Systems and methods for loading a cargo aircraft are described. The system includes at least one rail disposed in an interior cargo bay of a cargo aircraft that extends at an angle relative to an interior bottom contact surface of a forward portion of the interior cargo bay, through a kinked portion and an aft portion of the interior cargo bay. Payload-receiving fixtures are described that can be used in conjunction with the rail system, allowing for large cargo, such as wind turbine blades, to be transported by aircraft. Methods of loading a cargo aircraft can include advancing the large payload into the interior cargo bay of the aircraft such that at least one of the payload-receiving fixtures rises relative to a plane defined by the interior bottom contact surface of the forward portion of the interior cargo bay. Various systems, methods, components, and related tooling are also provided.

A system is described and includes a first track assembly for connecting a top surface of a pallet supporting payload to an upper interior surface of a payload bay of an aircraft; a second track assembly for connecting a side surface of the pallet to a side interior surface of the payload bay; and a pallet actuator system for selectively moving the pallet along the first and second track assemblies between a first position in which the pallet is fully extended from the payload bay and a second position in which the pallet is fully retracted into the payload bay.

In an aspect a system for loading and securing a payload in an electrical vertical take-off and landing (eVTOL) aircraft may comprise a fuselage further comprising structural elements configured to provide physical support for the aircraft fuselage. An eVTOL aircraft may also comprise a swing nose, where a portion of the nose of the aircraft may swing on a hinge in a radial direction orthogonal to the longitudinal axis of the aircraft. The hinge may be coupled to at least a portion of the fuselage and at least a portion of the nose of the aircraft. A latching mechanism may be configured to secure a payload in an aircraft fuselage. A conveyor mechanism may be configured to transport a payload into the fuselage from the opening of the aircraft.

A system is described and includes a first track assembly for connecting a top surface of a pallet supporting payload to an upper interior surface of a payload bay of an aircraft; a second track assembly for connecting a side surface of the pallet to a side interior surface of the payload bay; and a pallet actuator system for selectively moving the pallet along the first and second track assemblies between a first position in which the pallet is fully extended from the payload bay and a second position in which the pallet is fully retracted into the payload bay.

A freight carrier for a freight region of an aircraft, having a base element with a support side and roller elements. Each of the roller elements is retained on a retention member to be rotatable about a rotation axis, wherein each of the retention members is displaceable between a deployed position and a retracted position, wherein the spacing of the roller elements from the base face is greater in the deployed position. The rotation axes of the roller elements are in a common rotation axis plane when the retention members are in the deployed position, the roller elements retained on the base element so the rotation axis of each of the roller elements is rotatable about a vertical axis, wherein the vertical axis extends parallel with and with spacing from an axis which extends through the rotation axis of the roller element and perpendicularly to the rotation axis plane.

A caster roller assembly may comprise a base, a roller rotationally coupled to the base, and a thrust bearing assembly adjacent to an underside surface of the base. The thrust bearing assembly may include a bearing cup, a plurality of thrust rollers located in a channel defined by the bearing cup, and a top plate located between plurality of thrust rollers and the base. An inner circumferential surface of the top plate may define an opening configured to receive a protrusion extending from the underside surface of the base.

Systems and methods for extending the interior cargo bay of fixed-wing cargo aircraft into a replaceable tailcone bay are disclosed. The system includes an aircraft and a removable tailcone configured couple to the aft end of the fuselage. The aircraft fuselage includes a cargo bay and an aft end opening into the cargo bay. The tailcone, when attached, encloses the aft end opening the cargo bay. The tailcone can include an interior volume configured to extend the fuselage cargo bay such that the interior volume defines an aft end of a cargo bay of the cargo aircraft. In some examples, the tailcone includes a plurality of segments, which can be configured to extend from the aft end of the aircraft to adjust a length of the cargo extension provided by the tailcone.

A stowable cargo guide may be configured to couple to a roller tray. The stowable cargo guide may comprise a guide block configured to rotate between a stowed position and a raised position. In the stowed position, the guide block may be located below a conveyance plane of the roller tray. In the raised position, the guide block may be located above the conveyance plane of the roller tray.

A cargo handling system that utilizes a distributed antenna system for a cargo bay or compartment is disclosed. A cargo deck within the cargo bay may incorporate a plurality of power drive units. A mobile cargo controller may wirelessly communicate with the distributed antenna system to control movement of a ULD into/out of/within the cargo bay. A base station may be operatively interconnected with both the distributed antenna system and the plurality of power drive units (e.g., directly or indirectly via a control system, such as a control panel).

A tire may comprise a hub and a plurality of discrete traction elements coupled to the hub. Each of the traction elements may comprise a backing plate and an elastomeric material bonded to the backing plate. Circumferentially adjacent traction elements may axially overlap.