Abstract: A door construction for an airborne vehicle includes a door, a door frame, with the shape of door frame forming a gap between the door and the door frame in the outer surface of the door and the door frame when the door is closed, and a gap sealing device comprising an inflatable tube positioned in the gap with at least one tube inlet, the inflatable tube being configured to be inflated through the at least one tube inlet and to at least partially seal the gap between the door and the door frame when inflated.

Abstract: A toilet system for a lavatory of a vehicle comprises a toilet bowl, a cladding assembly for cladding the toilet bowl, forming a hollow space between the toilet bowl and cladding assembly, and a ventilation device with at least one suction line for extracting air. The cladding assembly extends from an exterior side of the toilet bowl over an edge of the toilet bowl, and thereby partially encases the edge. At least one of the at least one suction lines is fluidically connected with the hollow space.

Abstract: A method for the manufacture of a fiber composite component with a base element, and with at least one ancillary element bonded to the base element. A reinforcement element is introduced in at least one bonding region of the base element or the ancillary element for purposes of developing a bonding surface for the ancillary element or the base element. A reinforcement element with fiber sections, the ends of which emanate from a bonding surface is provided. A fiber composite component is provided with a base element, in the bonding regions of which reinforcement elements are introduced, on the bonding surfaces of which ancillary elements are bonded with one such.

Abstract: A method for integrating a fuel cell unit into a vehicle structural component, includes determining an available receiving space in an interior structural component of the vehicle, providing two casing parts assembleable to a closed casing, providing a fuel cell having an anode, a cathode and an electrolyte, assembling the casing parts and the fuel cell to form the fuel cell unit, and inserting the fuel cell unit into the receiving space. A casing part is additively manufactured such that the fuel cell unit precisely fits into the receiving space. A casing part includes an exterior fuel inlet and an interior fuel distributor for leading a fuel from the inlet to a fuel outlet couplable with the fuel cell. A casing part includes an exterior oxidant inlet and an interior oxidant distributor for leading an oxidant from the inlet to an oxidant outlet couplable with the fuel cell.

Abstract: A sleeping box for installation in an aircraft comprises a casing which is suitable for accommodating a person located in a reclining position parallel to a longitudinal axis of the casing and which has an access aperture in the area of a front side which extends perpendicularly to the longitudinal axis of the casing. The sleeping box also comprises a fastening apparatus which is configured to fasten the sleeping box within a passenger cabin of the aircraft in such a way that the longitudinal axis of the casing extends perpendicularly to a longitudinal axis of the passenger cabin and the access aperture of the casing borders on an aisle which is present within the passenger cabin.

Abstract: A method for producing a smooth aerodynamic surface of an aircraft component is depicted and described. The method includes: provision of an aircraft component with an aerodynamic surface, which has an uneven section, introduction of a liquid or viscous, uncured sealing compound into the uneven section, introduction of a solid, precured sealing body into the uneven section in such a way that the sealing body presses into the sealing compound until the sealing compound at least partially surrounds the sealing body, curing of the sealing compound.

Abstract: A motor actuating apparatus includes three phase connections for three motor phase connections, a high-connection for a supply voltage and a low-connection for a reference potential of the supply voltage, three bridge branches having a series connection of a high-switch and a low-switch and a control device for actuating the switches of the bridge branches. The high-switches are connected to the high-connection and the low-switches are connected to the low-connection. Each of the three phase connections is connected to exactly one of the three bridge branches between the high-switch and the low-switch. The control device is adapted for actuating the switches of the bridge branches such that during a first time period a first phase connection is switched to passive and the second phase connection and third phase connection are alternatingly connected to the high-connection and the low-connection in a predeterminable duty cycle if the supply voltage is applied.

Abstract: A structural component for reinforcing the fuselage of an aircraft or spacecraft is integrally formed and segmented into surface-like stiffening sections, whereby at least one stiffening section is formed as a rigid mesh section, and at least one stiffening section is formed as a solid section.

Abstract: An aircraft air-conditioning system including an air-conditioning unit which is designed to provide cooled process air. A process air line conducts cooled process air provided by the air-conditioning unit into a working area of an aircraft cabin. A cooler supplies cooling energy to a device to be cooled which is provided in the working area of the aircraft cabin. Finally, the aircraft air-conditioning system includes a heat transfer arrangement which transfers waste heat generated by the cooler to process air flowing through the process air line.

Abstract: A wing for an aircraft, including a main wing and a wing tip device, a front blade and a rear blade of the wing tip device extending from an attachment end, a front blade leading edge extending in front of a rear blade leading edge and a front blade trailing edge extending in front of a rear blade trailing edge, in a chord direction, and at a front blade tip the front blade extending under a different dihedral angle than the rear blade at a rear blade tip. The front blade leading and trailing edges, as well as the rear blade leading and trailing edges have a tangent-continuous developing. The front blade leading edge extends tangent-continuously with the wing leading edge. The rear blade trailing edge extends tangent-continuously with the wing trailing edge. The front blade trailing edge extends behind the rear blade leading edge, in the chord direction.

Abstract: An access system for a vehicle is provided. The access system includes a central rights management unit, an access control device, and a portable identification medium. The access control device makes it possible to run verification mechanisms on the identification medium with the use of input means for interacting with a user. To this effect the identification medium includes an authentication unit and also a data part that depends on it which for viral epidemic propagation of privilege data may forward this data to access control devices without its own data connection. Even in the case of an incomplete infrastructure, extensive vehicle movements and very substantial fluctuations in personnel it is nevertheless possible to achieve very high security and reliability of enabling access and vehicle functions.

Abstract: A construction group of an aircraft for feeding a line to a connector section of the cabin module includes a flex zone for providing of at least one cabin module having a connector section for physical connection to a line of the aircraft. The flex zone is configured to receive different cabin modules and/or a cabin module at different positions. The construction group further includes a guide element for guiding the line to be connected to the connector section along the fuselage of the aircraft, and a support element extending along the flex zone for feeding the line from the guide element to the connector section, wherein during the receiving of the construction group in the aircraft, the longitudinal axis of the support element includes a component in direction of the attitudinal axis of the aircraft.

Abstract: An aircraft includes a fuselage having a tapered rear shape, a landing gear for moving the aircraft on a runway, a wing attached to the fuselage, at least a main engine for providing a main thrust and a rear fan, wherein the rear fan is attached to a tail section of the fuselage, wherein the aircraft is designed for conducting a take-off rotation around the landing gear during take-off from the runway, such that the tail section of the fuselage approaches the runway, wherein the rear fan is an open fan having fan blades extending in a radial direction to a longitudinal axis of the fuselage, wherein the fan blades are dimensioned to equal at least a boundary layer thickness of the flow along the fuselage and to be smaller than the gap between the runway and the tail section of the fuselage during the take-off rotation.

Abstract: An aircraft server system includes a wireless transceiver configured to wirelessly emit and receive radio frequency signals in the passenger cabin of an aircraft, and a plurality of virtual network server units, each configured to remotely control one or more virtual network clients on one of a plurality of personal electronic devices, PEDs, wirelessly connected to the aircraft server system.

Abstract: A method for controlling the operation of an auxiliary power unit supplying an aircraft air conditioning system with compressed process air includes determining a heating or cooling requirement of an aircraft region to be air-conditioned, determining a desired value of at least one process air flow parameter in dependence on the determined heating or cooling requirement of the aircraft region to be air-conditioned, controlling the operation of the auxiliary power unit in dependence on the determined process air flow parameter desired value, acquiring an actual value of the at least one process air flow parameter, comparing the process air flow parameter actual value with the process air flow parameter desired value and controlling the operation of the auxiliary power unit in dependence on the result of the comparison of the process air flow parameter actual value with the process air flow parameter desired value.

Abstract: The invention relates to a fluid actuator for influencing the flow along a flow surface by ejection of a fluid. By means of a like fluid actuator a continuous flow is distributed to at least two outlet openings in order to generate fluid pulses out of these outlet openings. Control of this distribution takes place inside an interaction chamber supplied with fluid flow via a feed line. Into this interaction chamber there merge at least two control lines via control openings to which respective different pressures may be applied. The flow in the interaction chamber is distributed to the individual outlet openings as a function of the pressure difference at the control openings.

Abstract: An aircraft seat kit with one aircraft seat, and an aircraft seat and cabin arrangement with at least two aircraft seats for being mounted one after the other onto a seat rail are described. The seat rail provides a grid with a pre-determined grid pitch for mounting the at least two aircraft seats. Each of the at least two aircraft seats includes: a seating structure, a support for supporting the seating structure, and one of two types of seat rail adapters for mounting the support onto the seat rail. The two types of seat rail adapters differ from each other in that they configure at least one aircraft seat with a different distance in a longitudinal direction between a seat reference point and a reference mounting position, respectively.

Abstract: A rotary joint includes a socket rod having a socket rod flange with a basically spheroid con-cave bearing surface at a first end, a housing nut encircling the socket rod and having a threaded wrenching head, a ball rod having a basically spheroid convex bearing surface and threaded side walls around the convex bearing surface, and a joint actuator configured to actuate relative movement of the socket rod flange and the ball rod. A diameter of the threaded side walls of the ball rod corresponds to a diameter of the threaded wrenching head of the housing nut.