Aircraft control surface with linear actuator
US11827338B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 14, 2022 |
| Grant date | Nov 28, 2023 |
| Priority date | — |
| Expiry date | Feb 14, 2042 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An assembly is provided for an aircraft. This aircraft assembly includes an aircraft control surface. The aircraft control surface includes a first skin, a second skin and a support structure laterally between and connected to the first skin and the second skin. The support structure includes a spar, a first stiffener and a second stiffener. The spar extends spanwise within the aircraft control surface. The first stiffener extends longitudinally within the aircraft control surface to the spar. The second stiffener extends longitudinally within the aircraft control surface to the spar. An actuator receptacle projects longitudinally into the aircraft control surface from a base of the aircraft control surface to the spar. The actuator receptacle extends spanwise within the aircraft control surface between the first stiffener and the second stiffener.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.