Hexcel Composites Ltd.

Cambridgeshire, United Kingdom

Hexcel Composites Ltd.

Cambridgeshire, United Kingdom

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Patent
Hexcel Composites Ltd | Date: 2017-03-01

There is provided a method of constructing a laminate vehicle body shell component, comprising forming a damping prepreg or semipreg comprising a sheet-like curable prepreg or semipreg comprising resin and structural fibres having intimately contacted thereto a damping layer (14), wherein the damping layer (14) is formed by immersing a fibrous open web material in a solution of damping material and removing the solvent by evaporation, laying down the damping prepreg or semipreg, and forming the damping prepreg or semipreg into the eventual shape of the body shell component; either before or after, laying down additional fibre structural layers (12, 16) to form a curable laminate vehicle body shell component, then exposing the laminate to elevated temperature and optionally elevated pressure, thereby to cure the laminate to produce the laminate vehicle body shell component.


Patent
Hexcel Composites Ltd and Hexcel Corporation | Date: 2017-02-15

A prepreg comprising: a fiber reinforcement; and a curable resin which comprises: 25 to 35 weight percent tetrafunctional epoxy resin based on the total weight of the curable resin; 18 to 28 weight percent difunctional epoxy resin based on the total weight of the curable resin; 4 to 18 weight percent polyether sulfone based on the total weight of the curable resin; 2 to 10 weight percent polyamide 12 particles based on the total weight of the curable resin; 2 to 10 weight percent polyamide 11 particles based on the total weight of the curable resin; 1 to 8 weight percent potato shaped graphite particles based on the total weight of the curable resin; and 17.4 to 27.4 weight percent of a curing agent for said curable resin based on the total weight of the curable resin.


Patent
Hexcel Composites Ltd | Date: 2017-05-03

An adhesive composition comprising an aromatic epoxy resin, an epoxy resin rubber adduct, an amine curing agent; and optionally one or more of an oil absorbent, a corrosion inhibitor and a urone accelerator, wherein the adhesive composition is curable at 150C in no morethan 210 seconds.


Patent
Hexcel Composites S.A.S. and Hexcel Composites Ltd | Date: 2017-06-28

Mechanically attaching articles made from composites has problems due to the difference in properties of the composite in the x, y planar direction and the z perpendicular direction, this results in different properties between the composite and the attachment member such as differences in coefficients of thermal expansion which can weaken the joint further leading to differences in moisture uptake which can further reduce the strength and robustness of the joint. The invention relates to the selection of the position of a joint in order to reduce such problems and to operating the moulding process in a way that improves the provision of mechanical attachments such as bolt holes.


Patent
Hexcel Composites Ltd. | Date: 2017-08-02

This invention relates to an epoxy resin formulation containing a curative that can be cured at 150C to 95% cure in no more than 150 seconds, and can be cured at 120C to 95% cure in no more than 4 minutes. This results in a cured resin having a Tg no greater than 140C wherein the formulation further contains a mould release agent.


Grant
Agency: European Commission | Branch: H2020 | Program: MSCA-ITN-EID | Phase: MSCA-ITN-2016 | Award Amount: 495.75K | Year: 2016

The main objective of the DYNACOM (Dynamic behaviour of composite materials for next generation aeroengines) training network is to set up a European Industrial Doctorate (EID) programme on the design of the next generation of structural composite materials for high strain rate applications. This will be achieved by the development of a consistent, physically based multiscale simulation strategy informed by the dynamic properties of the constituents (fibre, matrix and fiber/matrix interface) measured with a novel micromechanical testing methodology. Two of the major milestones of this EID are: (1) to offer early stage researchers (ESRs) a multidisciplinary and intersectorial training with the objective of establishing a new design paradigm in structural design of composite materials and (2) to provide the European industry with new tools towards a knowledge-base incorporation of composite materials into new components, without the need of inefficient and expensive traditional trial and error approaches. In this sense, the technological focus is put into the introduction of new composite components into the next generation of aeronautical engines, but the implications are numerous in other sectors where composite materials have been identified as a key enabling technology, such as in transport, energy generation and biomedical applications. To accomplish this, the programme brings together one research institution, two industrial partners, one academic institution and a non-profit organization. The joint academic and industrial training program offered by this EID will ensure that the innovative aspects of the research work find a quick industrial integration and will provide the early stage researchers with a truly interdisciplinary and intersectoral training, enhancing their employability and career perspectives.


Patent
Hexcel Corporation and Hexcel Composites Ltd | Date: 2016-08-04

Uncured epoxy resin for use in making prepreg for aerospace applications. The resin includes an epoxy resin component comprising difunctional epoxy resin, trifunctional epoxy resin and/or tetrafunctional epoxy resin and a sufficient amount of [3-(4-aminobenzoyl) oxyphenyl] 4-aminobenzoate (3-ABOAB), as a curing agent, such that the uncured resin can be stored at room temperature of at least 6 weeks and wherein the uncured resin can be fully cured in no more than 2 hours at a temperature of between 175 C. and 185 C.


Patent
Hexcel Composites Ltd | Date: 2016-09-14

A prepreg comprising fibrous material impregnated with two films of an uncured thermosetting resin, comprising between 30 and 40 % resin by weight of the prepreg, the prepreg having a water pick up of from 3 to 9%, resulting in a moulding with improved void content once cured.


A method of controlling a process for the manufacture of a multicomponent sheet material having a desired pre-determined parameter comprising applying an acoustic or an electromagnetic signal to interact with the sheet material whereby the interaction modifies the applied signal, detecting the modified signal, comparing the modified signal or data derived from it with data relating to the pre-determined parameter and modifying at least one step of the process whereby the data relating to the modified signal is modified towards the data relating to the pre-determined parameter.


Grant
Agency: European Commission | Branch: H2020 | Program: CS2-RIA | Phase: JTI-CS2-2014-CFP01-AIR-02-04 | Award Amount: 350.01K | Year: 2016

NEODAMP is marked in the ITD Airframe part B, oriented to highly integrated innovative structural components, for the Large Passenger Aircraft. NEODAMP will develop new prepreg composite materials for structural purposes in the aircraft, able to support structural loads and other additional functions. The project is focused on acoustic damping and complemented with electrical conductivity studies while using techniques related to additional embedded and/or integrated functionality. Composite materials will be chosen among those provided by a widely experienced manufacturer, to meet the future needs and requirements given by the topic manager. Activities are distributed along 36 months, and tasks are associated to 3 main topics: material development, screening and process ability. In order to find the optimal material, a series of key characteristics will be selected, such as acoustic damping, structural and mechanical properties, HSE requirements, Fire, Smoke&Toxicity resistance for fuselage applications, resistance to environmental factors, automatic manufacturing and costs. The damping material will be improved and modified to adjusts properties such as tacking or curing parameters. All the cited features will be deeply studied through a test campaign, at coupon level using raw damping material and the embedded damping prepreg composite material. The wide variety of tests will include from damping behavior and vibro-acoustic performance to lightning strike protection, including aging, common mechanical properties and physicochemical tests. Needed panels and embedded design will be done and manufactured by the partners. Results of the cited works altogether will guide to the optimal design and manufacturing of trials, which will reach to material improvements also. The production of demonstrators will be oriented to automatic fuselage production by using automatic fiber placement techniques and always considering possible solutions for industrialization.

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