-
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
申请人： AAI CORPORATION
IPC分类号： B64B1/00
CPC分类号： B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/084 , B64C2201/102 , B64C2201/165 , B64C2201/201 , B64C2201/203 , B64F1/06
摘要： 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.
-
102.发明授权
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
CPC分类号： B64C27/20 , B64C27/10 , B64C39/024 , B64C2201/027 , B64C2201/104 , B64C2201/108 , B64C2201/126 , B64C2201/127 , B64C2201/162 , B64C2201/165
摘要： 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
申请人： Aerovironment Inc.
IPC分类号： B64D27/24
CPC分类号： 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
摘要： 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
申请人： Aerovironment Inc.
CPC分类号： 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
摘要： 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
发明人： Yavnai, Arie
IPC分类号： B62D57/032 , B62D57/04
CPC分类号： 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
摘要： 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.
摘要翻译： 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
申请人： SCHMITTLE HUGH J
发明人： SCHMITTLE HUGH J
CPC分类号： 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
摘要： 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).
-
公开(公告)号：EP0184226B1
公开(公告)日：1988-09-14
申请号：EP85116421.0
申请日：1983-10-12
申请人： DORNIER GMBH
发明人： Friedel, Franz , Frühauf, Werner , Harms, Günter , Heise, Georg, Dipl.-Ing. , Lükewille, Heinrich, Dipl.-Ing.
CPC分类号： F42B10/64 , B64C39/024 , B64C2201/028 , B64C2201/044 , B64C2201/165 , B64C2201/201 , F16D7/021 , F42B15/105
-
公开(公告)号：EP0184226A3
公开(公告)日：1987-05-06
申请号：EP85116421
申请日：1983-10-12
申请人： DORNIER GMBH
发明人： Friedel, Franz , Frühauf, Werner , Harms, Günter , Heise, Georg, Dipl.-Ing. , Lükewille, Heinrich, Dipl.-Ing.
CPC分类号： F42B10/64 , B64C39/024 , B64C2201/028 , B64C2201/044 , B64C2201/165 , B64C2201/201 , F16D7/021 , F42B15/105
-
公开(公告)号：EP0184226A2
公开(公告)日：1986-06-11
申请号：EP85116421.0
申请日：1983-10-12
申请人： DORNIER GMBH
发明人： Friedel, Franz , Frühauf, Werner , Harms, Günter , Heise, Georg, Dipl.-Ing. , Lükewille, Heinrich, Dipl.-Ing.
CPC分类号： F42B10/64 , B64C39/024 , B64C2201/028 , B64C2201/044 , B64C2201/165 , B64C2201/201 , F16D7/021 , F42B15/105
摘要： Unbemannter Flugkörper, der in einem Behälter transportiert und aus dem Behälter mittels eines Hilfsantriebes nach Lösung einer Arretierung gestartet wird und der während des Marschfluges durch ein Propellertriebwerk antreibbar ist, wobei eine Reibschlußkupplung (64, 65) am Flugkörper vorgesehen ist, die ohne Zuführung von Energie von aussen mittels des Antriebes (7) den innerhalb des Behälters (1') stillstehenden Propeller (6) mit dem bereits im Behälter laufenden Antriebsmotor (7) nach Verlassen des Behälters kuppelt.
摘要翻译： 这是在一个容器中的锁定机构的释放和后运送并从容器推出由辅助驱动装置无人驾驶飞机是由一个螺旋桨发动机，其特征在于，摩擦离合器（64，65）被设置在导弹，巡航飞行期间驱动其中没有能量的供给 从由所述驱动装置的外侧（7），所述容器（1“）的螺旋桨（6）与当前容器内部的固定到驱动马达（7）在离开容器后脱离。
-
公开(公告)号：EP3386851A1
公开(公告)日：2018-10-17
申请号：EP16822302.2
申请日：2016-12-07
CPC分类号： B64C27/58 , B64C11/02 , B64C27/12 , B64C39/024 , B64C2201/024 , B64C2201/042 , B64C2201/108 , B64C2201/162 , B64C2201/165 , H02K7/106 , H02K7/114 , H02K7/14 , H02K49/10
摘要： A propeller alignment device is described. The propeller alignment device can include a second retainer attached to a propeller and a motor. The propeller alignment device can also include a first retainer that does not rotate, but that is aligned with the second retainer. The first retainer can include two or more magnets oppositely orientated relative to each other. The second retainer can also include two or more magnets oppositely orientated relative to each other. As the second retainer rotates relative to the first retainer, the magnets may alternatingly align with each other. In the absence of a current applied to the motor, the magnets may magnetically bias the second retainer into a predetermined orientation relative to the first retainer. The predetermined orientation can be predetermined to correspond to an alignment of the propeller that is desirable (e.g., that minimizes aerodynamic drag on the propeller).
-
-
-
-
-
-
-
-
-
搜索结果
196 条记录 (耗时 0.017 秒)
