A method and an apparatus for producing a three-dimensional decoration piece that does not damage the tacky bonding or adhesion strength of the lower layer material of the decoration piece. The method includes putting an upper layer material on a first table operating as cathode; lowering an upper mold operating as anode onto the first table, emitting a high frequency wave for dielectric heating; stopping the high frequency dielectric heating; moving a second table carrying a lower layer material having a tacky bonding property to below the upper mold; and lowering said upper mold onto the second table. In the apparatus, the second table or the lower mold is provided on the top surface thereof with recessed sections that are transversally and inwardly separated from a position where an edge of the first machining means contacts, by 0.2 mm to 1 mm; and a cushion member being arranged in the respective recessed sections.

A method and an apparatus for producing a three-dimensional decoration piece that does not damage the tacky bonding or adhesion strength of the lower layer material of the decoration piece. The method includes putting an upper layer material on a first table operating as cathode; lowering an upper mold operating as anode onto the first table, emitting a high frequency wave for dielectric heating; stopping the high frequency dielectric heating; moving a second table carrying a lower layer material having a tacky bonding property to below the upper mold; and lowering said upper mold onto the second table. In the apparatus, the second table or the lower mold is provided on the top surface thereof with recessed sections that are transversally and inwardly separated from a position where an edge of the first machining means contacts, by 0.2 mm to 1 mm; and a cushion member being arranged in the respective recessed sections.

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.

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 inflatable stacked tube assembly may comprise a first panel and a second panel. The first panel may form a first portion of a top tube and a first portion of a bottom tube. The second panel may form a second portion of the top tube and a second portion of the bottom tube. A first seam tape may be bonded to a first top tube interior surface portion of the first panel and a second top tube interior surface portion of the second panel. The first seam tape may be located along a first fold formed by the first panel and along a second fold formed by the second panel.

An inflatable stacked tube assembly may comprise a first panel and a second panel. The first panel may form a first portion of a top tube and a first portion of a bottom tube. The second panel may form a second portion of the top tube and a second portion of the bottom tube. A first seam tape may be bonded to a first top tube interior surface portion of the first panel and a second top tube interior surface portion of the second panel. The first seam tape may be located along a first fold formed by the first panel and along a second fold formed by the second panel.

A dielectric welding film capable of providing excellent adhesiveness to a variety of adherends in a short period of dielectric heating, and an welding method using the dielectric welding film are provided. The dielectric welding film is configured to adhere a pair of adherends of the same material or different materials through dielectric heating, the dielectric welding film including a first thermoplastic resin as an A1 component having a predetermined solubility parameter, a second thermoplastic resin as an A2 component having a solubility parameter larger than the solubility parameter of the first thermoplastic resin, and a dielectric filler as a B component. The welding method uses the dielectric welding film.

A dielectric welding film capable of providing excellent adhesiveness to a variety of adherends in a short period of dielectric heating, and an welding method using the dielectric welding film are provided. The dielectric welding film is configured to adhere a pair of adherends of the same material or different materials through dielectric heating, the dielectric welding film including a first thermoplastic resin as an A1 component having a predetermined solubility parameter, a second thermoplastic resin as an A2 component having a solubility parameter larger than the solubility parameter of the first thermoplastic resin, and a dielectric filler as a B component. The welding method uses the dielectric welding film.

Applied power as a function of time is ramped up at the onset of an RF welding process in a manner that is predetermined to match source and load impedance as reflected by maximized forward power during at least the majority of the welding process. The ramp-up portion takes the form of a non-linear curve, such as an S-shaped curve, as opposed to one or more discrete steps. The applied power may then be maintained at or near that maximum required value at least a majority of the remainder of the heating portion of the welding process. The shape of the non-linear ramp-up portion of the applied power curve may be predetermined using, for example, virtual motor control using applied power as a virtual axis.

Applied power as a function of time is ramped up at the onset of an RF welding process in a manner that is predetermined to match source and load impedance as reflected by maximized forward power during at least the majority of the welding process. The ramp-up portion takes the form of a non-linear curve, such as an S-shaped curve, as opposed to one or more discrete steps. The applied power may then be maintained at or near that maximum required value at least a majority of the remainder of the heating portion of the welding process. The shape of the non-linear ramp-up portion of the applied power curve may be predetermined using, for example, virtual motor control using applied power as a virtual axis.