Abstract: A cargo hold comprises at least one luggage holder having at least one luggage compartment, wherein, when the hatch is in the closed state, the luggage holder is arranged in the cargo hold, and wherein, when the hatch is in the opened state, the luggage holder can be brought out of the cargo hold and can be introduced therein again by means of a guide mechanism in such a manner that the luggage holder, when it is brought out of the cargo hold, is arranged substantially radially to the substantially elliptical cross section of the fuselage.

Abstract: A disruption device for fixing to an aerial vehicle. The disruption device is adapted to disrupt at least one radio path between at least one receiving unit of an unmanned flying body and at least one transmitting unit provided for controlling the flight path of the unmanned flying body. An aerial vehicle having the disruption device is further provided.

Abstract: A cargo hold comprises at least one luggage holder having at least one luggage compartment, wherein, when the hatch is in the closed state, the luggage holder is arranged in the cargo hold, and wherein, when the hatch is in the opened state, the luggage holder can be brought out of the cargo hold and can be introduced therein again by means of a guide mechanism in such a manner that the luggage holder, when it is brought out of the cargo hold, is arranged substantially radially to the substantially elliptical cross section of the fuselage.

Abstract: A disruption device for fixing to an aerial vehicle. The disruption device is adapted to disrupt at least one radio path between at least one receiving unit of an unmanned flying body and at least one transmitting unit provided for controlling the flight path of the unmanned flying body. An aerial vehicle having the disruption device is further provided.

Abstract: A luggage article is provided. The luggage article includes a shell, an electronic processing module integrated with the shell, and an electronic display coupled to the electronic processing module and arranged on an outer surface of the shell. The processing module is configured to control the display to display information items to a user of the luggage article. The luggage article may be configured to display itinerary or travel related information on the display under the control of a user of the luggage article.

Abstract: A wearable device that is wearable by a user and connectable with one or more aircraft related systems, a device system comprising a plurality of such wearable devices, and an aircraft comprising such a device system. The wearable device that is connectable to one or more aircraft related systems comprises a system interface via which the wearable device is connectable to one or more aircraft related systems, and a control unit configured to communicate with at least one of the one or more aircraft related systems via the system interface.

Abstract: A riblet structure for a flow surface is provided. The riblet structure has a multitude of riblets that comprise a matrix material which includes reinforcement elements. The reinforcement elements can be designed as reinforcement fibers that extend in the longitudinal direction or as particles. In this manner the abrasion resistance can be improved and erosion can be retarded.

Abstract: A compression mold for use in a compression molding tool, is manufactured by an additive manufacturing method, particularly electron beam melting, selective laser melting, or selective laser sintering. A method for manufacturing a compression mold for use in a compression molding tool includes forming a compression mold body of the compression mold with an additive manufacturing (AM) method.

Abstract: A wearable device that is wearable by a user and connectable with one or more aircraft related systems, a device system comprising a plurality of such wearable devices, and an aircraft comprising such a device system. The wearable device that is connectable to one or more aircraft related systems comprises a system interface via which the wearable device is connectable to one or more aircraft related systems, and a control unit configured to communicate with at least one of the one or more aircraft related systems via the system interface.

Abstract: A forming tool with a predefined mold portion is provided in a method for producing a reinforced fiber composite component for aviation and aerospace. A forming/support element is molded by means of the mold portion of the forming tool. A semi-finished fiber product is then deposited at least in portions on the shaped forming/support element. The deposited semi-finished fiber product is deformed by means of the forming/support element to form at least one reinforcing portion. The forming/support element is then removed from the forming tool together with the reinforcing section formed on this element, followed by defined positioning of the reinforcing section thus formed with respect to an associated fiber composite component portion by supporting with the forming/support element. The reinforcing portion is cured to form the reinforced fiber composite component. A forming device is provided with a predefined mold portion which holds a forming/support element such that it can be removed.

Abstract: A manufacturing method for reinforced structural elements includes providing a reinforcement structure including a first material, and embedding the reinforcement structure in an encasing matrix comprising a second material using additive layer manufacturing, ALM. A manufacturing tool for reinforced structural elements includes a positioning component including a jig for clamping a reinforcement structure including a first material and an ALM robot configured to embed a reinforcement structure clamped in the jig in an encasing matrix including a second material.

Abstract: A passenger seat has a backrest and a seat which has first and second sections each having a first surface for a seat area and a second opposite surface. The second section pivots relative to the first section between a first position, in which the first surfaces of the first and second sections form a usable total seat area, and a second operational position, in which the second section is folded relative to the first section in the direction towards the backrest. Attached to the second seat section is a holder movable relative to the second surface of the second seat section between a first position, in which the holder extends substantially parallel to the second surface of the second seat section, and a second position, in which the holder extends at from 60° to 120° relative to the second surface of the second seat section.

Abstract: The present invention relates to a production method for a workpiece (15) composed of a fibre-composite material, having the following steps: at least one support means (3) is provided. A main material (6) composed of a pre-impregnated fibre semi-finished product and/or of a secondary material (7) are/is applied to the at least one support means (3) in order to form at least two blank-mould areas (1, 10), in such a manner that at least one of the at least two blank-mould areas (1, 10) has the main material, and at least one of the blank-mould areas (1, 10) has the secondary material. The blank-mould areas (1, 10) are pressure-bonded to one another to form a workpiece blank (14) such that the at least one support means (3) is provided on a surface of the workpiece blank (14). The at least one support means (3) and the secondary material (7) are removed from the workpiece blank (14) in order to form the workpiece (15).

Abstract: The invention relates to a method for joining cured stringers to at least one structural component of an aircraft or spacecraft, including placing the stringers onto the at least one structural component, depositing and pressing respective vacuum film strips such that each strip is attached to a pair of stringers and present between the pair of stringers with the use of vacuum sealing means in such a manner that a continuous vacuum arrangement, comprising the covering vacuum films and the vacuum film strips, is formed, and pressurized joining of the stringers to the at least one structural component by means of the continuous vacuum arrangement formed.

Abstract: A luggage article is provided. The luggage article includes a shell, an electronic processing module integrated with the shell, and an electronic display coupled to the electronic processing module and arranged on an outer surface of the shell. The processing module is configured to control the display to display information items to a user of the luggage article. The luggage article may be configured to display itinerary or travel related information on the display under the control of a user of the luggage article.

Abstract: The present invention relates to the use of live mycobacterium of the M. tuberculosis complex for preparing a medicament, wherein the function of the zmp1-gene is inactivated, pharmaceutical compositions prepared from such mycobacteria as well as a method for the treatment and/or prophylaxis of a disease or medical condition using said pharmaceutical composition.

Abstract: A method for manufacturing a flow body with a desired surface texturization in order to optimize its resistance. The method can include applying a coat of clear varnish on at least the primary surface areas of the flow body, and hardening the coat of clear varnish by exposing it to infrared radiation, determining the coordinates for the coated flow body surface in the form of real flow body data, determining a real flow body model for the outer shape of the flow body with the desired surface texturization to be created, and using a material removing laser to mill the desired surface texturization out of the clear varnish coating, along with a laser material removing device for creating a desired surface texturization on a coated flow body.

Abstract: The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft. A vacuum arrangement required for the joining is produced in two parts. In a first step, each precured stringer is covered in advance by a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Vacuum film strips are subsequently arranged in each case on adjacent stringers and over an intermediate space between the adjacent stringers. With the use of a vacuum sealing means, the vacuum film strips and the covering vacuum films 8 form a continuous vacuum arrangement. The stringers are subsequently joined under pressurization to the structural component with the use of this vacuum arrangement.

Abstract: A digital data storage device physically stores blocks of identical data only once on its storage medium wherein a second or even further identical blocks are stored only as reference referring to the first block of these identical blocks. By this technique, storage of duplicate data is most effectively avoided on the lowest storage level of the disk storage device, even in cases where identical blocks are written by different operating Systems. In the preferred embodiment, the underlying storage medium (magnetic hard disk, optical disk, tape, or M-RAM) is segmented into two areas, the first area particularly comprising a relatively small block reference table and the remaining physical storage area for storing real blocks of information.

Abstract: The invention relates to a method for determining at least one characteristic parameter of a CRP specimen (3, 4), in particular a specimen of prepreg material, for aerospace, comprising the following method steps: presenting the specimen (3, 4), irradiating the. specimen (3, 4) with a predetermined spectrum of electromagnetic radiation, recording the interaction between the specimen (3, 4) and the electromagnetic radiation in a data record (20) and determining the at least one characteristic parameter from the recorded data record (20).