Method for joining a profiled first structural component to a second structural component
View Patent ↗The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement required for the joining is produced in two parts. In a first step, each precured stringer is covered in advance by a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Vacuum film strips are subsequently arranged in each case on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.
1. 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.
2. The method according to claim 1 , wherein subsequently to the adhesive bonding, the auxiliary material is removed from the filled first structural component.
3. The method according to claim 1 , wherein at least one of the profiled first structural component and the second structural component is produced from a fiber composite material.
4. The method according to claim 1 , wherein the profiled first structural component is bar-shaped.
5. The method according to claim 1 , wherein the first structural component is at least one of a T-support and an I-shaped support.
6. The method according to claim 1 , wherein the profiled first structural component is a stringer of the aircraft or spacecraft.
7. The method according to claim 1 , wherein a tear-off film is deposited between the auxiliary material and the profiled first structural component.
8. The method according to claim 1 , wherein the auxiliary material is made of rubber material.