Method and system for fabricating a module
OwnerDomenico Furfari, Marco Pacchione +1inventors
InventorsDomenico Furfari, Marco Pacchione, Valentin Richter-Trummer
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Abstract
A method of fabricating a module for an airframe or fuselage structure of an aircraft or spacecraft includes positioning a first member adjacent to a second member at an assembly station; welding the first member to the second member at the assembly station to produce a module having a welded joint between the first and second members; and peening at least one of the first member, the second member, and the welded joint at the assembly station to compensate for or to correct distortion caused by the welding.
Claims18
A method of fabricating a module for an airframe or fuselage structure of an aircraft or spacecraft, comprising:
- positioning a first member adjacent to a second member at an assembly station;
- welding the first member to the second member at the assembly station to produce a module having a welded joint between the first and second members;
- and
- peening at least one of the first member, the second member, and the welded joint at the assembly station to correct or compensate for distortion caused by the welding.
A system for fabricating a module for an airframe or fuselage structure of an aircraft or spacecraft, comprising:
- a frame configured to position and hold a first member with respect to an adjacent second member;
- a welding head configured to produce a welded joint between the first member and the second member held by the frame;
- and
- a treatment head configured to correct or compensate for distortion in the module caused by welding.
A method of fabricating a module for an airframe or fuselage structure of an aircraft or spacecraft, comprising:
- positioning a first member adjacent to a second member at an assembly station;
- welding the first member to the second member at the assembly station to produce a module having a welded joint between the first and second members;
- and
- peening at least one of the first member, the second member, and the welded joint at the assembly station to correct or compensate for distortion caused by the welding, wherein the peening comprises generating residual compressive stresses in a surface region of the module, wherein the peening further comprises generating a shock wave in a region of at least one of the first member, the second member, and the welded joint.
Dependencies are inferred from the claim text.