公开(公告)号：US11679860B2

公开(公告)日：2023-06-20

申请号：US17494994

申请日：2021-10-06

Applicant: The NORDAM Group LLC

Inventor： Timothy Dustin Penn ,  Matthew Shaun Fritz ,  Jane Alice Benbenek

IPC: B64C1/40 ,  B32B7/12 ,  B32B5/18 ,  B32B5/12 ,  B32B15/04 ,  B32B15/14 ,  B32B15/20 ,  G10K11/168 ,  B32B3/12 ,  B32B37/12 ,  B29C65/00 ,  B32B37/14 ,  B32B38/00 ,  B64C1/00 ,  B29C44/18

CPC classification number: B64C1/40 ,  B29C66/727 ,  B29C66/72525 ,  B32B3/12 ,  B32B5/12 ,  B32B5/18 ,  B32B7/12 ,  B32B15/046 ,  B32B15/14 ,  B32B15/20 ,  B32B37/12 ,  B32B37/146 ,  B32B38/0004 ,  G10K11/168 ,  B29C44/186 ,  B29C66/72523 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/106 ,  B32B2266/0214 ,  B32B2305/022 ,  B32B2305/024 ,  B32B2307/102 ,  B32B2307/50 ,  B32B2605/18 ,  B64C2001/0072

Abstract: A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6, 7, 8) defining the outer skins (20,22).

公开(公告)号：US20190171191A1

公开(公告)日：2019-06-06

申请号：US16272828

申请日：2019-02-11

Applicant: THE BOEING COMPANY

Inventor： Aaron Coon ,  Chris G. McInelly ,  Bret Hoeksema ,  Ryan Lillibridge ,  Tom Allen ,  Steve Solack ,  Kevin Bowe ,  Gary K. Allen

IPC: G05B19/418 ,  B32B7/08 ,  B23P19/00 ,  B23P19/04 ,  B32B3/06 ,  F16B5/01 ,  B32B3/26

CPC classification number: G05B19/41805 ,  B23P19/001 ,  B23P19/04 ,  B29C65/483 ,  B29C65/542 ,  B29C65/564 ,  B29C65/7802 ,  B29C66/30321 ,  B29C66/30325 ,  B29C66/474 ,  B29C66/72525 ,  B29C66/863 ,  B29L2031/3076 ,  B32B3/06 ,  B32B3/266 ,  B32B7/08 ,  B32B2305/024 ,  B32B2607/00 ,  F16B5/01 ,  G05B2219/40111

Abstract: An automated fastener insert installation system for composite panels is provided. A first module receives and secures a composite panel with respect to an origin of a first coordinate system, wherein the composite panel has opposed major surfaces and defines an insert-receiving orifice extending through one of the major surfaces, and is secured such that one of the major surfaces is externally accessible. A second module engages each of a plurality of fastener inserts with an installation aide. Third module determines a configuration of the orifice defined by the composite panel, selects a corresponding one of the fastener inserts engaged with the installation aide, inserts the selected fastener insert into the orifice, and dispenses an adhesive material through the installation aide and into the orifice about selected fastener insert such that the adhesive material secures the selected fastener insert within the orifice. Associated systems are also provided.

公开(公告)号：US20180093752A1

公开(公告)日：2018-04-05

申请号：US15833317

申请日：2017-12-06

Applicant: LEARJET INC.

Inventor： Alain LANDRY ,  Germain BELANGER

IPC: B64C1/06 ,  B29C65/00 ,  B29C31/08 ,  B29C33/26 ,  B29C65/50 ,  B29C70/54 ,  B29C70/46 ,  B29C70/30 ,  B29C70/08 ,  B29C65/48 ,  B29C35/02 ,  B29L31/30 ,  B64C1/00

CPC classification number: B64C1/068 ,  B29C31/08 ,  B29C31/085 ,  B29C33/26 ,  B29C35/02 ,  B29C65/483 ,  B29C65/505 ,  B29C65/5071 ,  B29C65/5078 ,  B29C66/1162 ,  B29C66/12822 ,  B29C66/12842 ,  B29C66/543 ,  B29C66/721 ,  B29C66/72525 ,  B29C66/73752 ,  B29C70/088 ,  B29C70/30 ,  B29C70/462 ,  B29C70/54 ,  B29L2031/3079 ,  B29L2031/3082 ,  B64C2001/0072 ,  B64F5/10 ,  Y02T50/43 ,  Y10T428/13

Abstract: A method for fabricating a composite material assembly includes: a) providing an assembly system, b) laying down a first module on a first mold, the first module comprising a first laminate covering a first laminate support structure, c) laying down a second module on a second mold, the second module comprising a second laminate covering a second laminate support structure and extending over the at least one removable insert, d) removing the at least one removable insert from the second mold, and e) assembling the first mold with the second mold while overlapping a section of the second laminate extending over the at least one removable insert over the first laminate.

公开(公告)号：US20170146984A1

公开(公告)日：2017-05-25

申请号：US14949278

申请日：2015-11-23

Applicant: THE BOEING COMPANY

Inventor： Aaron Coon ,  Chris G. Mclnelly ,  Bret Hoeksema ,  Ryan Lillibridge ,  Tom Allen ,  Steven Solack ,  Kevin Bowe ,  Gary K. Allen

IPC: G05B19/418

CPC classification number: G05B19/41805 ,  B23P19/001 ,  B23P19/04 ,  B29C65/483 ,  B29C65/542 ,  B29C65/564 ,  B29C65/7802 ,  B29C66/30321 ,  B29C66/30325 ,  B29C66/474 ,  B29C66/72525 ,  B29C66/863 ,  B29L2031/3076 ,  B32B3/06 ,  B32B3/266 ,  B32B7/08 ,  B32B2305/024 ,  B32B2607/00 ,  F16B5/01 ,  G05B2219/40111

Abstract: An automated fastener insert installation system for composite panels is provided. A first module receives and secures a composite panel with respect to an origin of a first coordinate system, wherein the composite panel has opposed major surfaces and defines an insert-receiving orifice extending through one of the major surfaces, and is secured such that one of the major surfaces is externally accessible. A second module engages each of a plurality of fastener inserts with an installation aide. Third module determines a configuration of the orifice defined by the composite panel, selects a corresponding one of the fastener inserts engaged with the installation aide, inserts the selected fastener insert into the orifice, and dispenses an adhesive material through the installation aide and into the orifice about selected fastener insert such that the adhesive material secures the selected fastener insert within the orifice. Associated systems are also provided.

公开(公告)号：US09592901B2

公开(公告)日：2017-03-14

申请号：US14594292

申请日：2015-01-12

Applicant: Textron Innovations Inc.

Inventor： John R. McCullough ,  David Gordon Carlson ,  James Donn Hethcock ,  Paul K. Oldroyd ,  Carl A. May

IPC: B64C1/12 ,  B29D99/00 ,  B64C1/06 ,  F16B5/01 ,  F16B5/12 ,  F16B17/00 ,  B29C65/50 ,  B29C65/56 ,  B29C65/00 ,  B29L31/30 ,  B64C1/00 ,  B29C65/48

CPC classification number: B64C1/12 ,  B29C65/4835 ,  B29C65/5021 ,  B29C65/5057 ,  B29C65/5078 ,  B29C65/5085 ,  B29C65/562 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/1162 ,  B29C66/1282 ,  B29C66/12881 ,  B29C66/43441 ,  B29C66/721 ,  B29C66/72525 ,  B29C66/8416 ,  B29D99/001 ,  B29L2031/3076 ,  B64C1/06 ,  B64C2001/0072 ,  F16B5/01 ,  F16B5/12 ,  F16B17/00 ,  Y02T50/43 ,  Y10T29/49622 ,  Y10T403/70

Abstract: A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.

Abstract translation: 结构接头包括具有第一基部和第一腿部的第一构件。 结构接头还包括具有第二基部和第二基部的第二构件。 第一基部和第二基部在重叠部分处连接在一起。 第一腿部分和第二腿部部分形成用于结构上结合到结构构件的空腔。

公开(公告)号：US20170044934A1

公开(公告)日：2017-02-16

申请号：US15209161

申请日：2016-07-13

Applicant: ROLLS-ROYCE plc

Inventor： Mark J. HICKLIN ,  Stephen O. OSIYEMI ,  Ewan F. THOMPSON

IPC: F01D25/24 ,  B29C65/48

CPC classification number: F01D25/243 ,  B29C65/18 ,  B29C65/48 ,  B29C65/4835 ,  B29C66/1122 ,  B29C66/53241 ,  B29C66/612 ,  B29C66/634 ,  B29C66/7212 ,  B29C66/72525 ,  B29C66/81433 ,  B29C66/81455 ,  B29C66/81457 ,  B29C66/82421 ,  B29C66/8322 ,  B29L2031/3076 ,  B29L2031/7504 ,  F01D11/127 ,  F01D21/045 ,  F01D25/24 ,  F01D25/285 ,  F02C7/045 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/23 ,  F05D2230/68 ,  F05D2260/962 ,  B29K2309/08

Abstract: A method is provided of bonding a first component to a second component. The method includes: locating the first component against the second component to form an interface between the components, a curable adhesive being provided at the interface; locating a pressurisable, fluid-filled bladder against the first component such that the first component is sandwiched between the second component and the bladder; locating a backing member against the bladder such that the bladder is sandwiched between the backing member and the first component; pressurising the bladder such that a consolidating pressure is exerted by the bladder on the first component to conform the first component to the second component; and curing the adhesive while the first component is conformed to the second component by the consolidating pressure.

Abstract translation: 提供了将第一组分结合到第二组分的方法。 该方法包括：将第一组件定位在第二组件上以形成组件之间的界面，在界面处设置可固化粘合剂; 将可加压流体填充的气囊定位在所述第一部件上，使得所述第一部件夹在所述第二部件和所述囊之间; 将支撑构件定位抵靠所述囊，使得所述囊被夹在所述背衬构件和所述第一构件之间; 对气囊进行加压，使得气囊在第一部件上施加固结压力以使第一部件与第二部件一致; 并且通过合并压力使第一部件与第二部件一致地固化粘合剂。

公开(公告)号：US20150096678A1

公开(公告)日：2015-04-09

申请号：US14505892

申请日：2014-10-03

Applicant: Zephyros, Inc.

Inventor： Patrick Siboni ,  John Blancaneaux

IPC: B29C65/48

CPC classification number: B29C65/4815 ,  B29C65/542 ,  B29C66/474 ,  B29C66/72525 ,  B29K2063/00 ,  B32B3/12 ,  B32B7/00 ,  B32B7/02 ,  B32B7/12 ,  B32B27/38 ,  B32B37/146 ,  B32B2250/40 ,  B32B2605/00 ,  B32B2605/18 ,  C09J5/06 ,  C09J2463/00 ,  E04C2/365 ,  F16B5/01 ,  F16B11/006 ,  F16B37/048

Abstract: The present invention contemplates a method for the attachment of a component to a honeycomb structure comprising forming a cavity in the honeycomb structure whereby the cavity is formed within one or more honeycomb cells; placing an insert adapted to enable the attachment of the component to the honeycomb structure whereby a reformable epoxy resin adhesive is injected about the insert or an expandable reformable epoxy resin adhesive is overmolded onto the insert; heating the reformable epoxy resin adhesive; and hardening and adhering the reformable epoxy resin adhesive to one or more interior walls of the cavity upon cooling.

Abstract translation: 本发明涉及一种用于将部件附接到蜂窝结构体的方法，包括在蜂窝结构体中形成空腔，由此在一个或多个蜂窝单元内形成空腔; 放置适于使部件附着到蜂窝状结构上的插入件，由此将可重整的环氧树脂粘合剂注入到插入件周围，或者可膨胀的可重整环氧树脂粘合剂被包覆模制到插入物上; 加热可重整环氧树脂粘合剂; 并且在冷却时将可重整环氧树脂粘合剂硬化并粘附到腔的一个或多个内壁。

公开(公告)号：US08973619B2

公开(公告)日：2015-03-10

申请号：US12933993

申请日：2009-03-31

Applicant: Roland Hoefle ,  Markus Roy ,  Hubert Stuetzle ,  Michael Straubing

Inventor： Roland Hoefle ,  Markus Roy ,  Hubert Stuetzle ,  Michael Straubing

IPC: F16L9/14 ,  F16L9/18 ,  F16L9/00 ,  F24F13/02 ,  F16L9/19 ,  B29C53/40 ,  B29C65/50 ,  B29C65/00 ,  B29K105/06 ,  B29L23/00 ,  B29L31/18 ,  B29L31/60

CPC classification number: F24F13/0254 ,  B29C53/40 ,  B29C65/5042 ,  B29C65/5057 ,  B29C65/5071 ,  B29C65/5085 ,  B29C66/1142 ,  B29C66/4322 ,  B29C66/438 ,  B29C66/439 ,  B29C66/72525 ,  B29K2105/06 ,  B29L2023/22 ,  B29L2031/18 ,  B29L2031/608 ,  F16L9/14 ,  F16L9/19 ,  F24F13/0263 ,  B29C65/00

Abstract: A climate tube, in particular for aircraft, includes an inner layer and an outer layer of fiber composite plastic material. To achieve a high stiffness combined with a low weight and to achieve good thermal insulation properties, disposed between the inner layer and the outer layer is an at least almost completely circumferential honeycomb core, which is firmly connected to the inner layer the outer layer. The radial extent of the honeycomb core is large compared to the radial extent of the inner layer and the outer layer, and the mutually opposed longitudinal ends of the honeycomb core abut one another and are surrounded by a ply of fiber composite plastic material.

Abstract translation: 特别是用于飞机的气候管包括纤维复合材料的内层和外层。 为了实现与低重量结合的高刚度并且实现良好的隔热性能，设置在内层和外层之间的是至少几乎完全周向的蜂窝芯，其牢固地连接到内层的外层。 蜂窝芯的径向范围比内层和外层的径向程度大，蜂窝芯的相互相对的纵向端彼此邻接并被纤维复合材料层包围。

公开(公告)号：US08950159B2

公开(公告)日：2015-02-10

申请号：US13973097

申请日：2013-08-22

Applicant: Woodwelding AG

Inventor： Peter L. Cove ,  William E. T. Vallance ,  Mario Lehmann ,  Laurent Torriani

IPC: E04B1/00 ,  B29C65/08 ,  B29C65/64 ,  B29C65/00 ,  F16B5/01 ,  B29C65/56 ,  B29C65/60 ,  B29L31/00

CPC classification number: B29C65/08 ,  B29C65/082 ,  B29C65/561 ,  B29C65/601 ,  B29C65/602 ,  B29C65/603 ,  B29C65/645 ,  B29C66/112 ,  B29C66/114 ,  B29C66/30223 ,  B29C66/30326 ,  B29C66/474 ,  B29C66/53465 ,  B29C66/71 ,  B29C66/72525 ,  B29C66/73921 ,  B29C66/7487 ,  B29C66/8242 ,  B29C66/8322 ,  B29L2031/737 ,  F16B5/01 ,  F16B5/08 ,  Y10T403/477 ,  B29K2023/06 ,  B29K2023/12 ,  B29K2025/06 ,  B29K2025/08 ,  B29K2027/06 ,  B29K2033/12 ,  B29K2055/02 ,  B29K2067/00 ,  B29K2069/00 ,  B29K2077/00

Abstract: A connector and a method of anchoring the connector to a first object that includes providing the connector having a sleeve element and a piston element with a shaft portion, providing a through hole in the first object, and inserting the connector through the through hole and until a distal portion of one of the sleeve and/or the piston element rests against the second object. Mechanical oscillations are coupled into the piston element while the piston element is pressed towards the distal side, and thereby liquefying portions a thermoplastic material at an interface portion between the sleeve element and the piston element while a periphery of the interface portion is adjacent the circumferential wall, and causing the liquefied thermoplastic material to flow radially outward from the periphery and into structures of the first object and/or along an inner surface.

Abstract translation: 一种连接器和将连接器固定到第一物体的方法，包括提供具有套筒元件的连接器和具有轴部分的活塞元件，在第一物体中提供通孔，并将连接器插入穿过孔直到 套筒和/或活塞元件之一的远端部分靠在第二物体上。 机械振动在活塞元件被朝向远端侧挤压时联接到活塞元件中，从而在套筒元件和活塞元件之间的界面处液化热塑性材料的部分，同时界面部分的周边邻近周壁 并且使液化的热塑性材料从周边径向向外流动并进入第一物体的结构和/或沿内表面。

公开(公告)号：US20140237939A1

公开(公告)日：2014-08-28

申请号：US14271783

申请日：2014-05-07

Applicant: WOODWELDING AG

Inventor： Colin Clinch ,  Marcel Aeschlimann ,  Mario Lehmann ,  Laurent Torriani

IPC: F16B13/02

CPC classification number: F16B11/00 ,  B29C65/08 ,  B29C65/645 ,  B29C66/3022 ,  B29C66/30221 ,  B29C66/30223 ,  B29C66/30326 ,  B29C66/474 ,  B29C66/72525 ,  B29C66/727 ,  B29C66/7392 ,  B29C66/7487 ,  B29C66/8322 ,  B29K2101/12 ,  B29K2311/14 ,  B29L2007/002 ,  B29L2022/00 ,  B29L2031/22 ,  B29L2031/608 ,  B29L2031/737 ,  F16B5/01 ,  F16B13/02 ,  F16B17/00 ,  F16B37/061 ,  Y10T29/49934 ,  Y10T403/472 ,  Y10T403/477 ,  Y10T403/4949 ,  B29C65/00

Abstract: A method of anchoring a joining element to a hollow core board with the aid of mechanical vibration. The hollow core board has a first and second outer layers and a middle layer disposed between the outer layers. An opening, including a mouth, is provided in the hollow core board, the opening penetrating the first outer layer and the middle layer. The joining element includes a wall anchoring portion situated between a proximal end and a distal end thereof. A distal end of the wall anchoring portion is positioned into or onto the mouth with a sealing portion on a proximal end of the wall anchoring portion. The wall anchoring portion is forced through the mouth by applying mechanical vibration and a force parallel to the joining element axis, whereby thermoplastic material of the wall anchoring portion is liquefied and pressed into the first outer layer.

Abstract translation: 借助于机械振动将接合元件固定在中空芯板上的方法。 中空芯板具有第一外层和第二外层和设置在外层之间的中间层。 包括口部的开口设置在中空芯板中，该开口穿透第一外层和中间层。 连接元件包括位于其近端和远端之间的壁锚定部分。 壁锚定部分的远端定位在口中或上面，在壁锚定部分的近端上具有密封部分。 通过施加机械振动和平行于接合元件轴线的力将壁锚定部分强制通过口部，由此壁锚定部分的热塑性材料被液化并压入第一外层。