An aircraft cargo hold unloading and collection system having an aircraft body, a lifting device, and a netted shelf. The lifting device is arranged on the aircraft body, and the lifting device is connected to the aircraft body through communication. The lifting device has a retractable cable. One end of the cable can be connected to the cargo hold, and the other end is fixed relative to the aircraft body. The netted shelf is used to be arranged on the ground, and the aircraft body is provided with a position identification part. The netted shelf is provided with a trigger part, and the position identification part can identify the signal transmitted from the trigger part to locate the netted shelf.

An aircraft fuselage assembly includes a primary structure with first and second rows of support elements extending parallel to a longitudinal axis and into an interior space of the fuselage where they have a free end. The free ends of the first and second rows are spaced from one another to from a free space below a common plane of the free ends and extending to the primary structure. A cargo floor assembly with at least one first cargo floor element is fixedly connected to the free ends of the first row in the common plane and at least one second cargo floor element fixedly connected to the free ends of the second row in the common plane. At least one central cargo floor element is arranged between the first and second lines and is releasably connected to the support elements of the first and second rows.

A restraint assembly includes a fitting base, a bushing, and a restraint roller disk, according to various embodiments. The fitting base includes a fitting lower surface and a fitting upper surface that is angled relative to the fitting lower surface, according to various embodiments. The fitting base may be configured to be coupled, via an anchor, to a rail upper surface of a guide rail of the cargo system. In various embodiments, the bushing is configured to be disposed about the anchor. In various embodiments, the restraint roller disk includes a roller upper surface and a roller lower surface, wherein the restraint roller disk is configured to be rotatably coupled about the bushing and the roller lower surface is configured to engage the fitting upper surface of the fitting base.

A locking system for fixing at least one transport unit for cargo items in an aircraft. The locking system includes a plurality of locking devices and at least one actuating device. Each locking device has at least one locking element for fixing and releasing the transport unit at least one predetermined position and is displaceable in a displacement direction between a fixing position and a release position. The at least one actuating device has at least one actuating unit for initiating an actuating movement and at least one sliding unit for displacing the locking element. The actuating unit is connected to the sliding unit for transmitting the actuating movement by means of at least one transmission section extending transversely to the displacement direction. The sliding unit is mechanically coupled to the locking element to transmit the actuating movement and to move the locking element between the fixing position and the release position.

A control device for a cargo loading system on a cargo deck of a cargo aircraft. The control device includes a plurality of selection switch elements each for selecting a loading configuration from a plurality of possible loading configurations, at least one first indicator device, comprising a display for outputting an at least partial depiction of the cargo deck, at least one second indicator device to be arranged (directly) on the cargo deck, in particular on system components of the cargo loading system, and a computing unit. The computing unit is configured to: a) determine a selected loading configuration based on signals from at least some of the selection switch elements; b) using the selected loading configuration, determine an identification region on the cargo deck and/or an identification selection of system components; and c) visualize the identification region and/or the identification selection using the first indicator device and the second indicator device (simultaneously).

A cargo hold of an aircraft having cladding elements and at least one housing element for accommodating electronic components and/or cables. The cladding elements are attached to supports, in particular structural elements, of the aircraft and have a plurality of cladding holes with predefined cladding hole spacings for attachment. The at least one housing element has at least one pair of housing holes for receiving fastening devices. The housing holes have a housing hole spacing which corresponds to at least one pair of cladding hole spacings.

A side guide for guiding and/or fastening pieces of cargo, in particular containers and/or pallets, in an aircraft. The side guide has at least one side guide device and at least one holding unit. The holding unit comprises a fastening frame extending in a longitudinal direction and at least one securing device arranged on the fastening frame, which has a plurality of recesses extending transversely to the longitudinal direction. The side guide device is insertable at different positions into at least one of the recesses and can be secured in the inserted state at the different positions by the securing device. The side guide device has at least one contact element, which, in the inserted state, can be engaged with at least one fixing element, displaceable in the longitudinal direction of the securing device.

A fastening device for releasable connection to a perforated rail of an aircraft and a method of assembly for such a fastening device. The fastening device comprises a housing having at least one locking head portion fixedly connected to the housing, at least one shear pin and an actuating pin. The locking head portion is insertable into a rail hole of the perforated rail and slidable along the longitudinal direction of the perforated rail to a locking position in which the locking head portion engages a slot portion of the perforated rail. The shear pin can be engaged with a rail hole of the perforated rail by axial displacement. The actuating pin is rotatably arranged relative to the housing and connected to the shear pin in such a way that a rotation of the actuating pin causes an axial displacement of the shear pin relative to the housing.

A locking device for securing cargo items in a cargo deck of an aircraft. The locking device includes a frame having at least two longitudinal members, at least two fastening claws each with a locking lug, and at least two guide rails. The fastening claws are movably mounted on carriage elements. Each guide rail can be fastened to a respective longitudinal member at different positions. The at least two carriage elements are displaceably mounted on the guide rails. At least one compression spring may be formed between the carriage elements, so that the two carriage elements are spring-mounted with respect to one another.

A vibration damping system (VDS) for an aerial vehicle carrying a payload is disclosed. The VDS comprises a vibration damping base plate, a vibration damping top plate, and a damping device mechanically coupled to both the vibration damping base plate and the vibration damping top plate. The vibration damping base plate is configured to be attached to the aerial vehicle and the vibration damping top plate is configured to be attached to the payload. The damping device includes a flexible damping material and the vibration damping base plate is physically isolated from the vibration damping top plate via the damping device.