Primary structure for aircraft of composite material with improved crash resistance and associated energy-absorbing structural element
US8123166B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Sep 23, 2009 |
| Grant date | Feb 28, 2012 |
| Priority date | — |
| Expiry date | Sep 23, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16F7/12
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
The disclosed embodiments relate essentially to a primary structure of an aircraft fuselage that has at least a first strut linked at one end to a crossbeam and at the other end to a reinforcing frame. A second strut has one end fastened to the structure below the end of the first strut, and another end linked to the first strut through an intermediate sliding linkage. A deformable member is linked to the struts so that in case of a crash, the compressive forces press against the second strut, so that the end of the second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.