Abstract: A system for generating energy for a consumer element in an aircraft includes the consumer element with a fuel cell element and a rechargeable metal hydride storage cell. The rechargeable metal hydride storage cell is designed for supplying the fuel cell element with hydrogen such that energy can be generated for the consumer element. The rechargeable metal hydride storage cell is furthermore designed in such a way that it can be charged with hydrogen.

Abstract: With a device for error detection of adjustable flaps on aircraft wings, it is proposed that each flap is provided with a tube as a transmission element arranged in the wing span. The tube is connected fixedly at one end with the flap and is rotatably held. On the free end of the tube, a measuring arm is fixedly arranged on the tube and a sensor fixed to the flap structure is arranged. When an error occurs, the flap twists, whereby a distance change between the sensor and measuring arm occurs. The signals of the sensor are transmitted for error localization of each flap to an evaluation device, which switches off the drive via a control device with occurring errors.

Abstract: An airplane door window of a passenger plane, includes an outer pane, an inner pane, an intermediate pane situated parallel between the outer pane and inner pane and designed as an optical lens body for the inspection of impact surfaces for emergency slides, portable staircases or boarding fingers. The outer pane and the inner pane are spaced apart from each other, arranged substantially parallel to each other in a continuous window gasket, and form an intermediate space. The intermediate pane is inserted into a continuous groove of the window gasket, and extends essentially parallel to the outer pane and the inner pane over a partial area of the intermediate space.

Abstract: Apparatus and method for visualizing air stream by little threads on aerodynamic surfaces such that strips of adhesive tape populated with threads are automatically fabricated.

Abstract: A system for reducing the manual force required to move a lowerable shell of a luggage compartment in a passenger aircraft includes a load determination device for determining a load acting on the lowerable shell of the luggage compartment, and a state detection device for detecting whether the lowerable shell is in a closed position or an open position. The system also includes a force assisting device for applying a constant assisting force which opposes the load acting on the lowerable shell. The system further includes an actuating device adapted to move the force assisting device from a first inactive operating state to a second active operating state when the lowerable shell is in the open position and the load acting on the lowerable shell exceeds a predetermined threshold value.

Abstract: The individual room units presently used in aircraft, e.g. crew rest rooms, are usually fixed installations so that quick on-demand changeover of passenger seats to such a room unit may only be feasible with an extended change-over period in the repair hangar. According to an exemplary embodiment of the present invention, a modular wall construction system for aircraft cabins is provided, which comprises individually prefabricated wall construction panels (701, 702, 703) adapted for a quick installation with connecting elements without additional tools. This may result in the formation of at least one room of a room unit (1) of individual size and geometry.

Abstract: In a commercial aircraft with a main deck (2) and a lower deck (5, 6), at least one passenger cabin (16, 16?) is also provided on the lower deck. The fuselage diameter lies on the order of a wide-body aircraft, and an energy-absorbing deformation structure (22, 23, 24) is arranged underneath the lower deck cabin. The invention proposes to arrange the wings (7) on the aircraft fuselage in accordance with the shoulder wing configuration, and to arrange the landing gear (10) outside on the fuselage such that the landing gear bays are spaced apart from one another by a certain distance that is defined by the positioning of the bottom longeron spars (9). This may provide that the lower deck volume situated underneath the main deck can be optimally utilized for payloads. The lower deck areas may also be interconnected in such a way that a significant useful width of the passage between the landing gear bays is achieved.

Abstract: A sorting device and a method for sorting goods in transit for an aircraft are disclosed. The sorting device includes a sorting region with a sorting unit and a storage region. The sorting region is adapted such that goods in transit are capable of being provided to the sorting region in an undetermined first arrangement. The sorting region includes a longitudinal axis, where a sorting unit may be moved along the longitudinal axis of the sorting region. The sorting unit is capable of sorting the goods in transit from an undetermined first arrangement to a predetermined second arrangement, where the goods in transit may be provided in the predetermined second arrangement in the storage region.

Abstract: The present invention provides an airframe structure of an aircraft or spacecraft, with: a hollow body section which can be subjected to an internal pressure; a membrane arrangement which has at least one single-part, multi-curved membrane component for sealing off the internal pressure from an external pressure which acts on the hollow body section and differs from the internal pressure; and a joining structure for a pressure tight joining of the membrane arrangement to a region of the hollow body section; wherein the membrane arrangement forms a receiving well which is accessible from outside the hollow body section, extends at least partially into the hollow body section and is for receiving a component of the aircraft or spacecraft.

Abstract: The design and attachment of an insulation package near the fuselage structure to protect the cabin region of an aircraft against fire acting on the insulation package from outside the aircraft environment, thus clearly facilitating evacuation of the passengers from the vehicle. The insulation package arrangement may comprise several fuselage insulation packages of an elongated form. These packages may adjoin the aircraft fuselage structure in the direction of the longitudinal axis of the aircraft. They may be completely enclosed by a burn-through-proof foil which is arranged in a space enclosed by interior paneling and by the panels of the outer skin.

Abstract: A dispenser of cooled or heated liquid which in one embodiment is a server cart for an aircraft. To avoid the need for a pump, the reservoir has a cooling or heating heat exchanger that helically coils around the main reservoir, which cools from the top down or heats from the bottom up, forming a counter current. The reservoir is connected to at least two conduits, one near the cooler top of the reservoir and one near the relatively warmer bottom of the reservoir. The two conduits connect to one another at a distance from the reservoir forming a dispensing passage, thereby allowing fluid to constantly circulate through the dispensing passage due to difference in the specific gravity in the fluid caused by the temperature difference. The elimination of the pump device is especially desirable for weight sensitive environments such as an aircraft.

Abstract: The present invention relates to a circuit for detecting a functional status of an electro-motor. Typical electro-motors need additional components to identify the functional status of the motor. This means additional weight for such motors determining the functional status. According to the present invention a circuit is provided using a part of a motor as a sensor for detecting the functional status of the electro-motor.

Abstract: A pipeline for conducting air for air conditioning in aircrafts includes a body portion formed with foamed plastics material or with a dense plastics material. The body portion defines a longitudinal axis and includes an outer surface carrying a wrapping for reinforcing the pipeline. The wrapping includes a plurality of adjacent contacting layers formed by at least one linear reinforcing element wound into a plurality of windings, with adjacent layers having windings angled in opposite directions to form a net-like structure of the wrapping. At least one of the spacing between the windings along the longitudinal axis or the angle of slope between the windings and the longitudinal axis varies in certain sections to change the winding density as a function of local mechanical load requirements on the pipeline.

Abstract: A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state.

Abstract: When a fire breaks out, air flows that promote the spread of fire may occur in the region between the load bay and the skin of the aircraft. According to one embodiment of the present invention, a fire barrier is disclosed that allows rapid decompression of the passenger cabin in the normal operating mode of the aircraft and prevents flashovers in case of a fire. In this case, the fire barrier may be arranged at different positions in the intermediate wall space of the aircraft.

Abstract: An internal swivel door for an aircraft compartment. A door frame for entering the compartment includes a horizontal element and at least one door leaf which is mounted inside the door frame wherein the door leaf is turned about a vertical door rotational axis. The vertical door rotational axis is moved in parallel along a predetermined local curve. In order to take up less space during opening and closing of the door and to be able to operate the door with the least possible force, the door has a rotary sliding joint between the door leaf and the horizontal element. The door leaf has a rotational movement about a momentary rotational axis running through the rotary sliding joint wherein the momentary rotational axis is moved in parallel both in relation to the horizontal element and the door leaf.

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 arrangement (10) for installing a component (12) in an aircraft comprises a guide device (14) which is connectable to an aircraft structure or is formed integrally with the aircraft structure, as well as an elastically deformable damping element (16; 16a, 16b, 16c) which is adapted to enable the component (12) to be mounted in the guide device (14) in a self-supporting manner. A locking mechanism (26) is adapted to fasten the component (12) in a desired position in the guide device (14) in a releasable manner.

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 necessary for the joining is produced in two parts. In a first step, each precured stringer is covered in advance with a covering vacuum film. The stringers prepared in this manner are arranged on the structural component. Respective vacuum film strips are subsequently arranged 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: This device is provided for a luggage compartment designed to be placed overhead. The compartment comprises a mobile part (4) between an open position and a closed position and a mechanism for acting on said mobile part (4) to promote its closing. Said mobile part (4) presents an opening (14) designed for introducing and retrieving luggage as well as a lower exterior surface (12). The control device comprises detection means reacting when pressure is exerted on a predetermined zone of the lower exterior surface (12) of the mobile part (4) as well as for sending a control signal to the mechanism acting on the mobile part (4) to close the part when pressure is exerted on said detection means. The detection means are disposed at the lower exterior surface (12) of the mobile part (4).