公开(公告)号：US08523101B2

公开(公告)日：2013-09-03

申请号：US12178711

申请日：2008-07-24

申请人： Olivier Cazals ,  Alexander Koch

发明人： Olivier Cazals ,  Alexander Koch

IPC分类号： B64C15/00

CPC分类号： B64D27/20 ,  B64C5/12 ,  B64C15/02 ,  B64C39/12 ,  B64F5/40

摘要： An aircraft capable of making short takeoffs and landings includes essentially a fuselage, a wing secured to the fuselage, a front horizontal stabilizer secured to the fuselage on the front end of the fuselage and at least two jet engines for propulsion. According to the architecture proposed, the propulsion engines are arranged side by side above the fuselage in a rear part of the fuselage with a width at least equal to the width of the propulsion group, a fuselage flap device is arranged in the back of the fuselage so that the fuselage flaps adopt at least a position in which the flaps are considerably in a horizontal plane and take at least a high-lift position in which the flaps are turned downward in such a way that the blast created by the jet engines is channeled towards the top surface of the fuselage flaps to induce a blowing effect.

摘要翻译： 能够短时起飞和着陆的飞机基本上包括机身，固定在机身上的机翼，固定在机身前端的机身上的前水平稳定器和至少两个用于推进的喷气发动机。 根据所提出的结构，推进发动机在机身的后部并排布置在机身的后部，其宽度至少等于推进组的宽度，机身翼片装置布置在机身的后部 使得机身翼片至少采用襟翼相当于水平面的位置，并且至少采取高升力位置，在该位置襟翼向下转动，使得由喷气发动机产生的气流被引导 朝向机身襟翼的顶面，以引起吹风效果。

公开(公告)号：US08152095B2

公开(公告)日：2012-04-10

申请号：US12178704

申请日：2008-07-24

申请人： Olivier Cazals ,  Alexander Koch

发明人： Olivier Cazals ,  Alexander Koch

IPC分类号： B64D27/20

CPC分类号： B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  B64D29/04 ,  B64D29/08 ,  B64D33/02 ,  B64D33/06 ,  B64D2033/0286 ,  Y02T50/44

摘要： An aircraft, the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following: air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

摘要翻译： 飞机的推进单元包括发动机，其特征在于减少的噪声排放，包括固定到机身上部区域的机翼结构，以及具有至少两个垂直稳定器的垂直尾翼系统，该垂直尾翼系统通常垂直固定到 机身后部的机身结构。 发动机并排布置在设置在机身上方的推进式包装中，该推进式包装包括以下内容：用于推进包装的空气入口开口，该开口设置在机身的上方，位于前缘的一点和 机翼结构的气动根弦的后缘; 以及与排气喷嘴管道相关联的排气喷嘴导管出口，这些出口由推进式包装的结构（整流罩结构）形成，并且设置在机身的后端的机身前方和垂直稳定器之间。

公开(公告)号：US20090084889A1

公开(公告)日：2009-04-02

申请号：US12178704

申请日：2008-07-24

申请人： Olivier Cazals ,  Alexander Koch

发明人： Olivier Cazals ,  Alexander Koch

IPC分类号： B64C11/00 ,  B64D27/00 ,  B64D33/02 ,  B64D29/00

CPC分类号： B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  B64D29/04 ,  B64D29/08 ,  B64D33/02 ,  B64D33/06 ,  B64D2033/0286 ,  Y02T50/44

摘要： An aircraft the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following, air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

摘要翻译： 包括引擎在内的推进单元的飞机包括固定在机身上部区域的机翼结构以及具有至少两个垂直稳定器的垂直尾翼系统，该垂直尾翼系统通常垂直地固定在机身上 机身后部的机身结构。 发动机并排布置在设置在机身上方的推进式包装中，该推进包装包括用于推进包装的以下空气入口，这些开口设置在机身的上方，位于前缘的一点和 机翼结构的气动根弦的后缘; 以及与排气喷嘴管道相关联的排气喷嘴导管出口，这些出口由推进式包装的结构（整流罩结构）形成，并且设置在机身的后端的机身前方和垂直稳定器之间。

公开(公告)号：US09051042B2

公开(公告)日：2015-06-09

申请号：US13477270

申请日：2012-05-22

申请人： Olivier Cazals ,  Jaime Genty de la Sagne

发明人： Olivier Cazals ,  Jaime Genty de la Sagne

IPC分类号： B64C5/02 ,  B64C1/26 ,  B64C9/32

CPC分类号： B64C5/02 ,  B64C1/26 ,  B64C9/32 ,  Y02T50/44

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。

公开(公告)号：US08550400B2

公开(公告)日：2013-10-08

申请号：US12494845

申请日：2009-06-30

申请人： Olivier Cazals ,  Jaime Genty de la Sagne

发明人： Olivier Cazals ,  Jaime Genty de la Sagne

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。

公开(公告)号：US08398022B2

公开(公告)日：2013-03-19

申请号：US12108685

申请日：2008-04-24

申请人： Olivier Cazals ,  Thierry Druot

发明人： Olivier Cazals ,  Thierry Druot

IPC分类号： B64C1/00

CPC分类号： B64D27/20 ,  B64C2001/0027

摘要： A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are fixed at the rear under a horizontal tail held above the fuselage by vertical stabilizers and maintenance wells are formed in the fuselage in vertical alignment with each engine to allow the engines to be fitted and removed. The width of the fuselage is determined, on the one hand, so that the airplane landing gear is fixed to the fuselage and in the up position is included within the interior volume of the fuselage and, on the other hand, so that the rear engines are above the fuselage in order to make use of the beneficial effects of this position.

摘要翻译： 大容量飞机主要包括机身，前机身和后部之间没有恒定宽度的机身，机身固定在机身上。 优选地，发动机通过垂直稳定器固定在机身上方的水平尾部的后方，并且在机身中形成维护井，与每个发动机垂直对准，以允许发动机被安装和拆卸。 一方面确定机身的宽度，使得飞机起落架固定在机身上，并且在上部位置被包括在机身的内部容积内，另一方面使得后部发动机 在机身之上，以利用这个位置的有益效果。

公开(公告)号：US20120325958A1

公开(公告)日：2012-12-27

申请号：US12516594

申请日：2007-11-29

申请人： Olivier Cazals ,  Thierry Druot

发明人： Olivier Cazals ,  Thierry Druot

IPC分类号： B64C1/26 ,  B64C5/02 ,  B64D27/20

CPC分类号： B64D27/16 ,  B64C5/02 ,  B64C2039/105 ,  Y02T50/44

摘要： A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At lease one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area.

摘要翻译： 一种用于飞行器的后尾部组件，包括机身，机翼和至少一个推进发动机，其沿机翼的X纵向轴线安装在机身后部的机身的后部，其中上述组件包括连接在飞行器的空气动力学表面 机身的后部。 尾部组件基本上包括水平空气动力学表面和基本垂直的空气动力学表面，其布置成形成包括连接到机身的至少一个环的环形结构。 至少一个发动机被保持在由尾部组件形成的环中。 在一个实施例中，中心翅片用于限定环形结构中的两个环。 在包括这种尾部组件的飞行器的特定实施例中，一个或两个发动机可以安装在环形区域中。

公开(公告)号：USD621335S1

公开(公告)日：2010-08-10

申请号：US29355516

申请日：2010-02-09

申请人： Olivier Cazals ,  Jaime Genty de la Sagne

设计人： Olivier Cazals ,  Jaime Genty de la Sagne

公开(公告)号：USD621334S1

公开(公告)日：2010-08-10

申请号：US29355515

申请日：2010-02-09

申请人： Olivier Cazals ,  Jaime Genty de la Sagne

设计人： Olivier Cazals ,  Jaime Genty de la Sagne

公开(公告)号：US20100044502A1

公开(公告)日：2010-02-25

申请号：US12393625

申请日：2009-02-26

申请人： Olivier Cazals

发明人： Olivier Cazals

IPC分类号： B64D27/02 ,  B64D41/00 ,  B64D29/00

CPC分类号： B64D41/00 ,  B64D27/20 ,  B64D2033/0213 ,  B64D2041/002

摘要： A propulsive system for an aircraft including an auxiliary jet engine is integrated into a tail cone of a fuselage. A carrying structure of the jet engine is primarily formed with beams and frames or half-frames to which the auxiliary jet engine is fixed by lateral beams. The beams are interdependent of the frames and half-frames, and the beams are overhanging behind a frame behind which is fixed the engine. Each beam includes a lower half-beam and a higher half-beam, separated on at least a part of its length ahead from attachments of the jet engine to determine a space free of structure impediment for lateral air intakes.

摘要翻译： 用于包括辅助喷气发动机的飞行器的推进系统被集成到机身的尾锥中。 喷气发动机的承载结构主要由梁和框架或半框形成，辅助喷气发动机通过横梁固定到该框架或半框架上。 梁与框架和半框架是相互依赖的，并且横梁悬挂在框架之后，后面固定有发动机。 每个梁包括下半波束和较高的半波束，其在距离喷气发动机的附件的前方的至少一部分长度上分离，以确定不受侧向进气口的结构阻挡的空间。