US 12,404,008 B2
Control mechanism
Pierre-Jacques Labry, Faycelles (FR)
Assigned to RATIER-FIGEAC SAS, Figeac (FR)
Filed by RATIER-FIGEAC SAS, Figeac (FR)
Filed on Jun. 20, 2024, as Appl. No. 18/748,170.
Claims priority of application No. 23306019 (EP), filed on Jun. 26, 2023; and application No. 24305416 (EP), filed on Mar. 20, 2024.
Prior Publication US 2025/0121930 A1, Apr. 17, 2025
Int. Cl. B64C 13/34 (2006.01)
CPC B64C 13/34 (2013.01) 16 Claims
OG exemplary drawing
 
1. A control mechanism for an aircraft, the control mechanism comprising:
a conversion mechanism having a translatable part and a rotatable part, the translatable part being reversibly translatable;
an inceptor connector connected to the translatable part of the conversion mechanism;
a differential device connected to the rotatable part of the conversion mechanism, the conversion mechanism being configured to convert translational motion of the inceptor connector to rotational motion of the differential device;
an adjustment member connected to the differential device; and
a control member connected to the differential device;
wherein the differential device is configured such that the adjustment member is maintainable in position during an aircraft control process to permit:
translation of the inceptor connector from a translational neutral position; and
corresponding movement of the control member to control the aircraft through the differential device; and
wherein the differential device is configured such that the control member is maintainable in position during an adjustment process to permit:
translation of the inceptor connector; and
corresponding movement of the adjustment member through the differential device to adjust the translational neutral position.