公开(公告)号：EP1713689A4

公开(公告)日：2010-08-25

申请号：EP04821333

申请日：2004-03-25

Applicant: INSITU GROUP

Inventor： MCGEER BRIAN T ,  ROESELER CORY ,  VON FLOTOW ANDREAS

IPC: B64F1/06 ,  B64C3/56 ,  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

公开(公告)号：EP2193992A2

公开(公告)日：2010-06-09

申请号：EP09252585.6

申请日：2009-11-10

Applicant: Thales Holdings UK Plc

Inventor： Gleed, Gerald ,  Alders, Dean

IPC: B64C3/38 ,  B64C3/40 ,  B64C39/02 ,  B64C39/06 ,  B64D27/02

CPC classification number: B64C3/38 ,  B64C3/40 ,  B64C39/024 ,  B64C39/066 ,  B64C2201/028 ,  B64C2211/00 ,  B64D27/02

Abstract: An air vehicle comprising only one wing, which is thin and substantially flat, the wing being elongate and preferably diamond-shaped, and a pod removably coupled to the wing for relative rotation about an axis normal to the major surfaces of the wing, the pod bearing a propulsor for the air vehicle. The propulsor may be a propeller with a Custer duct for static lift.

公开(公告)号：EP2188176A1

公开(公告)日：2010-05-26

申请号：EP08857634.3

申请日：2008-09-11

Applicant: Altair

Inventor： LEHMANN, Benjamin

IPC: B64C39/02

CPC classification number: B64C39/024 ,  A63H27/02 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/127

Abstract: The present invention relates to a modular drone (1) consisting of a flying structure (2) and image acquisition means, characterized in that said image acquisition means as well as the motorization are supported by a rigid platen (6) connected to the flying structure (2) by links that are detachable when the loadings between said platen (6) and said flying structure (2) exceed a wrenching threshold value, these links being constituted by one from among electromagnetic links (41, 42) and self-adhering tapes and materials. The present invention also relates to an airborne image acquisition system consisting of such a modular drone.

公开(公告)号：EP1631493A2

公开(公告)日：2006-03-08

申请号：EP04809418.9

申请日：2004-05-26

Applicant: NORTHROP GRUMMAN CORPORATION

Inventor： CLARK, Walter, D.

IPC: B64C1/00 ,  B64C5/08 ,  B64C9/12 ,  B64C9/32 ,  B64C9/34 ,  B64C39/02

CPC classification number: B64C1/0009 ,  B64C5/08 ,  B64C9/12 ,  B64C9/32 ,  B64C9/323 ,  B64C9/34 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/22 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

Abstract: An aircraft (10) with swept back wings (16, 18) and spoilers (30,32) inlaid into the top surface (36) near the tips of the wings. The aircraft also includes an elevator (34) formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings.

公开(公告)号：EP1280700A2

公开(公告)日：2003-02-05

申请号：EP01954575.5

申请日：2001-04-03

Applicant: Aerovironment Inc.

Inventor： MACCREADY, Paul ,  HIBBS, Bart, D. ,  CURTIN, Robert, F. Jr. ,  SWANSON, Kyle, D. ,  BELIK, Paul

IPC: B64C39/02 ,  B64D27/02 ,  B64D37/30

CPC classification number: B64D27/24 ,  B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft (101), configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft (101) includes an extendable slat (205) at the leading edge of the wing (103), and a reflexed trailing edge. The aircraft comprises a flying wing (103) extending laterally between two ends and a center point. The wing (103) is swept and has a relatively constant chord. The aircraft (101) also includes a power module configured to provide power via a fuel cell (131). The fuel cell (131) stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell (131). A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft (101) of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing (103).

公开(公告)号：EP3209559A1

公开(公告)日：2017-08-30

申请号：EP15851788.8

申请日：2015-10-20

Applicant: Hohenthal, Markus

Inventor： Hohenthal, Markus

IPC: B64C29/02 ,  B64C39/02 ,  B64D27/24

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64D27/24

Abstract: An electrically powered vertical takeoff and vertical landing (VTOL) aircraft, which comprises at least two main propellers, wherein the main propellers are adapted to generate at least 70% of the aircraft propulsion. The aircraft also comprises at least one adjustment propeller, which has its propeller slipstream adapted to produce a torque relative to a first axis or the first and second axes with respect to a fuselage of the aircraft for turning the aircraft relative to said first axis or said first and second axes. In addition, not less than 35%, but not more than 85%, of the aircraft's mass is adapted to lie, during takeoff and/or landing, on a rear side of a propeller line of said main propellers with respect to a nose of the aircraft.

Abstract translation: 一种电动垂直起飞和垂直着陆（VTOL）飞机，其包括至少两个主推进器（101a，101b），其中主推进器适于产生飞机推进的至少70％。 飞机还包括至少一个调节螺旋桨（101a，101b，102），其具有适于相对于第一轴线（103）或第一和第二（104）轴线产生扭矩（113,114,115）的螺旋桨滑流， 轴相对于飞行器的机身（119）相对于所述第一轴线或所述第一和第二轴线转动飞机。 此外，飞机质量的不少于35％但不多于85％适于在起飞和/或着陆期间位于所述主螺旋桨的螺旋桨管线（108）的后侧（109）上 相对于飞机的鼻子（111）。

公开(公告)号：EP2212198B1

公开(公告)日：2017-01-25

申请号：EP08845839.3

申请日：2008-10-31

Applicant: Raytheon Company

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

IPC: B64C39/02 ,  B64C29/02

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

公开(公告)号：EP2903892A1

公开(公告)日：2015-08-12

申请号：EP13763040.6

申请日：2013-09-13

Applicant: Sensefly S.A.

Inventor： BEYELER, Antoine ,  KLAPTOCZ, Adam ,  ROBERTS, James F. ,  ZIMMERMANN, Loic ,  ZUFFEREY, Jean-Christophe ,  LAZZARATTO-PINÖSCH, Andreas

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：EP2902319A1

公开(公告)日：2015-08-05

申请号：EP14382029.8

申请日：2014-01-30

Applicant: The Boeing Company

Inventor： Criado, Alfredo ,  Kawiecki, Grzegorz M. ,  Valero, Omar

IPC: B64C39/02 ,  B64C39/10

CPC classification number: B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165 ,  G01R31/021 ,  G06K9/00637 ,  H04N7/185 ,  Y02T50/12

Abstract: An unmanned aerial vehicle adapted for hover and short/vertical take-off and landing (S/VTOL) is disclosed. The vehicle comprises: a body having an aspect-ratio less than two and having therein a payload volume, at least one propeller located forward of the body, at least one rudder. The body may have an inverse Zimmerman planform which provides lift as air flows across the body in horizontal flight/fixed wing mode, and further adapted such that during hover and/or short/vertical take-off and landing (S/VTOL) the vehicle operates as a rotorcraft with the body oriented with the at least one propeller substantially above the body. The vehicle is suited to a method of inspection, such as power line inspection where large distances can be analysed efficiently by flying in fixed wing mode, but by transitioning to hover mode allows detailed inspection of selected areas.

Abstract translation: 公开了适用于悬停和短/垂直起降的无人驾驶飞行器（S / VTOL）。 该车辆包括：具有小于2的长宽比并且具有有效载荷体积的主体，位于身体前方的至少一个螺旋桨，至少一个舵。 身体可以具有逆Zimmerman平面图，其在水平飞行/固定翼模式中随着空气流过身体而提供电梯，并且还适于使得在悬停和/或短/垂直起飞和着陆期间（S / VTOL），车辆 作为旋翼航空器运行，其中身体以至少一个螺旋桨取向，大致在身体上方。 该车辆适用于检查方法，例如电力线检查，其中通过以固定翼模式飞行可以有效地分析大距离，但是通过转换到悬停模式允许对所选区域进行详细检查。

公开(公告)号：EP2760739A1

公开(公告)日：2014-08-06

申请号：EP12835896.7

申请日：2012-09-14

Applicant: Singapore Technologies Aerospace Ltd

Inventor： CHAN, Keen Ian

IPC: B64C29/02 ,  B64C25/32 ,  B64C27/08 ,  B64C39/08 ,  B64C39/10 ,  B64C99/00 ,  B64C11/46 ,  A63H27/133 ,  A63H27/127 ,  A63H27/18

CPC classification number: B64C29/02 ,  A63H27/12 ,  B64C13/24 ,  B64C27/08 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165 ,  G05D1/0669 ,  Y10T29/49826

Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes.