US 12,077,283 B2
Electro-mechanical actuator for controlling the movement of an aircraft
Dan Telteu-Nedelcu, Brussels (BE); and Albert Britte, Brussels (BE)
Assigned to SOCIETE ANONYME BELGE DE CONSTRUCTIONS AÉRONAUTIQUES, S.A.B.C.A., Brussels (BE)
Appl. No. 17/788,282
Filed by SOCIÉTÉ ANONYME BELGE DE CONSTRUCTIONS AÉRONAUTIQUES, S.A.B.C.A., Brussels (BE)
PCT Filed Dec. 11, 2020, PCT No. PCT/EP2020/085751
§ 371(c)(1), (2) Date Jun. 22, 2022,
PCT Pub. No. WO2021/130032, PCT Pub. Date Jul. 1, 2021.
Claims priority of application No. 19219517 (EP), filed on Dec. 23, 2019.
Prior Publication US 2023/0023394 A1, Jan. 26, 2023
Int. Cl. B64C 13/50 (2006.01)
CPC B64C 13/506 (2018.01) [B64C 13/50 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An actuator for moving an aircraft control part controlling the movement of an aircraft, the actuator comprising:
a mobile element movable in a first direction and in a second direction;
an actuating means for moving the mobile element;
a mechanical brake which, in case of loss of electrical power and/or in case of a brake signal, brakes the mobile element in the first direction;
wherein the mechanical brake is configured to allow a movement of the mobile element in the first direction, if a force from the aircraft control part on the mobile element exceeds a threshold force, wherein the mechanical brake comprises a cam with a profiled surface and a braking element pushing, in the case of loss of electrical power and/or in case of a brake signal, on the profiled surface of the cam, wherein the profiled surface of the cam is designed such that the braking element pushing against the profiled surface brakes the mobile element in the first direction until the force from the aircraft control part on the mobile element exceeds the threshold force.