CNT-tailored composite air-based structures
An apparatus having a composite air-based structure with a first carbon nanotube infused material and a second carbon nanotube infused material. The first and second carbon nanotube infused materials each having a range of carbon nanotube loading selected to provide different functionalities.
1. An apparatus comprising:
a structure configured to carry a load on an aircraft, the structure comprising:
a first material comprising a plurality of carbon nanotubes (CNTs) that are bonded to substrate fibers thereby forming CNT-infused fibers that are distributed within a matrix material thereby imparting a first functionality to the structure, the first functionality selected from tensile strength, compressive strength, shear strength, and flexural strength; and
a second material, different from the first material, the second material comprising CNT-infused fibers imparting a second functionality to the structure, the second functionality selected from damage sensing, de-icing, crack resistance, electromagnetic interference shielding, lightning strike protection, and radar absorption.
2. The apparatus of claim 1 , wherein the CNT-infused fibers comprise CNTs grown on the fibers.
3. The apparatus of claim 1 , wherein a CNT loading of the second material is between 0% and 2%.
4. The apparatus of claim 3 , wherein the second functionality is damage sensing.
5. The apparatus of claim 1 , wherein a CNT loading of the second material is between 2% and 5%.
6. The apparatus of claim 5 , wherein the second functionality is de-icing.
7. The apparatus of claim 5 , wherein the second functionality is crack resistance.
8. The apparatus of claim 1 , wherein a CNT loading of the first material is between 5% and 40%.
9. The apparatus of claim 8 , wherein the second functionality is electromagnetic interference shielding.
10. The apparatus of claim 8 , wherein the second functionality is lightning strike protection.
11. The apparatus of claim 1 , wherein a CNT loading of the second material is a gradient.
12. The apparatus of claim 11 , wherein the second functionality is radar absorption.
13. The apparatus of claim 1 , wherein the structure is a fuselage.
14. The apparatus of claim 13 , wherein the fuselage comprises:
one or more panels comprising the first material wherein the first functionality comprises tensile strength;
an outer layer over the one or more panels and comprising the second material wherein the second functionality comprises electromagnetic interference shielding and lightning strike protection;
a skin over the outer layer and comprising a third material comprising CNT-infused fibers with a CNT loading between 0 % and 2 %, imparting a functionality of damage sensing; and
a middle layer disposed between the skin and the one or more panels and comprising a fourth material comprising CNT-infused fibers with a CNT loading, imparting a functionality of de-icing.
15. The apparatus of claim 1 , wherein the structure is a nose cone.
16. The apparatus of claim 1 , wherein the structure is an aircraft wing.
17. The apparatus of claim 1 , wherein the structure is a propeller.
18. The apparatus of claim 1 , wherein the structure is a helicopter rotor blade.
19. The apparatus of claim 1 , wherein the structure is a portion of an aircraft engine.
20. The apparatus of claim 1 , wherein the structure is a portion of a weather balloon instrument.
21. A method comprising:
providing a load-carrying structure for use with an aircraft, the structure comprising:
a first material comprising a plurality of carbon nanotubes (CNTs) that are bonded to substrate fibers thereby forming CNT-infused fibers that are distributed within a matrix material thereby imparting a first functionality to the structure, the first functionality selected from tensile strength, compressive strength, shear strength, and flexural strength; and
a second material different from the first material, the second material comprising CNT-infused fibers imparting a second functionality to the structure, the second functionality selected from damage sensing, de-icing, crack resistance, electromagnetic interference shielding, lightning strike protection, and radar absorption.
22. The method of claim 21 , wherein the first material and the second material overlap.
23. The method of claim 21 , further comprising:
determining the first functionality; and
selecting a CNT loading of the first material based on the first functionality.
24. The method of claim 21 , further comprising:
determining the second functionality; and
selecting a CNT loading of the second material based on the second functionality.