A method of operating an electromechanical actuator includes coupling an inner portion of a split ball screw with an outer portion of the split ball screw, rotating the split ball screw about an axis to drive a ball nut in a first axial direction, in response to a failure mode of the electromechanical actuator, decoupling the outer portion of the split ball screw from the inner portion of the split ball screw, and translating the outer portion of the split ball screw and the ball nut in a second axial direction.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

An aircraft system for an aircraft is disclosed including a controller. The controller is configured, during a take-off procedure, to initiate automatic closing of a landing gear bay door of the aircraft from an open position towards a closed position, on the basis of a determination that a predetermined door-closing criterion has been met and a command to retract a landing gear has not been received, the landing gear being arranged to retract into a landing gear bay to be at least partially covered by the landing gear bay door when the landing gear bay door is in the closed position.

An aircraft controller configured to determine a period and/or distance over which deployment of a landing gear can be initiated for landing including a determined first portion during which landing gear deployment can be safely initiated and a determined second portion, closer to aircraft landing than the first portion, during which the landing gear deployment can be safely initiated in an efficient landing mode; issue a first pilot feedback when the first portion is entered by the aircraft; issue a second pilot feedback when the second portion of the determined; and initiate landing gear deployment when the aircraft is in the determined period and/or distance in response to receiving a deployment signal from the pilot.

An aircraft landing gear comprising: a first member, a second member pivotally coupled to the first member, and a spring coupled to the first and second members, the spring comprising a plurality of elastically deformable washers, the spring being arranged to generate a biasing force between the first and second members to bias the first member toward a predetermined orientation relative to the second member.

An aircraft landing gear comprising: a first member, a second member pivotally coupled to the first member, and a spring coupled to the first and second members, the spring comprising a plurality of elastically deformable washers, the spring being arranged to generate a biasing force between the first and second members to bias the first member toward a predetermined orientation relative to the second member.

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.