Shaped geopolymeric particles, fibers, and articles incorporating at least one geopolymer are provided; the geopolymeric particles, fibers, and articles having a structure that is solid, foamed, hollow or with one or more voids. Geopolymers are formed by alkali activation of an aluminosilicate and/or aluminophosphate material. The end-products are shaped as spheres, flakes, fibers, aggregates thereof or articles. Such products are formed at low temperatures; wherein forming includes processing using techniques such as spray drying, melt spinning, or blowing. The shaped geopolymeric particles and fibers have high chemical durability, high mechanical strength, application-targeted flowability and packing properties, and are specially suited for incorporating into composite materials, articles, and for use in cementitious, polymeric, paint, printing, adhesion and coating applications. Shaped geopolymeric particles, fibers and articles having voids, hollow or foam-like structures are formed by adding one or more blowing agents.

Geopolymeric particles, fibers, shaped articles and methods of manufacture

The present invention relates to sandwich panels used as aircraft interior parts. In addition to provide a finishing function, the sandwich panels need to have certain mechanical properties and have sufficient fire resistance to retard the spread of fire within the vehicle interior. The present invention provides an aircraft interior panel with skins comprising natural fibre reinforced composites based either on an inorganic thermoset resin or a thermoplastic resin. Such panels provide the required flame and heat resistance, allow easy recycling and disposal, are cheaper and offer significant weight savings over conventional sandwich panels.

Green aircraft interior panels

The present invention relates to fire resistant composite structures. As an example, a fire resistant composite structure can have a foam material located between a first facing and a second facing, and a barrier layer on the foam material. The barrier layer can include an adhesive material and a heat absorption material, where the heat absorption material has a melting point of 40°C to 140°C and is 15 weight percent to 99 weight percent of the barrier layer.

Fire resistant composite structure

The invention provides a method for producing a component (37) for aerospace, with the following method steps: supplying a lay-up arrangement (1) to be laid by means of a tape-laying machine (25), with a glass-fibre lay-up (8), which is preimpregnated with a resin matrix (10), and/or supplying a structural arrangement (12) to be laid by means of a tape-laying machine (25), with a structure (16) which is made of metal and is preimpregnated with a resin matrix (18), laying the lay-up and/or structural arrangement (1; 12) on a laminating apparatus (23) by means of a tape-laying machine (25), and curing the lay-up and/or structural arrangement (1; 12) and therefore forming the component (37).

Lay-up arrangement and structural arrangement and method for producing a component for aerospace

Composite panel for air cargo containers including a fire resistant, closed cell foam core, a skin attached to each surface of the core formed by fire resistant fibers in a matrix resin, wherein the panel will contain an internal fire with temperatures of up to 1500° F. for a period of at least 4 hours.

Air cargo container

A fire resistant laminate for application to a core structure (12) to form a sandwich panel (10) having fire resistant face sheets (14 & 16). The laminate includes a fire protection (18) in which at least one layer of fibers (22) is embedded within a cured inorganic polymer matrix (24). The laminate further includes an adhesive layer (20) for bonding to the core structure.

F. Dana Blair

Papers

Composite panel with fire resistant face sheets