公开(公告)号：US12091096B2

公开(公告)日：2024-09-17

申请号：US16998289

申请日：2020-08-20

申请人： SUBARU CORPORATION

发明人： Hiroyasu Ito

IPC分类号： B32B3/12 ,  B29C70/44 ,  B29C70/86 ,  B62D29/04 ,  B29K105/04 ,  B29K105/08 ,  B29L31/30 ,  B62D25/04

CPC分类号： B62D29/043 ,  B29C70/446 ,  B29C70/865 ,  B29K2105/045 ,  B29K2105/08 ,  B29L2031/3041 ,  B62D25/04

摘要： A fiber-reinforced resin composite includes a honeycomb core, a fiber-reinforced resin layer, and a protection layer. The honeycomb core includes a plurality of cells that are defined by partition walls and extend in an axial direction. The fiber-reinforced resin layer is disposed around the honeycomb core. The fiber-reinforced resin layer includes continuous fibers wound around the honeycomb core. The protection layer is interposed between the honeycomb core and the fiber-reinforced resin layer. The protection layer is configured to prevent rupture of the continuous fibers.

公开(公告)号：US20240181727A1

公开(公告)日：2024-06-06

申请号：US18553382

申请日：2022-03-31

申请人： UNIVERSITE DE RENNES ,  CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE - CNRS ,  NANTES UNIVERSITÉ ,  CENTRALESUPELEC ,  INSTITUT NATIONAL DES SCIENCES APPLIQUEES DE RENNES

发明人： Maxime HARNOIS ,  Gaëtan HERRY ,  France LE BIHAN ,  Jean-Charles FUSTEC

IPC分类号： B29C70/86 ,  B29C70/54 ,  B29L31/34

CPC分类号： B29C70/86 ,  B29C70/541 ,  B29L2031/3493

摘要： A method of manufacturing a composite material including at least one ply integrating at least one electronic element situated at the surface of the ply. Also, materials obtained thereof and devices including such materials. The method includes: a) preparing or providing a first substrate having at least one layer; b) applying at least one electronic element onto a face of the first substrate; c) at least partially impregnating the so-obtained product within an impregnation material to form a matrix incorporating the at least one electronic element and the first substrate; d) preparing or providing an impregnable second substrate, the second substrate being placed on top of the impregnated at least one electronic element so that the at least one electronic element is interposed between the first substrate and the second substrate; e) removing the first substrate from the impregnated product obtained; and f) recovering the composite material.

公开(公告)号：US11976764B2

公开(公告)日：2024-05-07

申请号：US17616940

申请日：2020-06-05

申请人： ITREC B.V.

发明人： Nicolaas Thijs Pieter Max ,  Pieter Dirk Melis Van Duivendijk

IPC分类号： F16L47/16 ,  B29C70/34 ,  B29C70/54 ,  B29C70/86 ,  E21B17/043 ,  F16L9/128 ,  F16L15/00 ,  F16L15/08 ,  B29K309/08 ,  B29L23/00

CPC分类号： F16L47/16 ,  B29C70/345 ,  B29C70/541 ,  B29C70/86 ,  E21B17/043 ,  F16L9/128 ,  F16L15/003 ,  F16L15/08 ,  B29K2309/08 ,  B29L2023/22

摘要： The invention relates to an improved filament-reinforced tubular, and a method for providing such a tubular. A filament-reinforced tubular according to the invention comprises a tubular body (2), the tubular body comprising multiple fibre mats (10) encapsulated in a thermoset material (11), and is at least at one end provided with a male screw thread (3) comprising threading. According to the invention, the threading comprises a core member (12, 16). Furthermore, the threading comprises one or more fibre mats (13) that cover the core member. The one or more fibre mats are pulled between the windings of the core member by a positioning wire (14). The core member, the one or more fibre mats, and the positioning wire, are encapsulated by a, preferably thermoset, cover material (15), which cover material defines the shape of the screw thread.

公开(公告)号：US11951368B2

公开(公告)日：2024-04-09

申请号：US16946865

申请日：2020-07-09

申请人： EASTON DIAMOND SPORTS, LLC

发明人： Dewey Chauvin ,  Linda Hunt ,  Ian Montgomery ,  Frederic St-Laurent

IPC分类号： A63B60/00 ,  A63B59/51 ,  A63B59/54 ,  A63B60/54 ,  A63B102/18 ,  A63B102/20 ,  B29C70/30 ,  B29C70/86 ,  B29L31/52

CPC分类号： A63B60/00 ,  A63B59/54 ,  A63B60/54 ,  B29C70/30 ,  B29C70/86 ,  A63B59/51 ,  A63B2102/18 ,  A63B2102/182 ,  A63B2102/20 ,  A63B2209/00 ,  A63B2209/02 ,  B29L2031/5227

摘要： A ball bat includes outer shell segments longitudinally spaced apart from each other to form a gap between them. A joint connects the segments. A first outer shell segment may include a barrel portion of the ball bat and at least part of a tapered portion of the ball bat. A second outer shell segment may include at least part of the tapered portion. The joint may include a tubular element having a first portion positioned within the first outer shell segment and at least partially overlapping an interior surface of the first outer shell segment, and a second portion positioned within the second outer shell segment and at least partially overlapping an interior surface of the second outer shell segment. The tubular element may include an elastomeric material. In some embodiments, the joint may be formed by an elastomeric material connecting the outer shell segments in the gap.

公开(公告)号：US20230415426A1

公开(公告)日：2023-12-28

申请号：US18037303

申请日：2021-11-16

申请人： LM WIND POWER A/S

发明人： Klavs JESPERSEN ,  Lars NIELSEN

IPC分类号： B29C70/30 ,  B29C70/86 ,  B29C70/88 ,  F03D1/06 ,  F03D80/30

CPC分类号： B29C70/30 ,  B29C70/865 ,  B29C70/885 ,  F03D1/0675 ,  F03D80/30 ,  B29L2031/085

摘要： The present invention relates to a method of manufacturing a wind turbine blade (10), comprising the steps of placing a fibre lay-up including one or more fibre layers on the mould surface of a blade mould (60), arranging a load-bearing structure (45) and a core member (62) on the fibre lay-up such that the core member (62) is arranged between the load-bearing structure (45) and the leading edge (18) and/or between the load-bearing structure (45) and the trailing edge (20), and infusing resin into the blade mould to impregnate the fibre lay-up. The core member (62) comprises a first hole (64) with a circular cross section, a first cylindrical insert (70) rotatably arranged within the first hole (64) of the core member (62), the first cylindrical insert (70) having a central axis (71). A recess (80) is formed in the first cylindrical insert (70), wherein the recess (80) is arranged eccentrically with respect to the central axis (71) of the first cylindrical insert (70).

公开(公告)号：US20230356496A1

公开(公告)日：2023-11-09

申请号：US18222824

申请日：2023-07-17

申请人： Purple Innovation, LLC

发明人： Robert Wayne Taylor ,  Russell B. Whatcott ,  Matthew Eccles Rogers ,  Dhyey Y. Acharya ,  Lidia Saldaña

IPC分类号： B32B5/06 ,  B32B3/12 ,  B32B5/24 ,  A47G9/10 ,  B29C70/86

CPC分类号： B32B5/06 ,  B32B3/12 ,  B32B5/24 ,  A47G9/10 ,  B32B5/073 ,  B29C70/865 ,  B32B2479/00 ,  B29K2021/00

摘要： A cushioning element includes a fabric, a first cushioning element on a first side of the fabric, and a second cushioning element on a second side of the fabric. The first cushioning element and second cushioning element may be superimposed. The fabric may include a first layer and a second layer that are superimposed, with the first cushioning element secured to and protruding from the first layer and the second cushioning element secured to and protruding from the second layer. Each of the first cushioning element and second cushioning element may include a plurality of interconnected walls formed from an elastomeric gel material. The walls of the first cushioning element and second cushioning element may be aligned or offset.

公开(公告)号：US20230330953A1

公开(公告)日：2023-10-19

申请号：US18026908

申请日：2021-10-05

申请人： LM WIND POWER A/S ,  BLADE DYNAMICS LIMITED

发明人： Jeppe Bjørn JØRGENSEN ,  Ole NIELSEN ,  Rama RAZEGHI

IPC分类号： B29C70/86 ,  B29C70/48 ,  B29C70/20

CPC分类号： B29C70/86 ,  B29C70/48 ,  B29C70/205 ,  B29K2105/0881

摘要： A precured fibrous composite strip for a load-carrying structure for a wind turbine blade has a first longitudinal end and a second longitudinal end, a first side and a second side with a width defined as the distance between the first side and the second side, and an upper surface and a lower surface with a thickness defined as the distance between the upper surface and the lower surface. The strip includes a taper region with a taper length at the first longitudinal end. The taper region tapers in thickness towards the first longitudinal end. The taper region includes a first taper section proximal to the first longitudinal end and having a first average taper angle, a third taper section distal to the first longitudinal end and having a third average taper angle, and a second taper section between the first taper section and the third taper section.

公开(公告)号：US20230311429A1

公开(公告)日：2023-10-05

申请号：US18185676

申请日：2023-03-17

申请人： Thomas Beale

发明人： Thomas Beale

IPC分类号： B29C70/32 ,  B29C70/86

CPC分类号： B29C70/32 ,  B29C70/86 ,  B29L2031/75

摘要： A method of producing a universal joint assembly. The method comprises providing a joining member for forming a universal joint, said joining member comprising a first pivot and a second pivot; applying continuous fibre reinforcement and a polymer matrix to a form including said joining member to create a single fibre-reinforced polymer structure in which the joining member is embedded; and splitting said single fibre-reinforced structure into a first fibre-reinforced polymer shaft and a second fibre-reinforced polymer shaft that are coupled together by the joining member to form a universal joint.

公开(公告)号：US11760862B2

公开(公告)日：2023-09-19

申请号：US17322372

申请日：2021-05-17

申请人： Composite Technologies International, LLC

发明人： Stephen Gleason, Sr.

IPC分类号： C08K3/30 ,  G01N1/36 ,  C08J5/24 ,  C08J5/04 ,  C08J5/18 ,  G01N33/44 ,  C08K3/013 ,  C08L35/02 ,  B29C70/70 ,  B29C41/30 ,  B29C70/30 ,  B29C70/68 ,  B29C70/86 ,  B29C70/02 ,  B29C37/00 ,  B29C41/20 ,  B29C70/54 ,  B29C70/60 ,  B29C41/00 ,  B29C70/88 ,  B29C41/32 ,  B29C41/22 ,  B29K31/00 ,  B29K67/00 ,  B29K105/06 ,  B29K105/16 ,  B29K267/00 ,  B29K231/00 ,  B29K105/20 ,  B29K309/00 ,  B29K303/04 ,  B29K631/00 ,  B29K667/00 ,  B29K509/00 ,  B29K303/00 ,  G01N3/10

CPC分类号： C08K3/30 ,  C08J5/043 ,  C08J5/18 ,  C08J5/244 ,  C08J5/249 ,  G01N1/36 ,  G01N33/442 ,  B29C37/0025 ,  B29C41/00 ,  B29C41/003 ,  B29C41/20 ,  B29C41/22 ,  B29C41/30 ,  B29C41/32 ,  B29C70/02 ,  B29C70/30 ,  B29C70/305 ,  B29C70/545 ,  B29C70/60 ,  B29C70/68 ,  B29C70/682 ,  B29C70/70 ,  B29C70/86 ,  B29C70/865 ,  B29C70/88 ,  B29K2031/00 ,  B29K2067/00 ,  B29K2067/06 ,  B29K2105/06 ,  B29K2105/16 ,  B29K2105/20 ,  B29K2231/00 ,  B29K2267/00 ,  B29K2267/06 ,  B29K2303/00 ,  B29K2303/04 ,  B29K2309/00 ,  B29K2509/00 ,  B29K2631/00 ,  B29K2667/00 ,  B29K2667/06 ,  C08J2300/12 ,  C08J2335/02 ,  C08J2367/00 ,  C08K3/013 ,  C08K2003/3045 ,  C08L35/02 ,  G01N3/10 ,  G01N2001/364 ,  C08K3/30 ,  C08L35/02

摘要： A composite core material and methods for making same are disclosed herein. The composite core material comprises mineral filler discontinuous portions disposed in a continuous encapsulating resin. Further, the method for forming a composite core material comprises the steps of forming a mixture comprising mineral filler, an encapsulating prepolymer, and a polymerization catalyst; disposing the mixture onto a moving belt; and polymerizing said encapsulating prepolymer to form a composite core material comprising mineral filler discontinuous portions disposed in a continuous encapsulating resin.

公开(公告)号：US20230193766A1

公开(公告)日：2023-06-22

申请号：US18010751

申请日：2021-06-09

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Clément Pierre POSTEC ,  Thomas Alain DE GAILLARD ,  Teddy FIXY ,  Eddy Keomorakott SOURYAVONGSA

IPC分类号： F01D5/28 ,  F01D5/14 ,  B29C70/86 ,  B29C70/22 ,  B29C70/34

CPC分类号： F01D5/282 ,  F01D5/147 ,  B29C70/86 ,  B29C70/222 ,  B29C70/34 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2240/30 ,  B29L2031/082

摘要： A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.