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1.发明授权公开(公告)号：US08439310B2
公开(公告)日：2013-05-14
申请号：US12702869
申请日：2010-02-09
CPC分类号： B64C39/068
摘要： An aircraft comprises: a fuselage; a front pair of wings; a rear pair of wings; and a pair of bodies, each body interconnecting, at a distance from the fuselage, the front and rear wings that are situated on the same side of the fuselage.
摘要翻译： 飞机包括：机身; 一对前翅; 一对后翅; 以及一对身体，每个身体在与机身一定距离处相互连接，前后翼位于机身的同一侧。
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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：USD621776S1
公开(公告)日：2010-08-17
申请号：US29355518
申请日：2010-02-09
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公开(公告)号：US08308108B2
公开(公告)日：2012-11-13
申请号：US12494919
申请日：2009-06-30
IPC分类号： B64C1/00
CPC分类号： B64C1/0009 , B64C2001/0027 , B64C2001/0045 , B64D11/00 , Y02T50/12
摘要： An aircraft fuselage with a shape elongated along a longitudinal axis X along a longitudinal axis of the aircraft that determines a direction toward the front along a direction of motion of the aircraft in flight. A front section with straight cross sections widening relative to the X axis, located at the front of the fuselage and ending in the front of the fuselage in a fuselage nose, and delimited at the rear by a cross section for joining to a rear part of the fuselage behind the front section. The front section includes a cockpit located above a floorboard between a cockpit bulkhead to the rear and a front base to the front.
摘要翻译： 具有沿着纵向轴线X的形状的飞行器机身沿飞行器的纵向轴线确定沿着飞行器中的飞行器的运动方向朝向前方的方向。 前部具有相对于X轴的直线横截面，其位于机身前部并且在机身前端终止于机身前部，并且在后部由一个横截面限定，用于连接到机身的后部 前部后面的机身。 前部包括位于驾驶舱舱壁与后部之间的地板上方的驾驶舱和前部前部的驾驶舱。
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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：US20100012781A1
公开(公告)日：2010-01-21
申请号：US12494845
申请日：2009-06-30
IPC分类号： B64C1/00
CPC分类号： B64C1/068 , B64C25/04 , B64C2001/0045
摘要： An aircraft has a fuselage 1 of elongated form along a longitudinal axis X corresponding essentially to the longitudinal axis of the aircraft.In a first forward section, the fuselage comprises a cockpit 22 in front of a cockpit bulkhead 51 and a front landing gear 4 associated with a landing gear compartment 41 located behind the cockpit bulkhead 51. The front landing gear 4 and its landing gear compartment 41 are preferably at least partially beneath the floorboard of a compartment of the lower space of the fuselage and in a bulge 24 that increases the volume available for installation of the landing gear.
摘要翻译： 飞机具有基本上与飞行器的纵向轴线对应的纵向轴线X的细长形式的机身1。 在第一前部中，机身包括在驾驶舱隔板51前面的驾驶舱22和与起落架舱41相关联的前起落架4，其位于驾驶舱舱壁51后面。前起落架4及其起落架室41 优选地至少部分地在机身的下部空间的隔室的地板下方以及增加可用于安装起落架的体积的凸起24中。
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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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公开(公告)号：US09051042B2
公开(公告)日：2015-06-09
申请号：US13477270
申请日：2012-05-22
摘要： An aircraft including a fuselage which extends along a longitudinal axis. The fuselage includes a substantially cylindrical central portion and a rear portion that may have a flattened or conventional shape. This rear portion which comprises the rear end of the fuselage includes a support surface which bears at least one horizontal stabilizer and/or vertical stabilizer. The rear portion is able to pivot in relation to the central portion around an axis such as the pitch axis, at least one stabilizer or the support surface being equipped with at least one control surface.
摘要翻译： 一种飞机，包括沿着纵向轴线延伸的机身。 机身包括基本上圆柱形的中心部分和可以具有扁平或常规形状的后部部分。 该后部包括机身的后端，其包括支撑表面，该支承表面至少具有一个水平稳定器和/或垂直稳定器。 后部能够围绕诸如俯仰轴线的轴线相对于中心部分枢转，至少一个稳定器或支撑表面配备有至少一个控制表面。
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公开(公告)号：US08550400B2
公开(公告)日：2013-10-08
申请号：US12494845
申请日：2009-06-30
IPC分类号： B64C1/00
CPC分类号： B64C1/068 , B64C25/04 , B64C2001/0045
摘要： An aircraft has a fuselage of elongated form along a longitudinal axis X corresponding essentially to the longitudinal axis of the aircraft. In a first forward section, the fuselage includes a cockpit in front of a cockpit bulkhead and a front landing gear associated with a landing gear compartment located behind the cockpit bulkhead. The front landing gear and the landing gear compartment are at least partially beneath a floorboard of a compartment of a lower space of the fuselage and in a bulge that increases a volume available for installation of the landing gear.
摘要翻译： 飞行器具有沿着基本上与飞行器的纵向轴线对应的纵向轴线X的细长形式的机身。 在第一个前部，机身包括在驾驶舱舱壁前面的驾驶舱和与位于驾驶舱舱壁后面的起落架舱相关联的前起落架。 前起落架和起落架舱至少部分地位于机身较低空间的隔间的地板下方，并且在凸起中增加可用于安装起落架的体积。
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