Aircraft thickness/camber control device for low sonic boom
US7070146B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 29, 2003 |
| Grant date | Jul 4, 2006 |
| Priority date | — |
| Expiry date | Nov 24, 2023 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft thickness/camber control device mounts to the lower surface of a airfoil configuration, for example on a fuselage, and extends along a longitudinal axis. The device, when deployed, generates expansions ahead of compressions generated by off-design conditions, inlet spillage for example, and enables maintenance of a low boom signature. The device, when positioned at appropriate locations, may also be used as a drag reduction device. The thickness/camber control device comprises a structural member capable of coupling to the airfoil at a position forward of the concentrated source of added compression and a control element. The control element is coupled to the structural member and controls the structural member to adjust thickness/camber of the configuration to cancel the far-field effect of the extra compression or concentrated pressure source.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.