A method bilayer composite thin-film beam structure is described. The structure incorporates a bulk phase change material as small inclusions in one layer of a bimorph. The structure, also referred to as a phase change composite bimorph or PCBM, curls abruptly, and reversibly, at a phase transition temperature. Large curling and effective expansion coefficients are demonstrated. The PCBMs may be employed in various self-assembly mechanisms and actuators.

A method for manufacturing a structure by curing together a base laminate and structural components placed thereon. Particularly, the uncured structural component has a peripheral tapered foot edge so that the vacuum bag placed thereon follows all the uncured plies without an abrupt leap from the structural component foot to the base laminate.

In order to optimize a method for stiffening a metal component by pressing a fiber-reinforced plastic insert onto the metal component in such a way that the method can be integrated into the serial production of the car body, it is proposed that the fiber-reinforced plastic insert be picked up by means of a robot-controlled application head and pressed onto the metal component.

In order to optimize a method for stiffening a metal component by pressing a fiber-reinforced plastic insert onto the metal component in such a way that the method can be integrated into the serial production of the car body, it is proposed that the fiber-reinforced plastic insert be picked up by means of a robot-controlled application head and pressed onto the metal component.

A continuous reinforcement is disclosed for use in additive manufacturing. The continuous reinforcement may include a plurality of continuous primary fibers oriented in a general axial direction of the continuous reinforcement. The continuous reinforcement may also include a plurality of secondary fibers interspersed with the plurality of continuous primary fibers and oriented generally orthogonal to the plurality of continuous primary fibers.

The present disclosure is directed to a method for applying a multi-colored coating to a composite structure comprising applying a first co-curable film layer comprising a first color marking to a composite tool, applying a second co-curable film layer comprising a second color marking over the composite tool and at least partially over the first co-curable film layer to create a lay-up of a multi-colored marking, applying a composite structure over the lay-up of the multi-colored marking, and curing the lay-up of the multi-colored marking and the composite structure in a single curing step to create a cured multi-colored coating on the composite structure. A multi-colored coating for marking a composite structure and an aircraft part having a multi-colored marking are also provided.

A partially molded substrate and a partial molding apparatus and a method thereof, which cover and mold each of one or more conductors formed on the substrate with the insulator to prevent the sizes of the substrate from being increased due to molding, thereby efficiently preventing high voltage between the conductors on the substrate from being applied, and thereby preventing interference around the conductor.

Methods and apparatus for automating the fiber laying process during the repair of composite structures made of fiber-reinforced plastic material based on the three-dimensional printing technique. Continuous fiber rovings (e.g., carbon fibers) impregnated with liquid epoxy can be directly printed onto the damaged surface of the composite structure (e.g., an aircraft component made of carbon fiber-reinforced plastic) without human manipulation in an autonomous manner.

A friction damped insert for highly stressed engineering components is disclosed. The disclosed inventive concept provides a method and system for increasing the damping capacity of an engineering system by adding a non-flat solid, highly damped insert to a system component that contributes most to the system's dynamic response. The insert can either be embedded into a system component during casting or be fastened to the system component outer surface. The insert is made of the single layer of flexible material by forming it into a rigid elongated body. The layer of material can be turned over on itself without folding to create a cylinder or can be folded over a number of times to create a prismatic bar. The layer of material may be shaped into a corrugated panel. The layer of flexible material may have a number of relatively small openings or perforations with a uniform spatial distribution.

A friction damped insert for highly stressed engineering components is disclosed. The disclosed inventive concept provides a method and system for increasing the damping capacity of an engineering system by adding a non-flat solid, highly damped insert to a system component that contributes most to the system's dynamic response. The insert can either be embedded into a system component during casting or be fastened to the system component outer surface. The insert is made of the single layer of flexible material by forming it into a rigid elongated body. The layer of material can be turned over on itself without folding to create a cylinder or can be folded over a number of times to create a prismatic bar. The layer of material may be shaped into a corrugated panel. The layer of flexible material may have a number of relatively small openings or perforations with a uniform spatial distribution.