A cargo conveying system for conveying cargo items, in particular containers and/or pallets, in a cargo hold of an aircraft having at least one cargo conveying device, in particular roller conveyors. The cargo conveying device includes at least one frame, at least one roller drive unit having at least one roller for conveying the cargo items, at least one main line strand, in particular a partial cable harness, arranged on the frame, and at least one distributor module for connecting the at least one main line strand to at least one further main line strand. The distributor module is arranged on the frame and is connected to the roller drive unit via at least one secondary line strand.

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 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).

The disclosure provides a method of controlling the yaw of a fixed-wing UAV, with two traction propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two traction propellers, wherein the thrust ratio provided by the two traction propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed-wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.

The disclosure provides a method of controlling the yaw of a fixed-wing UAV, with two traction propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two traction propellers, wherein the thrust ratio provided by the two traction propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed-wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.

A cargo aircraft configured to carry a portion of its payload in a cargo bay volume enclosed by a moveable nose door and supported by a structural extension of the fuselage that extends forward into the moveable nose door is disclosed. Examples include an aircraft with a continuous cargo bay extending from an aft end of a fixed portion into forward portion inside a nose door, where the portion of the cargo bay in the nose door is supported by a cantilevered support structure extending forward a length from a cargo opening into the fixed portion and such that the support structure extends into the nose door when the door is closed. The length of the support structure defines a supported cargo volume of at least about 15% of the overall volume of the fuselage forward of an aft end of the support structure.

A cargo aircraft configured to carry a portion of its payload in a cargo bay volume enclosed by a moveable nose door and supported by a structural extension of the fuselage that extends forward into the moveable nose door is disclosed. Examples include an aircraft with a continuous cargo bay extending from an aft end of a fixed portion into forward portion inside a nose door, where the portion of the cargo bay in the nose door is supported by a cantilevered support structure extending forward a length from a cargo opening into the fixed portion and such that the support structure extends into the nose door when the door is closed. The length of the support structure defines a supported cargo volume of at least about 15% of the overall volume of the fuselage forward of an aft end of the support structure.

Walking VTOL vehicles and related systems and methods are disclosed. A representative system can include one or more vertical thrust propulsion systems for providing vertical thrust for the vehicle, one or more horizontal thrust propulsion systems for providing horizontal thrust for the vehicle, and leg elements that are rotatable between a first configuration in which each leg element extends downwardly and a second configuration different from the first configuration. A representative method of operating a vehicle includes using vertical thrust to raise the vehicle upward, rotating a leg element forward, lowering the vehicle, and then rotating the leg element rearward to propel the vehicle forward.

An aircraft fuselage end cargo door mechanism including a hinge rotatably coupling an aircraft fuselage end cargo door to a fuselage. The hinge being coupled to both the aircraft fuselage end cargo door and the fuselage so that an entirety of an axis of rotation of the aircraft fuselage end cargo door, defined by the hinge, relative to the fuselage is located forward of an entirety of a major joint line between the aircraft fuselage end cargo door and the fuselage. An uppermost portion of the major joint line comprises a joint line radius where a portion of the joint line radius formed by the aircraft fuselage end cargo door pivots within another portion of the joint line radius formed by the fuselage.

An unmanned aerial vehicle (UAV) includes a fuselage assembly, a further portion that attaches with the fuselage assembly, and a propulsion assembly coupled with the further portion. The propulsion assembly is constructed and arranged to provide propulsion for the UAV. The fuselage assembly includes a fuselage body constructed and arranged to operate as a forward portion of the UAV, lateral stringers coupled with the fuselage body and extending laterally along the fuselage body, and a set of interchangeable covers to cover at least a portion of a payload bay opening defined by the fuselage body. Utilizing such a fuselage assembly offers a highly configurable mounting architecture to accommodate a wide variety of payloads.