US 12,377,967 B2
Method for protecting the landing gear of an aircraft against impacts that may affect it
Florent Fortier, Moissy-Cramayel (FR); Sébastien Dubois, Moissy-Cramayel (FR); and Florent Dauphin, Moissy-Cramayel (FR)
Assigned to SAFRAN LANDING SYSTEMS, Velizy Villacoublay (FR)
Filed by SAFRAN LANDING SYSTEMS, Velizy Villacoublay (FR)
Filed on Dec. 17, 2019, as Appl. No. 16/716,926.
Claims priority of application No. 18 73262 (FR), filed on Dec. 18, 2018.
Prior Publication US 2020/0189726 A1, Jun. 18, 2020
Int. Cl. B64C 25/20 (2006.01); B64C 25/24 (2006.01); F16C 41/00 (2006.01)
CPC B64C 25/20 (2013.01) [B64C 25/24 (2013.01); F16C 41/004 (2013.01); F16C 2326/43 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A method for protecting an aircraft landing gear against stroke-end shocks wherein the landing gear is maneuverable between a retracted position and a deployed position by a single electromechanical actuator comprising:
a motor having a motor shaft,
an output shaft coupled to the aircraft landing gear, and
a strain wave gear arranged between the motor shaft and the output shaft, the method comprising:
equipping the single electromechanical actuator, in addition to the strain wave gear, with an internal rotary damper arranged between the output shaft and the strain wave gear or between the motor shaft and the strain wave gear to protect the motor from any sudden stops of said output shaft of the single electromechanical actuator.