An upper side brace for use in landing gear includes a main body having a mounting end configured to be proximal to an aircraft and a lower end configured to be proximal to a lower side brace. The upper side brace further includes an unlock actuator cylinder formed monolithic with the main body and configured to house a piston to form an unlock actuator.

An upper side brace for use in landing gear includes a main body having a mounting end configured to be proximal to an aircraft and a lower end configured to be proximal to a lower side brace. The upper side brace further includes an unlock actuator cylinder formed monolithic with the main body and configured to house a piston to form an unlock actuator.

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

A folding assembly is movable between a collapsed configuration and an extended configuration includes a first rotating link having a first end pivotably coupled to a structural member/frame and a second end. The folding assembly also includes a second rotating link having a first end pivotably coupled to the structural member/frame and a second end. A first connecting link is pivotably coupled between the first rotating link and the second rotating link. A first end of a second connecting link is pivotably coupled to the first rotating link second end. The folding assembly further includes a support link having a first end pivotably coupled to the first rotating link second end and a second end configured to couple to a component to be moved. The support link is configured to selectively move the component between, inclusively, a retracted position and a deployed position.

Shape memory actuators may be used in unmanned aerial vehicles to control various components. For example, shape memory actuators may adjust cant angles of motors, propellers, and other propulsion mechanisms. In addition, shape memory actuators may adjust positions or orientations of various other components of unmanned aerial vehicles, including wings, control surfaces, motor arms, frame sections, payload doors, and landing gears. The shape memory actuators may be formed of various shape memory materials, may be one-way or two-way shape memory actuators, and may change their configurations responsive to heat and/or magnetic fields.

Shape memory actuators may be used in unmanned aerial vehicles to control various components. For example, shape memory actuators may adjust cant angles of motors, propellers, and other propulsion mechanisms. In addition, shape memory actuators may adjust positions or orientations of various other components of unmanned aerial vehicles, including wings, control surfaces, motor arms, frame sections, payload doors, and landing gears. The shape memory actuators may be formed of various shape memory materials, may be one-way or two-way shape memory actuators, and may change their configurations responsive to heat and/or magnetic fields.

An additively manufactured component for a landing gear assembly may comprise a lug and a lubrication channel extending through the lug. The lubrication channel may comprise an inlet and an outlet. The outlet may be located at a pin orifice defined by the lug. A center axis of a first portion of the lubrication channel may be oriented at an angle relative to a center axis of a second portion of the lubrication channel.

An additively manufactured component for a landing gear assembly may comprise a lug and a lubrication channel extending through the lug. The lubrication channel may comprise an inlet and an outlet. The outlet may be located at a pin orifice defined by the lug. A center axis of a first portion of the lubrication channel may be oriented at an angle relative to a center axis of a second portion of the lubrication channel.

A landing gear including an outer cylinder, a shock strut assembly, and a passive shrink mechanism. The outer cylinder is coupled to a frame of an aircraft about a trunnion axis of rotation. The shock strut assembly is coupled to the outer cylinder for reciprocation along a longitudinal axis of the outer cylinder. The passive shrink mechanism includes: a first shrink link member coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member coupled to the outer cylinder, a first connecting link coupling the crank member to a walking beam of a landing gear retract mechanism, and a second connecting link coupling the crank member to the first shrink link member. The passive shrink mechanism is passively extended and shortened through actuation of the landing gear retract mechanism with deployment and retraction of the landing gear.

A landing gear including an outer cylinder, a shock strut assembly, and a passive shrink mechanism. The outer cylinder is coupled to a frame of an aircraft about a trunnion axis of rotation. The shock strut assembly is coupled to the outer cylinder for reciprocation along a longitudinal axis of the outer cylinder. The passive shrink mechanism includes: a first shrink link member coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member coupled to the outer cylinder, a first connecting link coupling the crank member to a walking beam of a landing gear retract mechanism, and a second connecting link coupling the crank member to the first shrink link member. The passive shrink mechanism is passively extended and shortened through actuation of the landing gear retract mechanism with deployment and retraction of the landing gear.