Aircraft control column with improved overall reduction ratio and method for using such a control column
US12252234B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 30, 2020 |
| Grant date | Mar 18, 2025 |
| Priority date | — |
| Expiry date | Feb 1, 2042 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05G2009/04766
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
The invention relates to an aircraft control column, the control column comprising a first shaft and a control lever configured to rotate the first shaft about a first axis through a first angular range [α1; α3] via a mechanical joint having a primary reduction ratio, the control column comprising a braking device configured to brake the first shaft via a first transmission device having a secondary reduction ratio, the secondary reduction ratio being maximum for an angular position, the secondary reduction ratio increasing over the range [α1; α4] and then decreasing over the range [α4; α3] so as to obtain an overall reduction ratio that has a limited amplitude of variation over the first angular range [α1; α3].
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.