US 12,252,234 B2
Aircraft control column with improved overall reduction ratio and method for using such a control column
Clément Guillon, Moissy-Cramayel (FR); Rémi-Louis Lawniczak, Moissy-Cramayel (FR); and Yvon Joncour, Moissy-Cramayel (FR)
Assigned to SAFRAN ELECTRONICS & DEFENSE, Boulogne-Billancourt (FR)
Appl. No. 17/757,630
Filed by SAFRAN ELECTRONICS & DEFENSE, Boulogne-Billancourt (FR)
PCT Filed Nov. 30, 2020, PCT No. PCT/EP2020/083970
§ 371(c)(1), (2) Date Jun. 17, 2022,
PCT Pub. No. WO2021/121941, PCT Pub. Date Jun. 24, 2021.
Claims priority of application No. 1915220 (FR), filed on Dec. 20, 2019.
Prior Publication US 2023/0020880 A1, Jan. 19, 2023
Int. Cl. B64C 13/38 (2006.01); G05G 9/047 (2006.01)
CPC B64C 13/38 (2013.01) [G05G 9/047 (2013.01); G05G 2009/04718 (2013.01); G05G 2009/04766 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A control column of an aircraft, the control column comprising a first shaft and a control lever configured to rotatably drive the first shaft about a first axis in a first angular range [α1; α3] by means of a mechanical joint having a primary reduction ratio, the primary reduction ratio being minimum for a given angular position α2, the primary reduction ratio for the first axis being decreasing over a range [α1; α2] and then increasing over a range [α2; α3]; the control column comprising a force application device comprising at least one 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 a given angular position α4, the secondary reduction ratio for the first axis being increasing over a range [α1; α4] and then decreasing over a range of range [α4; α3] so as to achieve an overall reduction ratio for the first axis between the control lever and the braking device having a first axis limited amplitude of variation over the first angular range [α1; α3].