Relates to a circumferential lap joint of fuselage sections. Specifically, systems and methods for splicing rack assemblies are provided. One embodiment is a method for assembling a frame of an aircraft. The method comprises the steps of: forming a first skin of a first circumferential section of the fuselage, the first skin comprising a distal portion, the distal portion comprising a lip and a shoulder; aligning a second skin of a second circumferential section of the fuselage with the shoulder such that the lip overlaps the second skin; and fixing the first skin and the second skin together through a circumferential joint.
涉及机身段的周向互搭接头。具体地,提供了用于拼接机架组件的系统和方法。一个实施方式是一种用于组装飞行器的机架的方法。该方法包括以下步骤:形成机身的第一周向段的第一蒙皮,该第一蒙皮包括远端部分,该远端部分包括唇部和肩部;对准机身的第二周向段的第二蒙皮与肩部,使得该唇部与第二蒙皮重叠;以及经由周向接头将所述第一蒙皮和所述第二蒙皮固定在一起。
Circumferential lap joint of fuselage section
机身段的周向互搭接头
2022-06-21
Patent
Electronic Resource
Chinese
On damage tolerance design of fuselage structure. Circumferential cracks
Tema Archive | 1987
|On damage tolerance design of fuselage structure - circumferential cracks
Tema Archive | 1987
|