21

Applicant: Gatewing NV

Inventor： De Smet, Bjorn ,  De Moor, Maarten ,  Cosyn, Peter

IPC: B64C39/00 ,  G05D1/00

CPC classification number: B64D31/06 ,  B64C11/002 ,  B64C39/00 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64C2201/18 ,  G05D1/0055 ,  G05D1/0676

Abstract: An unmanned aircraft (101; 201) comprises:
- a drive system (112; 212) to thrust the unmanned aircraft (101; 201) during a flight;
- a reverse thrust system (301) to reverse thrust the unmanned aircraft (101; 201) during a landing;
- a controller (304) operationally coupled to the reverse thrust system (301); and
- a detector (302) to detect and notify to the controller (304) that the unmanned aircraft (101; 201) is in an uncontrolled situation during the flight.
The controller (304) is then adapted to activate the reverse thrust system (301) in order to reverse thrust the unmanned aircraft (101; 201) in-flight upon notification from the detector (302) that the unmanned aircraft (101; 201) is in an uncontrolled situation.

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：EP2377757B1

公开(公告)日：2013-05-29

申请号：EP10004112.8

申请日：2010-04-19

Applicant: Gatewing NV

Inventor： Van Speybroeck, Maarten Maurits ,  Cosyn, Peter Hendrik ,  Vandenbroucke, Marteen Willem

IPC: B64C3/20 ,  B64C3/24 ,  B64C39/02

CPC classification number: B64C3/187 ,  A63H27/00 ,  B64C3/20 ,  B64C3/24 ,  B64C39/024 ,  B64C39/028 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127

公开(公告)号：EP2525243A1

公开(公告)日：2012-11-21

申请号：EP11166894.3

申请日：2011-05-20

Applicant: SIEMENS AKTIENGESELLSCHAFT

Inventor： Stege, Jason ,  Stiesdal, Henrik

IPC: G01W1/08

CPC classification number: G01W1/08 ,  B64C2201/028 ,  B64C2201/125 ,  F03D9/32 ,  F03D80/00 ,  F05B2240/921 ,  F05B2260/8211 ,  F05B2270/80 ,  Y02E10/72

Abstract: The invention relates to a method to collect meteorological data, which are used to influence the operation of at least one wind turbine. An unmanned automated vehicle is directed within a predefined ambient air-volume, which is assigned to the at least one wind turbine. The unmanned automated vehicle generates meteorological data by an instrument, while the instrument is carried by the unmanned automated vehicle. The data are related to the volume, which is assigned to the at least one wind turbine.

Abstract translation: 本发明涉及一种用于收集气象数据的方法，其用于影响至少一个风力涡轮机的运行。 无人自动车辆被引导到被分配给至少一个风力涡轮机的预定的环境空气体积内。 无人自动车辆由仪器生成气象数据，而仪器由无人自动车辆运载。 数据与分配给至少一个风力涡轮机的体积相关。

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：EP1720767B1

公开(公告)日：2008-10-29

申请号：EP05810520.6

申请日：2005-02-15

Applicant: The Boeing Company

Inventor： BOLLING, John, G.

IPC: B64D39/00

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104

Abstract: An in-flight refueling system for an unmanned aircraft (10) is responsive to sensed forces acting on a refueling receptacle (12) of the aircraft (10) by a separate refueling probe, to control movements of the aircraft (10) as it is being refueled to reduce the magnitude of the sensed forces and thereby maintain the coupling of the aircraft (10) with the refueling probe.

公开(公告)号：EP1827972B8

公开(公告)日：2008-10-22

申请号：EP05813078.2

申请日：2005-11-30

Applicant: Israel Aerospace Industries Ltd.

Inventor： SIRKIS, Omri

IPC: B64C9/18 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C9/18 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/201

Abstract: A method for landing a fixed wing aircraft is provided in which an inversion maneuver is performed so that the aircraft's back is facing the ground, and the aircraft's underside is facing away from the ground. After initiation or completion of this maneuver, deep stall is induced, and the aircraft descends almost vertically to land on its upper side, thus minimizing impact loads or damage on its underside. In a particular aerodynamic arrangement configured for carrying out the method, a flap (24), which may be stowed during normal flight, is deployed in a manner such as to aerodynamically induce a negative pitching moment on the aircraft and deep stall.

Abstract translation: 提供了一种用于着陆固定翼飞机的方法，其中执行反转操纵，使得飞机的背面朝向地面，并且飞机的底面背离地面。 在开始或完成这种机动之后，引起深度失速，并且飞机几乎垂直下降以落在其上侧，从而最小化撞击载荷或其下侧的损坏。 在构造成用于执行该方法的特定空气动力学布置中，可以在正常飞行期间收起的襟翼（24）以诸如在空气动力学上引起飞行器上的负俯仰力矩和深度失速的方式展开。

公开(公告)号：EP1713689A2

公开(公告)日：2006-10-25

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

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：EP1666356A1

公开(公告)日：2006-06-07

申请号：EP04732435.5

申请日：2004-05-12

Applicant: KAWADA INDUSTRIES, INC.

Inventor： TANABE, Yasutada, KAWADA INDUSTRIES, INC. ,  TOTSUKA, Chiharu, KAWADA INDUSTRIES, INC. ,  AKASAKA, Tsuyoshi, KAWADA INDUSTRIES, INC. ,  OKAMOTO, Masato

IPC: B64C39/10

CPC classification number: A63H27/02 ,  B64C39/028 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  Y10S244/903

Abstract: A small unmanned airplane includes; a main wing (1) having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps (2) extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers (3) placed at blade tips of left and right of the main wing; and two propellers (5) installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

Abstract translation: 一架小型无人机包括 主翼（1）具有下表面近似平坦的倾斜翼型，其锥形形状变窄为其前端具有扫掠角的叶片尖端，其具有无翅翼型的空气动力学表面的飞翼型， 是低纵横比; 在主翼的左右两侧的后缘部分中大致极大地延伸的活动翼片（2）具有至少在水平飞行中的二面角; 垂直稳定器（3）放置在主翼左右叶片尖端; 和两个螺旋桨（5）安装在主翼的顶面上。 这可以实现小型化和轻量化的小型无人飞机的个人承载能力，并适用于诸如用手抛出的剥离。

公开(公告)号：WO2017209796A1

公开(公告)日：2017-12-07

申请号：PCT/US2016/069608

申请日：2016-12-30

Applicant: GOOGLE LLC

Inventor： KREBS, Mark ,  BRANDMEYER, Jonathan Daniel

IPC: B64C3/52 ,  B64C13/16 ,  B64C39/10 ,  G05D1/08

CPC classification number: B64C13/18 ,  B64C3/38 ,  B64C3/52 ,  B64C9/04 ,  B64C13/16 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104 ,  G05D1/0841

Abstract: Systems and methods for operating control surfaces of an aircraft. The method involves receiving, by an aircraft control system from one or more sensors, deflection information related to a shape and motion of an aircraft, and decomposing, by the aircraft control system, the deflection information into a detected modal state including a first known mode having a first mode strength. The method may further involve determining, by the aircraft control system, a first modal compensation based on the first mode strength, and identifying, by the aircraft control system, a desired control corresponding to a second known mode. The method may yet further involve determining a first control response for a control surface having a first modal weight and a second modal weight, based on the first modal compensation and the first modal weight, and determining a second control response for the control surface based on the desired control and the second modal weight. The method may still further involve generating a control command for the control surface based on the first control response and the second control response.

Abstract translation:

用于操作飞机的控制表面的系统和方法。 该方法包括由飞行器控制系统从一个或多个传感器接收与飞行器的形状和运动有关的偏转信息，并且由飞行器控制系统将偏转信息分解为包括第一已知模式的检测模态 具有第一模式强度。 该方法还可以包括由飞行器控制系统基于第一模式强度确定第一模态补偿并且由飞行器控制系统识别与第二已知模式相对应的期望控制。 该方法还可以包括基于第一模态补偿和第一模态权重确定具有第一模态权重和第二模态权重的控制表面的第一控制响应，并且基于第一模态补偿和第一模态权重确定用于控制表面的第二控制响应 期望的控制和第二模态重量。 该方法还可以涉及基于第一控制响应和第二控制响应来产生用于控制表面的控制命令。