Curable prepregs possessing enhanced ability for the removal of gases from within prepregs and between prepreg plies in a prepreg layup prior to and/or during consolidation and curing. Each curable prepreg is a resin-impregnated, woven fabric that has been subjected to a treatment to create an array of openings in at least one major surface. Furthermore, the location of the openings is specific to the weave pattern of the fabric.

A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

The present technology provides a carbon fiber reinforced plastic that includes carbon fibers covalently bonded to an energetic polymer and a polymer matrix. Also described is a method for recycling carbon fibers from the carbon fiber reinforced plastic material using microwave energy to separate the carbon fibers from the polymer matrix.

Curable prepregs possessing enhanced ability for the removal of gases from within prepregs and between prepreg plies in a prepreg layup prior to and/or during consolidation and curing. Each curable prepreg is a resin-impregnated, woven fabric that has been subjected to a treatment to create an array of openings in at least one major surface. Furthermore, the location of the openings is specific to the weave pattern of the fabric.

Provided herein is a composition comprising from 50% to 60% polysiloxane consisting essentially of polyphenylmethylsiloxane and α,ω-methoxy-terminated polydimethylsiloxane, from 40% to 50% organic solvent, from 2% to 4% polysilazane, and polysilane of a formula (R.sub.1R.sub.2Si).sub.n, wherein n is greater than 1, and wherein R.sub.1 and R.sub.2 are the same or different and are alkyl, alkenyl, cycloalkyl, alkylamino, aryl, aralkyl, or alkylsilyl. The composition, after curing, is a flame resistant binder for forming a composition-fiber composite that withstands repeated temperatures over 1800° F. The composition may further comprise from 0.1% to 2% of an enhancer selected from butyltitanate and aminoethylaminopropyltrimethoxysilane (H.sub.2NC.sub.2H.sub.4NHC.sub.3H.sub.6—Si(OCH.sub.3).sub.3). The composition may be mixed with fibers in a ratio of 35:65 to 45:55 (w/w), and the composition-fiber mixture may be cured under vacuum at a temperature of 200° F. to 450° F. for 30 minutes to 180 minutes to form a composite.

A method and an article of manufacture are disclosed for reinforcing various structures with only partially accessible circumference, such as columns closely adjacent to or protruding out of a wall or beams holding a ceiling. Some of these structures may be partly or completely submerged in water, such as retaining walls on the sides of rivers and water-ways. In some embodiments a prefabricated shell will fully or partly cover the exposed and reachable part of the structure and will be secured in place by various means. The shell may hug the structure tightly or loosely and the space between the shell and the structure may be filled with such curable materials as glue, epoxy, grout, concrete and the like. In various embodiments additional reinforcement such as rebar may be placed in the space between the shell and the structure.

Curable prepregs possessing enhanced ability for the removal of gases from within prepregs and between prepreg plies in a prepreg layup prior to and/or during consolidation and curing. Each curable prepreg is a resin-impregnated, woven fabric that has been subjected to a treatment to create an array of openings in at least one major surface. Furthermore, the location of the openings is specific to the weave pattern of the fabric.

A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

Curable prepregs possessing enhanced ability for the removal of gases from within prepregs and between prepreg plies in a prepreg layup prior to and/or during consolidation and curing. Each curable prepreg is a resin-impregnated, woven fabric that has been subjected to a treatment to create an array of openings in at least one major surface. Furthermore, the location of the openings is specific to the weave pattern of the fabric.

Curable prepregs possessing enhanced ability for the removal of gases from within prepregs and between prepreg plies in a prepreg layup prior to and/or during consolidation and curing. Each curable prepreg is a resin-impregnated, woven fabric that has been subjected to a treatment to create an array of openings in at least one major surface. Furthermore, the location of the openings is specific to the weave pattern of the fabric.