A method for joining two components of a meltable material comprises the steps of providing a first component having a first border region and a second component having a second border region, placing the second component relative to the first component so as to form an overlap between the first border region and the second border region under a gap between the first border region and the second border region, continuously heating opposed sections of the first border region and the second border region at the same time through at least one energy source arranged in the gap at least partially, continuously providing a relative motion of the at least one energy source along the first border region and the second border region in the gap, and continuously pressing already heated sections of the first border region and the second border region onto each other.

A method apparatus, and system method for manufacturing a composite part. A set of composite preforms is placed on a set of slip sheets. The set of slip sheets with the set of composite preforms is attached to a cure mandrel to form a composite preform assembly.

An assembly is provided for induction welding. This assembly utilizes a heat shield (e.g., a mica heat shield) with a recess. An induction welding coil may be disposed within this heat shield recess during induction welding operations. The wall thickness of the heat shield within the recess may be reduced to enhance heat transfer to a workpiece during induction welding operations. Members may engage the heat shield on opposite sides of the recess (and that have an increased wall thickness) to support both the heat shield and the workpiece during induction welding operations, during which a biasing force may be exerted on both the heat shield and workpiece.

A system and method for welding thermoplastic components is provided. The system includes a component positioning system and a welding subsystem. The component positioning system includes a trailing force applicator having first and second lateral side trailing force applicators disposed on opposite lateral sides of a weld line. The welding subsystem is configured to weld the thermoplastic components together at a weld zone. The first and second lateral side trailing force applicators are laterally spaced apart from the weld zone, and at least a portion of the first and second lateral side trailing force applicators are disposed aft of the weld zone. During welding the first and second lateral side trailing force applicators and a welding subsystem probe are moved relative to the thermoplastic components, or vice versa.

Methods and apparatus' for induction welding a first workpiece to a second workpiece at a welding region may include a metallic strip. The metallic strip may be a mesh. The properties of the metallic strip, such as, for example, pore size, thickness, and density, may be configured to conduct heat uniformly across the welding region and prevent eddy current formation across a workpiece. The metallic strip may be embedded in a workpiece or may be fixed to an induction welding tool that acts on the welding region during induction welding. A removable polymer tape may be disposed between a workpiece and a metallic strip fixed to an induction welding tool. The workpieces may be thermoplastic composite structures and thermoplastic composite stiffeners in aircraft structures.

Systems and methods for induction welding a stiffener to a thermoplastic composite structure using a removeable metal mask to reduce excess heat along the edges of the stiffener generated from an electromagnetic field of an induction welding tool.

A method for treating a surface of a fibre composite component, wherein an abrasive removal of the surface of the fibre composite component takes place by blasting a removing agent transported by a gaseous transporting fluid onto the surface of the fibre composite component by a feed nozzle and a suction extraction of the removing agent and material removed by the removing agent takes place by an extraction nozzle arranged in the region of the feed nozzle.

A system for manufacturing modular aircraft includes at least a common tooling component, wherein the at least a common tooling component is configured to manufacture at least a flight component. The system includes at least a modular tooling component, wherein the at least modular tooling component wherein the at least a modular tooling component is configured to manufacture at least a fuselage component and a collar component. The system includes at least a tooling interface component, wherein the at least a tooling interface component is configured to mechanically connect the at least a common tooling component at a first end to the at least a modular tooling component at a second end.

A forming module for forming a composite laminate part over a tool is provided. The forming module comprises a base, a ply carrier control assembly adapted for controlling the position of a flexible ply carrier on which composite resin plies are mounted, and a head section mounted on the base and adapted for automatically forming the composite resin plies from the ply carrier onto the tool.

An assembly is provided for induction welding. This induction welding assembly includes a fixture. The fixture includes a first support structure and a second support structure. The second support structure includes a frame and a plurality of trunks. Each of the trunks is connected to and repositionable on the frame. The fixture is configured to secure a workpiece vertically between the first support structure and the second support structure using the trunks during induction welding of the workpiece.