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A structural substrate for an aircraft structure and methods are presented. A multi-layer hybrid composite material comprises an outermost layer, an intermediate layer, and an innermost layer. The outermost layer comprises an electrically conductive metal matrix composite that conducts electricity t

A structural substrate for an aircraft structure and methods are presented. A multi-layer hybrid composite material comprises an outermost layer, an intermediate layer, and an innermost layer. The outermost layer comprises an electrically conductive metal matrix composite that conducts electricity to provide electric heating. The intermediate layer comprises an electrical insulator coupled to the outermost layer. The innermost layer comprises a composite coupled to the intermediate layer. The intermediate layer electrically insulates the outermost layer from the innermost layer.

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1. A structural substrate for an aircraft structure, comprising: a multi-layer hybrid composite material comprising:an outermost layer comprising an electrically conductive metal matrix composite operable to conduct electricity to provide electric heating;an intermediate layer comprising an electric

1. A structural substrate for an aircraft structure, comprising: a multi-layer hybrid composite material comprising:an outermost layer comprising an electrically conductive metal matrix composite operable to conduct electricity to provide electric heating;an intermediate layer comprising an electrical insulator coupled to the outermost layer; andan innermost layer comprising a second composite coupled to the intermediate layer, the intermediate layer operable to electrically insulate the outermost layer from the innermost layer. 2. The structural substrate of claim 1, wherein the electrically conductive metal matrix composite comprises: an aluminum alloy, a titanium alloy, a steel alloy, a magnesium alloy, or a combination thereof. 3. The structural substrate of claim 1, wherein the electrical insulator comprises a fiber comprising: fiberglass, fiberglass reinforced polymer, ceramic, boron, silicon carbide, or a combination thereof. 4. The structural substrate of claim 1, wherein the second composite comprises a carbon-fiber-reinforced polymer comprising epoxy or epoxy and toughener, and configured comprising: a fabric, a unidirectional tape, or a combination thereof. 5. The structural substrate of claim 1, wherein the structural substrate is located on a wing of an aircraft and an electrical current is applied through the electrically conductive metal matrix composite to enable deicing and preclude icing of the wing. 6. The structural substrate of claim 1, wherein the outermost layer comprises riblets operable to reduce aerodynamic drag on an outer surface. 7. The structural substrate of claim 1, wherein the electrically conductive metal matrix composite provides an electromagnetic effect protection for the aircraft. 8. The structural substrate of claim 1, wherein the electric heating comprises: resistive heating, bimetal heating, Joule heating, ohmic heating, or a combination thereof. 9. A method for forming a structural substrate comprising a multi-layer hybrid composite material, the method comprising: configuring an innermost layer comprising a first composite to form a structural component;coupling an intermediate layer comprising an electrical insulator to the innermost layer;coupling an outermost layer to the intermediate layer, the outermost layer comprising an electrically conductive metal matrix composite operable to conduct electricity to provide electric heating; andconfiguring the intermediate layer to electrically insulate the outermost layer from the innermost layer. 10. The method of claim 9, further comprising grounding the electrically conductive metal matrix composite to provide electromagnetic effect protection in the electrically conductive metal matrix composite. 11. The method of claim 9, further comprising configuring the outermost layer to comprise riblets operable to reduce fluid dynamic drag on an outer surface. 12. The method of claim 9, further comprising configuring the electrically conductive metal matrix composite to comprise: an aluminum alloy, a titanium alloy, a steel alloy, a magnesium alloy, or a combination thereof. 13. The method of claim 9, further comprising configuring the electrical insulator to comprise a fiber comprising: fiberglass, fiberglass reinforced polymer, ceramic, boron, silicon carbide, or a combination thereof. 14. The method of claim 9, further comprising configuring the first composite to comprise a carbon-fiber-reinforced polymer comprising epoxy or epoxy and toughener, and configured comprising: a fabric, a unidirectional tape, or a combination thereof. 15. The method of claim 9, further comprising configuring the electric heating to comprise: resistive heating, bimetal heating, Joule heating, ohmic heating, or a combination thereof. 16. The method of claim 9, further comprising locating the structural substrate on a wing of an aircraft and an electrical current is applied through the electrically conductive metal matrix composite to enable deicing and preclude icing of the wing. 17. A method for deicing using a structural substrate comprising a multi-layer hybrid composite material, the method comprising: providing structural functionality via an innermost layer comprising a first composite;electrically heating an outermost layer comprising an electrically conductive metal matrix composite by conducting electricity through the outermost layer; andelectrically insulating the outermost layer from the innermost layer via an intermediate layer comprising an electrical insulator. 18. The method of claim 17, further comprising: receiving an electromagnetic effect in the electrically conductive metal matrix composite; andconducting the electromagnetic effect to an electrical ground to provide electromagnetic effect protection. 19. The method of claim 17, wherein the step of electrically heating further comprises: resistive heating, bimetal heating, Joule heating, ohmic heating, or a combination thereof. 20. The method of claim 17, further comprising applying an electrical current through the electrically conductive metal matrix composite to deice a surface of an aircraft and preclude icing of the surface, wherein the structural substrate comprises the surface.