Abstract: A vehicle includes a passenger compartment and a cargo compartment separated by a floor structure, and a cargo unit including a storage rack arrangement and a transport arrangement operable for selectively transporting objects between the storage rack arrangement and a predetermined transfer position in a cavity of the cargo unit. The transport arrangement includes a conveying apparatus including a table unit movable along a vertical transport path, and the vehicle includes a mounting means adapted for securing the cargo unit in a predetermined operating position inside the cargo compartment, in which an access aperture in an upper cover of the cargo unit is disposed in alignment with a through hole in the floor structure. A lift apparatus including a gripping device is operable to convey objects from the transfer position through the access aperture and the through hole between the cargo compartment and the passenger compartment.

Abstract: The invention pertains to a protective device for a pressure line for conveying pressurized fluids, as well as to a pressure line section with a pressure line for conveying pressurized fluids and a corresponding protective device.

Abstract: A construction kit for a housing structure of a monument for a cabin of a vehicle, in particular of an aircraft includes a plurality of integrally formed sandwich panels which each have two cover panels, which surround a core, and are formed with panel connecting structures which are each formed as a plug region or as a mating plug region. The mating plug region is formed so as to be complementary to the plug region in such a way that a plug region of a sandwich panel can be plugged into the mating plug region of another sandwich panel to connect the sandwich panels.

Abstract: A warning light circuitry includes a first logic gate adapted for receiving a first, a second, a third, and a fourth input signal; a second logic gate adapted for receiving a fifth, a sixth, and a seventh input signal; a third logic gate electrically connected to the first and second logic gate; and a warning light electrically connected to the third logic gate. The first logic gate is adapted for providing a first output signal to the third logic gate upon receiving the first, the second, the third, and the fourth input signals. The second logic gate is adapted for providing a second output signal to the third logic gate upon receiving the fifth, the sixth, and the seventh input signals. Therein the third logic gate is adapted for triggering the warning light upon receiving the first or the second output signal.

Abstract: An aircraft monument includes an elongate cavity having an open end and a lift apparatus mounted to the monument and adapted for lifting goods along the longitudinal axis of the cavity. The monument is adapted to be mounted on a floor structure of an aircraft separating two compartments of the aircraft from each other such that the open end of the cavity faces the floor structure. The lift apparatus includes a guide means including two straight guide members spaced apart, and extending parallel to the longitudinal axis of the cavity, a conveying means including two conveying members each mounted to a different guide member, a moving means for linearly moving the two conveying members, a control means for controlling the moving means to synchronize the linear movement of the conveying members, and a gripping means secured to the conveying means and adapted for selectively gripping and releasing goods.

Abstract: A method for producing a part is provided, the method including the following: a first step of a computer-aided simulation for a plurality of cross-sections of the part based on a 3D cross-sectional model and obtaining a first result, which represents shrinkage of the part basically caused by thermal and/or chemical reactions; a second step of a further computer-aided simulation for the plurality of cross-sections of the part based on a 2D shell model and obtaining a second result, which represents shrinkage of the part basically caused by thermal and/or chemical reactions; determining a scale factor for the second result in such a way that the second result corresponds to the first result; determining scale factors for any cross-sections which are between two adjacent cross-sections from the plurality of cross-sections, by interpolation; predicting a distortion of the part; and producing the part based on the predicted distortion of the part.

Abstract: A sheet entity, in particular for use as a skin panel for an aircraft fuselage, with a carbon fiber-reinforced plastic laminate and an aluminum-based metal laminate in the edge region, which are connected with one another by means of an adhesive bond, and thereby are electrically insulated from one another, and are stepped back by layers. Also disclosed is a fuselage cell of an aircraft with at least one sheet entity of this type.

Abstract: An apparatus and method for producing a fiber-reinforced plastics casting (FRP), includes a molding box filled with free flowing molding material, in what a prototype of casting or a textile preform is inserted, forming a mold cavity for infiltration the inserted preform of textile with synthetic resin material in order to form a fiber-reinforced plastics casting (FRP).

Abstract: A sandwich panel for an aircraft includes a lower top layer, an upper top layer and a core layer, wherein the core layer in turn includes pins. The pins extend from a lower top layer in the direction of the upper top layer, and the pins are interconnected by rods. In addition, the rods run inside the core layer, and the pins and rods form a one-piece network.

Abstract: The present invention provides a connecting device for connecting an unhardened fiber layer which is arranged on a surface section of a fiber compound structure to the fiber compound structure. The connecting device comprises pressure cushion comprising a pressure cap for being arranged above the surface section and a pressure tight cap mat which is pressure tightly connected to a circumferential border of the pressure cap, thereby forming a pressure area which is limited by the pressure cap and by the cap mat. The connecting device further comprises a pressure inducing means for inducing an overpressure which presses the cap mat against the fiber layer into the pressure area. According to a further aspect the invention provides a processing method for processing a fiber compound structure. In a first step at least one unhardened fiber layer is arranged on a surface section of the fiber compound structure.

Abstract: A fuselage cell for an aircraft includes at least two shell segments forming a fuselage cell. The shell segments are provided with a plurality of longitudinal and/or circumferential reinforcements that are integral with a skin panel of the respective shell segment. The reinforcements at least sectionally form a closed cross-sectional geometry together with at least the skin panel of the corresponding shell segment in order to create at least one hollow space, wherein at least one system component at least sectionally extends and/or at least one system medium is at least sectionally routed in the at least one hollow space. The reinforcements also fulfill the function of accommodating at least part of the system components and system mediums of the technical equipment of the aircraft. This results in weight savings and a simplified installation because the number of required mountings and connectors for the system components is reduced.

Abstract: The invention relates to a method for producing a plastic foil tube with an intended cross-section that derives from a circular cross-section as a means for the production of fiber compound components for aviation or aerospace. It comprises the following method steps: mounting a semi-finished tube on a core tool; charging the mounted semi-finished tube with a predetermined force to press the semi-finished tube on a core cross section of the core tool, wherein while charging the mounted semi-finished tube with the force crinkles are formed in longitudinal direction of the semi-finished tube; heating the semi-finished tube to a predetermined forming temperature for a predetermined time period for the production of the plastic foil tube with the intended cross-section and stripping the plastic foil tube which is formed in such a manner and cooled down off the core tool.

Abstract: A mounting device for a visual barrier of two areas of a passenger cabin of a transport. The mounting device provides an enlarged visual range in the cabin when the barrier is not used. The mounting device includes, but is not limited to a mounting module that is adapted for being inserted in a luggage compartment.

Abstract: A double-wall pipe for a transportation means which includes an outer pipe and an inner pipe extending therein. The outer pipe has two pipe segments which are formed like half-shells and are joined together to form the outer pipe along the longitudinal edges thereof. In this way, it is possible to make both the outer pipe and the inner pipe of metal, such that the wall thickness of the inner pipe can be relatively small.

Abstract: A system for repairing a structural component, in particular an aircraft structural component, includes a repair patch which is connected to the structural component in such a manner that it covers an opening in the structural component resulting from removing a damaged region of the structural component. A sensor is fastened to the repair patch in a region of the repair patch covering the opening in the structural component and is designed to detect strains and/or stresses occurring in the repair patch. An evaluating device is adapted to evaluate the strain values and/or stress values detected by the sensor and, in dependence on the result of this evaluation, output a signal which is characteristic of the quality state of the connection between the structural component and the repair patch.

Abstract: A particle separator comprises a pipeline that allows a fluid to flow in a curved direction of flow. The particle separator includes an inlet region, a curved deflection region, which in the direction of flow follows on from the inlet region, with an inside wall and an outside wall, and a delimitation body. The delimitation body at least in some sections extends between the inside wall and the outside wall in the interior of the deflection region and is curved in the same direction as the deflection region.

Abstract: An aircraft monument for installation in an aircraft cabin comprising a first functional module, a second functional module and a side wall for delimiting the first module from at least one of a region of the aircraft cabin adjacent to the first module and a region of the aircraft monument adjacent to the first module. The side wall is movable between a first and a second operational position and comprises a first side-wall region separating the first and second functional modules and in the second operational position, the side wall is displaced in the direction of the second module relative to its position in the first operational position, so that a movement of the side wall from its first operational position into its second operational position results in an enlargement of a base area of the first module and a corresponding diminution of a base area of the second module.

Abstract: A supply channel for a means of transportation is provided. The supply channel comprises a fluid line, an inflatable projection element having an opening and a pressure sensor which is configured for determining a pressure difference between an internal pressure in the projection element and an ambient pressure. The inflatable projection element is connected to the fluid line via the opening. The projection element is configured for being transferred from a compressed state to an inflated state by filling it with fluid from the fluid line. The projection element provides a predetermined projection surface in the inflated state.

Abstract: The present invention provides a structural element for an aircraft and spacecraft, having a core which includes core regions which are uncoupled from one another by means of an expansion joint arranged between the core regions. The present invention further provides a method for producing a structural element for an aircraft or spacecraft, including the following method steps: providing a core of the structural element, which core includes core regions; and arranging an expansion joint between the core regions. The present invention relates still further to an aircraft and/or spacecraft having such a structural element.

Abstract: The present invention relates to a method and a device for identifying an allocation of control circuits to at least one control device. In this context, it can be checked whether wiring for example of heating circuits and/or sensors to a central control device is correct. Provided actuation patterns are switched on at a number of control circuits. This makes it possible to identify correct wiring efficiently and without error. The invention can be used in vehicle construction, and especially in aircraft construction.