Tunable acoustic absorption system for an aircraft cabin
AssigneeSikorsky Aircraft Corporation
InventorStuart K. Drost
Life of this patent
Estimating the term…
Abstract
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.
Claims24
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.
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.
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.
Dependencies are inferred from the claim text.