Spliced laminate for aircraft fuselage

US5429326A · kind A · utility

Assignee

• Structural Laminates Company · US

Inventors

• Carl E. Garesche · New Kensington, US
• Gerandus H. J. J. Roebroeks · Den Bommel, NL
• Buwe V. W. Greidanus · Delft, NL
• Rob C. V. Oost · Heerjansdam, NL
• Jan Willem Gunnink · Nieuwerkerk aan den IJssel, NL

Key dates

• Filing date: Jul 9, 1992
• Grant date: Jul 4, 1995
• Expiry date: Jul 9, 2012

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y10T428/24752
• WIPO field: Surface technology, coating
• WIPO sector: Chemistry

Abstract

A laminated body panel for aircraft applications comprises first and second metal layers and an adhesive layer. First and second sections in each metal layer are generally coplanar and separated by a splice line. A first splice line in a first metal layer is generally parallel to a second splice line in a second metal layer, and spaced laterally from the second splice line. An adhesive layer between the metal layers preferably contains reinforcing fibers bridging across the splice lines. An aircraft fuselage or wing or empennage made with spliced body panels of the invention has fewer joints and weighs less than one made with narrower body panels containing unspliced metal layers.