Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.
CIRCUMFERENTIAL LAP SPLICES FOR SECTIONS OF FUSELAGE
23.06.2022
Patent
Elektronische Ressource
Englisch
Analytical methodology for predicting fatigue life distribution of fuselage splices
Tema Archiv | 2001
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