A resin-rich peel ply that does not leave behind residual fibers after peeling and can work well with different resin-based composite substrates. The resin-rich peel ply is composed of a woven fabric impregnated with a resin matrix different from the resin matrix of the composite substrate. The peel ply is designed such that, upon manual removal of the peel ply from the composite substrate's surface, a thin film of the peel ply resin remains on the composite substrate's surface to create a bondable surface capable of bonding with another composite substrate, but no fibrous material from the woven fabric remains on the same surface.

A resin-rich peel ply that does not leave behind residual fibers after peeling and can work well with different resin-based composite substrates. The resin-rich peel ply is composed of a woven fabric impregnated with a resin matrix different from the resin matrix of the composite substrate. The peel ply is designed such that, upon manual removal of the peel ply from the composite substrate's surface, a thin film of the peel ply resin remains on the composite substrate's surface to create a bondable surface capable of bonding with another composite substrate, but no fibrous material from the woven fabric remains on the same surface.

This invention relates to the production of cured polymeric skin materials. In particular, the invention relates to methods and substrates for the production of skin materials, for example, for use in building, furniture, and as architectural components for example in roofing materials such as roofing tiles, or for brick wall effect materials.

There is provided a fishing rod preventing or suppressing deviation or inclination of a fitting on a surface of a rod body. The fishing rod includes an elongated cylindrical rod body, a fitting having a mounting portion and mounted to an outer peripheral surface of the rod body via the mounting portion, a first layer formed by winding a first sheet so as to enclose the mounting portion and the rod body, the first sheet being made of a fiber-reinforced resin or a resin having a thermal shrinkage rate of 2.5% or lower, and a second layer formed by winding a second sheet made of a fiber-reinforced resin on an outer side of the first sheet, wherein a temperature at which a loss tangent of the first sheet has a maximum value is different from a temperature at which a loss tangent of the second sheet has a maximum value.

A joining method for joining together a first member in which fiber material is mixed into a first resin, and a second member that includes at least a second resin, includes abutting the first member and the second member together, and softening or melting the first resin of the first member and the second resin of the second member that are adjacent to abutting surfaces of the first member and the second member; and stirring a joint forming portion formed by the softened or melted first resin of the first member and the softened or melted second resin of the second member, and the fiber material included in the softened or melted first resin of the first member, in a direction inclined with respect to the abutting surfaces, and hardening the joint forming portion.

A joining method for joining together a first member in which fiber material is mixed into a first resin, and a second member that includes at least a second resin, includes abutting the first member and the second member together, and softening or melting the first resin of the first member and the second resin of the second member that are adjacent to abutting surfaces of the first member and the second member; and stirring a joint forming portion formed by the softened or melted first resin of the first member and the softened or melted second resin of the second member, and the fiber material included in the softened or melted first resin of the first member, in a direction inclined with respect to the abutting surfaces, and hardening the joint forming portion.

Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

A hollow fiber membrane is formed by embedding a braid having a spiral open weave of monofilaments only, to avoid a whiskering problem. The open weave is characterized by contiguous, circumferential, rhomboid-shaped areas of polymer film separated by monofilament. When the braid is supported on a plasticized PVA cable having a scalloped periphery, the braid can be infiltrated with membrane polymer which, when coagulated, embeds the braid positioning it around the lumen. The embedded spiral weave, free of any circumferentially constricting monofilament, allows the membrane to be biaxially distensible. The membrane has give not only in the axial or longitudinal direction but also in the radial direction. Give in the radial direction permits soiled membranes to be backwashed under higher pressure than in a comparable braid which is not radially distensible.

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.

Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.