公开(公告)号：EP1594736A4

公开(公告)日：2010-02-24

申请号：EP04809283

申请日：2004-02-19

Applicant: AAI CORP

Inventor： MILLER STEPHEN W ,  VELAZQUEZ MATTHEW T

IPC: B64B20060101 ,  B64B1/00 ,  B64C3/56 ,  B64C39/02 ,  B64F1/04 ,  B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

公开(公告)号：EP1827972B1

公开(公告)日：2008-09-10

申请号：EP05813078.2

申请日：2005-11-30

Applicant: ISRAEL AIRCRAFT INDUSTRIES, LTD.

Inventor： SIRKIS, Omri

IPC: B64C9/18 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C9/18 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/201

Abstract: A method for landing a fixed wing aircraft is provided in which an inversion maneuver is performed so that the aircraft's back is facing the ground, and the aircraft's underside is facing away from the ground. After initiation or completion of this maneuver, deep stall is induced, and the aircraft descends almost vertically to land on its upper side, thus minimizing impact loads or damage on its underside. In a particular aerodynamic arrangement configured for carrying out the method, a flap (24), which may be stowed during normal flight, is deployed in a manner such as to aerodynamically induce a negative pitching moment on the aircraft and deep stall.

公开(公告)号：EP1734333B1

公开(公告)日：2008-07-02

申请号：EP06019954.4

申请日：2005-11-02

Applicant: NEXTER Munitions

Inventor： Brunet, Luc ,  Regis, Muriel

IPC: F42B12/36 ,  C06B25/12 ,  C06C15/00 ,  C06D3/00 ,  F42C19/08 ,  F41J9/08 ,  B64C3/00 ,  B64C39/02 ,  F42B10/04

CPC classification number: F42B3/28 ,  B64C39/024 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/165 ,  C06B23/001 ,  C06B23/003 ,  C06B45/00 ,  F41J9/08 ,  F42B5/18 ,  F42B5/192 ,  F42B10/04 ,  F42B12/36 ,  F42B12/365 ,  F42B12/76 ,  F42C19/0803 ,  F42C19/0842

公开(公告)号：EP1740824A2

公开(公告)日：2007-01-10

申请号：EP05724553.2

申请日：2005-03-03

Applicant: The Insitu Group, Inc.

Inventor： DENNIS, Brian, D. ,  HILLEN, Kenneth

IPC: F03D1/00

CPC classification number: B64C11/44 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/165

Abstract: Apparatuses and methods for controlling the motion of a propeller blade are disclosed. In one embodiment, the apparatus can include a first motor that rotates a propeller about a first axis with a first shaft. A first signal transmission portion, fixed relative to the first motor, can transmit signals to a second signal transmission portion that rotates with the first shaft. A second motor can be carried by the first shaft and can receive signals from the second signal transmission portion. The second motor can drive blades of the propeller about a second axis generally transverse to the first axis via a second shaft to vary the pitch of the blades.

公开(公告)号：EP1616785B1

公开(公告)日：2006-11-15

申请号：EP04450196.3

申请日：2004-10-28

Applicant: Schiebel Industries AG

Inventor： Schiebel, Hans-Georg

IPC: B64C39/02 ,  A63H27/133

CPC classification number: B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

公开(公告)号：EP1687200A2

公开(公告)日：2006-08-09

申请号：EP04810203.2

申请日：2004-11-01

Applicant: The Insitu Group, Inc.

Inventor： SLIWA, Steven, M. ,  VON FLOTOW, Andreas, H. ,  DENNIS, Brian, D.

IPC: B63H1/00

CPC classification number: B64C11/003 ,  A63H27/02 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/206 ,  B64D41/007 ,  F02K5/023 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/672

Abstract: Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link between the fixture and the propeller.

公开(公告)号：EP1193168A3

公开(公告)日：2003-03-12

申请号：EP01121573.8

申请日：2001-09-10

Applicant: Rafael Armament Development Authority Ltd.

Inventor： Yavnai, Arie

IPC: B62D57/032 ,  B62D57/04

CPC classification number: G05D1/0038 ,  B62D57/02 ,  B62D57/04 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  G05D1/0044

Abstract: A remotely-controlled unmanned mobile device (UMD) adapted to function as a robot scout to enter and reconnoiter the site of a disaster and to communicate to a rescue mission information regarding conditions prevailing at the site, making it possible for the mission to decide on rescue measures appropriate to these conditions. The UMD is operable in either of two modes. In its air-mobility mode the UMD is able to vertically take off and land, to fly to the site and then hover thereover. In its ground-mobility mode, the UMD can walk on legs over difficult terrain and through wrecked structures and ruins. The UMD is provided with condition-sensitive sensors for gathering data regarding conditions prevailing at the site, and position-sensitive sensors for avoiding obstacles in the path of the walking UMD, thereby assuring safe mobility. Other sensors govern geo-referenced navigation and flight control functions.

公开(公告)号：EP1255673A1

公开(公告)日：2002-11-13

申请号：EP01907770.0

申请日：2001-02-13

Applicant: Bertin Technologies

Inventor： LEPRETRE, Marc ,  CHASTANG, Georges

IPC: B64C39/02 ,  B64C27/20

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

Abstract: The invention concerns a remote-controlled flying machine, in particular for surveillance and inspection, capable of hovering and comprising a spherical open-worked resistant shroud (40) integral with a cylindrical fairing (16) wherein rotates a propeller (10) powered by an engine (12) housed in a fuselage (18) secured to the fairing (16) with radial arms (28) and straightening vanes (30).

公开(公告)号：EP1175336A1

公开(公告)日：2002-01-30

申请号：EP00922096.3

申请日：2000-04-12

Applicant: Sikorsky Aircraft Corporation

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

IPC: B64C27/10 ,  B64C27/22 ,  B64C39/02 ,  B64C39/06 ,  B64C27/20

CPC classification number: B64C27/20 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

Abstract: A method for reducing a nose-up pitching moment in an unmanned aerial vehicle (10) during forward flight. The unmanned aerial vehicle includes counter-rotating rotor assemblies (38, 40) that are mounted within a duct (18). Each rotor assembly (38, 40) includes a plurality of rotor blades. The method involves adjusting the rotor blades to have substantially zero pitch. Then rotating the rotor asemblies (38, 40) to produce a virtual plane (62) across the duct (18). The virtual plane (62) is operative for substantially deflecting air (70) passing over the fuselage (44) away from the duct (18). In one embodiment of the invention, the method involves the further step of obstructing at least a portion of the bottom of the duct (18) to inhibit air (70) that is flowing across the bottom of the duct from passing into the duct (18).

公开(公告)号：EP0629164B1

公开(公告)日：1999-05-26

申请号：EP93907455.5

申请日：1993-03-12

Applicant: SCHMITTLE, Hugh J.

Inventor： SCHMITTLE, Hugh J.

IPC: B64C3/38

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: The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66).