Abstract: A vortex generator is useable in a model in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular, aircraft, to save wind tunnel time, it is suggested to configure the vortex generator to be switchable. A switchable vortex generator can be used, in particular, on models in fluid-dynamic channels and in fluid-dynamic channel tests.

Abstract: This application describes a tool, an arrangement, and a method of manufacturing a component. The manufacturing of the component is achieved by a resin transfer from a storage chamber via a transfer line into a working chamber. Before the resin transfer, taking place, for example by a compressed air charging of the storage chamber, the storage chamber is filled with an amount of resin adjusted to the size of the component. Furthermore, a semi-finished product, consisting of cut-to-size reinforcement fibers, is inserted into the working chamber that is adjusted to the form of the component to be produced. Storage chamber, transfer line, and working chamber are configured in a one-piece mould casing of the tool. The application further describes a component manufactured by the above-mentioned tool or by the above-mentioned method respectively.

Abstract: A frame element (10; 10?) for use in an aircraft component assembly system (46) is attachable to an aircraft structure (36) and comprises at least one fastening device for fastening at least one aircraft interior component (34) or at least one insulation pack (52) to the frame element (10; 10?). An aircraft component assembly system (46) comprises a plurality of such frame elements (10; 10?). In a method of fitting a component (34, 52) in an aircraft, a frame element (10; 10?) is provided. At least one interior component (34) or at least one insulation pack (52) is fastened to the frame element (10; 10?). Then the frame element (10; 10?) having the at least one interior component (34) or the at least one insulation pack (52) fastened thereto is attached to an aircraft structure (36).

Abstract: A fuel supply unit (10) for a fuel cell system which is in particular suitable for use in an aircraft comprises a fuel tank (12) and a feed line (14), which connects the fuel tank (12) to an inlet (16) of a fuel cell (18). A tank isolation valve (28) is disposed in the feed line (14). A removal line (46) connects an outlet (20) of the fuel cell (18) to an unpressurised region of the aircraft and/or the outer atmosphere. The fuel supply unit (10) also comprises a sensor (44) for detecting an electrical voltage in the fuel cell (18) and an electronic control unit (45) which is adapted to receive signals output from the sensor (44) and which is adapted to detect a fault caused by an unintentional opening or a failure of the tank isolation valve (28) based on the sensor signals, when in a quiescent operational state of the fuel cell system electrical energy is generated by the fuel cell (18).

Abstract: A device for distributing air in a cargo aircraft includes using an air distribution system which is connected to a cargo deck. The air distribution system includes a source for bleed air, at least one air conditioning unit for treating the bleed air, a mixing unit which receives an air supply of recirculation air exiting the cargo deck and treated bleed air from the air conditioning unit, and at least one shut-off valve between the mixing unit and the cargo deck in order to interrupt or completely release the air supply to the cargo deck. A control unit establishes a desired air volume balance for the current operating state of the air distribution system and adjusts the flow volume through the at least one air conditioning unit such that the pressure prevailing in the mixing unit remains at a constant, predetermined value for all operating states.

Abstract: A method for joining a first component made of a plastic material, in particular a thermoplastic and/or thermosetting plastic material, to a second component by applying a joining element on the first component, wherein the joining element has a supporting plate formed of a thermoplastic and/or thermosetting plastic material and comprising a connecting means and a supporting plate bore. A joining element for creating a junction in accordance with the method, is also disclosed. Furthermore, a device, in particular for performing the method, is disclosed.

Abstract: An aircraft cooling system includes a first coolant stream which cools at least one first heat load and a second coolant stream which cools at least one second heat load. The aircraft cooling system is formed such that the first heat load and the second heat load are thermally coupled together. The first heat load and the second heat load can be formed by two mutually redundant aircraft components. A third coolant stream thermally couples the first heat load and the second heat load together. The third coolant stream can be cooled by a heat sink, such as the outer skin of the aircraft in a bilge region.

Abstract: A wiring arrangement for protecting a bleed air supply system of an aircraft against overheating is associated with a bleed air supply system. The bleed air supply system includes a bleed air source, a bleed air feed, a shutoff valve arranged in the bleed air feed and a leakage monitoring device with a monitoring control device, which is connected via a shutoff circuit to the shutoff valve in such a way that the shutoff valve is closed when the shutoff circuit is interrupted. The wiring arrangement includes a thermal switch, which is connected in series with the shutoff valve and the monitoring control device to the shutoff circuit and which, once a predetermined limit temperature has been exceeded, interrupts the shutoff circuit.

Abstract: The application relates to a method for the electronic archiving of data objects by means of a data processing device, wherein the method comprises the following steps: receipt of a hash value tuple comprising one or a plurality of hash values, wherein each hash value is assigned to a data object, receipt of time information on the hash value tuple indicating a time period within which the hash values of the hash value tuple should be electronically archived and comparison of the time information with a predetermined time specification, wherein archiving steps are carried out if the time information specifies a time period for electronic archiving that is shorter than the predetermined time specification. The application furthermore relates to a computer program product.

Abstract: A vortex generator is useable in a model in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular, aircraft, to save wind tunnel time, it is suggested to configure the vortex generator to be switchable. A switchable vortex generator can be used, in particular, on models in fluid-dynamic channels and in fluid-dynamic channel tests.

Abstract: A method for monitoring loading and unloading procedures in the cargo holds of an aircraft, in which method the actual states that are present in each cargo hold are acquired. Furthermore, the invention relates to a device as well as to a computer program product for implementing the method according to the invention.

Abstract: The invention relates to a refrigerating device (10), in particular for an aircraft, having a refrigerant circuit, in which a refrigerant container (12), an expansion valve (14), an evaporator (16), a compressor (20) and a condenser (22) are disposed. To save energy during operation and to increase the reliability and availability of the refrigerating device (10), in the refrigerant circuit there is a compressor bypass line (26), in which a bypass valve (18) is disposed, and a refrigerant pump (30) that is disposed downstream of the condenser (22) and upstream of the evaporator (16). It is possible to dispense with the refrigerant pump (30) if the condenser (22) is disposed at a higher level than the evaporator (16) in the refrigerant circuit.

Abstract: The invention discloses the multistage cooling of an aircraft electronic system (2) with at least one electronic component which delivers heat. The multistage feature results from the use of a plurality of circuits for transferring the waste heat. An internal coolant (14) circulating in a closed circuit which is thermally coupled to the electronic component carries heat from the at least one electronic component to a heat exchanger (6) which delivers the heat to an external coolant which flows and/or circulates from a source outside of the aircraft electronic system (2) through the heat exchanger (6) to a sink outside of the aircraft electronic system (2). The internal coolant flows from the heat exchanger (6) in the direction of the at least one electronic component and/or circulates in a closed circuit.

Abstract: In a device for limiting the advance during a drilling operation, which can be used in conjunction with a hand drill or with an automatic manufacturing machine, the device comprising a housing with a stop cage and a spindle mounted rotatably and axially displaceably in the housing, and a stop which is adjustable in the axial direction being arranged for limiting the advance, the invention consists in that the stop cage (2a) comprises a pin fixed to the housing for breaking the chips, with a housing-side end and a free end, in such a way that it extends approximately parallel and directly adjacent to the workpiece surface and approximately radially from the outside towards the drilling tool in such a way that its free end almost touches the countersink. Damage to the surface of workpieces is prevented by the invention, so that corresponding refinishing is avoided. Moreover, the removal of the coiled chips from the drilling tool previously necessary after each drilling cycle is dispensed with.

Abstract: A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied with fuel via a fuel supply circuit (122) that extends from a reservoir (124) that is arranged at the airframe (110), whereby the airframe (110) includes at least one source of thermal effluents (134), wherein the process includes at least partially dissipating—at the level of at least one propulsion system (112)—the thermal effluents that are generated at the airframe (110) by using as coolant the fuel that is used for supplying the gas turbine engine (116).

Abstract: The invention relates to a method for configuring a test arrangement for a device to be tested, which is one component of a system containing, several components. The components of the system are described by data records, which have elements that describe relationships of components with one another. The method includes linking the data records to generate a system description based on the linked data records, simulating of the system by a simulation based on the system description, wherein an image of the device to be tested is in the simulation. The method also includes removal of the image of the device from the simulation and provision of one or more test interfaces in hardware for communication between the simulation facility and the device.

Abstract: A cooling air supply system for an aircraft is configured to supply cooling air from the surroundings of the aircraft to at least two devices requiring cooling air (38, 44, 56) within the aircraft. The cooling air supply system includes an air inlet, an air channel communicating with the air inlet, and an air distribution device for the distribution of air from the air channel to the at least two devices requiring cooling air. The air inlet is sized to provide sufficient air flow to accommodate a maximum cooling air requirement of the at least two devices requiring cooling air.

Abstract: A fiber composite component comprising at least two, first and second partial elements bordering one another, each having a fiber structure and different matrix systems which respectively embed the fiber structure and cure differently from a liquid state is produced by liquifying the matrix system of the first partial element so that it either penetrates irregularly into the region of the bordering second partial element or leaves an unwetted region in the first partial element adjacent the second partial element, and subsequently liquifying the matrix system of the second partial element so that it can be cured abutting the irregular boundary surfaces of the matrix system of the first partial element. The intermeshing or interlocking of the matrix systems with one another and the fibers increase shear strength.

Abstract: An aircraft air-conditioning system is disclosed, which includes at least one heat exchanger to which coolant circulating in a cooling circuit of a cooling system and air are fed. The coolant cools the fed air in the heat exchanger, and the air leaving the heat exchanger enters the aircraft cabin. The coolant of the cooling system is always in the liquid state in the cooling circuit. The liquid coolant can also cool an aircraft seat or a sitting area of the aircraft seat.

Abstract: An adjustable orifice for use in an aircraft air conditioning system includes a first orifice element which has an orifice frame as well as a first orifice area. When the orifice is assembled at a duct, the first orifice area of the first orifice element leaves open a part of a cross section of the duct. The orifice also includes a second orifice element with a second orifice area. When the orifice is assembled at the duct, the second orifice area of the second orifice element leaves open a part of the cross section of the duct. The second orifice element is rotatable about an axis, so that the second orifice area is rotatable relative to the first orifice area in order to set a desired flow cross section in the duct.