A tensioning method for a tensegrity keel includes the steps of: (Step 1) determining target values at an attainment of tensegrity; (Step 2) forming an outline of the integral keel; (Step 3) secondarily tensioning a middle stiffening ring through stretching a hub shaft, thereby attaining a self-equilibrium state; (Step 4) providing telescopic rods between stiffening rings and central trusses so that the stiffening rings and the central trusses are connected together; (Step 5) mounting longitudinal ties; (Step 6) releasing constraints on bisection points and the central trusses and tensioning the integral keel by stretching the telescopic rods, thereby introducing tension to the longitudinal ties; (Step 7) secondarily tensioning lateral stiffening rings by stretching the hub shaft, thereby attaining a self-equilibrium state; and (Step 8) making adjustments using iterative methods so that target values at the attainment of tensegrity will be reached.

A vehicle region with a roof section of a primary structure and with two luggage compartments. One of the luggage compartments comprises a detachable luggage compartment flap and a luggage compartment top, which forms the upper boundary of a part of a luggage space. A detachable fastening device can rotatably fasten the luggage compartment flap on the luggage compartment. A front edge of the luggage compartment top is at a distance from an end point in an intermediate space above a luggage compartment, to which end point a side of a ceiling panel is movable, the distance being greater than or equal to a width of the ceiling panel. Methods for installing and removing a ceiling panel above two luggage compartments are provided, wherein the ceiling panel is guided at least partially through a luggage space of a luggage compartment when the luggage compartment flap has been removed.

A vehicle region with a roof section of a primary structure and with two luggage compartments. One of the luggage compartments comprises a detachable luggage compartment flap and a luggage compartment top, which forms the upper boundary of a part of a luggage space. A detachable fastening device can rotatably fasten the luggage compartment flap on the luggage compartment. A front edge of the luggage compartment top is at a distance from an end point in an intermediate space above a luggage compartment, to which end point a side of a ceiling panel is movable, the distance being greater than or equal to a width of the ceiling panel. Methods for installing and removing a ceiling panel above two luggage compartments are provided, wherein the ceiling panel is guided at least partially through a luggage space of a luggage compartment when the luggage compartment flap has been removed.

The present disclosure discloses a model-based architecture design method for an unmanned aerial vehicle (UAV) system, which aims to deal with challenges of changeable operational requirements, shortened design period, and decreased technical risks in a current UAS design process. A data-driven architecture development method is used. By establishing an architecture development framework of the UAS, a framework modeling process oriented to different viewpoints is designed, and modeling and simulation specifications based on SysML and Modelica are defined, such that design of the UAS starts from conception and confirmation of an operational concept. The method focuses on forward analysis and design of a system framework, and concept verification and metric closed-loop are carried out at an early stage of the design of the UAS by virtue of logic modeling and system simulation.

The present disclosure discloses a model-based architecture design method for an unmanned aerial vehicle (UAV) system, which aims to deal with challenges of changeable operational requirements, shortened design period, and decreased technical risks in a current UAS design process. A data-driven architecture development method is used. By establishing an architecture development framework of the UAS, a framework modeling process oriented to different viewpoints is designed, and modeling and simulation specifications based on SysML and Modelica are defined, such that design of the UAS starts from conception and confirmation of an operational concept. The method focuses on forward analysis and design of a system framework, and concept verification and metric closed-loop are carried out at an early stage of the design of the UAS by virtue of logic modeling and system simulation.

A device is disclosed including a frame, a transfer roller with a circumferential lateral wall, a drive unit, a slit nozzle with a muzzle end for dispensing lacquer, and a deformation unit. The slit nozzle and the deformation unit are each connected to the frame, and an outside contact surface of the lateral wall includes several depressions, the transfer roller is mounted rotatably about an axis of rotation at the frame. The drive unit is configured to drive the transfer roller in a rotation direction of the transfer roller, such that the lateral wall continuously passes through a first angular range and the second angular range, each fixed to the frame. The deformation unit is arranged to elastically deform the lateral wall resulting in a respective first deformation section of the lateral wall passing through the first angular range and a respective second deformation section of the lateral wall passing through the second angular range.

A device is disclosed including a frame, a transfer roller with a circumferential lateral wall, a drive unit, a slit nozzle with a muzzle end for dispensing lacquer, and a deformation unit. The slit nozzle and the deformation unit are each connected to the frame, and an outside contact surface of the lateral wall includes several depressions, the transfer roller is mounted rotatably about an axis of rotation at the frame. The drive unit is configured to drive the transfer roller in a rotation direction of the transfer roller, such that the lateral wall continuously passes through a first angular range and the second angular range, each fixed to the frame. The deformation unit is arranged to elastically deform the lateral wall resulting in a respective first deformation section of the lateral wall passing through the first angular range and a respective second deformation section of the lateral wall passing through the second angular range.

A window unit for an aircraft includes a wall module having a side wall laterally delimiting an aircraft cabin. The side wall has a window opening and the wall module has retaining portions. A window module has a window frame accommodating at least one windowpane and the window module has fastening portions. A fastening configuration fastens the window module on the side wall in a region of the window opening. The fastening configuration is formed by a respective fastening portion engaging with a respective retaining portion. The retaining portions and the fastening portions are movable into a plug-in position by a plug-in movement of the window module and are movable from the plug-in position into a securing position by a rotary movement of the window module. The wall module and the window module are interconnected by a form-locking connection in the securing position.

A stiffened structural component for an aircraft includes a first material sheet with a first surface, and at least one elongate bulge that bulges out in a direction transverse to the first surface in order to stiffen the structural component, wherein each of the at least one bulge comprises two edges that extend along the first surface, wherein a continuous bulging surface extends between the edges, and wherein the bulges are formed integrally into the first material sheet through pressing.

A kit for manufacturing electronic aircraft control units having different specifications, the units including electronic modules of different types, including avionics platform modules comprising at least an electronic monitoring circuit and an electronic control circuit that are segregated from each other; first protection modules for protecting the avionics platform modules; first extended connection modules; and second protection modules for protecting the extended connection modules; the modules of each type being identical with one another.