Aircraft wing and method for reducing airframe-generated noise
US6454219B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Dec 4, 2000 |
| Grant date | Sep 24, 2002 |
| Priority date | — |
| Expiry date | Dec 4, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/10
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft wing useful for reducing wing-generated noise comprises:(a) a main element having a leading edge and a trailing edge;(b) at least one slat having a leading edge and a trailing edge, wherein the slat acts cooperatively with the main element to provide lift to the aircraft, and the main edge leading edge and slat trailing edge define a cavity there between; and(c) at least one sound-absorbing structure located on at least a portion of the main element leading edge, at least a portion of the slat trailing edge, in the cavity, or combinations thereof.If located on the main element leading edge or slat-trailing edge, the sound-absorbing structure may be a honeycomb load-bearing structure such as a honeycomb load-bearing structure having a perforated skin or a machine grid structure having an outer skin which is bonded or perforated. If located in the cavity, the sound-absorbing structure may be a flow blocker. The sound-absorbing structure is typically covered during the normal cruise portion of the aircraft's flight, and thus does not adversely impact aerodynamic performance. A method of reducing such wing-generated noise comprises providing the above-described wing for use…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.