Abstract: Disclosed are a method and a device for the connection of two components indirectly or directly in an overlap joint, wherein component sections located in the overlap are pressed together for each drilling procedure by means of a clamping unit formed from a pressure application device on the drilling machine side and a guide on the component side, such that any penetration of chips between the component sections is prevented and temporary connecting elements can be dispensed with.

Abstract: A device for determining ageing of a hydraulic fluid in a hydraulic system with a multitude of hydraulic components is provided. The device comprises at least one temperature determination device and at least one ageing determination device, wherein the temperature determination device determines the respective temperature of each discrete fluid volume of the hydraulic fluid in the hydraulic system, and from the aforesaid the ageing determination device determines an increase in ageing. Generally, the temperature determination device carries out a numerical thermal simulation of the hydraulic system, component by component, including determining at least one temperature of at least one hydraulic component of the hydraulic system, which simulation is supported by measuring the temperatures of individual hydraulic components by means of temperature sensors.

Abstract: A cooling assembly for cooling a thermal body for an aircraft. The cooling assembly has a Peltier element with a hot side and a cold side. Furthermore, the cooling assembly has a thermal body. The thermal body is arranged in heat-conductive contact with the cold side of the Peltier element. The hot side of the Peltier element is adapted to dissipate thermal energy to an aircraft structure, such that the thermal body may be cooled.

Abstract: The invention relates to an automated device for implementing a drape-forming step to form a laminated fibrous preform, which is then impregnated with resin to produce a part made of composite material. The invention relates more particularly to the production of preforms for manufacturing parts such as panels, in particular very thick panels, that extend basically in two dimensions. The device of the invention comprises a manipulator able to move and orient in space a tape laying head, said tape laying head comprising: a drum comprising a suction orifice leading to its surface and able to individually grasp a length of fabric on a mounting outside the tool and the tape laying head; means designed to subsequently place this length of fabric on the preform comprising means of compacting; and means of heating the length of fabric.

Abstract: Modern high-end technology products such as aircraft consist of a number of individual systems that are controlled by independent electronic control units and increasingly interconnected. According to one exemplary embodiment of the present invention, a test system assembly for testing several such systems for an aircraft in parallel is disclosed, wherein a master network is provided in order to exchange data between the individual test systems and a control unit, and wherein original electrical wiring is provided between the test systems in order to directly interconnect the tested systems. The flexibility of system tests for aircraft may be increased in this fashion.

Abstract: A composite structure has a first section, a second section, and a curved corner joining the first and second sections. The structure has a stack of fiber-reinforced plies including first and second external plies which run from the first section into the second section on an inside and an outside of the corner, respectively. A discontinuous first internal ply is sandwiched between the first and second external plies so that more of the first internal ply is located within the first section than within the second section. A second internal ply is sandwiched between the first and second external plies. The fibers of the first internal ply run at an angle ? to the fibers of the second internal ply. In some embodiments the angle ? is greater than 3° but less than 20°. In one embodiment the angle ? is between 35° and 42°.

Abstract: A modular seat system for a passenger compartment of a vehicle includes at least one seat, which has a seat unit with a seating element and a seat back and a seat frame with at least one pair of essentially vertical support elements, at whose upper end a bearing structure is arranged on which the seat unit rests, a fixing structure in the floor of the passenger compartment with at least two longitudinal rails, which have a predetermined spacing from one another, for accommodating the lower ends of the support elements, and an adapter plate for the fixing of the support elements, which adapter plate is fitted to the lower end of the support elements, and is fitted in a mobile fashion to at least one support element, so that the spacing of the support elements from one another is variable independently of the width of the seat unit.

Abstract: Composite aircraft frame (1) comprising two segments (10, 20), each of these segments (10, 20) being single unitary element made in composite material and comprising at least one web (2), a stiffening structure and a fitting (4), the two segments (10, 20) being joint by the fittings (4) using rivets, forming the aircraft frame (1). The invention also refers to a method for fabricating such an aircraft frame (1).

Abstract: A cabin attendant seat for an aircraft, an aircraft monument comprising such a cabin attendant seat and an aircraft comprising such an aircraft monument. The cabin attendant seat is movable from a starting position into at least one end position. The cabin attendant seat includes at least one backrest element and two seat elements. Each of the two seat elements is movable relative to the at least one backrest element between a folded position and an unfolded position.

Abstract: A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction.

Abstract: The present invention provides a method and apparatus for testing a valve control system in an aircraft fuel supply system having a plurality of control valves, wherein the control system includes a processor adapted to receive feedback signals from each of the plurality of control valves, the method comprising the steps of: connecting a test device to the control system such that the test device is connected for signal transmission to the processor; outputting a signal to the processor simulating a feedback signal from at least one of the control valves; detecting a control signal which is output by the processor to the at least one of the control valves; and identifying the detected control signal which is output by the processor to the control valve.

Abstract: A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer.

Abstract: A composite material elongate structural member, such as a spar or stringer, for use in an aerospace structure, comprises a web having an angled portion, for example in the form of a chamfer, curved surface or the like, which joins a foot of the member to the rest of the web. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. On/in the interposed portion there is a fifth surface which joins the first and third surfaces. The geometry of the member may vary along its length (L) so that with increasing distance, the first surface is displaced towards the second surface as the width of the fifth surface decreases.

Abstract: An engine assembly for an aircraft, including a rigid structure including a box rib extension protruding from a box of the structure, in a line of separation, towards a fuselage of the aircraft. The extension supports a first attachment in a position separating it from a second attachment in the line of separation. The first and second attachments enable the moment being exerted in a lengthways direction of the turbine engine to be transmitted jointly.

Abstract: An aircraft latch including a main hook; an operating lever; a safety device; a button on the operating lever and fastened to the safety device; and adjustment means attached to the safety device for adjusting the position of the safety device with respect to the main hook.

Abstract: A device for measurement of a thickness of a coating applied to a substrate includes a transmitter/receiver module configured to transmit and receive microwave radiation; a computing unit; and a probe having a flange and an inner and an outer conductor, wherein the outer conductor coaxially surrounds the inner conductor, and wherein the inner conductor includes at least one thickened section.

Abstract: A method is described for optimized energy management of an aircraft upon a flight along a trajectory. The method allows the aircraft to join a given point of the trajectory in a given energy state, with a given position of the slats and flaps, and with a given position of the landing gear. The method includes determining current parameter values of the aircraft. The method also includes determining optimized command orders based on the current parameter values by performing a sequence of operations in an iterative way. The method further includes applying the optimized command orders to an automatic slats and flaps command device and an automatic landing gear command device for automatic control of the slats and flaps and the landing gear, respectively.

Abstract: Methods and devices for non-intrusive identification and communication between a server node and at least one client node in a communication network. An identification message is first transmitted to at least one client node, the identification message including at the application level a duplicate of the addressing data, the physical address and the internet address of the server node, also contained in the MAC and IP layers. The reception of at least one couple of addresses from at least one client node, wherein a couple of addresses from a client node includes a physical address and an internet address according to the same duplication strategy, can be used for identifying the client node by the server. Similarly, the methods and devices can be used for identifying in a client node at least one server node in the network.

Abstract: According to the invention, on at least one of the faces (1E, 1I) of said leading edge (1), forward of the partition (3), an action is exerted on the fluid flow (EF) so as to cause the latter to switch from the laminar state (EFL) to the turbulent state (EFT) in order to increase the thermal exchanges and minimize the thermal stresses on said leading edge.

Abstract: The invention concerns a method of connecting a first material to a second material by means of a heat-activatable adhesive material (8) in aircraft construction, wherein the adhesive material (8) is arranged between the first material and the second material and an induction heat which is adequate to activate the adhesive material (8) is generated. The first material and/or the second material and/or the adhesive material (8) have an induction heat-generating means. The induction heat-generating means is a non-woven metallic mesh and/or the induction heat-generating means (53) has an amount of carbon fibers for induction heat generation. The invention further concerns an apparatus comprising a first material and a second material, wherein the first material and the second material have a connection which can be produced by a heat-activatable adhesive material arranged between the first material and the second material, in accordance with the method in accordance with the invention.