IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0953425
(2010-11-23)
|
등록번호 |
US-8662449
(2014-03-04)
|
발명자
/ 주소 |
- Shah, Tushar K.
- Alberding, Mark R.
- Malecki, Harry C.
- Markkula, Samuel J.
- Hughes, John Anthony
- Kline, Shawn C.
|
출원인 / 주소 |
- Applied NanoStructured Solutions, LLC
|
대리인 / 주소 |
McDermott Will & Emery LLP
|
인용정보 |
피인용 횟수 :
6 인용 특허 :
164 |
초록
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.
대표청구항
▼
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
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; anda 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; anda 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; anda 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; andselecting a CNT loading of the first material based on the first functionality. 24. The method of claim 21, further comprising: determining the second functionality; andselecting a CNT loading of the second material based on the second functionality.
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