Landing gear with realigning lock link assembly
View Patent ↗Aircraft landing gear having a leg ( 12 ) for hinging to a structure of the aircraft so as to be movable between a deployed position and a retracted position, a main brace ( 15 ), a secondary brace ( 20 ), and a double-acting type unlocking actuator ( 30 ) having a first end coupled to the secondary brace and controllable for causing its links to move out of alignment against the action of the resilient member during retraction or deployment of the landing gear. The landing gear includes couplers ( 31, 33 ) for coupling to a second end of the unlocking actuator, which couplers ensure movement of said second end relative to the leg so that, for a given action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of its positions and tends to confirm said alignment when the landing gear is in its other position.
1. An aircraft landing gear comprising:
a leg ( 11 ) for hinging to a structure of the aircraft to be movable between a deployed position and a retracted position;
a main brace ( 15 ) having a first set of two links ( 15 a , 15 b ) that are hinged together, one link of the first set of links being coupled to the leg and the other link of the first set of links being capable of being coupled to the structure of the aircraft, such that when the leg is in the deployed position, the two links in the first set of links are substantially in alignment;
a secondary brace ( 20 ) comprising a second set of two links ( 20 a , 20 b ) that are hinged together, one link of the second set of links being coupled to the main brace and the other link of the second set of links being coupled to the leg, such that when the leg is in the deployed position, the two links in the second set of links are substantially in alignment with each other and they are held in their alignment by a resilient member ( 22 ) confirming the two links in the second set of links in abutment in the aligned position; and that, when the leg is in the retracted position, the two links in the second set of links are substantially in alignment with each other and are held in alignment by the resilient member ( 22 ) confirming the two links in the second set of links in abutment in the aligned position; and
an unlocking actuator ( 30 ) having a first end coupled to the secondary brace and operable to cause the two links in the second set of links to move out of alignment during retraction or deployment of the landing gear by acting against the action of the resilient member;
wherein the unlocking actuator is of the double-acting type, and
wherein the landing gear includes couplers ( 31 , 33 ) for coupling to a second end of the unlocking actuator, said couplers ensuring movement of said second end relative to the leg so that, for a given action, the unlocking actuator tends to break the alignment of two links in the second set of links when the landing gear is in one of the deployed position or the retracted position and tends to confirm said alignment when the landing gear is in the other of the deployed position or retracted position.
2. The aircraft landing gear according to claim 1 , wherein the couplers comprise a rocker ( 31 ) hinge-mounted to the leg ( 11 ) of the landing gear, the unlocking actuator being coupled at one end to an arm of the rocker that has another arm with an end connected to a stationary point ( 32 ) of the structure of the aircraft by a guide link ( 33 ).