Abstract: Method for manufacturing a composite fiber component (1) the method comprising the following method steps: forming a moulding core (4) comprising a hollow profile (15) made of segments (16a . . . d) in order to establish an external geometry of the moulding core (4), wherein the segments (16a . . . d) of the moulding core (4) each extend in the direction of the longitudinal axis of the moulding core (4) and are each constructed so as to be pivotable about an axis running in the longitudinal direction of the moulding core (4), between a folded position (A), and an unfolded position (B) of the hollow profile (15) of the moulding core (4), wherein the segments (16a . . . d) are constructed so as to be coupled to one another via connections (18a . . . d, 19a . . .

Abstract: An apparatus for pressurizing an aircraft cabin structure and measuring the amount of leakage of the aircraft cabin structure comprises an air supply line which at a first end is connectable to a pressurized air source and which at a second end is connectable to the aircraft cabin structure so as to supply pressurized air from the pressurized air source into the aircraft cabin structure, an air supply valve disposed in the air supply fine, a pressure sensor for sensing the pressure inside the aircraft cabin structure and for providing signals indicative of the pressure inside the aircraft cabin structure, an air discharge line which at a first end is connectable to the aircraft cabin structure and which at a second end is connectable to an air discharge opening so as to discharge air from the inside of the cabin structure to the air discharge opening and an air discharge valve disposed in the air discharge line.

Abstract: A system is provided for water purification for a recirculation shower in a transport with a filtration unit, a first backwash line and a second backwash line. The filtration unit is designed to filter used shower water. The first backwash line and the second backwash line are designed to clean the filtration unit with a backwashing. The first backwash line is designed to convey backwash water to the filtration unit. The second backwash line is designed to discharge backwash water from the filtration unit.

Abstract: The invention pertains to an inerting system for an aircraft featuring at least one air separation module with at least one air inlet, a first air outlet and a second air outlet. The air separation module is designed for splitting an input air flow into a first air flow and a second air flow, wherein the first air flow is enriched with oxygen in comparison with the input air flow and discharged at the first air outlet and the second air flow is enriched with nitrogen in comparison with the input air flow and discharged at the second air outlet. In comparison with known inerting systems, the inerting system according to the invention is characterized in that the air inlet can be connected to an air extraction point in an air processing system and the inerting system is designed for routing the first air flow into a cabin to be air-conditioned.

Abstract: A distributor for connecting at least a first multiphase line to at least a second multiphase line, comprising a plurality of contacting points, wherein each of the contacting points is arranged to electrically connect a phase of the first line to a corresponding phase of the second line, the plurality of contacting points being arranged approximately on a circular line.

Abstract: The present invention provides a server system, in particular for an aircraft or spacecraft, comprising an integration device which has at least two server modules which have in each case at least one program-controlled arithmetic-logic means, at least one memory which is coupled with the program-controlled arithmetic-logic means, and at least one communication interface which is coupled with the program-controlled arithmetic-logic means, comprising at least one data line which interconnects the two server modules for data communication by the communication interfaces thereof, and comprising a server interface which is configured to connect the integration device to a data network for data communication by the communication interfaces of the server modules, the integration device being configured to exchange data with the data network. The present invention also provides an aircraft or spacecraft and a method.

Abstract: An aircraft includes, but is not limited to a central fuselage body without horizontal stabilizer, at least one high-lift control surface, at least one vertical stabilizer that is arranged on the central fuselage body and at least one extendable compensation control surface. The compensation control surface may be moved independently of the high-lift control surface of the aircraft and generates a positive tail-heavy pitching moment when it is moved into the flow against the aircraft. Due to this measure, a negative pitching moment during the actuation of high-lift control surfaces may be at least partially eliminated without influencing the high lift. Rudder segments that may be moved opposite to one another on two vertical stabilizers that are arranged mirror-symmetrical referred to the longitudinal axis of the aircraft preferably are used for this purpose.

Abstract: A connection device for a plurality of cabin components of an aircraft includes a rail extending in a longitudinal direction of an aircraft structure, wherein the plurality of cabin components is disposed on the rail; and a plurality of adjustment devices configured to self-adjust each of the plurality of cabin components in the longitudinal direction.

Abstract: A supporting component is provided for reinforcing the skin of an aircraft or spacecraft, for example a stringer or former, this component being configured as a closed profile (hollow profile), such that a system medium (M) can be conducted through the structural component. In this respect, the hollow profile itself serves as a load-bearing component.

Abstract: A window funnel for an aircraft is provided, which has a ring made of an elastic material, which is arranged by means of an adhesive layer on an outer side of the window funnel, the ring having a hollow profile. The ring serves as a sight screen, light screen and dust screen for the rear side of the window funnel.

Abstract: An aircraft (F) with wings (1; 1a, 1b) and a system for minimizing the influence of unsteady flow states, wherein the wing consists of a respective main wing (M) and at least one control flap (S) adjustably arranged relative thereto, a adjusting drive (21) for activating the at least one control flap (S), as well as a sensor arrangement for acquiring the setting position of the control flap (S), wherein the system for minimizing the influence of unsteady flow states exhibits: At least one arrangement (15) of flow-influencing devices (16) for influencing the fluid flow over the surface segment (10), which are functionally connected with the flight control device, and incorporated in at least one surface segment (10; 11a, 12a; 11b, 12b) of the main wing (M) of each wing (M; 1a, 1b) extending in a respective wingspan direction and/or at least one control flap (S), A detection device for detecting unsteady flow states acting on the aircraft, An actuating function that is functionally connected with the flow-in

Abstract: A test system for plug-in connectors, especially for plug-in connectors in an airplane. A transmitting device which is designed for sending out a test signal to the plug-in connectors to be tested, and comprising at least one receiving device for each plug-in connector to be tested which is electrically coupled with the respective plug-in connector and which is designed for receiving the transmitted test signal and outputting an acknowledgement signal in response to receiving the transmitted test signal. Furthermore, the present invention creates an aircraft or a spacecraft and a method.

Abstract: A wing tip device for a wing includes a root and a tip, and the following determinant characteristics: the local dihedral of the wing tip device continuously increases or decreases from the root to the tip; the local sweep of the trailing edge continuously increases along its progression from the root to the tip of the wing tip device; where the local sweep of the leading edge continuously increases in the progression of the leading edge from the root to a first intermediate point; continuously decreases from the first intermediate point to a second intermediate point; and continuously increases from the second intermediate point at least to a region before of the tip of the wing tip device; as well as a wing comprising a wing tip device.

Abstract: The present invention relates in to a device for supplying mechanical power to start at least one engine, with a power supply device for supplying electrical power with an alternating voltage and constant frequency; and with a number, N1, of conversion devices for the conversion of the supplied electrical power to a respective mechanical power for a respective engine, wherein a respective conversion device has a cascade starter generator for direct conversion of the supplied electrical power to mechanical power, wherein the cascade starter generator has a first stator, a second stator, a first rotor and a second rotor, the first stator being integrally formed with the second stator and the first rotor being integrally formed with the second rotor. The present invention further relates to an aircraft comprising such a power distribution network and a method for supplying mechanical power to start at least one engine in an aircraft.

Abstract: A structural element for a fuselage cell structure of an aircraft, in particular a stringer profile or an annular former segment, the structural element being made from a composite material, in particular from a carbon-fiber-reinforced epoxy resin. The structural element comprises at least one positioning aid for facilitating position determination by means of a measuring system. A laser measuring system and/or a tactile measuring system may be used as a measuring system. As a result of the reflector which can be attached to the positioning aid without clearance as a target for the laser measuring system, which is preferably a laser tracker, a spatial position of the structural element in relation to a further component can be determined very precisely and without contact. Following position determination and orientation of the structural element, the reflector can be removed from the positioning aid.

Abstract: Method for controlling the temperature of feed air injected into at least one cabin zone of a passenger aircraft, the temperature of injected feed air being controlled for each cabin zone dependent on the deviation of the injection temperature actual value of the feed air from an injection temperature target value, the injection temperature target value being established using an external ambient temperature actual value and not using a temperature sensor in the at least one cabin zone.

Abstract: A lining for an aircraft. The lining separates an intermediate space from an interior space of the aircraft in a pressuretight manner. The lining panels extend either substantially horizontally or are fastened approximately vertically on a lining framework formed by profiles for connection to the fuselage cell. At least one of the lining panels allows automatic pressure equalization between the interior space and the intermediate space in the event that the pressure in the interior space drops to something in the order of 0 hPa. This pressure corresponds to the air pressure prevailing at an altitude above 10,000 m. Mounts of the lining panels are provided with predetermined breaking points. The predetermined breaking points are formed in particular by plastic nuts, the thread of which tears away when a critical load-bearing capacity is exceeded.

Abstract: A line system arrangement in an aircraft or spacecraft having a fuselage includes at least one receiving region for receiving at least one component of a line system, wherein the at least one receiving region is accessible, at least in some sections, from outside the fuselage of the aircraft and spacecraft for installation and/or maintenance of the line system; and an aircraft or spacecraft with a corresponding arrangement.

Abstract: The invention relates to a vibrating rivet tool for pressing and fixing rivets in component holes in component of aircraft. The vibrating rivet tool comprises a rivet receptacle and a drive unit for producing a high static pressing force. According to the invention, the static pressing force is superimposed by a mechanical vibration, of which the amplitude acts substantially in the direction of a longitudinal axis of the rivet. As a result, the force necessary to press and fix the rivet in a component hole is reduced in such a way that the overall size and mass of the vibrating rivet tool according to the invention are smaller/lower in comparison with conventional rivet tools. Due to the small overall size and low weight, the vibrating rivet tool can more easily be integrated in automated riveting processes.

Abstract: The invention relates to a device for reducing latch loads during the process of loading and flying air cargo containers inside cargo holds of aircraft. The device exhibits a floor plate of a cargo unit of a transport means, an edge profile, a rail bumper as well as a first damping unit. The first damping unit is situated between the edge profile and the floor plate, or between the edge profile and the rail bumper of the cargo unit. The first damping unit is designed for damping a movement by the cargo unit in a direction of movement of the cargo unit so as to reduce the loads placed on the cargo unit.