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1. 发明公开

EP2625096A1 DEVICE AND METHOD FOR INCREASING THE AERODYNAMIC LIFT OF AN AIRCRAFT 有权
标题翻译： VORRICHTUNG UND VERFAHREN ZURERHÖHUNGDES AERODYNAMISCHEN HUBS EINES FLUGZEUGES
公开(公告)号：EP2625096A1
公开(公告)日：2013-08-14
申请号：EP11767986.0
申请日：2011-10-05
申请人： Airbus Operations GmbH
发明人： WEBER, Carsten , FISCHER, Markus , GROTE, Arne , RADESPIEL, Rolf , DREYER, Martin
IPC分类号： B64C5/12 , B64C9/34 , B64C23/06
CPC分类号： B64C23/06 , B64C5/12 , B64C9/34 , Y02T50/162 , Y02T50/44
摘要： A lift arrangement for an aircraft (2) comprises an aircraft fuselage section with an outside (3), an aerodynamic lift body (6, 8)attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies (12)arranged upstream of a leading edge (14) of the aerodynamic lift body (6, 8). The add-on bodies(12) comprise an aerodynamically effective surface and are equipped with incoming airflow to generate vortices (18) that impinge on the aerodynamic lift body (6, 8), thus leading to an increase inlift on the aerodynamic lift body (6, 8). Consequently it becomes possible with simple means to effectively influence lift generation on a lift body (6, 8), in particular to compensate for loss of lift as a result of icing. Preferably, the add-on bodies are moveable, and, when operational conditions do not require the use of said add-on bodies, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.
摘要翻译：飞机的电梯装置包括具有外部的飞机机身部分，附接到飞行器机身部分并从飞行器机身部分向外延伸的空气动力升降体，以及一对可移动地固定的附加物体，其布置在前缘的气动提升体。附加物体包括空气动力学有效的表面，并且配备有进入的气流以产生冲击空气动力升力体的涡流，从而导致空气动力升降体的升力增加。因此，电梯主体上的电梯产生有效地受到影响，特别是为了补偿结冰导致的电梯损失。附加物体是可移动的，并且可以移动到中性位置，在该位置中它们不会投射到飞机周围的流中，并且因此从流体动力学的角度来看是没有效果的。

2. 发明公开

EP0980823A3 Rumpfnase zur Steuerung von Fluggeräten 审中-公开
标题翻译：机头飞机的控制
公开(公告)号：EP0980823A3
公开(公告)日：2001-08-22
申请号：EP99115190.3
申请日：1999-08-16
申请人： DaimlerChrysler AG
发明人： Hakenesch, Peter, Dr.
IPC分类号： B64C23/00 , B64C5/12 , B64C23/06
CPC分类号： B64C9/36 , B64C5/12 , B64C23/00 , Y02T50/44
摘要： Steuerungseinrichtung für Fluggeräte mit einem Rumpfnasensegment (3) und zumindest einem Strake (5, 6), wobei das Rumpfnasensegment (3) rotatorisch gegenüber dem Flugzeugrumpf (1) verstellbar ist und der zumindest ein Strake (5, 6) an dem Rumpfnasensegment (3) ausklappbar angebracht ist.

3. 发明公开

EP3348955A1 ELEVON CONTROL SYSTEM 审中-公开
公开(公告)号：EP3348955A1
公开(公告)日：2018-07-18
申请号：EP17183571.3
申请日：2010-09-09
申请人： AeroVironment, Inc.
发明人： MIRALLES, Carlos Thomas , PLUMB, Nick , TAO, Tony Shuo , OLSEN, Nathan
IPC分类号： F42B15/01 , F41G7/00 , F41G9/00 , F41G7/22
CPC分类号： B64C13/28 , B64C3/44 , B64C3/50 , B64C3/56 , B64C5/12 , B64C9/02 , B64C9/08 , B64C9/18 , B64C11/00 , B64C13/18 , B64C39/024 , B64C2009/005 , B64C2201/021 , B64C2201/08 , B64C2201/102 , B64C2201/121 , B64C2201/14 , B64C2201/145 , B64C2201/146
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100,400,1000,1500) configured to control pitch, roll, and/or yaw via airfoils (141,142,1345,1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621,622). Embodiments include one or more rudder elements (1045,1046,1145,1146,1245,1345,1346,1445,1446,1545,1546) which may be rotatably attached and actuated by an effector member (1049,1149,1249,1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.

4. 发明公开

EP2475575A2 ELEVON CONTROL SYSTEM 有权
标题翻译：无人机飞行员Füstesteuerungsverfahren
公开(公告)号：EP2475575A2
公开(公告)日：2012-07-18
申请号：EP10833732.0
申请日：2010-09-09
申请人： AeroVironment, Inc.
发明人： MIRALLES, Carlos, Thomas , PLUMB, Nick , TAU, Shuo , OLSEN, Nathan
IPC分类号： B64C9/34 , B64C13/18 , B64C3/38 , B64C13/28
CPC分类号： B64C13/28 , B64C3/44 , B64C3/50 , B64C3/56 , B64C5/12 , B64C9/02 , B64C9/08 , B64C9/18 , B64C11/00 , B64C13/18 , B64C39/024 , B64C2009/005 , B64C2201/021 , B64C2201/08 , B64C2201/102 , B64C2201/121 , B64C2201/14 , B64C2201/145 , B64C2201/146
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100, 400, 1000, 1500) configured to control pitch, roll, and/or yaw via airfoils (141, 142, 1345, 1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621, 622). Embodiments include one or more rudder elements (1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546) which may be rotatably attached and actuated by an effector member (1049, 1149, 1249, 1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.
摘要翻译：一种包括飞行器或无人驾驶飞行器（UAV）的系统，其被配置为经由具有弹性安装的后缘的机翼来控制俯仰，滚动和/或偏航，所述后翼与机身偏转致动器喇叭相对。实施例包括一个或多个方向舵元件，其可以由设置在机身壳体内的效应器构件可旋转地附接和致动，并且部分地可部分地接合一个或多个舵元件。

5. 发明公开

EP3374260A1 AERIAL VEHICLE WITH DEPLOYABLE COMPONENTS 有权转让
公开(公告)号：EP3374260A1
公开(公告)日：2018-09-19
申请号：EP16864692.5
申请日：2016-04-21
申请人： Area-I Inc.
发明人： ALLEY, Nicholas Robert , STEELE, Joshua Lemming , WILLIAMS, Jesse Owen , KUEHME, Daniel , PHILLIPS, Jonathan Caleb
IPC分类号： B64C3/56
CPC分类号： B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

6. 发明公开

EP2368793A3 Bemanntes Luftfahrzeug 审中-公开
标题翻译：有人驾驶飞机
公开(公告)号：EP2368793A3
公开(公告)日：2014-05-07
申请号：EP11002233.2
申请日：2011-03-18
申请人： Deutsches Zentrum für Luft- und Raumfahrt e.V.
发明人： Hühne, Christian , Bartsch, Ivonne , Nickel, Jörg , Krajenski, Volker , Ernst, Gerald
IPC分类号： B64C5/02 , B64C5/18 , B64C5/16 , B64C5/14 , B64C5/12 , B64C5/10
CPC分类号： B64C5/02 , B64C5/10 , B64C5/12 , B64C5/14 , B64C5/16 , B64C5/18
摘要： Die Erfindung betrifft ein bemanntes Luftfahrzeug (1) mit wenigstens einer Tragfläche (2) zur Auftriebserzeugung und einem in Flugrichtung hinter der Tragfläche angeordneten Höhenleitwerk (3) zur Fluglagestabilisierung und Steuerung des Luftfahrzeuges (1). Das Höhenleitwerk (3) ist bezüglich wenigstens eines der folgenden Parameter des Höhenleitwerks (3) einstellbar:
a) aerodynamisch wirksamer Flächeninhalt (F H ),
b) Streckung (Λ H ),
c) Pfeilungswinkel ( ϕ H , ϕ 1 , ϕ 2 ),
d) Spannweite (b H ),
e) die Länge (r H ) des Höhenleitwerks-Hebelarms.

7. 发明公开

EP1479605A3 Helicopter 有权
标题翻译：直升机
公开(公告)号：EP1479605A3
公开(公告)日：2008-05-07
申请号：EP04252900.8
申请日：2004-05-19
申请人： Fuji Jukogyo Kabushiki Kaisha
发明人： Shiraishi, Takayuki c/o Fuji Jukogyo Kabushiki K. , Tsuura, Seiichi c/o Fuji Jukogyo Kabushiki Kaisha , Kuramochi, Kenji c/o Fuji Jukogyo Kabushiki K.
IPC分类号： B64C7/00 , B64C27/00 , B64D1/18
CPC分类号： B64D1/18 , B64C5/12 , B64C23/00 , B64C27/04
摘要： A helicopter (1) having: a flow control device (8) provided at one of a lower portion of a side surface (2a) of a fuselage (2) and a portion on a lower surface (2a) of the fuselage (2) near the side surface (2a) and extending downward.

8. 发明授权

EP2475575B1 UAV whith deployable wings and method of flight control 有权
标题翻译：无人机可展开的机翼和飞行控制方法
公开(公告)号：EP2475575B1
公开(公告)日：2017-11-01
申请号：EP10833732.0
申请日：2010-09-09
申请人： AeroVironment, Inc.
发明人： MIRALLES, Carlos, Thomas , PLUMB, Nick , TAO, Tony Shuo , OLSEN, Nathan
IPC分类号： F42B15/01 , F41G7/00 , F41G9/00 , F41G7/22
CPC分类号： B64C13/28 , B64C3/44 , B64C3/50 , B64C3/56 , B64C5/12 , B64C9/02 , B64C9/08 , B64C9/18 , B64C11/00 , B64C13/18 , B64C39/024 , B64C2009/005 , B64C2201/021 , B64C2201/08 , B64C2201/102 , B64C2201/121 , B64C2201/14 , B64C2201/145 , B64C2201/146
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100, 400, 1000, 1500) configured to control pitch, roll, and/or yaw via airfoils (141, 142, 1345, 1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621, 622). Embodiments include one or more rudder elements (1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546) which may be rotatably attached and actuated by an effector member (1049, 1149, 1249, 1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.

9. 发明公开

EP2475575A4 ELEVON CONTROL SYSTEM 有权
标题翻译： RUDERSTEUERUNGSSYSTEM
公开(公告)号：EP2475575A4
公开(公告)日：2015-07-08
申请号：EP10833732
申请日：2010-09-09
申请人： AEROVIRONMENT INC
发明人： MIRALLES CARLOS THOMAS , PLUMB NICK , TAO TONY SHUO , OLSEN NATHAN
IPC分类号： F42B15/01 , F41G7/00 , F41G7/22 , F41G9/00
CPC分类号： B64C13/28 , B64C3/44 , B64C3/50 , B64C3/56 , B64C5/12 , B64C9/02 , B64C9/08 , B64C9/18 , B64C11/00 , B64C13/18 , B64C39/024 , B64C2009/005 , B64C2201/021 , B64C2201/08 , B64C2201/102 , B64C2201/121 , B64C2201/14 , B64C2201/145 , B64C2201/146
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100, 400, 1000, 1500) configured to control pitch, roll, and/or yaw via airfoils (141, 142, 1345, 1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621, 622). Embodiments include one or more rudder elements (1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546) which may be rotatably attached and actuated by an effector member (1049, 1149, 1249, 1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.
摘要翻译：一种包括飞行器或无人驾驶飞行器（UAV）的系统，其被配置为经由具有弹性安装的后缘的机翼来控制俯仰，滚动和/或偏航，所述后翼与机身偏转致动器喇叭相对。实施例包括一个或多个方向舵元件，其可以由设置在机身壳体内的效应器构件可旋转地附接和致动，并且部分地可部分地接合一个或多个舵元件。

10. 发明公开

EP1863705A2 AEROFOIL SURFACE FOR CONTROLLING SPIN 审中-公开
标题翻译：机翼面积用于控制旋流
公开(公告)号：EP1863705A2
公开(公告)日：2007-12-12
申请号：EP06710183.2
申请日：2006-03-23
申请人： GFS Projects Limited
发明人： HATTON, Geoffrey , MCINTOSH, Simon
IPC分类号： B64C39/06
CPC分类号： B64C39/064 , B63G8/18 , B64C5/12 , B64C5/18
摘要： The invention concerns craft of the type in which a fan directs a jet of fluid (4) over a curved canopy ( 1 ). The canopy ( 1 ) is shaped to divert the flow from a radial to an axial direction to produce lift. A problem is that rotation of the fan causes unwanted rotation of the canopy ( 1 ). The problem is solved using vanes (6) on the canopy ( 1 ) that have an adjustable surface area; and by providing a control system to adjust the effective surface area so as to compensate for the tendency of the rotor to rotate the canopy. The vanes ( 6 ) can be designed to slide in and out of the canopy (1) to obtain the required adjustment. In a preferred arrangement the vanes are arranged between upstream and downstream ends of the flow at a position where the effects of changes in swirl angle with varying rotor speed at least partially compensate for consequential changes in the tendancy for the canopy to spin.

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