Abstract: The invention discloses a trailing edge (2) of an aircraft aerodynamic surface, which comprises an upper skin (6) and a lower skin (7), being the upper and lower skins (6, 7) made of composite material. In the trailing edge (2) a lightweight part (1) is assembled at an end section (13) of the upper and lower skins (6, 7). The lightweight part (1) is covered by a metallic sheet (8), and has a “V”-shaped cross section with arms and peak, where the peak of the “V”-shaped cross section has a rounded shape and is located opposite the end section (13) of the upper and lower skins (6, 7).

Abstract: A method for obtaining the inertial properties of a movable rotating around a hinge line in an aircraft control surface. The method includes the steps of removing the mechanical connections of the actuators from the movable, leaving the movable free to rotate around its hinge line, further balancing the movable and calculating in a first approach its coarse static momentum. The method includes refining the coarse static momentum and obtaining simultaneously a frictional momentum of the movable; incorporating an elastic element on the control surface and configuring a second order mechanical system; inducing forced oscillations on the movable at a certain frequency, this frequency being increased until it is sensibly close to the resonance frequency of the movable to produce a wave response; calculating, from the wave response, the momentum of inertia of the movable.

Abstract: Method for optimising the design of sealing rings of internal manhole covers which close the manhole openings over the inner surface of the skin of an aircraft structure, the surface that is in contact with the inner surface of the skin being the optimized surface of said sealing rings, the method including dividing the outer contour and the inner contour of the optimised surface into n points; grouping into families Fi the sealing rings of each manhole opening; generating the curves that are best adapted to the set of points taken for the outer contour and for the inner contour of each sealing ring for each one of the families Fi; generating a ruled surface among the curves generated for each one of the families Fi.

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: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

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 system for executing a given scientific code using a suitable finite-volume or finite-element solver for a large dataset represented as a grid, comprising a plurality of equal computing nodes interconnected by node communication means and a parallel computing software package for distributing and controlling the execution in sub-grids among said computing nodes; each computing node comprising at least a CPU-based first processing means and a FPGA-based second processing means interconnected by a bus; said package being configured for the simultaneous execution of at least one first solver process (which is fully executed in a first processing means) and one second solver process (which is fully executed in a second processing means) in each computing node for one sub-grid of said grid and for managing the exchange of boundary data with the solver processes that solve neighbour sub-grids.

Abstract: The present invention describes composite rods keeping two elements apart a determined distance carrying the loads between them, such as railways, industrial premises, etc. Besides, the manufacturing method thereof and the tool involved in this process are also described.

Abstract: Frame of a fuselage section of an aircraft that receives external loads, such as the rear section that receives the loads of the tail planes, comprising a first sector (11) configured specifically to withstand these external loads and a second sector along the remaining perimeter of the fuselage, said first sector (11) comprising the following structural elements: a) a foot piece (21) to be joined to the fuselage skin (13); b) a head piece (23); c) a web (25) comprising one or more fitting-pieces (27, 27?) for receiving said external loads and a plurality of X-shaped pieces (31) joined by its ends to said foot piece (21) and said head piece (23); d) two connecting pieces (39, 39?) of the ends of said foot piece (21) and said head piece (23) with the second sector of the frame.

Abstract: An APU air intake (AI) is disclosed having a foldable intake door (101), comprising a frame (102) with airfoil profiles (103, 103a, 103b). The frame (102) is turned to an aperture angle (?) with respect to the frame support (121), and each airfoil profile (103, 103a, 103b) is turned to a profile angle (?i) with respect to the frame (102). The aperture angle (?) varies from 0° to 22°, and the profile angles (?i) vary from 0° to 110°. The frame (102) is moved by an actuator (109) and the airfoil profiles (103a, 103b) are operated by extendable rods (111) and secondary rods (118), each secondary rod (118) having rod supports (119a, 119b). A latching mechanism is assembled onto each extendable rod (111), comprising a rare earth magnet (112) and either a magnet contact plate (113) or a plate with another magnet.

Abstract: The invention comprises, a first preliminary step of cleaning the treatment surface of the moulding base tool and a second step in which the necessary layers of mould-release agent are applied to the treatment surface of the moulding base tool. Based on said preliminary steps, the process is characterized in that, in a later step, the treatment surface (1), covered with a mould-release agent (3), is provided with a continuous uniform film (4) of resin having a low concentration of volatile elements and a laminar resin supporting a very high mould-release capability, which facilitates the transfer of resin to the treatment surface (1) of the moulding base tool (2).

Abstract: The invention comprises a triform fitting 1, essentially made from non-metallic composite materials including several strengthening cross ribs 4 for joining symmetrical flanges 3 and a longitudinal flange 2. The symmetrical flanges 3 include cross slots 8 for receiving the run-out 16 of the webs 11 of several T-shaped internal stringers 9 that form part of the torsion boxes 6. The feet 10 of the stringers 9 are joined along one of their faces to the skins 7 of the torsion boxes 6, while the end zones of the free faces of said feet 10 are placed against the outer face of the symmetrical flanges 3 of the triform fitting 1. This ensures that the symmetrical flanges 3 of the triform fitting 1 remain inside the torsion boxes 6. Alternatively, the fitting 1 may not include the cross slots 8.