Composite anti-crash structure with controlled buckling for an aircraft
US7780116B2 · kind B2 · utility
3Cited by
23References
22Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jan 26, 2007 |
| Grant date | Aug 24, 2010 |
| Priority date | — |
| Expiry date | Jun 11, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A structure (2) for an aircraft (1) comprises transverse walls (3-8) connected to longitudinal walls (9-12); each wall (3-12, 18, 18B) comprises two jackets (19) of composite material disposed on either side of an intermediate arrangement (20); a wall includes a corrugated core (70) presenting corrugations extending along an axis (Z) substantially parallel to the jacket, such that the capacity of the wall to absorb energy in the event of an impact along said axis is increased; a wall includes a zone of weakness (45) encouraging controlled degradation of the wall in the event of such a shock.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.