Patent search cpc:"B29C66/73753" Page 1

1.

发明授权
Methods of using compression collars for coupling a tube to a tube fitting 有权

公开(公告)号：US11821553B2

公开(公告)日：2023-11-21

申请号：US17576671

申请日：2022-01-14

Applicant: Life Technologies Corporation

Inventor： Ryan S. Beus , Brandon R. Burtenshaw , Eric Davis , Patrick L. Draper , Michael E. Goodwin , Brandon M. Knudsen , Jeremy K. Larsen , Kevin R. Pickup

IPC: F16L33/207 , A61M39/12 , F16L33/22 , B29C65/00 , B29C65/68 , B29C65/56 , B29L31/24

CPC classification number: F16L33/207 , A61M39/12 , B29C65/565 , B29C65/68 , B29C66/1122 , B29C66/12 , B29C66/1222 , B29C66/1224 , B29C66/131 , B29C66/30321 , B29C66/5344 , B29C66/7315 , B29C66/7392 , B29C66/7394 , B29C66/73753 , F16L33/227 , B29C66/71 , B29L2031/24 , B29C66/71 , B29K2023/06 , B29C66/71 , B29K2023/065

Abstract: A method for coupling a tube to a tube fitting includes radially outwardly expanding a tubular compression collar from a constricted state to an expanded state, the compression collar having a throughway extending there through and being made of a resiliently flexible material. An end of the tube is inserted within the throughway of the expanded compression collar, the tube bounding a passage. A tube fitting is inserted within the passage of the tube. The compression collar is allowed to resiliently rebound back towards the constricted state so that the compression collar pushes the tube against the tube fitting.

2.

发明授权
Composite material structure and method of manufacturing composite material structure 有权

公开(公告)号：US09931809B2

公开(公告)日：2018-04-03

申请号：US15259109

申请日：2016-09-08

Applicant: Fuji Jukogyo Kabushiki Kaisha

Inventor： Yoshikazu Kosugi , Masakatsu Abe , Yuichiro Yasunaga

IPC: B32B5/02 , B29C70/34 , B29C70/00 , B29C65/00

CPC classification number: B32B5/02 , B29C65/00 , B29C65/02 , B29C65/48 , B29C66/1122 , B29C66/1162 , B29C66/12443 , B29C66/12463 , B29C66/12464 , B29C66/1248 , B29C66/12841 , B29C66/1286 , B29C66/14 , B29C66/43 , B29C66/43421 , B29C66/7212 , B29C66/72141 , B29C66/73751 , B29C66/73753 , B29C66/742 , B29C70/00 , B29C70/34 , B29K2309/08 , B29K2307/04

Abstract: According to one implementation, a composite material structure includes a first member and a second member. The first member has at least one first bonded surface. The second member has at least one second bonded surface to be bonded to the at least one first bonded surface. The second member is made of a composite material. At least one surface formed by fibers forming the composite material is used as the at least one second bonded surface by disposing end portions of the fibers, in the first member side, inside the composite material.

3.

发明申请
COMPONENT DEVICE AND METHOD FOR DETECTING A DAMAGE IN A BONDING OF A COMPONENT DEVICE 审中-公开

公开(公告)号：US20170176282A1

公开(公告)日：2017-06-22

申请号：US15386269

申请日：2016-12-21

Applicant: Airbus Defence and Space GmbH , Airbus Operations GmbH

Inventor： Thomas KRUSE , Thomas KÖRWIEN , Alois FRIEDBERGER , Andreas HELWIG

IPC: G01M3/26 , G01N19/08 , G01M3/04

CPC classification number: G01M3/26 , B29C65/48 , B29C65/52 , B29C65/522 , B29C65/526 , B29C65/8246 , B29C66/026 , B29C66/1122 , B29C66/131 , B29C66/474 , B29C66/71 , B29C66/721 , B29C66/73753 , B29C66/73754 , B29C66/73755 , B29C66/73756 , B29C66/7394 , B29C66/742 , B64C1/12 , B64C3/26 , B64D45/00 , B64D2045/0085 , G01M3/04 , G01M3/3272 , G01N3/12 , G01N19/04 , G01N19/08 , B29K2049/00

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, the component device having a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, and a detector device having at least one interior space sensor device configured to measure a change in a pressure and/or a concentration of a gas surrounding the interior space sensor device. The first component element, the second component element, and the bonding confine an interior space. The interior space sensor device is arranged in the interior space.

4.

发明授权
Grooved resin molded part 有权

公开(公告)号：US09610713B2

公开(公告)日：2017-04-04

申请号：US14766835

申请日：2014-02-06

Applicant: Polyplastics Co., Ltd.

Inventor： Akihiro Mochizuki

IPC: B29C35/08 , B29C45/14 , B29C59/16 , B29C65/08 , B29C65/16 , B29C65/36 , B29C65/82 , B29C65/00 , B23K35/36 , B23K26/364 , B23K26/402 , B23K26/324 , B23K26/244 , B29K105/12 , B29K105/16 , B29L31/00 , B23K103/00 , B23K103/16

CPC classification number: B29C35/0805 , B23K26/244 , B23K26/324 , B23K26/364 , B23K26/402 , B23K35/3613 , B23K2103/16 , B23K2103/42 , B23K2103/50 , B29C45/14811 , B29C59/16 , B29C65/08 , B29C65/1616 , B29C65/1635 , B29C65/1654 , B29C65/1661 , B29C65/1683 , B29C65/3648 , B29C65/8253 , B29C66/0246 , B29C66/026 , B29C66/1122 , B29C66/1222 , B29C66/1224 , B29C66/1282 , B29C66/12841 , B29C66/14 , B29C66/21 , B29C66/3022 , B29C66/30325 , B29C66/3034 , B29C66/304 , B29C66/41 , B29C66/45 , B29C66/53461 , B29C66/54 , B29C66/71 , B29C66/712 , B29C66/7212 , B29C66/72143 , B29C66/73753 , B29C66/7392 , B29C66/73921 , B29C66/7394 , B29C66/73941 , B29C66/81267 , B29C66/81431 , B29C66/8322 , B29C66/939 , B29C2035/0838 , B29C2791/009 , B29K2105/122 , B29K2105/16 , B29L2031/756 , Y10T428/23943 , Y10T428/2395 , Y10T428/2457 , Y10T428/24579 , Y10T428/2462 , Y10T428/249941 , Y10T428/249946 , B29K2309/08 , B29K2307/04 , B29K2309/14 , B29K2081/04 , B29K2067/006 , B29K2059/00 , B29K2021/003

Abstract: A grooved resin molded part which when joined to another molded part, can form a composite molded product having an enhanced strength. This part contains an inorganic filler and has multiple grooves formed by partially removing the resin, such that the filler is exposed in these grooves. The depth of the grooves may be at least one-half of the length of the grooves in the shorter direction. The filler may have a fibrous shape; and the longer direction of the filler may be different from that of the grooves. The part is obtained by subjecting a resin molded part containing the filler to laser irradiation or the like to form multiple grooves in which the filler is exposed.

5.

发明申请
FLIGHT VEHICLE RADOME AND METHOD FOR PRODUCING FLIGHT VEHICLE RADOME 审中-公开
Title translation: 飞行车辆射线和生产飞行车辆射线的方法

公开(公告)号：US20160233578A1

公开(公告)日：2016-08-11

申请号：US15015503

申请日：2016-02-04

Applicant: MITSUBISHI ELECTRIC CORPORATION

Inventor： Masami KUME , Hiroki KOBAYASHI

IPC: H01Q1/42 , B29C65/48 , B29C70/34 , H01Q1/28 , B29C70/16

CPC classification number: H01Q1/422 , B29C65/02 , B29C66/1122 , B29C66/545 , B29C66/63 , B29C66/71 , B29C66/7212 , B29C66/72141 , B29C66/73753 , B29C66/73755 , B29C66/8322 , B29C70/026 , B29C70/086 , B29C70/16 , B29C70/34 , B29K2079/08 , B29K2105/04 , B29K2105/0845 , B29K2309/14 , B29K2995/0016 , B29L2009/00 , B29L2031/3076 , B29L2031/3456 , H01Q1/28

Abstract: A flight vehicle radome according to the present invention has a shape that covers radio equipment installed in a flight vehicle. The flight vehicle radome is formed of a sandwich panel structure in which a core member (30) resulting from foaming and compositing of a heat-resistant resin (32) and insulating reinforcing fibers (31) is sandwiched between skin members (20) made of a fiber reinforced material being a composite of quartz cloth (20) and a heat-resistant resin (22).

Abstract translation: 根据本发明的飞行器具天线罩具有覆盖安装在飞行器中的无线电设备的形状。飞行器车载雷达罩由夹层板结构形成，其中由耐热树脂（32）和绝缘增强纤维（31）的发泡和复合产生的芯构件（30）夹在由纤维增强材料是石英布（20）和耐热树脂（22）的复合材料。

6.

发明申请
Composite Strip 审中-公开
Title translation: 复合条

公开(公告)号：US20110195232A1

公开(公告)日：2011-08-11

申请号：US13074430

申请日：2011-03-29

Applicant: Kenneth M. Dull , William H. Ingram

Inventor： Kenneth M. Dull , William H. Ingram

IPC: B32B3/00 , B32B37/02 , B32B37/12 , B32B37/16 , B32B38/10

CPC classification number: B29C70/54 , B29C37/02 , B29C39/00 , B29C65/02 , B29C65/48 , B29C65/5057 , B29C66/1122 , B29C66/522 , B29C66/5326 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/723 , B29C66/73751 , B29C66/73753 , B29C66/7394 , B29C66/73941 , B29C70/342 , B29C70/446 , B29L2031/3082 , B32B17/04 , B32B19/04 , B32B37/00 , B32B37/02 , B32B2037/1253 , B32B2305/076 , B32B2309/10 , Y10T156/10 , Y10T156/1093 , Y10T428/24752 , Y10T428/2476 , B29K2307/04 , B29K2067/00 , B29K2063/00 , B29K2027/18 , B29K2071/00 , B29K2081/06 , B29K2309/08 , B29K2307/02 , B29K2309/02 , B29K2277/10

Abstract: A composite strip and a method of manufacturing a pre-cured composite strip. A pre-cured composite strip having a thermoset resin may be placed on a surface of a portion of a composite component where a caul plate seam may be expected. Caul plates may be placed on the composite component after placing the pre-cured composite strip to form the caul plate seam. The composite component may be cured after placing the caul plates on the composite component.

Abstract translation: 复合带材和预固化复合带材的制造方法。具有热固性树脂的预固化复合带可以放置在复合部件的可能预期产生刮板接缝的部分的表面上。在放置预固化的复合带材以形成挡板接缝之后，可以将复合板材放置在复合部件上。复合组件可以在将刮板放置在复合部件上之后固化。

7.

发明申请
Joining of Concentric Section Polymer Composite Components 审中-公开
Title translation: 同心段聚合物复合材料的连接

公开(公告)号：US20090277579A1

公开(公告)日：2009-11-12

申请号：US12440350

申请日：2007-09-04

Applicant: Michael Andrew Marelli , Andrew Beehag , Rowan Paton

Inventor： Michael Andrew Marelli , Andrew Beehag , Rowan Paton

IPC: B32B37/06

CPC classification number: B29C66/826 , B29C65/004 , B29C65/02 , B29C65/14 , B29C65/34 , B29C65/4815 , B29C65/5057 , B29C65/5071 , B29C65/565 , B29C65/76 , B29C65/8207 , B29C66/1122 , B29C66/21 , B29C66/242 , B29C66/24244 , B29C66/30325 , B29C66/3452 , B29C66/5344 , B29C66/612 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72525 , B29C66/73115 , B29C66/73117 , B29C66/73161 , B29C66/73753 , B29C66/73772 , B29C66/73774 , B29C66/7392 , B29C66/73921 , B29C66/7394 , B29C66/742 , B29C66/8181 , B29K2023/12 , B29K2027/16 , B29K2031/00 , B29K2063/00 , B29K2067/00 , B29K2071/00 , B29K2101/10 , B29K2101/12 , B29K2307/00 , B29K2995/0008 , B29K2995/0039 , B29K2995/004 , F16L47/02 , B29K2307/04 , B29K2067/003

Abstract: A process for assembling a composite component with a thermoplastic surface into or around a second component, the process including selecting a first component with a thermoplastic surface and a second component that, when assembled with the first component has at least some points of contact, shaping where necessary at least one component in the joint area, and pressing the components together to achieve relative immobility between the components. A second process involves the selection of a third thermoplastic component to be assembled with the first two components with at least some points of contact with the first and second components are achieved, shaping where necessary, and assembling such that relative immobility is achieved between all three components. In both processes, the joint area is then heated to allow the thermoplastic to flow and preferably weld the assembled components together.

Abstract translation: 一种用于将具有热塑性表面的复合部件组装到第二部件中或其周围的方法，所述方法包括选择具有热塑性表面的第一部件和第二部件，当与第一部件组装时，具有至少一些接触点，成形在必要时在接合区域中至少一个部件，并且将部件压在一起以实现部件之间的相对不动。第二种方法包括选择要与前两种组分组装的第三种热塑性组分，其中至少一些与第一和第二组分的接触点得到实现，在必要时进行成形，并组装使得在所有三种之间实现相对不动组件。在两个过程中，接合区域然后被加热以允许热塑性塑料流动并且优选地将组装的组件焊接在一起。

8.

发明申请
Connecting structure for an aircraft or spacecraft and method for producing the same 有权
Title translation: 飞机或航天器的连接结构及其制造方法

公开(公告)号：US20080210824A1

公开(公告)日：2008-09-04

申请号：US11974246

申请日：2007-10-12

Applicant: Ulrich Eberth

Inventor： Ulrich Eberth

IPC: B64C1/06

CPC classification number: B64C1/12 , B29C65/02 , B29C65/4815 , B29C65/486 , B29C66/05 , B29C66/1122 , B29C66/21 , B29C66/532 , B29C66/61 , B29C66/7212 , B29C66/73751 , B29C66/73753 , B29C66/81422 , B29C70/24 , B29C70/543 , B29K2995/0089 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , B64F5/10 , Y02T50/43 , B29K2307/04

Abstract: The present invention relates to a connecting structure for an aircraft or spacecraft, with a structural component and a stringer. The stringer is connected to the structural component by means of connecting regions. In order to reduce stress peaks that result for example from impact in the structural component, a high impact material is introduced into at least one of the connecting regions to provide a local increase in the energy absorbing capacity of the at least one connecting region.

Abstract translation: 本发明涉及一种具有结构部件和纵梁的飞机或航天器的连接结构。桁条通过连接区连接到结构部件。为了减少例如由于结构部件的冲击引起的应力峰值，将高冲击材料引入至少一个连接区域中，以提供至少一个连接区域的能量吸收能力的局部增加。

9.

发明申请
Method for joining precured or cured stringers to at least one structural component of an aircraft or spacecraft 有权
Title translation: 将预固化或固化的桁条连接到飞行器或航天器的至少一个结构部件的方法

公开(公告)号：US20080083494A1

公开(公告)日：2008-04-10

申请号：US11904310

申请日：2007-09-26

Applicant: Peter Sander , Hans Marquardt , Hauke Lengsfeld

Inventor： Peter Sander , Hans Marquardt , Hauke Lengsfeld

IPC: B29C65/00

CPC classification number: B29C66/721 , B29C65/02 , B29C66/1122 , B29C66/474 , B29C66/532 , B29C66/61 , B29C66/73751 , B29C66/73753 , B29C66/7394 , B29C66/81455 , B29D99/0014 , B29K2105/06 , B29K2105/24 , B29L2031/3076 , B29L2031/766 , Y10T156/1089

Abstract: The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement necessary for the joining is produced in two parts. In a first step, each precured stringer is covered in advance with a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Respective vacuum film strips are subsequently arranged on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.

Abstract translation: 本发明涉及一种用于将预固化桁条连接到飞行器或航天器的至少一个结构部件的方法。连接所需的真空布置分两部分。在第一步中，每个预固化的桁条预先用覆盖真空膜覆盖。以这种方式制备的桁条被布置在结构部件上。随后将各真空薄膜条布置在相邻的桁条上并在相邻桁条之间的中间空间上。通过使用真空密封装置，真空膜条和覆盖真空膜8形成连续的真空装置。随后使用该真空装置，将桁条随后在加压下结合到结构部件。