Maro Publications

Lay-Up

Patents with Abstracts

*12/6/2012

Maro Encyclopedia

Notes

xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxx 

11. 8,303,757 
Tensioning device for composite structures
 
Glain et al of the The Boeing Company, Illinois, develop a preform for fabrication including a mandrel, anchoring groove, anchoring device, tensioning groove, and tensioning device.  The mandrel receives the preform.  The mandrel has a first mandrel end and a second mandrel end. The preform has a first preform end and a second preform end.  The anchoring groove is disposed at the first mandrel end.  The anchoring device is configured and located to urge the first preform end towards the anchoring groove to secure the first preform end therebetween.  The tensioning groove is disposed between the first mandrel end and the second mandrel end. The tensioning device is configured and located to urge a portion of the preform into the tensioning groove. (RDC 12/6/2012)

10. 8,303,751 
Method for integral vent screen in molded panels
 
Gomes and Krajewski of GM Global Technology Operations LLC, Michigan, produced a fiber reinforced panel including a vent screen.  Holes are made in each of first and second sheets of fiber and the holes register with each other when the sheets are stacked within a mold.  A screen material is placed between the first and second sheets so that a part of the screen material that registers with the holes in the first sheet and second sheet is exposed.  Filler inserts are inserted into the holes of the first and second sheets to mask the screen. A resin is provided and cured to bond together the first and second sheets and the screen.  Thus, the screen remains exposed after the first and second sheets and screen have been bonded together by the resin, thereby forming a fiber reinforced panel having an integrally molded vent screen therein. (RDC 12/6/2012)

9. 8,302,522 
Composite material, composite part and methods for making such
 
Levesque  of Marquez Transtech Ltee, Canada, developed a composite material consisting of fiber tape strips woven or braided together.  Each of the fiber tape strips is made of a single layer of unidirectional fibers.  The fibers are at least partially embedded in a thermoplastic matrix.  A tubular composite part is made from this composite material and of an internal film.  A method of manufacturing the composite material comprises weaving or braiding the fiber tape strips, especially in the form of a tube.  A method of manufacturing a composite part comprises pressurizing the film inside the tube while heating both the tube and the film up to their forming temperature so as to bond the film to the woven fiber tape strips. (RDC 11/9/2012)

8. 8,287,790 
Method for manufacturing beams of fiber-reinforced composite material

Westerdahl et al of SAAB AB, Sweden, developed a method for manufacturing a hollow load-bearing beam structure of fiber-reinforced composite material. The method includes preparing a first lay-up of a first plurality of layers, and a second lay-up of a second plurality of layers. The first and second lay-ups are positioned on different sides of a mandrel and formed to a beam structure by bending the lay-ups against the mandrel, such that the side edges of the respective layers of the first and second lay-ups are arranged as offset butt joints in the circumferential direction of the formed beam structure. (RDC 10/31/2012)

7. 8,282,758 
System and method for the automated delivery and layup of resin infused fibers
 
Van Nieuwenhove and Ostojic of the General Electric Company, New York, developed an automated in-line feed-through system integrating the delivery, application and infusion of a resin to one or more fiber tows and layup of the one or more infused fiber tows to form a composite structure.  The system includes an automated resin delivery, deposition and infusion system configured to deposit the resin on one or more fiber tows and form the infused fiber tows.  The system integrates an automated layup system including a compaction roller, a guide roller coupled to an extending cylinder, and an auxiliary roller configured to adhere the one or more infused fiber tows to a substrate. The system further includes a controller configured to control system parameters, including the control of tension of the one or more infused fiber tows within the automated layup system. (RDC 10/11/2012)

6. 8,256,484 
End effector for constructing composite members
 
Kisch et al of the Boeing Company, Illinois, developed an end effector constructing composite members, in which a compaction roller and redirect rollers translate synchronously along the compaction axis.  Additionally, the end effector includes an advantageous arrangement of spools and rollers that directs tow to the redirect rollers at substantially a right angle.  Movement of the compaction roller along the compaction axis induces little, if any, changes in tow tension.  The substantially constant tow tension advantageously reduces rewinding of the tow supply spools, which can degrade the quality of the lay up and contribute to despooling problems. (RDC 9/5/2012)

5. 8,241,711 
Method of manufacturing composite material 
 
Inston of Airbus Operations Limited, Great Britain,  irradiates a sheet of fibres (instead of a single fibre) and simultaneously runs an impregnation process to produce a sheet of fibres impregnated with matrix (commonly known in the art as a "prepreg").  The method enables a sheet to be formed without having to treat the fibres with an intermediate product (RDC 8/20/2012)

4. 8,231,820 
Epoxy resin composition
 
Dixit et al of Aditya Birla Chemicals, Thailand, developed a molded composite by reacting a reaction mass containing a  20 to 50 wt% polyepoxide,  10 to 20 wt% diol, , 20 to 50 wt% hardener and  0.5 to 10 wt% accelerator either alone or in solution with compatible diluents, to obtain an epoxy resin mix having intrinsic viscosity in the range of 100 to 850 cPs.  This mixture is poured into a mold having an in-situ glass fiber scaffold at 45 to 50 C. and applying pressure to the resin mix in the mold to form a compressed green composition: partially curing the compressed green composition at a temperature in the range of 60 to 80 C,  This is further cured at 80 to 90 C.  The composite is used for structural applications like windmill blades, yachts, domes, ships made from a composite made in accordance with the process as mentioned herein. (RDC 8/7/2012)

3. 8,177,933 
Method to manufacture a hollow, single-piece bladed disc
 
Foucault et al of SNECMA, France, formed a disc by placing A first insert forming a ring inside and in contact with a core in degradable material.  On the outer face of the core a plurality of inserts  is arranged each comprising a platform  applied against the outer face of the core and at least one blade extending substantially radially outwards. A fibrous structure is wound around the core passing over the platforms  and over the inner surface of the ring-shaped insert. Molding of the fibrous structure, impregnated with a composition containing a resin, is performed before polymerization of the resin and removal of the core. (RDC 5/23/2012)

2. 8,137,602 
Method for manufacturing composite components
 
Farmer and Buckley of Airbus, Great Britain, fabricated a composite component by loading a preform into mold or container; soaking with a solvent/catalyst mixture and, then removing the liquid; heating with a carbonaceous gas to grow carbon nanotubes on the catalyst; removing the carbonaceous gas and adding a liquid resin material into the material; finally curing the whole composite. (RDC 5/14/2012)

1. 8,132,487 
Cutting sequence for net trimming a composite layup at an oblique angle 
 
Evans and Heigl of the Boeing Company, Illinois, produced  a bevel in an uncured composite layup.   An edge of part cut through the composite layup is performed at about 90.degree. relative to the composite layup and a bevel cut is performed on the edge of part. (RDC 4/24/2012)

xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxx 

Roger D. Corneliussen
Editor
www.maropolymeronline.com

Maro Polymer Links
Tel: 610 363 9920
Fax: 610 363 9921
E-Mail: cornelrd@bee.net  

***********************************

Copyright 2012 by Roger D. Corneliussen.
No part of this transmission is to be duplicated in any manner or forwarded by electronic mail without the express written permission of Roger D. Corneliussen
**************************************

** Date of latest addition; date of first entry is 4/24/2012.