公开(公告)号：US06409122B1

公开(公告)日：2002-06-25

申请号：US09761076

申请日：2001-01-17

Applicant: Leland M. Nicolai

Inventor： Leland M. Nicolai

IPC: B64C3500

CPC classification number: B64C35/005 ,  B60V1/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/187

Abstract: An anti-submarine warfare system includes an unmanned “sea-sitting” aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

Abstract translation: 一种反潜战系统包括一个无人“海坐”飞机舱潜艇检测设备，该飞机包括一个主体部分，该主体部分具有适于在坐在水中时稳定地支撑主体部分的双体船结构，该主体部分包括机身和横向 通过平台连接到机身的安装支架，以及容纳在机身内的潜艇检测设备，并且适于与设置在相邻水位的声波电子电子连接。

公开(公告)号：US5918832A

公开(公告)日：1999-07-06

申请号：US818582

申请日：1997-03-14

Applicant: Siegfried Hermann Zerweckh

Inventor： Siegfried Hermann Zerweckh

IPC: B64C3/38 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C3/38 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  Y02T50/145

Abstract: An air vehicle defining a plane of symmetry includes a pair of outboard panels which are rotatably mounted on the lifting body of the vehicle and respectively extend in opposite directions from the plane of symmetry. A control system collectively rotates the outboard panels to selectively contribute forces from the panels to the lift on the air vehicle. The control system also differentially rotates the outboard panels to control roll of the air vehicle. A pair of empennage panels are also rotatably mounted on the lifting body to establish a dihedral angle centered on the plane of symmetry. The control system collectively rotates these empennage panels to control pitch, and differentially rotates the empennage panels to control yaw, of the air vehicle. In a high speed flight regime the lifting body alone is sufficient and the outboard panels are collectively rotated to reduce drag and contribute substantially zero lift. In a slow speed flight regime, the outboard panels are collectively rotated to contribute to the lift on the air vehicle.

Abstract translation: 限定对称平面的空中车辆包括一对舷外面板，其可旋转地安装在车辆的提升体上并且分别沿着对称平面的相反方向延伸。 控制系统共同地旋转外侧面板，以选择性地贡献从面板到机动车辆上的电梯的力。 控制系统还将外侧面板差分地旋转以控制空中车辆的滚动。 一对尾翼也可旋转地安装在提升体上，以建立以对称平面为中心的二面角。 控制系统将这些尾翼面板共同旋转以控制俯仰，并差速旋转尾翼面板以控制飞行器的偏航。 在高速飞行状态下，单独的提升体就足够了，并且外侧面板共同旋转以减少阻力并大体上提供零升力。 在慢速飞行状态下，外侧面板被集体旋转以对飞行器上的电梯做出贡献。

公开(公告)号：US4032088A

公开(公告)日：1977-06-28

申请号：US675004

申请日：1976-04-08

Applicant: John Jerome McAvoy

Inventor： John Jerome McAvoy

IPC: B60V3/08 ,  B64C39/02 ,  B64C25/56

CPC classification number: B60V3/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187 ,  B64D2201/00

Abstract: An air bag landing system for an aircraft. The landing system has an air bag assembly which is stored in the fuselage of the aircraft during cruise and which extends for landing. The assembly consists of a rigid arm with either two or three folding portions and an inflatable bag attached to the underside of the arm. The inflatable bag cushions the impact of the aircraft at landing. Actuators are provided to extend and retract the assembly.

Abstract translation: 飞机的气囊着陆系统。 着陆系统具有气囊组件，其在巡航期间存储在飞行器的机身中并且延伸以着陆。 该组件包括具有两个或三个折叠部分的刚性臂和附接到臂的下侧的可充气袋。 充气袋缓冲飞机在着陆时的冲击。 提供致动器以延伸和缩回组件。

公开(公告)号：EP2874875B1

公开(公告)日：2018-03-07

申请号：EP13742690.4

申请日：2013-07-19

Applicant: Astigan Limited

Inventor： ELSON, Andrew Charles

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187 ,  B64D2211/00

Abstract: A method of launching a powered unmanned aerial vehicle, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, wherein the vehicle is prevented from entering its flight mode during ascent, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

公开(公告)号：EP2727834A3

公开(公告)日：2017-11-22

申请号：EP13184403.7

申请日：2013-09-13

Applicant: Airbus Defence and Space GmbH

Inventor： Steinwandel, Jürgen ,  van Toor, Jan ,  Voit-Nitschmann, Rudolf ,  Scholz, Werner

IPC: B64C31/024 ,  B64F5/00 ,  B64C1/26 ,  B64D27/02

CPC classification number: B64C31/024 ,  B64C1/26 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2211/00 ,  B64D2027/026 ,  Y02T50/64

Abstract: Die Erfindung betrifft einen Bausatz (104) und ein Herstellverfahren zum Herstellen eines unbemannten Luftfahrzeugs (10) mit einem maximalen Startgewicht von wenigstens 250kg, wobei der Bausatz (104) eine Rumpfstruktur (13) mit einer Auftriebserzeugungsstrukturbefestigungsschnittstelle (24) zur Befestigung einer Auftriebserzeugungsstruktur (14) und weiter eine erste Auftriebserzeugungsstrukur (14a) und eine unterschiedliche zweite Auftriebserzeugungsstruktur (14b) aufweist, wobei die erste und die zweite Auftriebsstrukturerzeugungsstruktur (14a, 14b) jeweils eine gleich ausgebildete Rumpfstrukturbefestigungsschnittstelle (25) zur Befestigung an der Auftriebsstrukturerzeugungsschnittstelle (24) der Rumpfstruktur (13) aufweist.

Abstract translation: 本发明涉及一组（104）和具有至少250千克的最大起飞重量，一种制造无人驾驶飞行器（10）的制造方法，其中所述试剂盒（104）的主体结构（13）与提升用于固定升力产生结构产生结构连接接口（24）（14 有），并且进一步的第一Auftriebserzeugungsstrukur（14a）和不同的第二升程产生结构（14B），其中，第一和第二升程模式生成结构（14A，14B）（每一个相同设计的机身结构的安装接口（25）用于附接到机身结构的浮力结构生成界面（24） 13）。

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：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：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：EP1784331A1

公开(公告)日：2007-05-16

申请号：EP05759026.7

申请日：2005-07-06

Applicant: ELBIT SYSTEMS LTD.

Inventor： SIRKIS, Omri

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187

Abstract: There is provided an Unmanned Air Vehicule (uav) (2) including an engine (4) and an airframe (6), including means for performing a deep stall maneouvre; at least one inflatable sleeve (12) connected or connectable to the airframe (6), and means for inflating the sleeve (12) during flight, wherein the inflated sleeve (12) extends along the lower side of the airframe (6) so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

公开(公告)号：EP1242279B1

公开(公告)日：2004-01-07

申请号：EP00990085.3

申请日：2000-12-20

Applicant: Institut de Recherche pour le Développement ( IRD)

Inventor： ASSELINE, Jean ,  DE NONI, George

IPC: B64C39/02 ,  B64C31/036 ,  B64D47/08

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: The invention concerns a small-size radio-controlled flying device propelled by a heat engine (20) with pusher propeller (10) for remote sensing, said device enabling short take-off and landing and a maximum flying speed of 34 Km/h. The device comprises a nacelle and a wing system, the nacelle (1) being a rigid three-wheeled carriage capable of being disassembled by denesting a more or less pyramidal jig with rear base (2) and front top (7), a lower plane (3) two lateral planes (4, 5) and an upper plane (6), the base being a single-piece welded element and comprising the engine, the propeller, a tank and the remote sensing unit, the top being a single-piece welded element, the lower plane and the two lateral planes comprising side members (11, 12) at least assembled at the base and at the top, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being arranged overlapping forward in the top and the wheels being low pressure tyres, the wing system (13) being a wing box flexible parafoil, said wing system being linked to the nacelle adjustable by two front suspension cables (17), two braking suspension cables (18) acting on the two flaps/wings.