Systems and methods for folding landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a yoke pivotally coupled with the shock strut via a lower trunnion, and pivotally coupled with an aircraft structure via an upper trunnion. The yoke is configured to pivot about the upper trunnion in a direction back toward a tail of the aircraft and up toward a fuselage of the aircraft, and the shock strut is configured to pivot about the lower trunnion in a direction forward toward a nose of the aircraft and up toward the fuselage of the aircraft to retract the one or more wheels.

Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

An aircraft includes an airframe, forming a nose structure of the aircraft, and at least one high-level system. The aircraft also includes a wheel well assembly, coupled to the airframe and forming a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. The aircraft further includes a floor-panel support, supported by the pressure deck. The aircraft also includes a plurality of transport elements, located between the floor-panel support and the pressure deck.

An aircraft includes an airframe, forming a nose structure of the aircraft, and at least one high-level system. The aircraft also includes a wheel well assembly, coupled to the airframe and forming a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. The aircraft further includes a floor-panel support, supported by the pressure deck. The aircraft also includes a plurality of transport elements, located between the floor-panel support and the pressure deck.

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.

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.

A system for use with a landing gear of an aircraft includes a drag brace assembly having an upper end configured to be rotatably coupled to the aircraft and a lower end configured to be rotatably coupled to a shock strut of the landing gear. The system further includes a jury linkage having a brace portion configured to be pivotally coupled to the drag brace assembly and a strut portion pivotally coupled to the brace portion and configured to be rotatably coupled to the shock strut.

A system for use with a landing gear of an aircraft includes a drag brace assembly having an upper end configured to be rotatably coupled to the aircraft and a lower end configured to be rotatably coupled to a shock strut of the landing gear. The system further includes a jury linkage having a brace portion configured to be pivotally coupled to the drag brace assembly and a strut portion pivotally coupled to the brace portion and configured to be rotatably coupled to the shock strut.