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公开(公告)号：JP3745754B2
公开(公告)日：2006-02-15
申请号：JP2003299869
申请日：2003-08-25
CPC classification number: A63H27/02 , B64C39/028 , B64C39/10 , B64C2201/028 , B64C2201/141 , B64C2201/146 , B64C2201/165 , Y10S244/903
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公开(公告)号：TW201738148A
公开(公告)日：2017-11-01
申请号：TW106110138
申请日：2017-03-27
Applicant: 洛克希德馬丁公司 , LOCKHEED MARTIN CORPORATION
Inventor： 甘伯爾 道斯汀 E. , GAMBLE, DUSTIN ELI , 庫蘭 馬修 , CURRAN, MATTHEW
CPC classification number: B64C3/42 , B64C1/26 , B64C1/28 , B64C3/38 , B64C3/385 , B64C39/024 , B64C39/026 , B64C2201/028 , B64C2201/10
Abstract: 一種航空載具包括機身、機翼及機翼移位裝置。該機翼移位裝置經組配來耦接至該機身。該機翼移位裝置包含用於將該機翼耦接至該航空載具之多個孔隙。該等多個孔隙經組配來准許該機翼基於該航空載具之重心沿著該機身在向前或向後方向上移位。
Abstract in simplified Chinese: 一种航空载具包括机身、机翼及机翼移位设备。该机翼移位设备经组配来耦接至该机身。该机翼移位设备包含用于将该机翼耦接至该航空载具之多个孔隙。该等多个孔隙经组配来准许该机翼基于该航空载具之重心沿着该机身在向前或向后方向上移位。
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公开(公告)号：EP3388336A1
公开(公告)日：2018-10-17
申请号：EP18160186.5
申请日：2018-03-06
Applicant: Facebook, Inc.
Inventor： LIU, Zhang , TALMOR, Amnon G. , CAO, Yusong
CPC classification number: B64C23/065 , B64C11/00 , B64C39/10 , B64C2201/028 , B64C2201/122 , Y02T50/12 , Y02T50/164
Abstract: A wing and propeller design may reduce the power required to propel an aircraft (400) in flight. This may be achieved by reducing downwash and trailing vortices that occur naturally on the aircraft's wings. A reduction in downwash and trailing vortices may in turn reduce the overall drag on the aircraft. In one embodiment, an aircraft includes a number of propellers (410, 420, ..., 450, 460) N prop , wherein each propeller comprises a diameter d prop , has a propeller efficiency η prop , and is configured to absorb power p prop to rotate at a rate RPM to generate thrust for a flight speed V of the aircraft. The aircraft may further include a total power p total absorbed by the propellers that is approximately p prop × N prop , a wing having a circulation distribution, wherein the wing comprises a wingspan B, a drag D that is approximately equal to p total × η prop / V. For V and B , the circulation distribution, d prop , and RPM substantially minimizes D.
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公开(公告)号：EP3172130B1
公开(公告)日：2018-10-03
申请号：EP15747241.6
申请日：2015-07-21
Applicant: Atmos Uav B.V.
Inventor： HULSMAN, Sander , DE GROOT, Jurjen , MILIS, Maarten , DOKTER, Dirk Lucas Eduard , BOUMAN, Joost Leon , KNOOPS, Ruud
CPC classification number: B64C29/02 , B64C39/024 , B64C2201/028 , B64C2201/042 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/165
Abstract: An aircraft, in particular an unmanned aerial vehicle with wing-borne flight mode and hover flight mode, comprises a wing structure (4) having a left (6), middle (7), and right wing section (8). A support structure extends from the wing structure (4), and has an upper and lower support section. Each one of the left and right wing section (6, 8), and upper and lower support section (18, 20) has a thrust unit (10, 12, 22, 24). Left and right wingtip sections are rotatable relative to a left and right wing base section, respectively, around an axis extending substantially in a lengthwise direction of the wing structure. The thrust units (10,12) of the left and right wing sections(6, 8) are provided at the respective wingtip sections, in particular at the extremities thereof.
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公开(公告)号：EP3282335A1
公开(公告)日：2018-02-14
申请号：EP17185061.3
申请日：2017-08-07
Applicant: Parrot Drones
IPC: G05D1/00
CPC classification number: G05D1/0088 , A63H30/04 , B64C39/024 , B64C39/10 , B64C2201/00 , B64C2201/028 , B64C2201/104 , B64C2201/141 , B64C2201/146 , B64C2203/00 , B64D47/08 , G05D1/0038 , G05D1/101
Abstract: Le module intègre dans un même boitier monobloc (48) un circuit électronique (100) et une pluralité de capteurs d'attitude, d'altitude, de vitesse, d'orientation et/ou de position du drone (104-116). Il intègre également un circuit électronique de puissance (200) recevant des consignes de commande élaborées par le processeur du circuit électronique en fonction des données délivrées par les capteurs intégrés, et délivrant en sortie des signaux correspondants pour l'alimentation directe en courant ou en tension des moyens propulseurs du drone et des gouvernes.
Abstract translation: 该模块将电子电路（100）和无人驾驶飞机（104-116）的多个传感器姿态，高度，速度，取向和/或位置集成到同一整体式封装（48）中。 它还集成了电子电源电路（200），接收由电子电路的处理器根据由集成传感器传送的数据开发的控制命令，并输出用于直接电源或电压的相应信号 无人机和控制表面的推进手段。
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Patent Agency Ranking
公开(公告)号：EP2760739B1
公开(公告)日：2017-11-22
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 , B64C39/02
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.
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公开(公告)号：EP3172130A1
公开(公告)日：2017-05-31
申请号：EP15747241.6
申请日：2015-07-21
Applicant: Atmos Uav B.V.
Inventor： HULSMAN, Sander , DE GROOT, Jurjen , MILIS, Maarten , DOKTER, Dirk Lucas Eduard , BOUMAN, Joost Leon , KNOOPS, Ruud
IPC: B64C39/02
CPC classification number: B64C29/02 , B64C39/024 , B64C2201/028 , B64C2201/042 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/165
Abstract: An aircraft, in particular an unmanned aerial vehicle with wing-borne flight mode and hover flight mode, comprises a wing structure (4) having a left (6), middle (7), and right wing section (8). A support structure extends from the wing structure (4), and has an upper and lower support section. Each one of the left and right wing section (6, 8), and upper and lower support section (18, 20) has a thrust unit (10, 12, 22, 24). Left and right wingtip sections are rotatable relative to a left and right wing base section, respectively, around an axis extending substantially in a lengthwise direction of the wing structure. The thrust units (10,12) of the left and right wing sections(6, 8) are provided at the respective wingtip sections, in particular at the extremities thereof.
Abstract translation: 一种飞机，特别是具有机翼飞行模式和悬停飞行模式的无人驾驶飞行器，包括具有左（6），中（7）和右翼部分（8）的机翼结构（4）。 支撑结构从机翼结构（4）延伸，并具有上支撑部分和下支撑部分。 左右翼部（6,8）和上下支承部（18,20）中的每一个具有推力单元（10,12,22,24）。 左翼尖部分和右翼尖部分可以分别围绕基本上在翼结构的纵向方向上延伸的轴线相对于左翼基部部分和右翼基部部分旋转。 左翼部分（6）和右翼部分（8）的推力单元（10，12）设置在相应的翼尖部分处，特别是在其末端。
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公开(公告)号：EP2440456A1
公开(公告)日：2012-04-18
申请号：EP10728388.9
申请日：2010-06-02
Applicant: Elta Systems Ltd.
Inventor： PRATZOVNICK, Arie , RON, Shmuel
IPC: B64C39/02
CPC classification number: B64C39/024 , B64C2201/028 , B64C2201/127
Abstract: A sensor/emitter arrangement (M1-M3) is integrated into the fuselage (120) structure of a specially designed air vehicle (100), in which the air vehicle is configured for optimizing operation of the sensor/emitter arrangement (M1-M3) with respect to at least azimuthal lines of sight radiating along a azimuthal reference plane of the air vehicle (100). The azimuthal reference plane intersects the air vehicle fuselage (120). In at least some embodiments, the fuselage (120) is formed with a plurality of oblate cross-sections that facilitate maximizing the room available for a sensor/emitter array (172, 174, 176) that is elongated along an elongate axis that may be aligned with the azimuthal reference plane. In at least some embodiments one or more such elongate axes may be inclines to the longitudinal (roll) axis and the pitch axis of the air vehicle (100). In at least some embodiments, the air vehicle may have a blunt aft end incorporating an elongate aft-facing sensor/emitter array (172, 174, 176).
Abstract translation: 传感器/发射器装置（M1-M3）被集成到专门设计的飞行器（100）的机身（120）结构中，其中飞行器被配置用于优化传感器/发射器装置（M1-M3） 至少相对于沿航空器（100）的方位参考平面辐射的方位角视线。 方位参考平面与飞行器机身（120）相交。 在至少一些实施例中，机身（120）形成有多个扁平横截面，这有助于最大化可用于传感器/发射器阵列（172,174,176）的空间，该传感器/发射器阵列沿着细长轴线伸长，该细长轴线可以是 与方位参考平面对齐。 在至少一些实施例中，一个或多个这种细长轴线可以倾斜至飞行器（100）的纵向（滚动）轴线和俯仰轴线。 在至少一些实施例中，飞行器可以具有包含细长的面向后方的传感器/发射器阵列（172,174,176）的钝后端。
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公开(公告)号：EP2377757A1
公开(公告)日：2011-10-19
申请号：EP10004112.8
申请日：2010-04-19
Applicant: Gatewing NV
CPC classification number: B64C3/187 , A63H27/00 , B64C3/20 , B64C3/24 , B64C39/024 , B64C39/028 , B64C2039/105 , B64C2201/028 , B64C2201/127
Abstract: A wing for an unmanned aircraft (400) adapted for image acquisition, surveillance or other applications consists of a ribbed frame (100) and a foam (200) wherein the ribbed frame (100) is integrated. The foam (200) has a container (301, 02, 303) for holding the electric and/or electronic components. The foam (200) constitutes the outer layer of the unmanned aircraft (400) at impact side (204, 205, 206). The wing can be produced at low cost and low complexity in large volumes, increases the impact resistance and safety when used in civil areas, and is removable and disposable thereby enabling reuse of the electric and/or electronic components.
Abstract translation: 适用于图像采集，监视或其它应用的无人机（400）的机翼由肋框架（100）和泡沫（200）组成，其中肋框架（100）被集成。 泡沫（200）具有用于保持电气和/或电子部件的容器（301,02,303）。 泡沫（200）在冲击侧（204,205,206）构成无人飞行器（400）的外层。 机翼可以低成本和低复杂性大量生产，当在民用区域中使用时增加抗冲击性和安全性，并且是可拆卸的和一次性的，从而能够重复使用电气和/或电子部件。
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公开(公告)号：EP2277775A1
公开(公告)日：2011-01-26
申请号：EP10188051.6
申请日：2008-04-16
Applicant: GO SCIENCE LIMITED
Inventor： Gosling, Harry George Dennis
CPC classification number: B64C39/062 , B64C39/024 , B64C2201/028 , B64C2201/162
Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. The wing-body carries at least one rudder (80-85) on its left side and at least one rudder on its right side. A propulsion system is provided comprising one or more pairs of propulsion devices (70,71), each pair comprising a first propulsion device (70) mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device (71) mounted to the wing-body and positioned on a second side of the plane including the wing-body axis.
Abstract translation: 一种机载车辆，其具有限定翼体轴线的翼体，并且当沿翼体轴线观察时呈现大致环形，所述环形空间的内部限定在两端敞开的管道。 翼体在其左侧至少携带一个舵（80-85），右侧至少有一个舵。 提供了包括一对或多对推进装置（70,71）的推进系统，每对推进装置（70,71）包括安装到翼体的第一推进装置（70），并位于包括翼体轴线的平面的第一侧 ，以及第二推进装置（71），其安装到翼体并且定位在包括翼体轴线的平面的第二侧上。
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