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1.发明公开
公开(公告)号：EP3181443A1
公开(公告)日：2017-06-21
申请号：EP16190299.4
申请日：2016-09-23
申请人： The Boeing Company
摘要： An aircraft (10) includes a fuselage (17) with structural interfaces for connection to any one or more of a variety of vertical tails, horizontal tails and canards. Vertical tails, horizontal tails and/or canards of different sizes, shapes, sweep angles, box chords, and/or root chords may connect to the fuselage (17) without changing the structural layout or configuration of the fuselage (17) structural interfaces.
摘要翻译： 飞机（10）包括机身（17），其具有用于连接到各种垂直尾部，水平尾巴和鸭尾中的任何一个或多个的结构接口。 具有不同尺寸，形状，俯仰角度，箱和弦和/或根和弦的垂直尾巴，水平尾巴和/或犬只可以连接到机身（17），而不改变机身（17）结构接口的结构布局或配置。
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公开(公告)号：EP3402718B1
公开(公告)日：2022-12-21
申请号：EP17701961.9
申请日：2017-01-12
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公开(公告)号：EP2038602A2
公开(公告)日：2009-03-25
申请号：EP07873817.6
申请日：2007-07-06
发明人： BANKS, Johnny, E.
摘要： A trajectory control system includes a first control mechanism having a pair of outputs operably associated with a first pair of control surfaces, the first control mechanism operable to articulate the first pair of control surfaces in unison and a second control mechanism having a pair of outputs operably associated with a second pair of control surfaces, the second control mechanism operable to articulate the second pair of control surfaces in unison. The second control mechanism is nested in the first control mechanism such that the pair of outputs of the first control mechanism is substantially coplanar with the pair of outputs of the second control mechanism.
摘要翻译： 轨迹控制系统包括第一控制机构，该第一控制机构具有与第一对控制表面可操作地关联的一对输出，第一控制机构可操作以一致地铰接第一对控制表面，以及第二控制机构具有可操作地一对输出 与第二对控制表面相关联，第二控制机构可操作以一致地铰接第二对控制表面。 第二控制机构嵌套在第一控制机构中，使得第一控制机构的一对输出基本上与第二控制机构的一对输出共面。
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公开(公告)号：EP2961652A1
公开(公告)日：2016-01-06
申请号：EP14709508.7
申请日：2014-02-25
摘要： An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for supersonic flight and disconnected from each other for subsonic flight.
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公开(公告)号：EP0388068B1
公开(公告)日：1994-07-06
申请号：EP90302407.3
申请日：1990-03-07
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公开(公告)号：EP0388068A2
公开(公告)日：1990-09-19
申请号：EP90302407.3
申请日：1990-03-07
摘要： A flight vehicle includes a fuselage 10 having a consumable fuel supply 18,12, main wings 12 each with an elevon 14 and a pair of jettisonable foreplanes 16. The foreplanes provide lift at take-off and during transonic flight and, at higher supersonic speeds they are jettisoned.
摘要翻译： 飞行器车辆包括具有消耗燃料供应18,12的机身10，每个主翼12具有升降翼14和一对可抛弃的前板16.前平面在起飞时和跨音速飞行期间提供升力，并且在更高的超音速 他们被抛弃。
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公开(公告)号：EP2961652B1
公开(公告)日：2017-01-04
申请号：EP14709508.7
申请日：2014-02-25
摘要： An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for supersonic flight and disconnected from each other for subsonic flight.
摘要翻译： 飞机包括机身，枢转地联接到机身的后部的主翼，以及耦合到机身的前部的鸭舌，其中主翼和鸭被构造成连接在一起用于超音速飞行并且与每个机身断开连接 其他为亚音速飞行。
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公开(公告)号：EP2499042A2
公开(公告)日：2012-09-19
申请号：EP10788157.5
申请日：2010-11-05
申请人： Marganski, Edward
发明人： Marganski, Edward
IPC分类号： B64C5/04
摘要： The object of the invention is an aircraft provided with a device for creating a constant moment in relation to the axis of rotation of an additional control surface placed at the front of the aircraft at an as large as possible distance from the centre of gravity of the aircraft. The aircraft is characterised in that the control of the aerodynamic vertical force (7) is effected by deflecting control elements (3) pivotably mounted on the rotation axis (4), the deflection of said control elements causing rotation of a balance and control surface (1) mounted rotatably on axis (2), wherein the axis (2) is mounted perpendicularly to the plane of symmetry (5) of aircraft (6) forward of the resultant aerodynamic vertical force (7) generated by the balance and control surface (1).
摘要翻译： 本发明的目的是提供一种飞行器，该飞行器用于相对于放置在飞机前部的附加控制表面的旋转轴线产生恒定的力矩，该力矩与飞行器的重心距离尽可能大 飞机。 该飞行器的特征在于，通过偏转枢转地安装在旋转轴线（4）上的控制元件（3）来实现气动垂直力（7）的控制，所述控制元件的偏转导致平衡和控制表面（ 其中轴（2）垂直于飞机（6）的对称面（5）安装在由平衡和控制表面（7）产生的合成气动垂直力（7） 1）。
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公开(公告)号：EP0388068A3
公开(公告)日：1991-02-06
申请号：EP90302407.3
申请日：1990-03-07
摘要： A flight vehicle includes a fuselage 10 having a consumable fuel supply 18,12, main wings 12 each with an elevon 14 and a pair of jettisonable foreplanes 16. The foreplanes provide lift at take-off and during transonic flight and, at higher supersonic speeds they are jettisoned.
摘要翻译： 飞行器包括机身10，机身10具有消耗性燃料供应18,12，主翼12，每个主翼12具有升降机14和一对可抛弃的前机16.前机在起飞和跨音速飞行期间提供升力，并且在更高的超音速 他们被抛弃。
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