Metallic layer material, reinforced with basalt fibers, as well as products made thereof
View Patent ↗A metallic layer material includes at least two metal sheets. Each sheet has a thickness of less than 1.5 mm. Between the sheets, a plastic layer is disposed, which is bonded to the metal sheets. The plastic layer comprises a plastic material and basalt fibers, and the basalt fibers have a modulus of elasticity exceeding 50 GPa. The basalt fibers may constitute 35-75% of the volume of the plastic layer. and may be comprised of 35-55 weight % of SiO 2 , 10-25 weight % of Al 2 O 3 , and 3-10 weight % of MgO. In aerospace applications and other applications requiring good specific strength, stiffness and damage tolerance, the metal sheets may be made of a metal having a tensile strength exceeding 0.20 GPa.
1. A laminate, comprising:
at least two metal sheets, each having a thickness of less than 1.5 mm;
a plastic layer disposed between the at least two metal sheets;
wherein the plastic layer is bonded to the at least two metal sheets;
wherein the plastic layer comprises a plastic material and basalt fibers;
wherein the basalt fibers constitute 35-75% of a combined volume of the plastic material of the plastic layer and the basalt fibers together;
wherein the basalt fibers have a modulus of elasticity of 90-120 GPa;
wherein the basalt fibers include 35-55 weight % of SiO2;
wherein the basalt fibers include 10-25 weight % of Al2O3;
wherein the basalt fibers include 3-10 weight % MgO ; and
wherein the at least two metal sheets include a material with a tensile strength exceeding 0.20 GPa.
2. The laminate of claim 1 , wherein
the basalt fibers are substantially aligned parallel to each other in at least one direction or interwoven in the form of woven fabric.
3. The laminate of claim 1 , wherein
the laminate includes the basalt fibers having an elongation at rupture in a range from 2-5%.
4. The laminate of claim 1 , wherein
the at least two metal sheets comprise a number of metal sheets ranging from 2 to 20.
5. The laminate of claim 1 , wherein
the plastic layer has a layer thickness and the layer thickness of the plastic layer is less than the thickness of each of the at least two metal sheets between which the plastic layer is disposed.
6. The laminate of claim 1 , wherein:
the plastic material is of a duroplastic material.
7. The laminate of claim 1 , wherein
the plastic material is a thermoplastic material.
8. The laminate of claim 1 , wherein
the at least two metal sheets are comprised of a metal selected from the group of metals consisting of aluminum alloy, aluminum-copper alloy, aluminum-copper alloy of the type M(USA) Nr. 2024, aluminum-zinc alloy, aluminum-zinc alloy of the type M(USA) Nr. 7075, aluminum-lithium alloy, aluminum-lithium alloy with a lithium content of 0.5 to 3%, steel, titanium alloy, copper, copper alloy, magnesium alloy and combinations thereof.
9. The laminate of claim 1 , wherein
the basalt fibers include 47-50 weight % of SiO2;
the basalt fibers include 15-18 weight % of Al2O3; and
the basalt fibers include 5-7 weight % of MgO.
10. Structural element for an aircraft, comprising:
at least two metal sheets, each having a thickness of less than 1.5 mm;
a plastic layer disposed between the at least two metal sheets;
wherein the plastic layer is bonded to the at least two metal sheets;
wherein the plastic layer comprises a plastic material and basalt fibers,
wherein the basalt fibers constitute 35-75% of a combined volume of the plastic material of the plastic layer and the basalt fibers together;
wherein the basalt fibers have a modulus of elasticity of 90-120 GPa;
wherein the basalt fibers include 35-55 weight % of SiO2;
wherein the basalt fibers include 10-25 weight % of Al2O3;
wherein the basalt fibers include 3-10 weight % MgO; and
wherein the at least two metal sheets include a material with a tensile strength exceeding 0.20 GPa.
11. The structural element of claim 10 , wherein the structural element is a skin panel for a fuselage of the aircraft or a skin panel of an aircraft wing.
12. The structural element of claim 10 , wherein the structural element is a stiffening element in a structural component of the aircraft.
13. The structural element of claim 12 , wherein the stiffening element is a stringer or a frame.
14. The structural element of claim 10 , wherein at least a portion of the fibers are continuous filaments.
15. The structural element of claim 14 , wherein the continuous filaments are substantially aligned parallel, such that the continuous filaments do not overlap each other.
16. The structural element of claim 14 , wherein the continuous filaments are interwoven.
17. The structural element of claim 10 , wherein the fibers are substantially aligned parallel.
18. The structural element of claim 10 , wherein the fibers are interwoven.