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21.发明公开Sealing system for the gap existing between the fuselage and the elevator of the orientable horizontal stabiliser of an aircraft, extended with an aerodynamic fairing for sealing of the opening existing between the fuselage and the orientable horizontal stabiliser 有权密封用于飞机机身和可调节的水平尾翼的电梯之间的间隙，与气动整流罩延长所述主体和所述可调节尾翼之间的开口的密封
公开(公告)号：EP1857360A3
公开(公告)日：2010-06-23
申请号：EP07380110.2
申请日：2007-04-19
摘要： Sealing system for the gap (2) between the fuselage (3) and the elevator (4) of the orientable horizontal stabiliser (5) of an aircraft, extended with an aerodynamic fairing (8) for sealing of the opening (24) between the fuselage (3) and said orientable horizontal stabiliser (5) which comprises a main body (1) and an aerodynamic fairing (8) which is extended from the main body (1) in continuity with the latter, and a plurality of first elastic sealing profiles (9) between the first surface (11) of the main body (1) including the aerodynamic fairing (8) and the outer surface of the fuselage (3) and making contact with them, and a plurality of second elastic sealing profiles (13) between the second surface (12) of the main body (1) and the first end of the elevator (15) and making contact with them, in such a way that the sealing takes place of the gap (2) and the opening (24) and an aerodynamic continuity is produced between the orientable horizontal stabiliser (5), the fuselage (3) and the elevator (4) when the elevator (4) is at rest in the plane of the orientable horizontal stabiliser (5) for any of the orientation positions of the orientable horizontal stabiliser (5).
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22.发明公开
公开(公告)号：EP1544100A1
公开(公告)日：2005-06-22
申请号：EP04292844.0
申请日：2004-12-01
申请人： AIRBUS FRANCE
发明人： Boe, Régis , Sauvinet, Frédéric
IPC分类号： B64C9/00 , B64C9/02 , B64C9/06 , B64C9/08 , B64C9/10 , B64C9/12 , B64C9/30 , B64C5/00 , B64C5/02 , B64C5/10 , B64C13/00
摘要： Procédé pour la réduction des charges aérodynamiques appliquées aux gouvernes de profondeur d'un aéronef lors d'un décollage.
Selon l'invention, préalablement à la rotation, on surbraque à cabrer l'empennage horizontal réglable (2) et on braque à piquer les gouvernes de profondeur (4).摘要翻译： 该方法涉及在一个方向上的倾斜角度比对应于一个通常结构的值大的有效值接通水平尾翼基团（2）至鼻子起来，用。 电梯（4）在一个方向转动潜水，谋求确实鼻子的动作的组合起来，产生潜水的气动力率确实等于力通过在配置尾部基团和电梯的组件生成的。
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公开(公告)号：EP0416268A2
公开(公告)日：1991-03-13
申请号：EP90114406.3
申请日：1990-07-27
发明人： Nash, William
IPC分类号： B64C5/10
CPC分类号： B64C5/10
摘要： The tailplane 6 is mounted to an aircraft by a spigot 7 and is also rotatable about the spigot 7 to provide aerodynamic control. At the same time the tail plane is pivotable about an axis extending generally parallel to the longitudinal axis of the aircraft in order to optimise the tail plane configuration for various speeds.
摘要翻译： 尾翼6通过插口7安装到飞行器上，并且还可以围绕插口7旋转以提供空气动力学控制。 同时，尾翼平面可围绕大致平行于飞行器的纵向轴线延伸的轴线枢转，以便为各种速度优化尾翼构型。
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公开(公告)号：EP3597534A1
公开(公告)日：2020-01-22
申请号：EP19196564.9
申请日：2013-03-27
申请人： The Boeing Company
发明人： ROMAN, Dino L. , VASSBERG, John Charles , FRIEDMAN, Douglas M. , MALACHOWSKI, Adam P. , VEGTER, Christopher A.
摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to a ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move from the static position to an in-flight position and resulting in a relative span increase of the wing.
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28.发明公开MULTIPLE CONTROLLABLE AIRFLOW MODIFICATION DEVICES 审中-公开VORRICHTUNGEN ZUR MODIFIKATION MEHRERER STEUERBARER LUFTSTREME
公开(公告)号：EP2834146A4
公开(公告)日：2015-12-09
申请号：EP13773104
申请日：2013-03-22
发明人： GUIDA NICHOLAS R
CPC分类号： B64C3/54 , B64C5/16 , B64C13/16 , B64C23/076 , Y02T50/145 , Y02T50/164
摘要： An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, and/or increase efficiency.
摘要翻译： 主动翼延伸部包括基本上平行于飞行器的翼的主体部分，好像它是机翼的延伸部分。 主体部分可附接到飞行器机翼并且包括耦合到其上的多个可控气流改变装置。 由于具有多个可控气流改变装置，机翼延伸部能够响应于飞行中的条件来调节多个可控气流改变装置的控制表面，以减少机翼载荷，改善机翼疲劳特性，增加范围和/或 提高效率。
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公开(公告)号：EP2502826B1
公开(公告)日：2015-01-21
申请号：EP12160197.5
申请日：2012-03-19
CPC分类号： B64C13/00 , B64C5/10 , B64C5/12 , B64C17/02 , B64C27/20 , B64C39/001 , B64C39/064
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