Patent ID: 8808493

Claim:
A method for joining cured stringers to at least one structural component of an aircraft or spacecraft, comprising: placing the cured stringers onto the at least one structural component, wherein the stringers are arranged with the stringers parallel to each other on the at least one structural component with an intermediate space being formed; arranging a flow fabric in the respective intermediate space; after the flow fabric is arranged in the respective intermediate space, depositing and pressing respective vacuum film strips between the cured stringers with the use of a vacuum sealing means in such a manner that a continuous vacuum arrangement, comprising the stringers cured in advance and the vacuum film strips, is formed, wherein a thickness of the flow fabric corresponds to a vertical distance of a supporting point of the vacuum sealing means from a surface of the structural component; and pressurized joining of the stringers to the at least one structural component by the continuous vacuum arrangement formed.