Composite-material aircraft part and method of manufacturing same
US12172392B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 31, 2021 |
| Grant date | Dec 24, 2024 |
| Priority date | — |
| Expiry date | Dec 6, 2042 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
An aircraft structure (such as a T-shaped structure, a convex structure, a curved structure, or the like) includes: a laminated structure including composite-material layers that are laminated; and wherein the composite material aircraft structure is a three-dimensional structure that includes at least one of a standing structure, a convex structure, or a curved structure. The composite-material layers include at least a composite-material layer in which a reinforced fiber is a single continuous fiber, wherein the single continuous fiber includes a partial slit region. When a thickness of a flat-plate formed body including a same laminated structure as the aircraft structure but not including the three-dimensional structure, is defined as a reference thickness, the aircraft structure includes a thin plate region which has a thickness that is smaller than the reference thickness while maintaining the laminated structure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.