Abstract: A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.

Abstract: A locking system is disclosed for locking and unlocking a door such as a cockpit door between the cockpit and cabin of an aircraft. The locking system has a door held by hinges on a door frame and movable between an open position and closed position, and at least one closing means that can lock the door when it is in the closed position. The locking system includes a compressed air source that can be coupled to the closing means to move the closing means from an unlocking position to a locking position by supplying compressed air, and at least one venting valve coupled to each of the closing means in order to conduct compressed air away from each closing means when in the open state, in order to move the at least one closing means from the unlocking position to the locking position.

Abstract: Interface arrangement for aircraft lifting surface between a first component and a second component made of composite materials and having an aerodynamic contour, wherein the first component comprises a primary joggled area and the second component comprises a secondary joggled area, such that the first component is joined to the second component by means of a supplementary part which accommodates in the primary joggled area and in the secondary joggled area, the secondary part being designed to maintain continuity of aerodynamic contour at the interface arrangement and to fill the gap between the first component and the second component, so the maximum thickness of the supplementary part being the depth of the primary joggled area, the depth of the primary joggled area being lower than the depth needed to accommodate the second component on the first component.

Abstract: The invention relates to a structural component (1) of a flow body, comprising at least one lining shell (B) that carries a main load, said lining shell having a core layer (33) that absorbs shear load and that comprises a plurality of core-layer sections (33a) arranged next to each other in the longitudinal extension of the foam layer, wherein said core-layer sections are connected to each other at the sides lying against each other by a core-layer reinforcement area (37), which extends through the core layer perpendicularly to the longitudinal extension of the core layer (33).

Abstract: A weaving process for direct manufacture of three-dimensional structures with bidimensional walls with corners, without the need for sewing or other assembly between two ridges. The weaving is made by transforming weft threads into warp threads for making at least one face. The process is particularly adapted for the weaving of reinforcing elements for composite structures of corner fitting type.

Abstract: An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.

Abstract: This aircraft nose structure comprises frames (2, 4, 6), a lower windshield frame member (12) and an upper windshield frame member (14) which are adapted to receive a windshield. The lower windshield frame member (12) has an arcuate shape with two branches which are connected together by a tie-rod (26).

Abstract: The invention provides a test apparatus for providing axial stresses in a structure, comprising a first set of formations for abutting a first surface of the structure at a first plurality of locations, a second set of formations for abutting a second surface of the structure at a second plurality of locations, and a force actuator, and wherein each set of formations comprises at least three formations and wherein at least two formations in each set of formations are aligned with a notional alignment line along the structure and at least one formation in each set of formations is out of alignment along the structure with said notional alignment line, such that when the force actuator applies a force, loads are applied at different locations, causing the structure to bend biaxially and thereby providing biaxial stresses in the structure.

Abstract: A device and a method for exchanging information between at least one operator and a machine which comprises the following components: a display means, which is set up so as to display information from the machine to the at least one operator visually and three-dimensionally; an input means, which is set up so as to detect the position of objects, preferably the position of the fingers of at least one operator, in three-dimensional space in relation to the display means, in a time-resolved manner by optical and/or acoustic and/or electromagnetic measurement methods, and to detect at least one operator input from the detected progression over time in accordance with at least one predetermined criterion and to pass said operator input on to the machine.

Abstract: An engine attachment pylon for mounting an aircraft engine to an aircraft structure while minimising vibrations induced into the engine attachment pylon during flight and operation of the engine. The engine attachment pylon according to the present invention comprises a rigid box like structure housing a resonator which is tuned to attenuate tension and compression vibrations, experienced by the engine attachment pylon. The engine attachment pylon is primarily used in combination within another identical engine attachment pylon, both being linked together on a vertical plane within the fuselage by a hinge like junction, and each engine attachment pylon being raised approximately 30° from the horizontal axis of the fuselage.

Abstract: An aerodynamic body with at least one ancillary flap on the aerodynamic body so it can be moved with a guide mechanism, and with a drive device for actuating the ancillary flap. The guide mechanism has a connecting lever, which at its first end is articulated on the aerodynamic body by a first pivotal articulation, and which at its second end is articulated on the ancillary flap by a second pivotal articulation. The second pivotal articulation is located at some distance from a trailing edge of the ancillary flap, and from a leading edge of the ancillary flap. The guide mechanism has an actuation element, which is coupled with the drive device. The actuation element is articulated on the ancillary flap by a third pivotal articulation. The third pivotal articulation is arranged such that it can be moved in the chordwise direction of the aerodynamic body.

Abstract: A structural component for an aircraft or spacecraft having an outer skin, comprising at least one former element for reinforcing the outer skin. The former element is arcuately curved in accordance with an inner contour of the outer skin 10, wherein the former element has a plurality of first cutouts for receiving longitudinal reinforcements and at least one second cutout, which is configured between adjacent first cutouts of one or more former elements. The invention furthermore relates to an aircraft or spacecraft with the structural component according to the invention.

Abstract: A clamp block assembly for securing hydraulic pipes, the clamp block assembly comprising one or more unitary clamp blocks of deformable material each having a through hole for receiving a respective pipe, and a clamp adapted to apply a predetermined load around the clamp block(s).

Abstract: A composite panel with protected parallel stiffeners has a multiply front face coming to an edge and extending between two lateral flanks of outside plies, symmetrically relative to a median plane (Pm). A device for protecting each stiffener includes a structural section that caps the stiffener symmetrically relative to this median plane (Pm). This structural section includes a so-called upper section formed above the edge and configured to envelop a space above the edge, a so-called lower section framing the lateral flanks by means of longitudinal walls (Pi) fastened to these flanks, and an intermediate section bearing at least partially on the edge via transverse walls (Pb) so as to minimize the propagation of impact forces to the lower section.

Abstract: A head of a riveting device—for Hi-Lite type rivets—of at least two components of a structure for installing automatically collars on pins previously inserted in the structure. The head comprises: a collar installation tool; a collar supply to supply collars to the collar installation tool; a tool actuating device; a linear displacement device to linearly move the tool during the threading operation; a withdrawal device arranged to withdraw the second part of the collars; a control arrangement configured to automatically perform the installation of collars on pins and after this the withdrawal of the second part of the collars, using tools and collars appropriate for the pins. Also a robot having as end-effector the head and to a method of riveting two components of an aircraft fuselage are provided.

Abstract: A compound engine for a means of transportation, includes a diesel engine and a gas turbine with at least one compressor and with at least one turbine. The diesel engine and the gas turbine are interconnected in such a manner that during continuous duty operation the compound engine is configured to be operated only by way of the diesel engine, and the diesel engine is optionally operated on its own or together with a compressor and a turbine of the gas turbine as a turbocharger for the diesel engine. The compound engine is configured to be operated by way of the diesel engine or the gas turbine.

Abstract: A method for the joining of moulded components with a punching, stamping rivet, wherein a punched hole is radially widened in at least certain sections of the moulded components that are to be punched. A punching, stamping rivet is provided which has a deforming section that has a greater external diameter than a punching section.

Abstract: An aircraft ground or sea approach anomaly detection method. The method includes the steps of characterizing a flight phase of the aircraft, determining a prohibited flight envelope, defining a set of prohibited vertical speeds of the aircraft for given altitudes in relation to the ground or the sea, as a function of the flight phase of the aircraft characterized, and detecting a ground approach anomaly of the aircraft as a function of a current vertical speed and altitude in relation to the ground or the sea of the aircraft, in relation to the prohibited flight envelope determined.

Abstract: A composite structure comprising: a first stack comprising a plurality of plies of composite material and at least one ply of self-healing material, the ply of self-healing material comprising a plurality of containers each containing a curable healing liquid; and a second stack comprising a plurality of plies of composite material, the stacks being joined together at a bond line. By placing a ply of self-healing material in one of the stacks (preferably relatively close to the bond line) the ply of self-healing material can resist the propagation of cracks between the first stack and the second stack. Preferably the global strength of the first stack is greater than the global strength of the second stack.

Abstract: An earth connection for electrically and mechanically connecting a plurality of earth wires to a structure, in particular to an aircraft structure, comprising an angled element which element is formed in one piece and is made of electrically conductive material, which comprises a first and a second fastening portion. The first fastening portion is fastened to the structure and the second fastening portion comprises a plurality of electrical connections for connecting the earth wires. The electrical connections comprise socket contact elements which are formed so as to receive pin contact elements of the earth wires.