公开(公告)号：EP1799545A1

公开(公告)日：2007-06-27

申请号：EP05789189.7

申请日：2005-02-14

Applicant: RAYTHEON COMPANY

Inventor： CORDER, David, A. ,  KOESSLER, Jeffrey, H. ,  WEBB, George, R.

IPC: B64C39/02

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/145 ,  B64C2201/165 ,  B64C2201/201

Abstract: An air-launched aircraft (10) includes deployable wings (16, 18), elevons (20, 22), and vertical fins (26, 28) that deploy from a fuselage (12) during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module (14) that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and/or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.

公开(公告)号：EP1761430A2

公开(公告)日：2007-03-14

申请号：EP05761246.7

申请日：2005-04-14

Applicant: Arlton, Paul E. ,  Arlton, David J.

Inventor： Arlton, Paul E. ,  Arlton, David J.

IPC: B64C27/10

CPC classification number: B64C27/10 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

公开(公告)号：EP1689638A2

公开(公告)日：2006-08-16

申请号：EP04817324.9

申请日：2004-10-19

Applicant: Baldwin, Douglas G.

Inventor： Baldwin, Douglas G.

IPC: B64C27/28

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: A disclosed flying craft (100) includes a suspension structure (110) having a first end and a second end, a lift unit (150), and a payload unit (190). The lift unit includes a nacelle (128) and a tailboom (140), and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure’s second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

公开(公告)号：EP1645505A2

公开(公告)日：2006-04-12

申请号：EP05017978.7

申请日：2003-10-07

Applicant: FUJI JUKOGYO KABUSHIKI KAISHA

Inventor： Yamane, Akihiro, Fuji Jukogyo K.K.

IPC: B64C13/20 ,  B64C39/02 ,  G05D1/06

CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  G05D1/0669 ,  G05D1/0676

Abstract: An unmanned helicopter 20 includes altitude control device for giving a command of a collective pitch blade angle based on an altitude change rate command, etc., and performing altitude control of an airframe. The unmanned helicopter further includes descending device for causing the airframe to descend to a second altitude while changing descent rate command of the altitude control device and giving a descent rate command smaller than the descent rate command to the second altitude to the altitude control device for causing the airframe to descend from the second altitude to the ground.

Abstract translation: 无人直升机20的速率包括用于给在海拔高度变化命令等基于一个共同桨距的叶片角度的指令，并执行机体的高度控制高度控制装置。 无人直升机还包括用于使所述机身下降到第二高度，同时改变高度控制装置的下降率指令和至所述第二高度给人一种下降速度指令比所述下降率命令更小，以高度控制装置，用于使降装置 机身从第二海拔到地面下降。

公开(公告)号：EP1594736A2

公开(公告)日：2005-11-16

申请号：EP04809283.7

申请日：2004-02-19

Applicant: AAI CORPORATION

Inventor： MILLER, Stephen, W. ,  VELAZQUEZ, Matthew, T.

IPC: B64B1/00

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

Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

公开(公告)号：EP1175336B1

公开(公告)日：2003-07-23

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：EP1257466A2

公开(公告)日：2002-11-20

申请号：EP01937143.4

申请日：2001-02-07

Applicant: Aerovironment Inc.

Inventor： MACCREADY, Paul ,  HIBBS, Bart, D. ,  COX, Earl, C. ,  LISOSKI, Derek, L. ,  KENDALL, Greg, T.

IPC: B64D27/24

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.

公开(公告)号：EP1257465A2

公开(公告)日：2002-11-20

申请号：EP01934833.3

申请日：2001-02-12

Applicant: Aerovironment Inc.

Inventor： MACCREADY, Paul ,  HIBBS, Bart, D. ,  COX, Earl, C. ,  LISOSKI, Derek, L. ,  KENDALL, Greg T.

IPC: B64C39/02 ,  G05D1/00 ,  H04B7/185

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.

公开(公告)号：EP1193168A2

公开(公告)日：2002-04-03

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.

Abstract translation: 一种远程控制的无人值守移动设备（UMD），适用于作为机器人侦察员进入和侦察灾害现场，并向救援任务通报有关现场情况的信息，使特派团有可能决定 对这些条件适用的救援措施。 UMD可以在两种模式之一中操作。 在其空中移动模式下，UMD能够垂直起飞和着陆，飞到现场，然后悬停在此处。 在地面移动模式下，UMD可以在困难的地形上通过失踪的结构和遗迹走路。 UMD配有条件敏感的传感器，用于收集有关现场情况的数据，以及位置敏感传感器，用于避免步行UMD路径中的障碍物，从而确保安全的移动性。 其他传感器控制地理参考导航和飞行控制功能。

公开(公告)号：EP0629164A4

公开(公告)日：1995-07-12

申请号：EP93907455

申请日：1993-03-12

Applicant: SCHMITTLE HUGH J

Inventor： SCHMITTLE HUGH J

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

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).