A structure formed from composite material and method of forming a structure composite material, in which one or more metal layers are disposed on the composite material and a sealant is disposed in between structural member and metallic layer, thus reducing galvanic corrosion. This structure is intended to be used as structural element (e.g. 113, figure 1) in wing or fuselage of an aircraft; the metal being integrated into the structural member in order to dissipate electrical charges (e.g. static or lightning). The composite structural member 201 is preferably a carbon fibre reinforced polymer (CFRP) made of carbon fibre layers 203 bound in a matrix 205. The sealant layer 207 is disposed on the structural member and it may be a polyurethane (PU) clear coat varnish of less than 15 µm thickness, which is impact resistant and resiliently deformable. The metallic layer 209 may be a thermally applied film of aluminium (or copper, silver, zinc, nickel) of less than 15 µm thickness; the metal layer may not cover the edges of the panel, e.g. a strip 211 of 10 mm width may be left without metal coverage. A paint coat 213 may be applied on sealant and metal layer.
A structure formed from composite material
2017-06-21
Patent
Electronic Resource
English
IPC: | B32B LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM , Schichtkörper, d.h. aus Ebenen oder gewölbten Schichten, z.B. mit zell- oder wabenförmiger Form, aufgebaute Erzeugnisse / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |