Stringerless Sandwich Fuselage Panels Provided are sandwich panel assemblies. Specifically, a sandwich fuselage panel (212-A) comprises an outer skin member (302) and an inner skin member (304) coupled to the outer skin member at a first edge (230-A) and a second edge (230-B), forming a cavity (220) comprising a center portion (222), a first transition portion (224-A) extending from the center portion to the first edge, and a second transition portion (224-B) extending from the center portion to the second edge. A cured foam adhesive (532) may occupy each of the first transition portion (224 A) and the second transition portion (224-B) of the cavity (220). A core structure (610), such as a honeycomb structure (400) may occupy the center portion of the cavity. Alternatively, the cured foam adhesive (532) may occupy the center portion of the cavity. The density of the cured foam adhesive (532) in the transition portions may gradually increase from the center portion to the respective edge. The cured foam adhesive (532) may comprise a polymer foam adhesive. 04i
Stringerless sandwich fuselage panels
17.12.2020
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Response of Composite Fuselage Sandwich Side Panels Subjected to Internal Pressure and Axial Tension
Online Contents | 2006
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