Aircraft turbine engine assembly comprising a hinged cover
US11247781B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 17, 2019 |
| Grant date | Feb 15, 2022 |
| Priority date | — |
| Expiry date | Aug 25, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/90
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft turbine engine assembly including a nacelle structure with a strut attachment zone, a first cover forming an air intake lip, a hinged cover arranged on the nacelle upper portion, between the first cover and the attachment zone, a hinge system of the cover comprising, on either side of a mid-plane of the nacelle, a front rod and a rear rod that are one in front of the other. The two ends of each rod are co-planar, parallel to the mid-plane. A first end of each rod is hinged on the cover. A second end of each rod is hinged on the structure. A locking system is actuatable from the outside of the nacelle between a locked and an unlocked positon. The nacelle comprises at least one cylinder with a first end mounted hinged on the structure and the other end mounted hinged on the cover.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.