An aircraft landing gear assembly having a reinstating geometry in which a lock link can be moved to assume a first locking condition to inhibit movement of a stay when a main strut is in a deployed condition and a second locking condition to inhibit movement of the main strut when in a stowed condition. An unlock actuator is coupled between a first element of the stay and the lock link such that the actuator can break the lock link from the first locking condition and force it to assume the second locking condition by operational force in a single direction.

An aircraft landing gear assembly having a reinstating geometry in which a lock link can be moved to assume a first locking condition to inhibit movement of a stay when a main strut is in a deployed condition and a second locking condition to inhibit movement of the main strut when in a stowed condition. An unlock actuator is coupled between a first element of the stay and the lock link such that the actuator can break the lock link from the first locking condition and force it to assume the second locking condition by operational force in a single direction.

A method for extending a landing gear system for a vehicle is disclosed. The landing gear system includes a first landing gear assembly and a second landing gear assembly. The method includes the steps of sensing a first load on the first landing gear assembly after the first landing gear assembly has reached a wheels-on-ground state and comparing the first load to a first target value. The method further includes the step of controlling an extension speed of the first landing gear assembly according to a difference between the first load and the first target value.

An aircraft undercarriage includes a leg for mounting on a structure of the aircraft so as to be movable between a deployed position and a retracted position, the undercarriage being fitted with a breaker strut including two hinged elements that are hinged together at a knee, with a first element for coupling to the structure of the aircraft and a second element for coupling to the undercarriage, a return member being arranged between the two elements to urge them towards a substantially aligned position that is defined by respective abutments. According to the invention, one of the strut elements incorporates a linear actuator having a slidable rod that is coupled to the other strut element by means of a link, the assembly being arranged in such a manner that moving the slidable rod of the actuator in a single direction causes, in succession, the elements of the strut to move out of alignment and the undercarriage to move from the deployed position to the retracted position.

An aircraft undercarriage includes a leg for mounting on a structure of the aircraft so as to be movable between a deployed position and a retracted position, the undercarriage being fitted with a breaker strut including two hinged elements that are hinged together at a knee, with a first element for coupling to the structure of the aircraft and a second element for coupling to the undercarriage, a return member being arranged between the two elements to urge them towards a substantially aligned position that is defined by respective abutments. According to the invention, one of the strut elements incorporates a linear actuator having a slidable rod that is coupled to the other strut element by means of a link, the assembly being arranged in such a manner that moving the slidable rod of the actuator in a single direction causes, in succession, the elements of the strut to move out of alignment and the undercarriage to move from the deployed position to the retracted position.

A linear electromechanical actuator with a main screw-nut assembly driven by a main motion device and having a hollow screw with an abutting surface; an anti-jamming piston arranged coaxially within the screw and shiftable between an engaged position in which locking dogs interfere with the abutting surface and a disengaged position in which the piston is free to slide within the screw; and actuating elements configured to shift the piston from the engaged to the disengaged position upon electrical or mechanical failure of the actuator. The actuating elements include a key axially movable between the engaged and disengaged positions and having a locking section, configured to bias the locking dogs into interference with the abutting surface in the engaged position, and an unlocking section, configured to allow free sliding of the piston within the screw in the disengaged position. An anti-jamming device for operating a critical flight control surface.

Systems and methods for mechanically rotating an aircraft about its center-of-gravity (C.sub.G) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

A force-shunting device including a tube defining a main axis and an inner wall, a first member sliding within the tube, a primary leg arranged obliquely, attached to the first member and including a primary pad in frictional contact with the inner wall, such that, when an external force is applied in a first direction on the first member, the primary leg rubs, or grips by mechanical camming, against the inner wall, the tube thus reacting all or part of the external force, the device including a second member mounted within the tube, sliding along the main axis and securely provided with a driving element of the primary pad so as to reduce the friction on the inner wall, to unprime the rubbing or mechanical camming.

A force-shunting device including a tube defining a main axis and an inner wall, a first member sliding within the tube, a primary leg arranged obliquely, attached to the first member and including a primary pad in frictional contact with the inner wall, such that, when an external force is applied in a first direction on the first member, the primary leg rubs, or grips by mechanical camming, against the inner wall, the tube thus reacting all or part of the external force, the device including a second member mounted within the tube, sliding along the main axis and securely provided with a driving element of the primary pad so as to reduce the friction on the inner wall, to unprime the rubbing or mechanical camming.

A retractable wheel assembly includes arm assemblies, wheels, a retraction arm, and a threaded shaft. The arm assemblies are hingedly attached to a lower frame of a utility vehicle. Each arm assembly comprises a first arm, a second arm, and a third arm hingedly linked there between. Each wheel is connected to the third arm of each arm assembly. The retraction arm is connected to the second arm, and a threaded shaft. The threaded shaft is configured to be actuated rearwardly where the retraction arm is rearwardly pulled causing the second arm to unfold the arm assembly outwardly and deploy the wheels and for motion of the utility vehicle. Then, the threaded shaft is configured to be actuated forwardly where the retraction arm is pushed forward causing the second arm to fold the arm assembly inwardly and fold the wheels and when the utility vehicle is positioned at rest.