Patent ID: 8574391

Claim:
A method for joining a profiled first structural component to a second structural component of an aircraft or spacecraft, comprising the following method steps: (a) providing the profiled first structural component, which comprises at least one fillable region; (b) depositing an auxiliary material on the at least one fillable region in order to form the profiled first structural component into a filled first structural component having a rectangular cross section, the auxiliary material being of a material different from a fiber composite material, wherein the auxiliary material is provided in the form of adhesive strips; (c) arranging the at least one filled first structural component on the second structural component, wherein the second structural component is supplied as an unimpregnated semifinished fiber product; (d) depositing a vacuum film over the filled first structural component and at least partially over the second structural component for the pressurized pressing of the filled first structural component onto the second structural component by environmental pressure by application of a vacuum; (e) softening the first structural component under action of heat; and (f) adhesive bonding of the softened first and the second structural element by inserting a resin matrix into the second structural component by an injection or infusion method.