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公开(公告)号：US08297551B2
公开(公告)日：2012-10-30
申请号：US12721083
申请日：2010-03-10
IPC分类号： B64C25/14
CPC分类号： B64C25/12 , B64C25/34 , B64C2025/125
摘要： The airplane comprises a fuselage having frames, and at least two undercarriages each comprising a support and at least one wheel, the support being carried directly by the fuselage and being hinged to the fuselage about an axis that lies outside the frames.The undercarriage is movable between an operational position in which the or each wheel is vertical, and a rest position.The support and the wheel have a configuration such that, in the rest position, the undercarriage extends circumferentially relative to the fuselage and outside the frames.
摘要翻译： 飞机包括具有框架的机身，并且至少两个底架，每个底架包括支撑件和至少一个车轮，所述支撑件由机身直接承载并且围绕位于框架外部的轴线铰接到机身。 起落架可在其中每个车轮垂直的操作位置和静止位置之间移动。 支撑件和车轮具有这样的构造，使得在静止位置，起落架相对于机身并且在框架外部周向延伸。
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公开(公告)号：US20060011779A1
公开(公告)日：2006-01-19
申请号：US11179611
申请日：2005-07-13
IPC分类号： B64D27/00
CPC分类号： B64D27/20
摘要： The present invention relates to a multi-engined aircraft of which one (7) of the engines is positioned at the tail (9) of the fuselage (6), which comprises the rear tail units, and in the vertical longitudinal plane of symmetry of said fuselage. Advantageously, said tail engine (7) is disposed in front of the rear tail units, on the upper part (8) of the tail of the fuselage, and is mounted, in detachable manner, on a rigid supporting structure (15) attached to that of said fuselage and there is formed, in the tail (9) of said fuselage and plumb with said engine (7) supported by said structure (15), a lowering shaft (16) for the passage of said engine between, on the one hand, a high position corresponding to the operational position of said engine and, on the other hand, following the separation of said engine from the supporting structure and its displacement through said lowering shaft, a low position in which said engine has come out of said fuselage (6) and is under said tail.
摘要翻译： 本发明涉及一种多引擎飞机，其中一（7）个发动机位于机身（6）的尾部（9），其包括后尾翼单元，并且在垂直纵向对称平面 机身表示 有利地，所述尾部发动机（7）设置在后尾部单元的前部，位于机身尾部的上部（8）上，并且以可拆卸的方式安装在刚性支撑结构（15）上，该刚性支撑结构 在所述机身的尾部（9）上形成有由所述结构（15）支撑的所述发动机（7）的所述机身的尾部（9），用于使所述发动机通过所述发动机的下降轴 一方面，对应于所述发动机的操作位置的高位置，另一方面，在所述发动机与所述支撑结构分离并且其通过所述下降轴的位移之后，所述发动机从所述下部位置脱离 机身（6），位于尾部。
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公开(公告)号：US09102395B2
公开(公告)日：2015-08-11
申请号：US12789761
申请日：2010-05-28
IPC分类号： F02K3/02 , F02K1/00 , F02K1/54 , B64C29/00 , B64C15/02 , B64D35/04 , F02K1/58 , F02K1/60 , F02K1/76 , F02K1/12 , F02K1/70 , F02K1/72
CPC分类号： B64C15/02 , B64D35/04 , F02K1/008 , F02K1/12 , F02K1/1223 , F02K1/58 , F02K1/60 , F02K1/70 , F02K1/72 , F02K1/763 , Y02T50/671
摘要： A propulsive system for aircraft that has a jet engine and a nacelle surrounding the aforementioned jet engine. The nacelle has a front section fixed relative to the jet engine, and a rear extremity behind the front section, and has a rear section with two petals hinged relative to the front section. Each of the two petals in a position called zero-setting forms an extension of the front section of the nacelle in which the inside and outside surfaces of the petals and, respectively, determine the aerodynamic forms of the rear section, which are in geometric continuity with the inside and outside surfaces and, respectively, that determine the aerodynamic forms of the front section. The petals can be set individually at a positive or negative setting angle to put into play the reverser, APU, air brake, vectorial, and taxiing modes of the propulsive system.
摘要翻译： 用于具有喷气发动机和围绕上述喷气发动机的机舱的飞行器的推进系统。 机舱具有相对于喷气发动机固定的前部分，并且在前部后方具有后端，并且具有后部，其具有相对于前部铰接的两个瓣。 位于称为零位置的两个花瓣中的每一个形成机舱的前部的延伸部，其中花瓣的内侧和外侧表面分别确定后部的空气动力学形状，其具有几何连续性 内表面和外表面分别确定前部的空气动力学形式。 花瓣可以以正或负设置角度单独设置，以投入推进系统的反向器，APU，空气制动，矢量和滑行模式。
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公开(公告)号：US08651414B2
公开(公告)日：2014-02-18
申请号：US13255720
申请日：2010-03-12
IPC分类号： B64C1/00
CPC分类号： B64C1/068 , B64C1/26 , B64C5/06 , B64C2001/0045 , B64D27/20 , B64D29/04 , Y02T50/12 , Y02T50/44
摘要： An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage.
摘要翻译： 一种飞机，包括沿着飞机的纵向轴线具有细长形状的机身，以及至少一个机翼，其附接到机身的前端和后端之间的机身，以及基本上圆柱形的中心部分和后可缩放部分，垂直 尾部组件和后推进组件。 在用于将后部连接到机身中心部分的部分和后端之间：每个机身部分的最大宽度是恒定的或者朝向后方增加到最大机身宽度L; 每个机身部分的高度朝向后方减小，使得机身的后端在飞机的指示线上形成基本上水平的薄的后缘，并且基本上是直线的; 用于推进组件的反应器以机身中的所谓半埋式构造提供。
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公开(公告)号：US20080073459A1
公开(公告)日：2008-03-27
申请号：US11632225
申请日：2005-06-29
IPC分类号： B64D27/02
摘要： The invention relates to a multi-engine aircraft whose at least two engines (2, 3) are fixed to the fuselage wings symmetrically with respect to the longitudinal vertical plane of symmetry thereof, respectively and the third engine (7) is provided for the tail of the fuselage which comprises tail-planes in the view of said longitudinal plane. The tail-planes (9, 10) define a channel (11) symmetrical with respect to the longitudinal plane of the fuselage and the third engine (7) is disposed on the plane of symmetry of the channel corresponding to the longitudinal plane and mounted on the top part of the fuselage in an elevated manner and before the tail-planes in such a way that output of said third engine is arranged substantially upon the input of the channel (11) defined by said tail-planes.
摘要翻译： 本发明涉及一种多引擎飞机，其至少两个发动机（2,3）分别相对于其纵向垂直对称平面对称地固定在机身翼上，并且第三发动机（7）分别设置用于尾部 的机身，其包括在所述纵向平面的视图中的尾翼。 尾翼（9,10）限定了相对于机身的纵向平面对称的通道（11），并且第三发动机（7）设置在对应于纵向平面的通道的对称平面上并安装在 机身的顶部以升高的方式并且在尾翼之前以这样的方式使得所述第三发动机的输出基本上布置在由所述尾平面限定的通道（11）的输入上。
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公开(公告)号：US20120138736A1
公开(公告)日：2012-06-07
申请号：US13255720
申请日：2010-03-12
CPC分类号： B64C1/068 , B64C1/26 , B64C5/06 , B64C2001/0045 , B64D27/20 , B64D29/04 , Y02T50/12 , Y02T50/44
摘要： An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage.
摘要翻译： 一种飞机，包括沿着飞机的纵向轴线具有细长形状的机身，以及至少一个机翼，其附接到机身的前端和后端之间的机身，以及基本上圆柱形的中心部分和后可缩放部分，垂直 尾部组件和后推进组件。 在用于将后部连接到机身中心部分的部分和后端之间：每个机身部分的最大宽度是恒定的或者朝向后方增加到最大机身宽度L; 每个机身部分的高度朝向后方减小，使得机身的后端在飞机的指示线上形成基本上水平的薄的后缘，并且基本上是直线的; 用于推进组件的反应器以机身中的所谓半埋式构造提供。
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公开(公告)号：US20100133377A1
公开(公告)日：2010-06-03
申请号：US12579054
申请日：2009-10-14
CPC分类号： B64C5/02 , B64C1/0009 , B64C5/06 , B64C2001/0045 , Y02T50/12
摘要： An aircraft includes a fuselage having a shape elongated along a longitudinal axis X of the aircraft and at least one wing fixed to the fuselage between the front end and the rear end of the fuselage. The fuselage includes a substantially cylindrical central part and a rear tapered part on which a vertical empennage is fixed. Between a section connecting the rear part with the central part of the fuselage and the rear end the maximum width of each section of the fuselage is constant or increasing rearwards up to a maximum width L of the fuselage, the height of each section of the fuselage is decreasing rearwards in the direction of the negative X, so that the rear end of the fuselage forms a trailing edge having a small thickness which is substantially horizontal in an aircraft reference system and substantially rectilinear.
摘要翻译： 飞机包括具有沿着飞行器的纵向轴线X细长的形状的机身和至少一个固定在机身的前端和后端之间的机翼的机翼。 机身包括基本上圆柱形的中心部分和后锥形部分，垂直尾翼固定在该后锥形部分上。 在连接后部与机身中央部分的部分和后端之间，机身每个部分的最大宽度是恒定的或向后增加到机身的最大宽度L，机身每一部分的高度 在负X的方向上向后减小，使得机身的后端形成具有小的厚度的后缘，其在飞行器参考系中基本上是水平的并且基本上是直线的。
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公开(公告)号：US07240877B2
公开(公告)日：2007-07-10
申请号：US11179611
申请日：2005-07-13
IPC分类号： B64D27/00
CPC分类号： B64D27/20
摘要： A multi-engine aircraft having one engine positioned at the tail of the fuselage may include rear tail units in a vertical longitudinal plane-of-symmetry of the fuselage. The tail engine is disposed in front of the rear tail units on the upper part of the tail of the fuselage. The tail engine is mounted, in a detachable manner, on a rigid supporting structure attached to the supporting structure of the fuselage. A lowering shaft, formed in the tail of the fuselage and plumb with the engine, is supported by the rigid supporting structure. The lowering shaft provides a passage for the engine between a high position corresponding to the operational position of the engine and a low position in which the engine is removed from the fuselage.
摘要翻译： 具有位于机身尾部的一个发动机的多引擎飞机可以包括机身垂直纵向对称平面中的后尾部单元。 尾部发动机设置在机身尾部上部后尾部单元的前面。 尾部发动机以可拆卸的方式安装在附接到机身的支撑结构的刚性支撑结构上。 由发动机形成在机身和铅锤尾部的下降轴由刚性支撑结构支承。 下降轴为发动机在对应于发动机的操作位置的高位置和发动机从机身移除的低位置之间提供通道。
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