公开(公告)号：US08251310B2

公开(公告)日：2012-08-28

申请号：US12509906

申请日：2009-07-27

Applicant: Herve Marche ,  Fabien Raison

Inventor： Herve Marche ,  Fabien Raison

IPC: B64D27/14

CPC classification number: B64C39/10 ,  B64C2039/105 ,  B64D27/20 ,  B64D2027/264 ,  B64F5/50

Abstract: Sail wing aircraft which includes a wing (6) and at least one propulsion engine (8). It includes an upper beam (22) which is firmly fixed at its front end to a first frame (12) located on an air inlet (14) of the propulsion engine and which is in addition firmly fixed at its median part to a second frame (16) located to the rear of the first frame. The sail wing aircraft includes in addition a pylon (26) for attachment of the engine onto the fuselage, where the engine is fixed to the pylon (26).

Abstract translation: 帆翼飞机包括翼（6）和至少一个推进发动机（8）。 它包括一个上梁（22），其在其前端牢固地固定在位于推进发动机的空气入口（14）上的第一框架（12）上，另外在其中间部分牢固地固定在第二框架 （16）位于第一框架的后部。 帆翼飞机还包括用于将发动机附接到机身上的塔架（26），其中发动机被固定到塔架（26）。

公开(公告)号：US08091832B2

公开(公告)日：2012-01-10

申请号：US12065629

申请日：2006-08-17

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B64C1/14

CPC classification number: B64D29/08

Abstract: A nacelle cowling for a turbojet, characterized in that it is provided with a fixed part and a mobile part, the mobile part being adapted to slide along the fixed part, from a closed position wherein the mobile part extends in the extension of the fixed part, up to an open position wherein the mobile part is at least partly superimposed to the fixed part. For example, the fixed part is located in the upper part of the cowling, the mobile part being located in the lower part of the cowling.

Abstract translation: 一种用于涡轮喷气发动机的机舱罩，其特征在于，其设置有固定部分和可移动部分，所述可移动部分适于沿着所述固定部分滑动，其中所述可移动部分在所述固定部分的延伸部中延伸 ，直到其中移动部分至少部分地叠加到固定部分的打开位置。 例如，固定部分位于整流罩的上部，移动部分位于整流罩的下部。

公开(公告)号：US20090025366A1

公开(公告)日：2009-01-29

申请号：US11996019

申请日：2006-07-07

Applicant: Jean-Marc Martinou ,  Herve Marche

Inventor： Jean-Marc Martinou ,  Herve Marche

IPC: F02K99/00

CPC classification number: B64D13/08 ,  F02C7/185 ,  F02C7/20 ,  F05D2250/12 ,  F05D2250/22 ,  F05D2250/314 ,  F05D2260/208 ,  Y02T50/676

Abstract: An aircraft propulsion unit including a turbojet and a heat exchanger located above the turbojet and drawing a cooling air stream and a hot air stream in the turbojet. Wherein the cooling air intake and hot air intake surfaces in the housing are directed forward of the turbojet and have normal lines inclined relative to the axis of the turbojet. The embodiment also concerns an aircraft equipped with at least one such propulsion unit.

Abstract translation: 飞机推进单元包括位于涡轮喷气发动机上方的涡轮喷气发动机和热交换器，并且在涡轮喷气发动机中抽取冷却空气流和热空气流。 其中壳体中的冷却空气入口和热空气入口表面被引导到涡轮喷气发动机的前方，并且具有相对于涡轮喷气发动机的轴线倾斜的法线。 该实施例还涉及配备有至少一个这种推进单元的飞机。

公开(公告)号：US20080277529A1

公开(公告)日：2008-11-13

申请号：US12065629

申请日：2006-08-17

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B64D29/00

CPC classification number: B64D29/08

Abstract: A nacelle cowling for a turbojet, characterized in that it is provided with a fixed part and a mobile part, the mobile part being adapted to slide along the fixed part, from a closed position wherein the mobile part extends in the extension of the fixed part, up to an open position wherein the mobile part is at least partly superimposed to the fixed part. For example, the fixed part is located in the upper part of the cowling, the mobile part being located in the lower part of the cowling.

Abstract translation: 一种用于涡轮喷气发动机的机舱罩，其特征在于，其设置有固定部分和可移动部分，所述可移动部分适于沿着所述固定部分滑动，其中所述可移动部分在所述固定部分的延伸部中延伸 ，直到其中移动部分至少部分地叠加到固定部分的打开位置。 例如，固定部分位于整流罩的上部，移动部分位于整流罩的下部。

公开(公告)号：US20050269444A1

公开(公告)日：2005-12-08

申请号：US11059442

申请日：2005-02-17

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B64D27/26 ,  B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/264 ,  B64D2027/268

Abstract: This invention relates to a mounting system (1) inserted between an aircraft engine and a rigid structure of an attachment strut, the system particularly comprising a thrust resistance device (20). The thrust resistance device (20) comprises two lateral actuators (30) each provided with a rod (34) in which a forward end (34b) is a piston located inside a chamber (38) of a central casing (22) of the engine, the chamber (38) comprising a forward compartment (40) and an aft compartment (42). Moreover, the thrust resistance device (20) comprises a device (32) including a piston (48) fixed to the forward mount (16) and located inside a chamber (50) fixed to the central casing, the chamber (50) comprising a forward compartment (52) and an aft compartment (54), the forward compartment (52) of the chamber (50) being hydraulically connected to the aft compartments (42) of the actuators (30).

Abstract translation: 本发明涉及一种插入在飞行器发动机和连接支柱的刚性结构之间的安装系统（1），该系统特别包括一个推力阻力装置（20）。 推力阻力装置（20）包括两个侧向致动器（30），每个侧向致动器（30）均设有杆（34），其中前端（34b）是位于中心壳体（22）的腔室（38）内部的活塞 发动机，所述腔室（38）包括前舱（40）和后舱（42）。 此外，推力阻力装置（20）包括装置（32），该装置包括固定到前部安装件（16）并位于固定到中心壳体的腔室（50）内部的活塞（48），所述腔室（50）包括 前舱（52）和后舱（54），舱室（50）的前舱（52）液压地连接到致动器（30）的后舱（42）。