Thermally laminated foam boards, methods for making thermally laminated foam boards, apparatus for making thermally laminated foam boards, smaller foam pieces made from thermally laminated foam boards, methods for making smaller foam pieces from thermally laminated foam boards, parts made from thermally laminated foam boards, methods for making parts from thermally laminated foam boards, and tools for making parts from thermally laminated foam boards are disclosed. The thermally laminated foam boards are made by thermally bonding at least two polystyrene boards together.

A method for integrating a backing-structure assembly in a structure of an aircraft or spacecraft is described. In this case, a plurality of individual elements is joined to form the backing-structure assembly. The individual elements for the backing-structure assembly and a skin portion for the structure are provided. The elements are arranged on a pre-assembly device which comprises retaining devices, which are each configured to hold one of the elements so as to be adjustable with respect to the position and/or location thereof. Some or all of the elements are connected to the skin portion. In the method, by adjusting the retaining devices for tolerance compensation, gaps between joint regions of the elements and the skin portion are eliminated or adjusted.

An apparatus for handling and locally fixing flat thermoplastic materials includes at least one holding device to be applied with a holding region for exerting a holding force against a surface of the flat thermoplastic material. Arranged within or surrounded by the holding region of the at least one holding device is at least one heating element by which the flat thermoplastic material can be locally thermally fixed to a join partner within or surrounded by the holding region of the at least one holding device.

A joining system includes a holding fixture assembly configured to hold a fuselage skin. The stringers are temporarily attached to the fuselage skin. The joining system includes an upper beam assembly including an upper beam and a lower beam assembly. The lower beam assembly includes a lower beam and at least one lower heating element. The holding fixture assembly is coupled to the upper beam assembly. The holding fixture assembly is coupled to the lower beam assembly. The upper beam is movable relative to the lower beam to clamp the at least one of the plurality of stringers and the fuselage skin together prior to and during welding.

A method and apparatus for mechanically deforming a substrate assembly. The substrate assembly may advance toward a bonder apparatus. The bonder apparatus may rotate about an axis of rotation. The bonder apparatus may include a plurality of manifolds positioned about the axis of rotation. The substrate assembly may be advanced onto the bonder apparatus such that the substrate assembly is disposed on the plurality of manifolds. Fluid may be passed to the manifolds onto which the leading edge portion and the trailing edge portion of the substrate assembly are disposed. The manifolds may heat the fluid and the heated fluid may be released onto the trailing edge portion and the leading edge portion of the substrate assembly. The heated portion of the substrate assembly may then be bonded forming a seam.

A method and apparatus for mechanically deforming a substrate assembly. The substrate assembly may advance toward a bonder apparatus. The bonder apparatus may rotate about an axis of rotation. The bonder apparatus may include a plurality of manifolds positioned about the axis of rotation. The substrate assembly may be advanced onto the bonder apparatus such that the substrate assembly is disposed on the plurality of manifolds. Fluid may be passed to the manifolds onto which the leading edge portion and the trailing edge portion of the substrate assembly are disposed. The manifolds may heat the fluid and the heated fluid may be released onto the trailing edge portion and the leading edge portion of the substrate assembly. The heated portion of the substrate assembly may then be bonded forming a seam.

A joining method is provided during which a first thermoplastic component joint section and a second thermoplastic component joint section are arranged between first tooling and second tooling. The second thermoplastic component joint section is abutted against the first thermoplastic component joint section at a joint area. The first thermoplastic component joint section is joined to the second thermoplastic component joint section to provide a unitized thermoplastic structure. The joining includes: pressing the first thermoplastic component joint section against the second thermoplastic component joint section at the joint area between the first tooling and the second tooling using a pressure device; and heating the first thermoplastic component joint section and the second thermoplastic component joint section at the joint area using a first heater configured with the first tooling. The unitized thermoplastic structure is cooled at the joint area using a first cooler configured with the first tooling.

Apparatus and methods for impinging a heated fluid onto the surface of a substrate and then locally removing the impinged fluid. The apparatus and methods may be used to heat a surface of a substrate e.g. so that the substrate can be melt-bonded to another substrate.

A membrane cartridge including: a filtration membrane (2); and a support plate (3). The support plate (3) includes a reference surface, a first joint portion (32) protruding from the reference surface, and a second joint portion (33) retreated from the reference surface, the second joint portion (33) is provided closer to an outer edge (35) of the support plate (3) than the first joint portion (32) is, at least a portion of an outer edge portion (21) of the filtration membrane (2) is joined to the support plate (3) at the second joint portion (33), and a portion of the filtration membrane (2) inward of the outer edge portion (21) is joined to the support plate (3) at the first joint portion (32).

A joining system includes a holding fixture assembly configured to hold a fuselage skin. The stringers are temporarily attached to the fuselage skin. The joining system includes an upper beam assembly including an upper beam and a lower beam assembly. The lower beam assembly includes a lower beam and at least one lower heating element. The holding fixture assembly is coupled to the upper beam assembly. The holding fixture assembly is coupled to the lower beam assembly. The upper beam is movable relative to the lower beam to clamp the at least one of the plurality of stringers and the fuselage skin together prior to and during welding.