Tunable acoustic absorption system for an aircraft cabin
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/40
B64C-001/00
출원번호
US-0017241
(2004-12-20)
등록번호
US-7410126
(2008-08-12)
발명자
/ 주소
Drost,Stuart K.
출원인 / 주소
Sikorsky Aircraft Corporation
대리인 / 주소
Carlson, Gaskey & Olds
인용정보
피인용 횟수 :
3인용 특허 :
26
초록▼
A tunable acoustic absorption system according to the present invention includes an airframe batting area; a primary soundproofing blanket area; an interior trim panel area; and a hard trim area, which are layered over an aircraft outer skin. Specifically tailoring or "tuning" materials within each
A tunable acoustic absorption system according to the present invention includes an airframe batting area; a primary soundproofing blanket area; an interior trim panel area; and a hard trim area, which are layered over an aircraft outer skin. Specifically tailoring or "tuning" materials within each area to the particular aircraft acoustic signature achieves significant increases in acoustic absorption achieved over conventional generic sound treatments.
대표청구항▼
What is claimed is: 1. An acoustic absorption system for an aircraft cabin comprising: an airframe batting mounted adjacent an airframe frame member; a primary soundproofing blanket mounted to said airframe frame member and at least partially over said airframe batting; and an interior trim panel m
What is claimed is: 1. An acoustic absorption system for an aircraft cabin comprising: an airframe batting mounted adjacent an airframe frame member; a primary soundproofing blanket mounted to said airframe frame member and at least partially over said airframe batting; and an interior trim panel mounted to said airframe frame member and at least partially over said primary soundproofing blanket. 2. The system as recited in claim 1, wherein said interior trim panel is mounted to an interior skeleton member, said interior skeleton member mounted to said airframe frame member. 3. The system as recited in claim 1, wherein said airframe batting includes a foam portion and a mass barrier layer bonded over said foam portion. 4. The system as recited in claim 1, wherein said primary soundproofing blanket includes material layers tuned in thickness and density of the layers to the specific acoustic output generated by the aircraft. 5. The system as recited in claim 1, wherein said interior trim panel includes a mass barrier layer mounted to a composite core to at least partially surround a decoupler layer. 6. The system as recited in claim 5, wherein said mass barrier layer is tuned in mass to a specific acoustic output generated by the aircraft. 7. The system as recited in claim 5, wherein said decoupler layer is tuned in thickness to a specific acoustic output generated by the aircraft. 8. The system as recited in claim 5, wherein a material of said composite core is selected to a specific acoustic output generated by the aircraft. 9. A method of acoustic absorption within an aircraft cabin comprising the step of: (1) tuning a multiple of acoustic absorption systems to a specific acoustic output generated by the aircraft, the multiple of acoustic absorption systems including an airframe batting, a primary soundproofing blanket at least partially over the airframe batting, and an interior trim panel at least partially over the primary soundproofing blanket. 10. A method as recited in claim 9, wherein said step (1) further comprises arranging the multiple of acoustic absorption system systems in a layered arrangement relative to an aircraft outer skin. 11. A method as recited in claim 9, wherein said step (1) further comprises tuning a material layer of a primary soundproofing blanket in thickness and density of the layers to the specific acoustic output generated by the aircraft. 12. A method as recited in claim 9, wherein said step (1) further comprises tuning a mass barrier layer of an interior trim panel in mass to a specific acoustic output generated by the aircraft. 13. A method as recited in claim 9, wherein said step (1) further comprises selecting a core composite material of an interior trim panel in response to a specific acoustic output generated by the aircraft. 14. A method as recited in claim 13, further comprises selecting a core composite material of an interior trim panel in response to a specific acoustic output generated by the aircraft. 15. A method as recited in claim 14, further comprises selecting a skin of the interior trim panel in response to the core composite material. 16. An aircraft section suitable for use in an aircraft, comprising: an airframe component having a multitude of frame members which define a void; a foam portion which provides an interference fit with said multitude of frame members; a mass barrier layer mounted to said multitude of frame members; a primary soundproofing blanket mounted to said airframe frame member and at least partially over said airframe batting said primary soundproofing blanket includes material layers tuned in thickness and density of the layers to a specific acoustic output generated by the aircraft; and an interior trim panel mounted to said airframe frame member and at least partially over said primary soundproofing blanket, said interior trim panel including a mass barrier layer mounted to a composite core to at least partially surround a decoupler layer, said mass barrier layer tuned in mass to the specific acoustic output generated by the aircraft. 17. The system as recited in claim 16, wherein said interior trim panel is mounted to an interior skeleton member, said interior skeleton member mounted to a vertical airframe frame member of said multitude of frame members. 18. The system as recited in claim 1, wherein said airframe batting, said primary soundproofing blanket and said interior trim panel are each tuned to a specific acoustic output generated by the aircraft. 19. The system as recited in claim 1, wherein said interior trim panel includes a mass barrier layer mounted to a composite core to at least partially surround a decoupler layer, said mass barrier layer tuned in mass to a specific acoustic output generated by the aircraft; said decoupler layer tuned in thickness to the specific acoustic output generated by the aircraft; said composite core selected to the specific acoustic output generated by the aircraft; and said primary soundproofing blanket includes material layers tuned in thickness and density to the specific acoustic output generated by the aircraft. 20. A method as recited in claim 9, wherein said step 1 further comprises the steps of: (a) tuning a mass barrier layer of an airframe batting to the specific acoustic output generated by the aircraft; (b) tuning a thickness of material layers and density of the material layers of a primary soundproofing blanket to the specific acoustic output generated by the aircraft; and (c) tuning a mass barrier layer of an acoustic absorption trim panel to the specific acoustic output generated by the aircraft. 21. A method as recited in claim 9, wherein said step 1 further comprises the steps of: (a) layering a primary soundproofing blanket over an airframe batting; and (b) layering an interior trim panel over the primary soundproofing blanket such that the layers are tuned to the specific acoustic output generated by the aircraft and to each of the preceding layers. 22. The system as recited in claim 1, wherein said airframe batting includes a foam portion. 23. The system as recited in claim 1, wherein said primary soundproofing blanket includes a soundproofing blanket having a multiple of material layers. 24. The system as recited in claim 1, wherein said interior trim panel includes an interior trim panel.
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