Structural mode shape alignment
US8511609B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | May 14, 2004 |
| Grant date | Aug 20, 2013 |
| Priority date | — |
| Expiry date | Jul 15, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49622
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
Apparatus and method for controlling the orientation of a fundamental panel vibration mode shape of a structure, such as a skin panel of a fuselage of an aircraft, relative to the direction of a turbulent boundary layer flow over the fuselage, and in a manner to achieve a level of noise reduction within the fuselage. The fuselage is constructed either through orientating stringers and/or frame members, or by using stiffening members placed diagonally between the stringers and frame members, in a manner that produces a fundamental panel vibration mode shape that extends at an angle of between about 30°-45° relative to the direction of the turbulent boundary layer flow over the fuselage. Aligning the fundamental panel vibration mode shape at an angle of between about 30°-45° relative to the direction of the turbulent boundary layer flow results in a reduction of the vibration response of the skin panel, and thus a reduction in the noise level within the fuselage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.