Safran Electronics & Defense

Clément Guillon

Rémi-Louis Lawniczak

Yvon Joncour

Philippe Bezivin

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].

Aircraft control column with improved overall reduction ratio and method for using such a control column

The invention relates to a force application device for an aircraft control column, the control column comprising a control lever configured to rotate a first shaft and a second shaft, the force application device comprising a first force feedback member configured to exert a resistive force opposing the rotation of the first shaft, a second force feedback member configured to exert a resistive force opposing the rotation of the second shaft and a common braking device comprising a housing, a first braking member and a second braking member which are coaxial and mounted rotatably inside the housing and configured to engage with the first shaft and the second shaft, respectively, so as to brake them, preferably simultaneously.

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Moissy-Cramayel, France

Clément Guillon