公开(公告)号：EP3192739A1

公开(公告)日：2017-07-19

申请号：EP17150611.6

申请日：2017-01-09

Applicant: David, Benjamin

Inventor： David, Benjamin

IPC: B64C39/08 ,  B64D27/24

CPC classification number: B64C39/024 ,  B64C3/00 ,  B64C39/08 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/104 ,  B64D27/24 ,  B64D2211/00 ,  Y02T50/62

Abstract: L'invention concerne un drone volant (1) comprenant :
- un fuselage (2) ;
- des moyens de propulsion alimentés au moins par des accumulateurs électriques et/ou des cellules photovoltaïques (3) ;
- une première aile portante (4) définie par une envergure et par une superficie de face supérieure, la face supérieure de la première aile portante étant essentiellement recouverte de cellules photovoltaïques,
caractérisé en ce qu'il comprend une deuxième aile portante (5) présentant une envergure et une superficie de face supérieure sensiblement identiques à celles de la première aile portante, la deuxième aile portante étant décalée le long du fuselage et en hauteur par rapport à la première aile portante, la face supérieure de la deuxième aile portante étant essentiellement recouverte de cellules photovoltaïques.

Abstract translation: 本发明涉及一种飞行无人机（1），包括： - 机身（2）; 至少由电蓄电池和/或光伏电池（3）供电的推进装置; 由跨度和上表面区域限定的第一承载翼（4），所述第一翼型的上表面基本上被光伏电池覆盖，其特征在于，所述第一承载翼（4）包括第二支撑翼（5），所述第二支撑翼 分和顶表面面积与第一翼型件和第二翼型件的基本上相同的沿所述机身和高度相对于第一翼型件偏移，第二翼型件的上侧基本上被覆盖 的光伏电池。

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。

公开(公告)号：EP3162705A1

公开(公告)日：2017-05-03

申请号：EP16196359

申请日：2016-10-28

Applicant: EWATT TECH CO LTD

Inventor： ZAHO GUOCHENG ,  LUO WEI

IPC: B64C25/58 ,  B64C1/00 ,  B64C3/00 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C1/00 ,  B64C1/06 ,  B64C3/00 ,  B64C5/02 ,  B64C25/58 ,  B64C39/028 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187

Abstract: The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.

Abstract translation: 本发明公开了一种手推无人机，属于无人机技术领域。 手推式无人飞行器包括本体，尾部，至少一个动力源和透镜仓，其中本体包括中间部分，第一侧部和第二侧部; 中间段的两侧分别对应地分别与第一侧段和第二侧段可拆卸连接; 尾部固定在中间部分; 电源固定在中间部分; 透镜仓固定在中间部位并设有柔性垫。 本发明克服了现有技术中手动无人机的机体维护成本高，且手持无人飞机车透镜仓碰撞容易造成透镜仓损坏的技术缺陷 和地面。

公开(公告)号：EP3124379A1

公开(公告)日：2017-02-01

申请号：EP15178886.6

申请日：2015-07-29

Applicant: Airbus Defence and Space GmbH

Inventor： STEINWANDEL, Jürgen ,  WANG, Ning ,  JUDAS, Michael ,  VAN TOOR, Jan

IPC: B64C29/00

CPC classification number: B64D35/08 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/24 ,  B64D2027/026

Abstract: Die Erfindung betrifft ein senkrechtstartfähiges Fluggerät (10) mit einem Schubantrieb (31) zum Erzeugen einer in eine Horizontalrichtung (1) wirkenden Antriebskraft und einem Hubantrieb (32) zum Erzeugen einer in eine Vertikahichtung wirkenden Auftriebskraft. Das Fluggerät weist ferner einen Motor (12) zum Bereitstellen von mechanischer Energie für den Schubantrieb (31) und einen ersten Generator (11) zum Bereitstellen von elektrischer Energie für den Hubantrieb (32) auf. Zudem weist das Fluggerät einen Abgasturbolader (40) für den Motor (12) mit einer von einem Abgasstrom (44) des Motors (12) angetriebenen ersten Turbine (41) auf, die dazu ausgeführt ist, mechanische Energie für den Schubantrieb (31) bereitzustellen.

Abstract translation: 具有用于产生在水平方向上有效的驱动力的推进驱动器的垂直起飞飞机和用于产生在垂直方向上有效的提升力的提升驱动装置包括用于为推进驱动提供机械能的马达和 用于为升降机驱动提供电能的第一发电机。 此外，该飞行器包括用于马达的废气涡轮增压器，其中第一涡轮机由马达的排气流驱动，其中第一涡轮机构造成为推进驱动提供机械能。

公开(公告)号：EP3013680A4

公开(公告)日：2017-01-18

申请号：EP14817368

申请日：2014-06-26

Applicant: PLIMP INC

Inventor： EGAN JAMES C ,  EGAN JOEL D

IPC: B64B1/00

CPC classification number: B64B1/20 ,  B64B1/14 ,  B64B1/22 ,  B64B1/28 ,  B64B1/30 ,  B64B1/34 ,  B64B1/38 ,  B64B1/58 ,  B64B1/60 ,  B64B1/70 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/104

Abstract: A hybrid VTOL vehicle having an envelope configured to provide hydrostatic buoyancy, a fuselage attached to the envelope and having at least one pair of wings extending from opposing sides thereof to produce dynamic lift through movement, and a thrust generation device on each wing and configured to rotate with each wing about an axis that is lateral to a longitudinal axis of the envelope to provide vertical takeoff or landing capabilities. Ideally, the envelope provides negative hydrostatic lift to enhance low-speed and on-the-ground stability.

公开(公告)号：EP2897863A4

公开(公告)日：2016-04-27

申请号：EP13838658

申请日：2013-09-12

Applicant: ISRAEL AEROSPACE IND LTD

Inventor： DEKEL GUY ,  ZIVAN LIOR ,  EFRATY YOAV ,  WOLFF AMIT ,  VOLOVICK AVNER

IPC: B64C29/00

CPC classification number: B64C27/52 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187 ,  G05D1/042 ,  G05D1/0808 ,  G05D1/0858 ,  G05D1/102

公开(公告)号：EP2814735A1

公开(公告)日：2014-12-24

申请号：EP13710309.9

申请日：2013-02-13

Applicant: Reiter, Johannes

Inventor： Reiter, Johannes

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

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 an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

公开(公告)号：EP2720948A1

公开(公告)日：2014-04-23

申请号：EP11867771.5

申请日：2011-06-17

Applicant: Sing, Robert, L.

Inventor： Sing, Robert, L.

IPC: B64F1/22 ,  B64D9/00 ,  B64F1/28 ,  B64D45/00 ,  B64C13/18

CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/187

Abstract: The self-sustaining drone aircraft freight and observation system (5) comprises a fleet of jet-powered drone aircraft (10) designed to carry freight (12) only. The drones (10) operate from a separate airfield in outlying areas to decrease land costs and to avoid disturbing residential and business areas. Navigation is automated using guidance from GPS satellites (16), and the aircraft (10) can be assisted by a hydraulic catapult (13) during takeoff to reduce the fuel payload. The observation component (18) includes sensors that can observe weather conditions and emergency signals from boats, ships and other sources. The system (5) may include a large-scale energy production center and multi-acre vegetable, herb and flower production center (26). The energy production center includes solar panels (30), fuel cells (38), and batteries (44). Thus, the system (5) does not need to be connected to the public utility electrical grid.

公开(公告)号：EP1963185B1

公开(公告)日：2014-01-22

申请号：EP06838485.8

申请日：2006-11-29

Applicant: Exelis Inc.

Inventor： PAGE, Gregory S.

IPC: B64F1/10 ,  F42B15/36 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  F42B15/36

公开(公告)号：EP2448832A1

公开(公告)日：2012-05-09

申请号：EP09786046.4

申请日：2009-07-01

Applicant: Philip Morris Products S.A.

Inventor： WEISS, Jacques ,  MERMOD, Jacques ,  SUCHET, Virginy

IPC: B65D5/42 ,  B65D85/10

CPC classification number: B64C3/16 ,  B41M3/16 ,  B64C3/32 ,  B64C11/001 ,  B64C39/024 ,  B64C39/04 ,  B64C39/066 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/165 ,  B65D5/4212 ,  B65D65/42 ,  B65D85/1045 ,  B65D2203/00 ,  Y10T428/24802

Abstract: Packaging (10) for consumer goods having a discontinuous tactile coating (16) is provided. The discontinuous tactile coating (16) is formed by applying one or more varnishes (18) to the outer surface of the packaging (10) in a pattern comprising a plurality of raised features having a height of at least about 10 microns and a separation of at least about 20 microns. In a preferred embodiment, the discontinuous tactile coating is formed by applying one or more tinted varnishes to the outer surface of the packaging.