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：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：EP1233905B1

公开(公告)日：2008-06-11

申请号：EP00952173.3

申请日：2000-07-24

Applicant: Advanced Aerospace Technologies, Inc.

Inventor： MCDONNELL, William, R.

IPC: B64C25/68

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: An improved method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10) is disclosed. The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

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：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：EP1185457A4

公开(公告)日：2002-08-07

申请号：EP00950213

申请日：2000-06-06

Applicant: MCGEER BRIAN T ,  VON FLOTOW ANDREAS H ,  ROESELER CORY ,  JACKSON CLIFFORD

Inventor： MCGEER BRIAN T ,  VON FLOTOW ANDREAS H ,  ROESELER CORY ,  JACKSON CLIFFORD

IPC: B64C25/68 ,  B64C39/02 ,  B64F1/02

CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/104 ,  B64C2201/148 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02

Abstract: A method and an apparatus for capturing a flying object (5) are revealed. The apparatus includes a generally linear fixture (2), such as a length of rope; a means for suspending (1) the fixture (2) across the path of the flying object (5); and one or more hooks (19) on the flying object (5). The method involves suspending the fixture (2) such that its orientation includes a component normal to the flying object's line of approach; striking the fixture (2) with the flying object (5), which causes the flying object (5) to rotate and decelerate, while the fixture (2) slides along a surface of the flying object (5) into a hook (19); capturing the fixture (2) in the hook (19); and retrieving the flying object (5) from the fixure (2).

Abstract translation: 揭示了用于捕捉飞行物体（5）的方法和装置。 该设备包括大致线性的固定装置（2），例如一段绳索; （1）悬挂在飞行物体（5）的路径上的夹具（2）的装置; 和飞行物体（5）上的一个或多个钩子（19）。 该方法包括悬挂夹具（2），使得其定向包括垂直于飞行物体的接近线的部件; （2）沿着飞行物体（5）的表面滑动到钩（19）中时，使飞行物体（5）撞击固定装置（2），使飞行物体（5）旋转并减速。 ; 捕获钩（19）中的夹具（2）; 并从固定装置（2）取回飞行物体（5）。

公开(公告)号：EP1173360A1

公开(公告)日：2002-01-23

申请号：EP00942624.8

申请日：2000-04-12

Applicant: Sikorsky Aircraft Corporation

Inventor： CYCON, James ,  SCOTT, Mark, W. ,  DEWITT, Christopher, W.

IPC: B64C39/02 ,  B64C27/20

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

Abstract: An unmanned aerial vehicle that includes a fuselage (12) with a partial toroidal forward portion, and an aft portion. A duct (18) is formed through the fuselage and extends from the top to the bottom of the fuselage. Two counter-rotating rotor assemblies (16) are mounted within the duct for providing downward thrust through the duct. The rotor assemblies are supported by a plurality of support struts (20). At least one engine is mounted within the fuselage and engages with the rotor assemblies. A pusher prop assembly (50) is amounted to the aft portion of the fuselage. The pusher prop assembly is designed to provide forward thrust along the longitudinal axis of the aircraft. The pusher prop assembly includes a drive shaft (58) that is engaged with the engine. A plurality of propellers (56) are attached to and rotated by the drive shaft. A shroud (54) is mounted to the aft portion of the fuselage around the propellers and is operative for channelling the air passing through the propellers in a substantially aft direction. A pair of wings (42) is removably attached to the sides of the fuselage. Each wing preferably includes a fixed portion and a pivotal flaperon portion hinged to the fixed portion. Directional vanes (60) are preferably mounted to the shroud downstream from the propellers and control flow out of the shroud. Deflectors may be mounted to the bottom of the fuselage across a portion of the duct to control flow of air into the duct.

公开(公告)号：EP0696983B1

公开(公告)日：1997-03-26

申请号：EP94915945.3

申请日：1994-04-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FLEMMING, Robert, J., Jr. ,  ROSEN, Kenneth, M. ,  SHEEHY, Thomas, W.

IPC: B64C27/20 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: An unmanned aerial vehicle (UAV) (100) having a toroidal fuselage (120) and a rotor assembly (170) including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures (18) having a cambered airfoil profile to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV. The ancillary aerodynamic structures are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes. In a first embodiment, the ancillary aerodynamic structures (18) are fixedly mounted in combination with the toroidal fuselage (10) at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures (19) are rotatably mounted in combination with the toroidal fuselage (10') to provide variable incidence ancillary aerodynamic structures for the UAV.

公开(公告)号：EP0629164A1

公开(公告)日：1994-12-21

申请号：EP93907455.0

申请日：1993-03-12

Applicant: SCHMITTLE, Hugh J.

Inventor： SCHMITTLE, Hugh J.

IPC: B64C3 ,  B64C29 ,  B64C39

CPC classification number: B64C39/024 ,  B64C3/385 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

Abstract: Un aéronef à décollage et à atterrissage verticaux (10) comprend une aile libre (16) constituée d'ailes situées sur les côtés opposés du fuselage (12) et interconnectées de manière à pouvoir tourner librement sans joints, dont le pas différentiel peut être ajusté par le pilote, par un ordinateur ou par télécommande. Pendant le lancement vertical, les gouvernes de profondeur (26) et de direction (24), ainsi que le réglage du pas différentiel des ailes commandent la profondeur, le lacet et le roulis, respectivement. Pendant le lancement, la gouverne de profondeur (26) incline le nez du fuselage (12) vers le bas afin de modifier le vecteur de poussée et accélérer horizontalement l'aéronef, alors que l'aile libre (16) tourne par rapport au fuselage (12) jusqu'à une position généralement horizontale afin de porter l'aéronef pendant le vol horizontal. La transition du vol horizontal au vol vertical est obtenue par le procédé inverse et l'aéronef peut être doucement récupéré dans ou sur une surface élastique telle qu'un filet (66).

公开(公告)号：EP0472927A1

公开(公告)日：1992-03-04

申请号：EP91112652.2

申请日：1991-07-27

Applicant: E-SYSTEMS INC.

Inventor： Loucks, Kenneth Wayne

IPC: B64C39/02 ,  B64D39/00

CPC classification number: B64C39/024 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64D39/00

Abstract: A method and apparatus for in-flight refueling of unmanned aircraft includes a manned tanker aircraft having a refueling probe mounted thereon. The probe is extendable for increased visual reference. A drogue mounted on the distal end of a flexible refueling hose is trailed from the unmanned aircraft. The refueling hose is stored on a reel assembly mounted on the fuel tank of unmanned aircraft. The reel assembly is remotely actuated from the manned tanker to pay out the refueling hose. A homing system transmits signals from the manned aircraft guiding the drogue to the probe. Upon insertion of the probe into the drogue, automatic coupling occurs and the unmanned aircraft is refueled.

Abstract translation: 一种用于无人驾驶飞机加油的方法和装置包括一个载人油轮飞机，其上安装有加油探头。 探头是可扩展的，以增加目视参考。 安装在柔性加油软管的远端的锥套从无人驾驶飞机落下。 加油软管储存在安装在无人驾驶飞机燃油箱上的卷轴组件上。 卷轴组件从载人油轮远程启动，以支付加油软管。 一个归位系统从载人航空器传送信号，将导管引导到探头。 在将探头插入锥套后，会发生自动联轴器，并且无人驾驶的飞机被加油。