FIELD: aircraft engineering.
SUBSTANCE: proposed invention in producing high-strength structures, for example, fuselage facing panels and aircraft wings. The proposed laminate comprises, at least, two metal layers, each with thickness less than 1 mm. A plastic binder layer reinforced by fibers is arranged between aforesaid metal layers. At least, one metal layer comprises butt-welded metal sheets. The welded joint features the thickness, in fact, equal to that of metal sheets made in Al, Cu, Li, Mg, Si or Ti, or alloys thereof.
EFFECT: proposed laminate features no bulges on joints or fractures on panel surface.
4 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
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RU2761841C1 |
| SYSTEM OF AIRCRAFT FUSELAGE TWO SECTIONS AND CONNECTION STRUCTURE FOR FUSELAGE SKIN CONNECTION | 2008 |
|
RU2479466C2 |
| METHOD OF WELDING | 0 |
|
SU1797505A3 |
