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: The invention relates to a membrane. Partly permeable membranes often have holes or perforations having a specific diameter to allow substances having a smaller particle diameter to pass through, but to hold back substances having a larger particle diameter. Such membranes are subject to wear primarily at the holes, i.e. cracks form which grow through the membrane proceeding from a hole. Particularly in the case of micromechanical membranes having holes having a small diameter in the range of 1 ?m or less, it is very difficult to detect the state of the membrane, in particular whether the latter has cracks. Membranes having cracks can then undesirably allow passage even of those particles which should actually be held back. In medical or hygienic applications, the function can then be impaired.

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: 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: 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 method for manufacturing a tool equipment used in molding a panel for a fuselage of an aircraft from a composite material is provided. The method includes manufacturing a mold such that a fixed part includes a hub and an intermediary member. A plurality of removable modules which are able to be mounted on this fixed part are also manufactured and then fastened to the fixed part so as to modify an external surface upon which composite material is laid-up or draped during the molding of the panel.

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: 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: The device comprises an intrusion detection module (6), an image acquisition module (14), an energy management module (13) and an autonomous power source (9), the said detection module (6) being designed to furnish a detection signal having a first predetermined state when an intrusion is detected and a second predetermined state otherwise, and the said management module (13) being designed to make the said device change over from a waiting mode to a working mode by activating the supply of the image acquisition module (14) by the said autonomous power source (9) when the said signal changes over from the second state to the first state. The method includes a step consisting in furnishing the detection signal and, when the detection signal changes over from the second state to the first predetermined state, a step consisting in making the said device change over from the waiting mode to the working mode and a step consisting in achieving image acquisition.

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 structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection.

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 device for reducing the aerodynamic drag of a leading surface of an aircraft includes at least one air permeable structure disposed in an area of the leading surface and a suction device configured to interact with the at least one air permeable structure.

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: A composite material elongate structural member, such as a spar, for use in an aerospace structure, comprises a web disposed between upper and lower flanges. The web may include a clockwise twist about an axis parallel to the length L at a first portion towards the wing-root-end of the spar and a counter-twist in the anticlockwise direction at a second portion towards the wing-tip-end of the spar. The geometry of the spar may vary non-linearly along its length (L) so that the developed width of the spar as measured from a distal edge of the upper flange via the web to a distal edge of the lower flange varies linearly with increasing distance along the length (L). The risk of causing, during fabrication of the spar, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the member varies non-linearly may be reduced by means of such an arrangement.

Abstract: A blade seal comprising: a base; a tip; a first part formed from an elastomeric material which extends continuously from the base to the tip; and a second part formed from an elastomeric material mixed with conductive filler which extends continuously from the base to the tip. The blade seal is manufactured by compressing the first and second parts together; and curing one or both of the parts as they are compressed together.

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: 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 monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap.