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: 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: A switched-mode power supply device includes a charger (10) to be connected on one side to a direct current electrical network, or rectified alternating current electrical network (RC), a power reserve (11) connected to a second side of the charger (10), and DC-DC output converters (12) delivering regulated output voltages (VS). The output converters (12) are connected by an input to the first side of the charger (10). The charger (10) is a current bidirectional, voltage unidirectional converter which, in a first phase, enables the power reserve (11) to be recharged and maintained charged from the network, where the output converters (12) are powered by the network (RC) and, in a second phase, in the presence of a power brown-out of the network (RC), enables the power reserve (11) to be discharged to power the output converters (12).

Abstract: A drive system for driving control surfaces of an aircraft includes at least one drive unit, at least one main shaft connectable to the at least one drive unit and at least two adjusting units for each control surface to be driven. Each adjusting unit includes a differential, two rotary actuators and an adjustment lever. The differential has at least one input means and two output means and is adapted to transfer torque from the at least one input means to the two output means. The input means is connectable to the main shaft, the two rotary actuators each have a rotation input means and a motion output means. The rotation input means is connectable to one of the output means of the differential each and the adjustment lever is connected to the motion output means of both rotary actuators.

Abstract: The invention relates to an aircraft cockpit centre pedestal for the attachment of control and instrumentation equipment for this aircraft, wherein the centre pedestal includes an equipment module including controls connected to at least one first electrical connector, and a single-piece frame including an upper face provided with a recess including at least one second electrical connector installed at the bottom of the recess and connected to computers onboard this aircraft in which this equipment module is installed, the at least one first electrical connector of the equipment module being inserted into at least one second electrical connector so as to connect the controls of the equipment module and these onboard computers. The invention also relates to an aircraft including such a pedestal.

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: An attaching system for attaching two components together, such as an aircraft engine and a mounting pylon, includes front trunnions and rear trunnions for supporting the aircraft engine. In this attaching system, at least two of the front or rear trunnions are vibration damping type trunnions that include a suspension assembly with an elastic element and resonant mass. The suspension assembly is shaped as a bent arm carrying the resonant mass on a free end and associated with the elastic element on another end. The vibration damping type trunnions also include a shackle attached between the engine and the suspension assembly so that the vibration damping type trunnions minimize any vibrations and efforts that would otherwise be applied to aircraft structure via the pylon.

Abstract: A sliding door system includes at least one sliding door having an upper and lower sliding-door mount, as well as an upper and lower guide rail for displaceably receiving the upper and lower sliding-door mount, respectively. The guide rails extend parallel to each other and each have a clear inner width that is at least twice as large as the thickness of the sliding door. The upper and lower sliding-door mounts are each at most half as wide as the clear inner width of each guide rail, allowing moving the sliding door into recessed and lifted-out positions, each constituting a stable state. By overcoming a resistance force, the sliding door can be moved between stable states. The sliding door system is lightweight and robust, and enables sliding doors to be displaced freely without a particular sliding door being assigned in a fixed manner to a particular opening to be covered.

Abstract: A method for debugging the program of operational software of an onboard system, including flagging the program by positioning flags along an execution path for dividing the aforementioned execution path into adjacent functional intervals; normal execution of the program; acquiring an execution condition of the program by flag condition vectors; when an error is detected, searching a faulty functional interval based on the flag condition vectors, reverse execution of the program in the aforementioned faulty functional interval, and determination and correction of the error.

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.

Abstract: The invention has in particular as an object the synchronization of a local clock of an equipment item in a communication network according to synchronization frames emitted by a reference equipment item and transmitted via a switch. After it has received (700) a synchronization frame emitted by the reference equipment item and including its time point of emission, the switch transmits (730) the said received synchronization frame after a delay that is fixed, at least on average, counting from the reception of the said synchronization frame by the said switch (725). The local clock of the equipment item, after reception of the said synchronization frame by the equipment item, is synchronized according to the said time point of emission, to the time point of reception of the said synchronization frame and to the said delay.

Abstract: A clamping device is provided for an assembly of a stringer coupling in a region of a lateral butt joint between a first and a second fuselage section of an aircraft for coaxially connecting a respective first and second stringer of the first and the second fuselage sections, the stringer coupling intersecting a frame element profile in the region of the lateral butt joint. A supporting yoke is configured to bridge the frame element profile in an arc-shaped manner and includes a first end foot supported by the stringer coupling on the first side of the frame element profile and a second end foot supported by the stringer coupling on the second side of the frame element profile. The supporting yoke includes a middle tensioning hook configured to interact with the frame element profile. The first and the second end feet are tensionable against the stringer coupling.

Abstract: An aircraft passenger seat has at least one seat element characterized by at least one monitoring apparatus for monitoring the seat element. The seat arrangement has a plurality of seats, wherein at least one seat includes at least one sensor module for monitoring a seat element and a control unit for checking and controlling the monitoring, wherein the at least one sensor module is in a data exchange relationship with the control unit.

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: A device for communication between a portable computer system including a display screen and avionic equipment items comprises shielded walls forming at least a partial Faraday cage. The device also includes at least one wide band high output wireless transmitter-receiver arranged inside the shielded walls and adapted for carrying out a very short range point-to-point radio communication with the portable computer system when the portable computer system is placed inside the shielded walls. The device also includes at least one interface connected to the avionic equipment items and adapted for transmitting data originating from the portable computer system to the avionic equipment items and data originating from the avionic equipment items to the portable computer system, through the at least one said transmitter-receiver.

Abstract: A device for keeping objects, especially luggage, in an aircraft hold, the device including a flexible partition and at least one winding mechanism. The flexible partition is mounted on the winding mechanism such that it can be both wound onto the winding mechanism or unwound from the winding mechanism. The flexible partition includes an attaching mechanism that operates with a complementary mechanism to maintain the flexible partition in an unwound position.

Abstract: The invention relates to a device comprising a base plate and a support for adjusting the height of an assembly, in particular of a galley module in an aircraft, without using tools. According to the invention, two opposing wedge bodies are arranged such that they can be displaced horizontally between the base plate and the support, the oppositely directed manual displacement of the two wedge bodies, when the lock levers have been raised, causes in the “adjusting position” a raising or lowering of the support for the height adjustment. The assembly is connected to the support, for example by a conventional screw connection through the attachment hole in the support. The device according to the invention allows a user to perform a simple and rapid height adjustment of an assembly arranged thereon, thereby greatly reducing the assembly effort required for prefabricated assemblies or modules in aircraft.

Abstract: A method for attenuating effects of turbulence on an aircraft, and a device to implement the method, the method including: using at least one signal on a wind profile signal, along an excitation direction, representing, at a given moment in an aircraft referential, a component along the excitation direction of the wind speed at a front of the aircraft according to a distance along a longitudinal direction of the aircraft; carrying out a frequency determination, in which the wind profile signal is processed to determine a frequential content; and selecting a control strategy to be adopted according to the previously determined frequential content, the strategy enabling at least one applicable control law to be identified.

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.