An aircraft structure (10) and its method of construction avoids the inefficiencies involved in current methods of constructing the aircraft structure, reduces the manufacturing time required for constructing the aircraft structure and reduces the cost involved in constructing the aircraft structure. The aircraft structure and its method of construction is comprised of a geodesic or multi-grid framework of intersecting thermoplastic composite strips (22) that are joined to an interior surface of a thermoplastic composite fuselage skin panel (18) through overmolding/co-consolidation of the grid framework and the skin panel.
THERMOPLASTIC MULTI-GRID OVERMOLDED/CO-CONSOLIDATED AIRCRAFT FUSELAGE STRUCTURE
THERMOPLASTISCHE MEHRGITTERIGE UMSPRITZTE/CO-KONSOLIDIERTE FLUGZEUGRUMPFSTRUKTUR
STRUCTURE DE FUSELAGE D'AÉRONEF THERMOPLASTIQUE SURMOULÉE/CO-CONSOLIDÉE À GRILLAGES MULTIPLES
2022-01-19
Patent
Electronic Resource
English
Thermoplastic multi-grid overmolded/co-consolidated aircraft fuselage structure
European Patent Office | 2022
|THERMOPLASTIC MULTI-GRID OVERMOLDED/CO-CONSOLIDATED AIRCRAFT FUSELAGE STRUCTURE
European Patent Office | 2020
|THERMOPLASTIC MULTI-GRID OVERMOLDED/CO-CONSOLIDATED AIRCRAFT FUSELAGE STRUCTURE
European Patent Office | 2020
|THERMOPLASTIC MULTI-GRID OVERMOLDED/CO-CONSOLIDATED AIRCRAFT FUSELAGE STRUCTURE
European Patent Office | 2023
|Thermoplastic multi-grid overmolded aircraft fuselage structure
European Patent Office | 2020
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