Abstract: An attachment device for attaching an equipment component in an aircraft, comprising a second attachment element for attaching an equipment component in an aircraft, the second attachment element comprising a guiding element, a contact element and a locking element, wherein the guiding element is introducible into a first section of a first attachment element, wherein the guiding element is movable from the first section of a first attachment element according to the present invention into a second section of the first attachment element, wherein the first attachment element and the second attachment element are mechanically couplable by engaging from behind the first attachment element in the second section of the first attachment element, wherein, in the coupled state, the contact element provides a mechanical contact between first and second attachment element and wherein by operating the locking element the first attachment element and the second attachment element are releasably fixable relative to one a

Abstract: The invention relates to a method for operating an aircraft cooling system (10), comprising the steps guiding a cooling medium through a cooling circuit (26) which is coupled to a refrigerating machine (12) and to at least one cooling energy consumer (14a-14d) in order to supply cooling medium cooled by the refrigerating machine (12) to the cooling energy consumer (14a-14d), and controlling the operation of the refrigerating machine (12) by a control unit (42), such that coolant medium cooled by the refrigerating machine (12) to a predetermined cooling medium flow temperature is supplied to the cooling energy consumer (14a-14d). The method for operating an aircraft cooling system (10) further comprises detecting a cooling energy requirement of the cooling energy consumer (14a-14d) and transmitting a signal indicative of the cooling energy requirement of the cooling energy consumer (14a-14d) to the control unit (42).

Abstract: An electrical energy generating device for a propfan-type aircraft propulsion unit rotor. The propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit. The turbomachine generates a flow of hot gases that exit via an annular hot vein, which is concentric with the moving annular crown, and defined for part of its surface by an inner wall of the moving annular crown, and includes, within the moving annular part, a mechanism to transform thermal energy into electrical energy, preferably by thermal diodes. Such a device, as an example, can find application to a device for controlling a pitch of rotors of a propfan-type propulsion unit.

Abstract: A monitoring system and a monitoring method applied to the monitoring system, in which the monitoring system includes detectors detecting a state of a turbojet thrust reverser, a monitoring computer device controlling the reverser monitored by the computer as a function of information from the detectors provided to the computer by way of the control device, and a device regulating the turbojet monitored by the computer as a function of the information from the detectors provided to the computer by way of the control device.

Abstract: A tank module for an aircraft is designed for being fitted into the aircraft fuselage from outside. The tank module comprises at least one receptacle and a shell section that forms an outer end of the tank module and is connected to the receptacle. The shell section can be fitted into a fuselage opening in such a way that the receptacle is positioned in the interior of the aircraft fuselage.

Abstract: The invention relates to an aircraft turbojet nacelle including a cowling assembly (60) made up of four covers (62, 64, 66, 68). Each cover extends in arcuate shape around part of the longitudinal axis of the nacelle, in symmetrical manner about a vertical plane (P) containing the axis. On either side of said plane, the cowling assembly comprises a top cover (62, 66) hinged at its top portion and a bottom cover (64, 68) hinged at its bottom portion. Access to the internal space (e) of the nacelle is obtained by moving the covers away from the longitudinal axis by pivoting them about their hinge axes. A top cover is less heavy for handling purposes than is a single cover of the prior art.

Abstract: An insulation blanket to be connected at the inside surface (16) of an aircraft fuselage, includes at least one opening that allows a through element (20) to pass, at which is connected a sealing device, characterized in that this sealing device includes a core (28) that is combined with a body (30) that extends over a closed contour delimiting the opening (26), with the core (28) having a spring action that tends to flatten the body (30) against the through element (20) over at least a part of the circumference of the opening (26).

Abstract: An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the first and second engine mounts is associated a reinforcing structure forming a shear plane, fixedly connected: in an area of the annular structure at a first anchoring point; in an area of the fan casing at a second anchoring point; and in an area of a structural arm or of the intermediate casing at a third anchoring point. The structure extends along a radial imaginary plane passing through an anchoring point of the mount on the fan casing.

Abstract: A fastening device is provided for an aircraft interior equipment component, with at least one suspension point which is formed to transmit forces to a holding structure in at least one direction. In order to install the aircraft interior equipment components quickly and without tools, each suspension point is formed by a rotatable sliding block and a groove, wherein the groove has a transverse dimension as well as a first open end and a second end which leads into a circular recess. The sliding block also has a transverse dimension which is smaller than or equal to the transverse dimension of the groove and a longitudinal dimension which is greater than the transverse dimension of the groove, so that the sliding block can be positively locked by a rotation thereof in the circular recess.

Abstract: A covering device includes a sealing element and a rib structure which is disposed on a surface of the sealing element. The rib structure includes a plurality of ribs which extend parallel to the surface of the sealing element, wherein the bendability of the ribs parallel to the surface of the sealing element is high, and perpendicular to the surface of the sealing element is low.

Abstract: A mounting system (10) for attaching a structural monument in a desired position in an aircraft cabin comprises a support element (12) that is connectable to a base body (14) of the structural monument in a pedestal area of the structural monument. The mounting system (10) further comprises a receiving device (50) that is attachable in an area of a floor of the aircraft cabin, and a first coupling element (38) attached to the support element (12), designed for connecting the supporting element (12) to the receiving device (50) that is attachable in an area of a floor of the aircraft cabin. Finally, the mounting system (10) comprises a retaining element (76) that is connectable to the base body (14) of the structural monument in a ceiling area of the structural monument, and a second coupling element (86) attached to the retaining element (76), designed for connecting the retaining element (76) to a structurally solid component of the aircraft.

Abstract: A tank for containing a fluid, such as fuel, oil or gas within a chamber. The walls of the chamber are partially defined by a rigid structure having an opening; and partially defined by an elastomeric diaphragm which is attached around its periphery to the rigid structure and covers the opening in the rigid structure. An attachment frame engages the diaphragm and the rigid structure, and extends around the periphery of the diaphragm. The attachment frame has a first portion which engages the diaphragm, and a second portion which is positioned outside an outer edge of the diaphragm and attached to the rigid structure.

Abstract: An insulation package is provided for insulating a cabin of a vehicle that includes, but is not limited to at least one wrapping foil and at least one core layer of an insulation material. The wrapping foil envelopes the core layer at least in some regions and includes, but is not limited to at least one opening for feeding-through a holding element. On the wrapping foil a fastening element is arranged that is designed to establish a mechanical connection with the holding element fed through the opening. This can be a positive-locking or a non-positive-locking connection. By integrating the fastening element in the insulation package, the expenditure for separate fasteners can be saved so that the installation time and the different components can be reduced.

Abstract: The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimize the natural vibration behavior of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behavior of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behavior of the structural element is optimized. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element.

Abstract: A gap covering device for covering a gap between two mutually adjacent first aircraft interior panels includes a visible portion as well as a retaining portion connected to the visible portion and extending opposite the visible portion. A receiving structure is fastened to an inner surface of the visible portion and/or of the retaining portion and has a receiving contour adapted to an edge contour of the first aircraft interior panels.

Abstract: Disclosed is a connecting arrangement for purposes of connecting an electrical line to a component section, with a holding device, which has a holding element for purposes of arranging on the component section and a connecting element for purposes of connecting the line with the holding element, with a breakthrough to be provided on the component section for purposes of guiding through the connecting element, wherein the holding element is embodied in the form of a clamp for purposes of encompassing the component section in at least some sections, and wherein a positioning device is provided for purposes of positioning the holding element in a design position on the component section, which has a holding element-side positioning element and a counter element to be provided on the component section, which interact in a form fit, and also a holding element for such a connecting arrangement with a clamp-type profile and a positioning element for purposes of a form-fit positioning of the holding element on the co

Abstract: A cabin attendant seat for an aircraft, a seat system comprising such a cabin attendant seat, an aircraft monument comprising such a cabin attendant seat and an aircraft comprising such an aircraft monument. The cabin attendant seat comprises a backrest element and a seat element. The cabin attendant seat is movable from a starting position into at least one end position. The cabin attendant seat further comprises an adapter element, the adapter element being arranged in the cabin attendant seat and configured to connect the cabin attendant seat, in the at least one end position, to an aircraft seat provided in the aircraft.

Abstract: A passenger supply system installed in a passenger supply channel (PSC) on board a vehicle, such as an aircraft. The supply system comprises a rail track configured to be mounted along the PSC. The supply system further comprises an indiv panel mounted on the rail track and connectable to the PSC for supplying a passenger with conditioned air, medical outlet and/or oxygen. The indiv panel comprises a crossover area. The supply system further comprises a passenger supply unit mounted on the rail track and connectable to the PSC for supplying the passenger with light, visual information and/or sound information. The supply unit comprises an overlapping area. The supply unit and the indiv panel are configured such that in a mounted state of the supply unit and of the indiv panel the overlapping area of the supply unit at least partially overlaps with the crossover area of the indiv panel.

Abstract: An aircraft having an elongated fuselage and a lifting surface fastened to the fuselage. The aircraft has a device for controlling the torque around the yaw axis GZ of the aircraft in which aerodynamic forms that have devices to generate aerodynamic drag are fastened to each end of the lifting surface at non-zero distances from each side of a vertical plane of symmetry XZ of the aircraft. The drag-generating devices are commanded to produce a different aerodynamic drag at each of the two ends to generate a yaw torque on the aircraft. The aerodynamic forms, for example, have winglets improving the aerodynamics of the lifting surface, and are provided with aerodynamic drag generators.

Abstract: An accumulator arrangement suitable for use in a cooling system designed for operation with a two-phase refrigerating medium, includes an accumulator vessel with a receptacle for receiving a refrigerating medium. A liquefier of the accumulator arrangement is adapted to liquefy refrigerating medium to be received into the receptacle of the accumulator vessel before fed in the receptacle of the accumulator vessel and includes a refrigerating medium outlet for discharging refrigerating medium which liquefied in the liquefier from the liquefier.