Abstract: A passenger lavatory unit has an enclosing structure enclosing a lavatory space, and a toilet assembly inside the lavatory space. The toilet assembly has a toilet bowl and a shroud to support the user during use. The toilet assembly serves as a hybrid toilet to be used as a sitting toilet or as a squatting toilet. The shroud includes an upper edge surrounding an upper opening of the toilet bowl. To accommodate a user sitting position, the upper edge is provided as a toilet seat, and a feet-placing area is provided on a floor segment in front of the toilet assembly. The shroud has two lateral tread portions, one on either side of the toilet bowl. To accommodate a user squatting position, the tread portions are provided as elevated rest-platforms arranged on an intermediate level provided above a floor level and below a toilet seat level.

Abstract: A system for air conditioning at least one partial region of an aircraft includes an air providing device for providing air to be supplied to a region of the aircraft to be ventilated at a desired temperature and pressure. A supply air duct is connected at a first end to the air providing device. A second end of the supply air duct is connected to an air inlet which opens near the floor into the aircraft region to be ventilated. A control device is set up to ensure that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a speed that the air is distributed near the floor in the aircraft region to be ventilated and rises at heat sources present in the aircraft region to be ventilated.

Abstract: The present invention proposes a cap having a collar portion with three or more contact regions arranged to contact the end of a fastener around which the collar portion is provided, the collar portion having a lobed shape in cross-section such that an outwardly projecting lobe extends between each neighboring pair of contact regions. An advantage of this lobed arrangement is that the cap can tolerate relatively large manufacturing tolerances at the fastener end. For example, the cap may be for fitting over a nut or fastener head, with the contact regions of the cap being arranged to contact corresponding contact regions on a cylindrical collar base portion of the nut or fastener head. The diameter of this cylindrical collar portion may not be well controlled, so that the manufacturing tolerance is high.

Abstract: The invention relates to a structure having a panel, a stringer and a rib. The stringer has a stringer flange that is joined to an inner surface of the panel and a stringer web that extends away from the stringer flange. The rib has a rib web and a rib foot. The rib foot has a rib foot flange that is joined to the stringer web, first and second rib foot base parts that are joined to the inner surface of the panel or to the stringer flange and a rib foot web that is joined to the rib web. The rib foot is formed as a single folded piece such that the rib foot flange is connected to the rib foot web by a first folded corner, the first rib foot base part is connected to the rib foot flange by a second folded corner and the second rib foot base part is connected to the rib foot web by a third folded corner.

Abstract: A vacuum bagging system for vacuum bagging a fiber-reinforced polymer component for an aircraft or spacecraft includes a vacuum bagging film or membrane which is configured to cover and seal the component during molding. The vacuum bagging film or membrane is pre-formed, e.g. thermoformed, to a shape or to an external geometry of the component to be molded. A method of vacuum bagging a fiber-reinforced polymer component of an aircraft or space-craft, includes the steps of: arranging a component to be molded in a vacuum bagging assembly for forming a fiber-reinforced polymer component; pre-forming a vacuum bagging film or membrane to a shape or external geometry of the component; and arranging the vacuum bagging film or membrane on or over the component in the vacuum bagging assembly such that the film or membrane form-fittingly covers the component.

Abstract: A flight management assembly for an aircraft includes at least one flight management system and at least one display device, the flight management system configured to manage at least one flight plan of the aircraft and one long-term reference path of the aircraft. The flight management assembly additionally includes an auxiliary computer, the auxiliary computer being separate from and independent of the flight management system, the auxiliary computer linked to the flight management system and to the display device, the auxiliary computer configured to perform prediction computations to generate at least one short-term path, from at least the long-term reference path received from the flight management system and from current flight parameters of the aircraft and from piloting setpoints of the aircraft.

Abstract: An estimation system includes a module for measuring a current angle of attack and current flight parameters of the aircraft, a module for estimating a current lift coefficient of the aircraft from the current flight parameters and from a mass of the aircraft, a module for estimating an angle of attack for a zero lift from the current angle of attack, from the current lift coefficient and from a slope of an affine part of at least one theoretical curve describing a lift coefficient of the aircraft as a function of an angle of attack, a module for estimating the current position of the flaps of the aircraft from the angle of attack for a zero lift and a module for sending the current position of the flaps to a user device.

Abstract: A method for producing a component from a fibre-reinforced plastic includes the steps of providing a moulding tool having a tool surface, positioning a first layer of a textile semifinished product comprising dry fibres on the tool surface, arranging a second layer of an electrically conductive, resin-permeable grid on the first layer, arranging an uppermost arrangement of layers, sealing the arrangement of layers by a closure device to form a mould, introducing resin into the mould for infiltration of all the layers with the resin and curing and removal of the component.

Abstract: An air-conditioning system for an aircraft has a fresh air line, a recirculation device, an air-mixing device, an air distribution system with multiple cabin air outlets, and a control unit. The control unit is designed to determine or to receive flight-specific parameters characterizing the flight state of the aircraft, and to determine or to receive environment-specific parameters which characterize an air quality in the environment of the aircraft. A first operating state of the air-conditioning system is brought about in the case of a predefined limit value of at least one environment-specific parameter being exceeded, and a second operating state of said system is brought about during a second flight state, which is outside the first flight state. In the second operating state, the fresh air line is fluidically connected to the air-mixing device, and in the first operating state, the fresh air line is separated from the air-mixing device.

Abstract: An aircraft has: a cargo hold, a first fire-extinguishing agent container with a fluid-like fire-extinguishing agent, a first line section extending from the first container to the cargo hold, such that the fire-extinguishing agent can flow from the first container into the cargo hold, a controllable valve coupled to the first line section for controlling a flow of fire-extinguishing agent through the first line section, a concentration sensor arranged in the cargo hold for sensing a concentration of the fire-extinguishing agent in the cargo hold, and a monitoring unit. The concentration sensor is coupled to the monitoring unit for transmitting to the monitoring unit a concentration sensor signal representing the sensed concentration of the fire-extinguishing agent in the cargo hold. The monitoring unit is coupled, to the valve for controlling the valve. The monitoring unit is configured to control the valve on the basis of the sensed concentration.

Abstract: A waste-gas line has a first pipe section connectable to a battery and having an inlet end and a first flange, a separate second pipe section having a second outlet end and a second flange, and an inner sleeve and an outer sleeve, both of a non-conductive material. The inner sleeve is positioned on an outer side of the first flange and of the second flange. The outer sleeve surrounds the first flange, the second flange and the inner sleeve. The first and the second flanges are fastened to one another in such a way that at least the second pipe section is electrically insulated by the inner and the outer sleeves and, by the combination of inner and outer sleeves, is heat-resistant up to a temperature of at least 1100° C. and pressure-resistant up to a pressure of at least 8 bar, for a duration of at least 120 seconds.

Abstract: A coupling system has two coupling halves, each having a main body and a closure device arranged therein. The coupling halves can be pressed onto one another in order to release the closure devices and establish a fluid connection. By virtue of the configuration of the seals and of the closure devices, only a coarse tolerance is required for placing the coupling halves on one another.

Abstract: A battery core has a positive electrode layer, a separator layer and a negative electrode layer. The separator layer is arranged between the positive electrode layer and the negative electrode layer. The positive electrode layer, the separator layer and the negative electrode layer have nanocellulose fibres. The battery core is folded and forms a cellular structure as a core for a sandwich component. The sandwich component has an upper covering layer, a lower covering layer and a battery core. The battery core is arranged between the upper covering layer and the lower covering layer. A method for producing such a battery core is also described.

Abstract: An aircraft includes a fuselage, each wing with a movable flap element arranged on the wing, having a sensor element providing a sensor signal corresponding to vibrations on the flap element, and being movable between a retracted and an extended positions, drive means having a movable driven output connected by an actuation assembly with each of the flap element and configured such that a movement of the output effects a movement of each of the flap element between the extended and retracted positions. A control unit is adapted to compare for each sensor element during operation of an excitation means the amplitude of the vibrations in the frequency interval detected by that sensor element with a predetermined threshold of that sensor element and to provide a failure signal when for at least one sensor signal the amplitude is below the threshold of that at least one sensor signal.

Abstract: A vehicle door unit comprises a rotating lever supported rotatably about a first shaft at a first end, a door mounting coupled rotatably about a second shaft to a second end of the rotating lever, a door attached to the door mounting and being configured to cover an opening in a vehicle and to close off a vehicle interior, and a drive unit configured to rotate the rotating lever about the first shaft between a closed position and an open position. The rotating lever is configured to move the second shaft, on a movement from the closed position to the open position, on a circular path, due to which the door mounting is first moved into the vehicle interior and, on further rotation of the rotating lever, out of the vehicle interior.

Abstract: This pertains to a method for connecting fiber-reinforced structural components. In a first step of the method, a first fiber-reinforced structural component and a second fiber-reinforced structural component are supplied. In another step, the first fiber-reinforced structural component and the second fiber-reinforced structural component are heated by means of a heating device. A penetration through the first fiber-reinforced structural component and the second fiber-reinforced structural component is produced in another step by means of a fastening device. In another step, the first fiber-reinforced structural component is connected to the second fiber-reinforced structural component by means of the fastening device. This furthermore pertains to a structural aircraft element.

Abstract: The invention relates to a control device for controlling a plurality of network nodes of a computer network, comprising a master computing means for controlling the network nodes in accordance with a program, which master computing means assigns at least one program to each network node, comprising a control logic which is configured to group the network nodes in accordance with the programs assigned to these network nodes in each case and to transmit the same program in parallel to those network nodes of the same group which have been assigned this same program by the master computing means. The invention further relates to a method for operating a computer network and to a computer network.

Abstract: An oxygen supply device for an aircraft has a reaction tank for chemical oxygen generation and a pressurized tank filled with oxygen. The oxygen supply device also has an energy converter for converting thermal energy into electrical energy and also a control unit for setting a first amount of oxygen, provided by the reaction tank to a consumer unit, and a second amount of oxygen, provided by the pressurized tank to the consumer unit. The energy converter is designed to convert a thermal energy, generated by the chemical oxygen generation in the reaction tank, into electrical energy and to provide the electrical energy. The control unit is designed to set the second amount of oxygen, provided by the pressurized tank to the consumer unit, by using the electrical energy provided by the energy converter. The invention also relates to a method for supplying a passenger cabin of an aircraft with oxygen.

Abstract: A device for supporting and connecting electronic circuit cards, including a metal electronic circuit card guide which has grooves, one for each electronic circuit card, each groove being configured to guide an electronic circuit card in a direction of insertion towards a connector associated with it, solid walls for linking the grooves, slots which pass through at least one wall of the electronic circuit card guide, are separated by fins and grouped to form at least one heat exchange area and are arranged and designed so as to distribute the first air flow received from below the electronic circuit card guide in at least a second air flow above the electronic circuit card guide and in contact with the electronic circuit cards.

Abstract: The present disclosure refers to the manufacturing process of an aperture surrounding frame for an aircraft fuselage. The method includes providing a tubular braiding material (2) with a perimeter equal to the perimeter of the frame to be manufactured, cutting the tubular braiding material (2) to obtain annular-shaped braiding slices (3), providing an annular-shaped inner mold (4) where the annular-shaped inner mold has a surface with a desired shape for the aperture surrounding frame, layering up at least one braiding slice (3) around the inner mold (4), forming the at least one braiding slice (3) around the inner mold (4), and curing the aperture surrounding frame pre-form. The present disclosure also refers to an aperture surrounding frame (1) for an aircraft fuselage formed as a continuous body by at least one annular-shaped braiding slice (3) with a perimeter equal to the perimeter of the desired aperture surrounding frame.