公开(公告)号：US09341142B2

公开(公告)日：2016-05-17

申请号：US13770653

申请日：2013-02-19

Applicant: AIRCELLE

Inventor： Alexandre Bellanger ,  Florent Bouillon ,  Laurent Dubois

IPC: F02K1/72 ,  F02K1/80 ,  B64D29/06

CPC classification number: F02K1/72 ,  B64D29/06 ,  F02K1/80 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/612 ,  F05D2300/614 ,  Y02T50/672

Abstract: The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material.

Abstract translation: 本公开涉及一种梁，特别是用于级联推力反向器的梁，包括由复合材料制成并限定封闭部分的表皮，其中所述梁填充有芯材料。

公开(公告)号：US09341083B2

公开(公告)日：2016-05-17

申请号：US14524099

申请日：2014-10-27

Applicant: AIRCELLE

Inventor： Hazem Kioua ,  Vincent Peyron ,  Laurent Georges Valleroy

IPC: B64D29/06 ,  F01D25/24 ,  F02K1/72 ,  B64D33/04

CPC classification number: F01D25/24 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72 ,  F05D2220/30

Abstract: A turbofan engine nacelle has a downstream section which includes at least one front frame. The front frame is attached to a stationary portion of the nacelle, and the downstream section is provided with at least one rail or slide which extends in a longitudinal direction of the nacelle and is capable of engaging with at least one corresponding slide or rail of an attachment pylon of the turbofan engine. The front frame is connected to the rail or slide of the downstream section by means of at least one swiveled connecting rod.

Abstract translation: 涡轮风扇发动机舱具有包括至少一个前框架的下游部分。 前框架连接到机舱的静止部分，并且下游部分设置有至少一个轨道或滑块，其沿着机舱的纵向方向延伸并且能够与至少一个相应的滑轨或轨道接合 涡扇发动机的附件塔。 前框架通过至少一个可旋转的连接杆连接到下游部分的导轨或滑块。

公开(公告)号：US09327945B2

公开(公告)日：2016-05-03

申请号：US14194942

申请日：2014-03-03

Applicant: AIRCELLE

Inventor： Pascal Boisson ,  Patrice Raymond

IPC: F16B23/00 ,  B66C1/66

CPC classification number: B66C1/66

Abstract: A device for handling a load provided with a thread includes a screw assembly equipped with a gripper and capable of connecting to the load, a first screwing indicator secured to the screw assembly, a second screwing indicator movable in translation relative to the first screwing indicator, and a spring. In particular, the spring is inserted between the first screwing indicator and the second screwing indicator and has an effect of returning the second screwing indicator such that the second screwing indicator abuts against the load, so that a coincidence between the first and second screwing indicator indicates a sufficient screwing of the device onto the load.

Abstract translation: 用于处理设置有螺纹的负载的装置包括：装配有夹具并能够连接到负载的螺钉组件，固定到螺钉组件的第一螺丝指示器，可相对于第一螺钉指示器平移的第二螺纹连接指示器， 和春天。 特别地，弹簧插入在第一螺丝指示器和第二螺丝指示器之间，并且具有使第二螺合指示器返回以使得第二螺钉指示器抵靠负载的效果，使得第一和第二螺钉指示器之间的一致表示 将设备充分拧紧到负载上。

公开(公告)号：US20160023771A1

公开(公告)日：2016-01-28

申请号：US14877098

申请日：2015-10-07

Applicant: AIRCELLE

Inventor： Audrey RIQUET ,  Caroline COAT-LENZOTTI

IPC: B64D15/00 ,  B64D33/02

CPC classification number: B64D15/00 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/0286 ,  F02C7/04 ,  F05D2300/512

Abstract: The present disclosure provides an aircraft element including a leading edge section and a trailing edge section, and the leading edge section includes an anti-frost treatment device. This aircraft element is remarkable in that the trailing edge section includes a superhydrophobic surface.

Abstract translation: 本公开内容提供了一种包括前缘部分和后缘部分的飞行器元件，并且前缘部分包括防霜处理装置。 该飞机元件是显着的，因为后缘部分包括超疏水表面。

公开(公告)号：US20150354105A1

公开(公告)日：2015-12-10

申请号：US14829309

申请日：2015-08-18

Applicant: AIRCELLE

Inventor： Fréderick VEYET ,  Boris DUCHAMP ,  Julien BARDY

IPC: D03D25/00

CPC classification number: D03D11/02 ,  D03D25/005 ,  D03D41/004 ,  D03D49/20 ,  D10B2403/0331 ,  D10B2403/0333 ,  D10B2505/02

Abstract: A weaving loom includes a system for inserting weft threads in a plurality of layers and a system for inserting and sequencing warp threads in such a way as to produce a multilayer fabric having a defined weave. It includes at least two feed systems of which the speed and traction force are controlled such that, at least locally, one portion of the layers of fabric is driven by the feed mechanism of same at a different speed to at least one other portion of the layers of multilayer fabric so as to produce at least one aperture on the multilayer fabric.

Abstract translation: 编织机包括用于在多个层中插入纬纱的系统以及用于插入和排序经线的系统，以便制造具有限定织物的多层织物。 它包括至少两个进给系统，其速度和牵引力被控制，使得至少局部地，织物层的一部分由其的进给机构以不同的速度驱动到至少另一部分 多层织物层，以便在多层织物上产生至少一个孔。

公开(公告)号：US09162747B2

公开(公告)日：2015-10-20

申请号：US14093749

申请日：2013-12-02

Applicant: Aircelle

Inventor： Franck Maze ,  John Moutier

IPC: B64D33/02 ,  B29C51/14 ,  B64C1/40 ,  B32B3/12 ,  F02K1/82 ,  G10K11/168 ,  F02C7/045 ,  B64F5/00 ,  B32B3/02 ,  B64D33/00

CPC classification number: B64C1/40 ,  B32B3/02 ,  B32B3/12 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2307/102 ,  B32B2605/18 ,  B64F5/00 ,  F02C7/045 ,  F02K1/827 ,  G10K11/168 ,  Y02T50/672

Abstract: The present disclosure provides a method for manufacturing a sound attenuation panel having a first cellular core structure and a second cellular core structure joined in a junction area (J). The method includes: a) a joining edge of the first cellular core structure is joined to a corresponding joining edge of the second cellular core structure, thereby forming the junction area; b) the first cellular core structure and the second cellular core structure are placed between an inner skin and an outer skin of the panel.In particular, the method further has a step prior to step a), in which one junction reinforcement is inserted between the joining edge of the first cellular core structure and the corresponding joining edge of the second cellular core structure in the junction area.

Abstract translation: 本公开提供一种用于制造具有连接在接合区域（J）中的第一蜂窝状芯结构和第二蜂窝状芯结构的声音衰减板的方法。 该方法包括：a）第一多孔芯结构的接合边缘连接到第二多孔芯结构的对应接合边缘，由此形成接合区域; b）第一细胞芯结构和第二细胞核结构放置在面板的内皮和外皮之间。 特别地，该方法还具有步骤a）之前的步骤，其中一个接合加强件插入在第一多孔芯结构的接合边缘和第二多孔芯结构的接合区域的相应接合边缘之间。

公开(公告)号：US09151225B2

公开(公告)日：2015-10-06

申请号：US14304555

申请日：2014-06-13

Applicant: AIRCELLE

Inventor： Nicolas Dezeustre ,  Pierre Caruel ,  Patrick Gonidec ,  Patrick Boileau

IPC: F02C7/045 ,  B64D33/02

CPC classification number: F02C7/045 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286

Abstract: An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural.

Abstract translation: 用于涡轮喷气发动机机舱的进气结构包括具有连接外壁和内壁上游的内壁，外壁和进气口结构的基本上环形的主结构。 进气结构还包括第一声衰减结构，该第一声衰减结构具有孔声学皮肤，多孔芯和固定的后壁，内壁装有该第一声衰减结构，以及具有类似结构的第二声衰减结构， 进气口基本上在与内壁的接合处附近。 第一声​​衰减结构的后表皮与第二声衰减结构的后表皮对准，两个后皮都是结构的。

公开(公告)号：US20150267643A1

公开(公告)日：2015-09-24

申请号：US14464649

申请日：2014-08-20

Applicant: AIRCELLE

Inventor： Patrick GONIDEC ,  Laurent Albert Blin ,  Olivier Kerbler

IPC: F02K1/72

CPC classification number: F02K1/72 ,  Y02T50/671

Abstract: A cascade-type thrust reverser for an aircraft turbojet engine includes a front frame, a sliding cowl between a direct jet position and a reverse jet position, a plurality of actuating cylinders interposed between this front frame and this sliding cowl, and a plurality of cascades pivotally mounted on the front frame between the direct and reverse jet positions. In the direct jet position, the cascades are substantially parallel to the axis (A) of the thrust reverser, and in the reverse jet position, the cascades are inclined relative to the axis (A) of the thrust reverser. In particular, the cascade-type thrust reverser includes a single radial layer of cascades.

Abstract translation: 用于飞行器涡轮喷气发动机的级联型推力反向器包括前框架，在直接喷射位置和反向喷射位置之间的滑动罩，插入在该前框架和该滑动罩之间的多个致动缸以及多个级联 在直接和反向喷射位置之间枢转地安装在前框架上。 在直接喷射位置，级联基本上平行于推力反向器的轴线（A），并且在反向喷射位置中，级联相对于推力反向器的轴线（A）倾斜。 特别地，级联型推力反向器包括单个径向的级联层。

公开(公告)号：US20150260125A1

公开(公告)日：2015-09-17

申请号：US14716908

申请日：2015-05-20

Applicant: AIRCELLE

Inventor： Vincent PEYRON

IPC: F02K1/56 ,  F02K1/76

CPC classification number: F02K1/56 ,  B64D7/02 ,  B64D29/06 ,  F02K1/72 ,  F02K1/76 ,  F02K1/763

Abstract: The present disclosure provides a thrust reverser device for a turbojet engine nacelle which includes at least two cowls each mounted with the ability to move translationally with respect to a fixed structure between an upstream closed position and a downstream open position. In the upstream position, the two cowls provide aerodynamic continuity of the nacelle, and in the downstream open position, they open a passage in the nacelle. The thrust reverser device further includes at least one synchronization cable extended between the two mobile cowls so as to have a first end attached to an upstream point of one of the two cowls, and a second end attached to a downstream point of the another cowl. In particular, the upstream and downstream attachment points are determined relative to a fixed central zone where the cable passes between the two cowls.

Abstract translation: 本公开提供了一种用于涡轮喷气发动机机舱的推力反向装置，其包括至少两个整流罩，每个整流罩具有在上游关闭位置和下游打开位置之间相对于固定结构平移地移动的能力。 在上游位置，两个整流罩提供机舱的空气动力学连续性，并且在下游打开位置，它们在机舱中打开通道。 推力反向器装置还包括在两个移动整流罩之间延伸的至少一个同步电缆，以便具有附接到两个整流罩之一的上游点的第一端和附接到另一整流罩的下游点的第二端。 特别地，上游和下游连接点相对于电缆在两个整流罩之间通过的固定中心区域来确定。

公开(公告)号：US09109509B2

公开(公告)日：2015-08-18

申请号：US13671233

申请日：2012-11-07

Applicant: AIRCELLE

Inventor： Christophe Thorel ,  Bertrand Desjoyeaux ,  Florent Bouillon ,  John Moutier ,  Stéphane Bardin

IPC: B64D33/02 ,  F02C7/04 ,  B64D29/06 ,  F02C7/045 ,  F02K1/80 ,  F02K1/82

CPC classification number: F02C7/04 ,  B64D29/06 ,  F02C7/045 ,  F02K1/80 ,  F02K1/827 ,  Y02T50/672 ,  Y10T29/49826 ,  Y10T403/45

Abstract: A unit for an aircraft thruster is provided that includes a first ferrule configured to be attached to a second ferrule and a first connection flange configured to be secured to a second corresponding connection flange secured to the second ferrule. The connection flange includes a portion forming a plane extending along a radial direction with respect to the first ferrule. A link between the first ferrule and the corresponding connection flange is offset to a distance from said plane corresponding to a length for damping a shear-generating flexural moment, generated by fluxes of forces passing through the first ferrule.

Abstract translation: 提供了一种用于飞机推进器的单元，其包括构造成附接到第二套圈的第一套圈和构造成固定到固定到第二套圈的第二对应连接凸缘的第一连接凸缘。 连接凸缘包括形成相对于第一套圈沿径向方向延伸的平面的部分。 第一套圈和对应的连接凸缘之间的连接偏移到与所述平面相对应的距离，该长度与用于阻尼通过第一套圈的力的通量产生的剪切产生弯曲力矩的长度相对应。