Abstract: A fuselage section for the pressure fuselage of an aircraft which comprises a fuselage shell structure and at least one pressure bulkhead made of a fiber composite material, the pressure bulkhead being formed in one piece with the fuselage shell structure. A fuselage shell comprising at least one fuselage section of this type.

Abstract: The invention pertains to a spoiler (5) for an aerodynamically active surface of an aircraft (1), particularly for an airfoil of an aircraft, wherein said spoiler is supported on the aerodynamically active surface such that it is articulated about an axis (11) extending transverse to the air flow direction and can be adjusted relative to the air flow. According to the invention, the spoiler features two or more segments (6, 7) that are arranged behind one another referred to the air flow direction and extend transverse to the air flow direction, wherein said segments are connected to one another in an articulated fashion and can be adjusted to different angles referred to the air flow. The successively arranged segments of the spoiler (5) can be actuated, in particular, by means of an actuating device (8, 9, 10) in such a way that the rear segment (7) is adjusted relative to the air flow by a greater angle than the front segment (6).

Abstract: An ice separator is provided that includes, but is not limited to at least one curved airflow deflection surface. The ice separator includes, but is not limited to an inflow aperture with a downstream trapping pocket at the airflow deflection surface, in which trapping pocket ice particles from an airflow flowing onto the ice separator are trapped due to their inertial forces. In this way with simple means an effective device for removing ice particles from airflow may be achieved.

Abstract: A display system manages the states of two cursors that are situated on an interactive window of a display screen, as a function of the last actions carried out by the crew.

Abstract: The invention concerns a device for stiffening a flat component, a process for the production of a flat component, in particular a fiber composite component, and a fiber composite component. The device has a portion for producing a space for receiving a mold core for the transmission of a pressure for pressing the flat component and the device. It is characterised by means for positively lockingly and/or frictionally lockingly positioning the mold core in the space of the device. The process according to the invention includes the following steps: introducing the mold core into the portion of the device, positively lockingly and/or frictionally lockingly positioning the mold core in the portion of the device by means of the means, applying the device including the mold core to the non-hardened material layer or layers, pressing the material layers, and hardening the material layer or layers and joining the device to the material layer or layers.

Abstract: The invention relates to a method for the production of sandwich components with an open core structure and a cover layer applied to each side, wherein the cover layers are formed with a curable plastic material, and the sandwich component is cured in a closed device under pressure. A charging gas, which may be nitrogen or air, is introduced to the core structure prior to at least partial solidification of the cover layers, wherein a charging gas pressure p Charging gas is selected that is less than or equal to an operating pressure p operating of the closed device in order to, in particular, at least largely prevent the formation of sink marks in the cover layers. Furthermore, the invention relates to a press for implementing the method.

Abstract: A noise reduction assembly located at a junction plane between an air intake structure and a fan casing of an aircraft turbojet has improved acoustic properties since the alternation of acoustic and non-acoustic zones is displaced or eliminated. In particular, the inner wall of the air intake structure includes a projecting part that extends towards the aft direction beyond the junction plane, in other words the flange of the fan casing. The projecting part may be sufficiently long so that its inner skin is continuous as far as the limit between the acoustic zone and the non-acoustic zone of the nacelle.

Abstract: Disclosed is a ventilating air intake arrangement of an aircraft. The arrangement includes at least one air duct connected to an air intake orifice. At least one confined zone connects with the air duct and the air intake orifice, and the confined zone is configured in a manner in which outside air enters through the air intake orifice. A controllable mobile element modifies the flow of air entering the confined zone by varying a cross section of the air duct. A control unit is used to control the controllable mobile element, with the control unit being arranged so as to control the controllable mobile element to vary the cross section of the at least one air duct as a function of speed and altitude of the aircraft.

Abstract: A pipe connector is disclosed, comprising two connector elements, arranged for interconnection of two pipes, wherein one or both of the connector elements is formed from electrically resistive material so as to provide electrical resistance between the connected pipes.

Abstract: An aircraft fuselage structure which is constructed from a plurality of shells which are joined together is disclosed. Each shell forms part of the aircraft fuselage and comprises a support structure and a skin which is arranged on the latter and outwardly seals the aircraft fuselage in a compression-proof manner. The aircraft fuselage structure comprises an upper and side shell and a lower shell, of which the lower shell has a radius which is essentially significantly larger than the radius of the upper and side shell. The upper and side shell and the lower shell are joined together at transition regions extending in the longitudinal direction of the aircraft. The support structure of the lower shell is designed in terms of its strength in such a manner that it is capable of absorbing the internal pressure loading of the lower shell without the use of a main crossmember.

Abstract: A computer-aided method for carrying out the structural design of a part subjected to damages having significant effects on its structural integrity, such as an aircraft fuselage section subjected to a propeller blade release event, is provided. The method includes: obtaining finite element models that include all the relevant information for an optimization analysis for the un-damaged part and for at least one possible damaged part; defining at least one design variable of the part and at least one design constraint and one load case for the un-damaged part and for the damaged part; providing at least one simulation module for analyzing one or more failure modes of the part; iteratively modifying the design variables of the part for the purpose of optimizing a target function by analyzing simultaneously the un-damaged part and the at least one damaged part using the at least one simulation module.

Abstract: Overhead stowage compartments are provided for an aircraft. The stowage compartments feature an opening device that can be displaced or rolled up. This may make it possible to prevent lights or air outlets from being covered by pivoting a door upward, as well as to preserve the headroom during the opening process and to prevent collisions between the doors. The architecture of the aircraft may be optimized in this fashion.

Abstract: The present invention provides a device for mounting systems, for example an electrical or fluid-conveying line, on a structure, in particular of an aircraft or spacecraft, the device comprising: a basic holder which can be fastened to the structure; and at least a first system holder for mounting the systems; the basic holder being made up of at least a first part comprising a first interface for fastening the first system holder and a second part comprising a second interface for fastening the first or a second system holder, the interfaces being formed in an identical manner and pointing in different spatial directions.

Abstract: An aircraft wing assembly, comprising: a fixed wing portion; a first and second flight control surfaces; a first and second actuators operatively coupled to the first and second flight control surfaces for moving respective first and second flight control surfaces with respect to the fixed wing portion; a control system operatively coupled to the first and second actuators for controlling movement of the first and second flight control surfaces; and a third actuator selectively engaged with the second flight control surface for engaging and moving the second flight control surface out of a path of movement of the first flight control surface only in the event of a failure in the second actuator or its control, so as to avoid direct contact between the first and second flight control surfaces.

Abstract: A water amount controlling device includes a control unit for controlling an amount of water to be supplied, and a washing agent receptacle including a detection unit , wherein the detecting unit is adapted for detecting and identifying e.g. a type, a consistency or an amount of washing agent dispensed from a washing agent reservoir to be received in the washing agent receptacle, and wherein the control unit is adapted for controlling an amount of water based on the detected and identified property of the quantity of washing agent.

Abstract: A slat support and deployment apparatus comprising a master slat support and deployment assembly and a slave slat support and deployment assembly is disclosed. The master and the slave slat support and deployment assembly each include an arm having a free end attachable to the same slat at spaced locations along its length for deployment and retraction of said slat in a direction generally parallel to a wing in response to simultaneous movement of said arms. The master and the slave slat support assemblies each include a coupling for attaching said free end of each arm to a slat and the coupling that couples the free end of the arm of each slat support and deployment assembly to a slat is configured to allow movement of that slat relative to said free end of said arm of each slat support and deployment assembly during deployment and retraction of said slat.

Abstract: A device for improving performance of an aircraft with a propeller includes a constant torque blade setting device that slaves, automatically and independently, blade setting angles, respectively associated with blades of the propeller, to a constant reference control moment predetermined, for a desired propeller thrust value. The blade setting angles are intended to be applied on each blade such that torsion aerodynamic moments applied on blades stay roughly equal to the reference control moment regardless of the angular position of blades in the propeller plane. A corresponding method for improving performance of an aircraft includes the use of the constant torque blade setting device to slave blade setting angles to a constant reference control moment.

Abstract: An engine assembly for an aircraft including a dual-flow turbomachine and an attachment strut. The turbomachine includes a structural case extending downstream of the hub of an intermediate casing, the case contributing to the internal radial delimitation of a passage for a secondary flow of the turbomachine. Also, the primary structure includes a structural case, assembled on the structural case and positioned directly downstream of the structural case such that it also contributes to the internal radial delimitation of the passage for the secondary flow. The primary structure also includes an offset structure positioned in the passage, and configured to connect the case to an element of the aircraft. The structural case also includes a thrust reversal system.

Abstract: An aircraft wheel assembly comprising a wheel and an aircraft taxiing actuator comprising, a first shaft for connection to a drive source, the first shaft defining a first axis and a second shaft for connection to the wheel to rotate the wheel, the second shaft defining a second axis substantially perpendicular to the first axis, in which the first shaft and second shaft are connected in driving engagement by a ball-worm gear.

Abstract: An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.